Aircraft, system and method for transporting a payload

Abstract

The group of inventions relates to aircraft, a system and a method for transporting a pay load. Each of the aircraft comprises: a body with a through-passage; a control module; and a gripper. An aircraft according to a second embodiment further comprises a payload transportation module. The claimed system comprises two or more of the aforesaid aircraft and includes aircraft of both types. To transport a payload, the payload is releasably grasped by the gripper of a first aircraft such that the payload can be moved through the through-passage in the body of said first aircraft under the control of a control device, and the payload is grasped by the second aircraft when the payload at least partially exits the body of the first aircraft, allowing transfer of the payload to the second aircraft under the control of a control device. The invention makes it possible to increase the speed of in-air transfer of a payload.

Description

AIRCRAFT, SYSTEM AND METHOD FOR MOVING PAYLOAD

[0001] The present invention relates to transport technology, in particular to technical means and methods for moving payload, namely aircraft, a system and method for moving payload. [STATE OF TECHNOLOGY]

[0002] Currently, a variety of aircraft, as well as payload transport systems and methods, have been developed for transporting or moving payloads, based on the use of such aircraft for payload pickup and transfer operations. Despite the high level of automation of such aerial transport systems, as well as the acceptable speed of transporting or moving payloads to their destinations using such aerial transport systems, existing aerial transport systems and payload transfer methods based on the use of such aerial transport systems still suffer from a significant drawback: insufficient payload range.

[0003] Therefore, the development of methods and systems for moving payloads is a pressing issue.

[0004] In particular, various aerial transport systems and methods of transporting payloads have become widespread, based on the use of automated aircraft, each of which has a body of a different design, equipped with one or more air propulsion units, which ensure the possibility of movement and navigation of the said aircraft in airspace.

[0005] For example, U.S. Patent No. 12037117 (hereinafter US 12037117), issued under U.S. Application No. 202016817427 (IPC: B64C 27 / 08, B64C 39 / 02, B64D 1 / 02, B64D 1 / 22), published on July 2, 2020, describes an aircraft for moving a payload, as well as a system and method for moving a payload using such an aircraft.In particular, the aircraft for moving a payload described in US 12037117 comprises: (i) a body equipped with air movers that enable the said aircraft to move through the air and that is capable of accommodating a payload therein; (ii) a control module with which the body is equipped and that is capable of controlling the operation of this aircraft, and (iii) a gripper connected to the body by means of an unwinding cable or rope and capable of gripping the payload and ensuring the possibility of its reeling in under the controls of the control module for accommodating the said captured payload in the body of the aircraft.

[0006] However, the payload transfer aircraft, system and method for transferring a payload using such an aircraft disclosed in US12037117 each have the disadvantage of increasing the difficulty of transferring the payload in the air from one aircraft to another aircraft.

[0007] Thus, there is an obvious need for further improvement of known aircraft, systems and / or methods for transporting payloads, in particular to simplify the process of transferring payloads in the air.

[0008] Therefore, the technical problem solved by the present invention consists in creating aircraft, a system and a method for moving a payload, in each of which at least the above-mentioned disadvantage of the known aircraft, system and method for moving a payload is at least partially eliminated, which consists in the increased complexity of transferring a payload in the air from one aircraft to another aircraft.

[0009] The objective of the present invention is to create aircraft, a system and a method for moving a payload, each solving at least the technical problem of the prior art as outlined above, as well as to expand the arsenal of technical means for moving a payload.

[0010] The stated problem is solved in the first aspect of the present invention due to the fact that the proposed aircraft for moving a payload comprises: (i) a housing with a through passage; and (ii) a control module with which the housing is provided and which is configured to control the operation of the aircraft, and (iii) a gripper connected to the housing with the possibility of releasably gripping the payload, ensuring the possibility of advancing the gripped payload through said through passage and configured to exit interaction with said payload at least upon partial extension of this payload from said through passage of the housing.

[0011] Furthermore, the stated problem is solved in the second aspect of the present invention due to the fact that the proposed aircraft for moving a payload comprises: (i) a body with a through passage; (ii) a control module with which the body is provided and which is designed with the possibility of controlling the operation of the aircraft; and (iii) a gripper connected to the body with the possibility of detachably gripping the payload with the possibility of installing the captured payload in the said through passage.

[0012] Furthermore, the stated problem is solved in the third aspect of the present invention due to the fact that the proposed system for moving a payload comprises: (i) two or more aircraft, at least one of which is a first aircraft according to the first aspect of the present invention or the second aspect of the present invention; (ii) one or more control devices configured to control the operation of said aircraft, wherein at least one second aircraft of said aircraft is configured to capture a payload extended from the body of the first aircraft.

[0013] Furthermore, the stated problem is solved in the fourth aspect of the present invention due to the fact that the proposed method for moving a payload comprises the steps of: (i) releasably capturing, by means of capturing the first aircraft according to the first aspect of the present invention or the second aspect of the present invention, the payload with the provision of the possibility of its advancement through the through passage of the body of the first aircraft under the control of the control device; and (ii) capturing the payload, by means of the second aircraft, during its at least partial extension from the body of the first aircraft with the provision of its transfer to this second aircraft under the control of the control device.

[0014] The above-described payload transfer aircraft according to the first aspect of the present invention, the payload transfer aircraft according to the second aspect of the present invention, the payload transfer system according to the third aspect of the present invention and the payload transfer method according to the fourth aspect of the present invention each provide a technical result consisting in increasing the payload transfer speed in the air.

[0015] The above technical advantage of the claimed group of technical solutions is not limiting. Additional advantages of the claimed group of technical solutions and individual technical solutions within this group, including specific implementation options, will be apparent to those skilled in the art from the detailed description of the present invention below and the accompanying drawings.

[0016] In addition, the above-described first, second, third and fourth aspects of the present invention each provide an additional technical result consisting in increasing the versatility of the aircraft, since it can be used both to capture a payload from a support surface (for example, from the ground surface) or from another aircraft, and to move and transfer the captured payload directly in the air.

[0017] In addition, the above-described first, second, third and fourth aspects of the present invention each provide another additional technical result, which consists in increasing the safety of the movement of the payload, in particular due to improved stabilization of the captured payload before its transfer to another aircraft.

[0018] In addition, the above-described first, second, third and fourth aspects of the present invention each provide another additional technical result, which consists in expanding the arsenal of technical means for moving payload through the air.

[0019] The accompanying drawings, which are provided to provide a better understanding of the essence of the present invention, form a part of this document and are included herein to illustrate the embodiments and aspects of the present invention described below. The accompanying drawings, in combination with the description below, serve to explain the essence of the present invention. In the drawings:

[0020] Fig. 1A schematically shows a first state of the first system for moving a payload according to the present invention (see Fig. 2A on the left), in which the first aircraft with a gripping ring is in the air in a given region of space at a distance from the payload placed on the surface of the earth; a second state of the first system for moving a payload according to the present invention (see Fig. 2A in the center), in which the payload, still located on the surface of the earth, is captured by the gripping ring of the first aircraft; and a third state of the first system for moving a payload according to the present invention (see Fig.2A on the right), in which the payload, captured by the capture ring of the first aircraft, is pulled toward the body of this first aircraft, ensuring its separation from the surface of the earth and placement in the air at a distance from the body of the first aircraft;

[0021] Fig. 1B schematically shows a fourth state of the first system for moving a payload according to the present invention (see Fig. 1B on the left), in which the captured payload is advanced through a through passage in the body of the first aircraft with the provision of its partial extension from this through passage on the opposite side of the body of the first aircraft; a fifth state of the first system for moving a payload according to the present invention (see Fig. 1B in the center), in which the first aircraft with the payload placed on it, partially extended from the through passage of the body of the first aircraft, is in the airspace at a distance from the second aircraft; and a sixth state of the first system for moving a payload according to the present invention (see Fig.1B (right), in which the payload, partially extended from the through passage of the body of the first aircraft, is captured in the airspace by the capture ring of the second aircraft;

[0022] :3 schematically shows a seventh state of the first system for moving a payload according to the present invention (see Fig. 1C on the left), in which the payload, still held by the gripping ring of the first aircraft, is pulled toward the body of this second aircraft, ensuring its release from interaction with the first aircraft and moving away from this body of the first aircraft by a predetermined distance; an eighth state of the first system for moving a payload according to the present invention (see Fig. 1C in the center), in which the payload, still held by the gripping ring of the first aircraft, is pulled more toward the body of this second aircraft, ensuring a greater distance of the gripping ring of the first aircraft from the body of the first aircraft; and a ninth state of the first system for moving a payload according to the present invention (see Fig.1C on the right), in which the payload, held by the gripping ring of the second aircraft and removed from interaction with the gripping ring of the first aircraft, is pulled even more toward the body of this second aircraft, ensuring an even greater distance from the body of the first aircraft, and the gripping ring of the first aircraft, removed from interaction with the payload, is brought closer to the body of the first aircraft from the side of its bladed air movers of the first aircraft;

[0023] Fig. 1D schematically shows a tenth state of the first system for moving a payload according to the present invention, in which the payload, held by the gripping ring of the second aircraft, which is in contact with the body of the second aircraft, is advanced through a through passage in the body of the second aircraft, ensuring its partial extension from this through passage on the opposite side of the body of the second aircraft, and the gripping ring of the first aircraft is suspended on flexible connecting elements on the opposite side of the body of the first aircraft;

[0024] Fig. 2A schematically shows a first state of the second system for moving a payload according to the present invention (see Fig. 2A on the left), in which the first aircraft with a ring gripper is in the air in a given region of space at a distance from the payload placed on the surface of the earth; and a second state of the second system for moving a payload according to the present invention (see Fig. 2A on the right), in which the payload is captured by the gripper ring of the first aircraft;

[0025] Fig. 2B schematically shows a third state of the second system for moving a payload according to the present invention (see Fig. 2B on the left), in which the payload, captured by the gripping ring of the first aircraft, is pulled toward the body of this first aircraft, ensuring its separation from the ground surface and placement in the air at a distance from the body of the first aircraft; a fourth state of the second system for moving a payload according to the present invention (see Fig. 2B in the center), in which the payload, held by the gripping ring of the first aircraft, is advanced through a through passage in the body of the first aircraft, ensuring its partial extension from this through passage on the opposite side of the body of the first aircraft; and a fifth state of the second system for moving a payload according to the present invention (see Fig.2B (right), in which the first aircraft with the payload placed on it, partially extended from the through passage of the body of the first aircraft, ends up in the airspace at a distance from the second aircraft equipped with its own capture ring;

[0026] Fig. 2C schematically shows a sixth state of the second system for moving a payload according to the present invention (see Fig. 2C on the left), in which the payload, partially extended from the through passage of the body of the first aircraft and still held by the gripping ring of the first aircraft, is captured in the airspace by the gripping ring of the second aircraft; a seventh state of the second system for moving a payload according to the present invention (see Fig. 2C in the center), in which the payload, held by the gripping ring of the second aircraft and removed from interaction with the body of the first aircraft, is pulled toward the body of the second aircraft, ensuring its placement at a distance from the body of the second aircraft; and an eighth state of the second system for moving a payload according to the present invention (see Fig.2C (right), in which the payload held by the gripping ring of the second aircraft is advanced through a through passage in the body of the second aircraft, with its partial extension from this through passage on the opposite side of the body of the second aircraft, and the gripping ring of the first aircraft is transferred to a state of readiness for its use to grip another payload;

[0027] A block diagram of one of the illustrative embodiments of the method for moving a payload according to the present invention is shown. [IMPLEMENTATION]

[0028] Some examples of possible embodiments of the present invention are described below with reference to the accompanying drawings, but it should not be considered that the following description defines or limits the scope of the present invention.

[0029] In the following description, well-known functions or constructions are not described in detail since this might obscure the essence of the present invention with unimportant details.

[0030] It should be understood that in the following description, terms such as "first," "second," "upper," "lower," "side," "front," "rear," and the like are used solely for convenience and should not be construed as limiting terms. In particular, in the context of the present invention, unless otherwise explicitly stated in the description of this document, the terms "first," "second," "third," or the like are used to distinguish from each other the elements, components, parts, assemblies, modules, blocks, embodiments, or the like to which they relate, and not for the purpose of describing any specific relationship between them.For example, it should be borne in mind that the use of the terms "first aircraft" and "second aircraft" does not imply any order, classification, chronology, hierarchy or ranking of these aircraft within a plurality of aircraft, nor does their use (in itself) exclude the possibility that there may additionally be a "third aircraft", "fourth aircraft", etc. Further, as may be used in this document in other contexts, the reference to "first aircraft" and "second aircraft document" in this document does not exclude the possibility that these aircraft may include identical structural elements and / or functional components.For example, in some cases the “first aircraft” and “second aircraft” may be the same or may be implemented identically in terms of design and functionality, while in other cases they may differ in terms of design and functionality.

[0031] Unless otherwise expressly stated or unless otherwise clearly follows from the context of this document, it should be understood that the reference to an object in the singular does not exclude the presence of a plurality of such objects, just as the reference to an object in the plural (for example, a set of objects, a group of objects, several objects, a part of objects, a subset of objects, a subgroup of objects, etc.) does not exclude the presence of a single or individual such object.

[0032] Grammatical relations express any or all alternative and combined combinations of related clauses, sentences, words, etc., unless otherwise expressly stated or otherwise clearly evident from the context of this document. Therefore, the term "or" should be understood to generally mean "and / or," etc.

[0033] The recitation of ranges of values ​​in this document is not limiting, since it refers individually to any and all values ​​falling within the range, unless otherwise specified herein, and each individual value (including any integer value, as well as tenths, hundredths, and thousandths thereof) in such range is included in the description as if it were individually recited herein.

[0034] The words "approximately," "approximately," or the like, when used in conjunction with a numerical value, are to be interpreted as indicating a possible deviation that, in the opinion of a person skilled in the art, would ensure proper functioning for solving the required task. Ranges of values ​​and / or numerical values ​​are provided herein solely as examples and do not limit the scope of the described embodiments.

[0035] All examples given in this document, or at least some of them, as well as the corresponding expressions ("for example", "such as", "in particular" or the like), are essentially used to improve the understanding of the essence of the present invention and to ensure the completeness of the disclosure of the present invention, however, these expressions do not impose any restrictions on the embodiments of the present invention, for the description of which they are used in this document, in particular, they do not limit the practical embodiments of the elements, components, parts, units, modules, blocks, devices, means and / or the like, used to disclose the design features and operation of the present invention.

[0036] Terms and definitions used in the description of this document

[0037] The term "illustrative" means a non-limiting example, embodiment, or illustration. Similarly, the terms "for example" and "by way of example," as used herein, define lists of one or more non-limiting examples, embodiments, or illustrations.

[0038] In the context of the present invention, the term "correspondence" and its derivatives (i.e., adjective, verb, adverb) do not necessarily mean exact agreement or exact equality in something, with something, or between something in any respect, but may imply a deviation or departure from said equality within specified limits. For example, the term "corresponding coordinates," unless otherwise clearly follows from the description of this document, means not only that these coordinates may be exactly equal to each other or may exactly coincide, but also implies that said equality or coincidence of coordinates may be established with some error (for example, with the error of the GPS system) or within a specified geographic area surrounding the exact geographic point or area indicated by these coordinates, or the exact geographic location indicated by these coordinates.

[0039] In the context of the present invention, the term "aircraft", unless the description herein clearly indicates otherwise, refers to an air vehicle that is capable of flight or that is capable of moving through the air in an automatic mode, i.e. without human intervention or external control sources, or is capable of moving through the air in a semi-automatic mode, i.e. receiving at least some control commands from a person (e.g., a pilot, operator, etc.) or an external source (e.g., a control panel, a control server, an external control device, etc.) via specified communication channels. Non-limiting examples of aircraft include various multi-rotor UAVs (e.g., multi-copter drones), single-rotor UAVs (e.g., an unmanned helicopter), hybrid UAVs (e.g., drones with rotors and wings), etc.

[0040] In the context of the present invention, the term "hull", unless the description herein clearly indicates otherwise, refers to a frame, skeleton, shell, skin, fuselage, supporting support or body of a physical inanimate object, each of which may be formed from a single supporting element or a set of interconnected supporting elements, while the type, shape, overall dimensions, design features and / or material of such a frame are not in any way particularly limited.

[0041] In the context of the present invention, the term "payload", unless the description of the present document clearly indicates otherwise, refers to people or living beings (in particular, to people or living beings as such, or to people or living beings placed in a capsule, cabin, habitation module, cryomodule, rescue module, habitation compartment, habitation unit, etc.) or to cargo (to cargo as such, or to cargo placed in boxes, cartons, packages, bags, containers, reservoirs, vessels, tanks, canisters, receptacles, barrels, cisterns, cylinders, vessels, reservoirs, containers, bottles, flasks, glass containers, cylinders, boxes, storage modules, etc.), which can be placed in / on the body of a vehicle that performs the function of a carrier and is intended for the delivery, carriage, transportation or movement of people, various living beings and / or various cargo by air.

[0042] In the context of the present invention, the term "module," unless otherwise clearly indicated in the description herein, refers to a functional element or set of functional elements of a device in the form of a part, unit, block, or other assembly unit that performs specific technical functions enabling the device's functions to be performed. The module as a whole may be implemented in practice using a combination of known structural elements, a combination of known structural elements and known hardware, a combination of known structural elements and known firmware, or a combination of known hardware and known software. For example, a control module may be implemented using firmware.In the context of the present invention, the control module may be a physical device, apparatus, or a plurality of modules implemented using hardware, such as an application-specific integrated circuit (ASIC) or a field-programmable gate array (FPGA), or a combination of hardware and software, such as a microprocessor system and a set of instructions implementing the functionality of the control unit, which (when executed) transform the microprocessor system into a special-purpose device or system (e.g., an autopilot).In addition, each of the modules described in this document, or at least one of them, may be implemented as a combination of hardware and software, wherein some of the functionalities described in this document with respect to one of the modules may be implemented only by means of hardware, and other functionalities described in this document with respect to the same module or another module may be implemented by using hardware in combination with software.Furthermore, in the context of the present invention, the docking module may be configured to detachably interact with at least one unmanned aerial vehicle, wherein the docking module may be implemented using a combination of known structural elements, a combination of known structural elements and hardware, a combination of structural elements and software or a combination of hardware and software.

[0043] In the context of the present invention, the term "navigation command," unless otherwise clearly indicated in the description of the present document, refers to instructions sent to aircraft included in the payload movement system. Navigation commands may be issued or provided by the aircraft movement control system in the form of digital or analog data, instructions, control signals, or the like. Navigation commands may be initially generated, without limitation, by an automatic operator, an operator (both locally and remotely), and / or an obstacle avoidance system. In the case of aircraft, navigation commands may be communicated, for example, to a control module for controlling the aircraft or to a system for controlling the direction of movement of the aircraft.

[0044] In the context of the present invention, the term "manual control," unless otherwise clearly indicated in the description herein, refers not only to control performed solely by a person's hands, but also by a person's feet, fingers, voice, pupils, or any suitable combination thereof. Thus, in the context of the present invention, the term "manual control" refers to at least one of the following: buttons, levers, joysticks, toggle switches, pedals, a touchscreen, gesture sensors, pupil tracking scanners, a microphone, and / or the like.

[0045] In the context of the present invention, the term "charger", unless the description of the present document clearly indicates otherwise, refers to a device for replenishing the range of an aircraft by recharging its battery and / or by replenishing its fuel supply.

[0046] In the context of the present invention, the term "database," unless otherwise clearly indicated in the description herein, refers to any structured collection of data, regardless of the specific structure, database management software, or computer hardware on which the data is stored, used, or otherwise made available for use. A database may reside on the same hardware that runs the process that stores or uses the information stored in the database, or it may reside on separate hardware, such as a dedicated server or multiple servers.

[0047] In the context of the present invention, the term "control device" refers to computing equipment executing a computer program to provide the ability to receive requests (e.g., from other computing devices) over a communications network, the ability to execute or process such requests, and / or the ability to send such requests over a communications network (e.g., to other computing devices). The computing equipment executing the computer program may be, without limitation, a single physical computer or a single physical computer system. In the context of the present invention, the use of the term "control device" does not mean that every computing task (e.g., instructions or commands received) or any other specific task will be received, executed, or will cause to be executed by the same control device (i.e.,(the same software and / or hardware), meaning that any number of software or hardware elements may be involved in receiving / sending, executing, or may cause to be executed any task or request, or the consequences of any task or request, and all of this software and hardware may be implemented as one or more control devices.

[0048] In the context of the present invention, the term "server" refers to computing equipment executing a computer program to enable the receipt of requests (e.g., from other computing devices) over a communications network, the ability to execute or process such requests, and / or the ability to send such requests over a communications network (e.g., to other computing devices). The computing equipment executing the computer program may be, without limitation, a single physical computer or a single physical computer system. In the context of the present invention, the use of the term "server" does not imply that every computing task (e.g., instructions or commands received) or any other specific task will be received, executed, or cause to be executed by the same server (i.e.,(the same software and / or hardware), meaning that any number of pieces of software or hardware may be involved in receiving / sending, executing, or may cause to be executed any task or request, or the consequences of any task or request, and all of this software and hardware may be implemented as one or more servers. The first system for moving payloads

[0049] In Fig. 1A-1.D, one of the illustrative embodiments of the first system 1000 for moving a payload is schematically shown, comprising a first aircraft 100 for moving a payload and a second aircraft 200 for moving a payload, each of which has a body 10 equipped with bladed air movers 20 mounted on beams on the outer side of the body 10 to ensure the possibility of flight or movement of the said aircraft through the air or in airspace along a given trajectory to a given (target) destination, including in accordance with a given flight program in response to control commands and / or navigation commands from one or more control devices (not shown) included in the first system 100 and configured to remotely control the operation or functioning of the first and second aircraft 100,200 by issuing control commands and / or navigation commands to them, generated by said control devices in accordance with the flight programs of these aircraft, available to said control devices, and / or generated by said control devices in response to requests or signals of these first and second aircraft 100, 200.,

[0050] In particular, one or more control devices included in the first system 1000 are each configured to establish a wireless connection or wireless communication channel via a communication network (not shown) included in the first system 1000 with at least one or each of the first and second aircraft 100, 200 for issuing control commands and / or navigation commands to said at least one aircraft, ensuring the ability to remotely control its operation or functioning. In some embodiments of the present invention, such a communication network may not be included in the first system 1000.

[0051] The communication network of the system 1000, to which at least one or more control devices of the system 100 and the aircraft 100, 200 are connected with the ability to communicate, essentially allows said control devices of the system 1000 and the aircraft 100, 200 to exchange system and / or operational data with each other, which they use to implement their functions or functionalities described in this document. For example, any suitable wireless communication line known in the art can be used as such a communication network, for example, a communication line based on the wireless communication technology "WiFi", a communication line based on the wireless communication technology "2G", "3G", "4G" or "5G", a communication network based on the technology "LTE" and / or the like.

[0052] In one embodiment of the present invention, the first system 1000 may include two or more wireless communication networks, each designed similarly to the above-described communication network of the system 1000, for exchanging data between the control devices of the system 1000, the aircraft 100, 200 and / or any other functional devices that may additionally be included in the first system 1000 and / or that are described in this document, in real time or in real time.

[0053] It should be noted that in the body 10 of each of the first and second aircraft 100, 200 included in the first system 1000, a communication module (not shown) is placed or installed, which may contain at least one of the following wireless communication means: a HF radio antenna, a VHF radio antenna, a microwave radio antenna, an optical communication module, a half-duplex / simplex satellite communication module, a 2G / 3G / 4G / LTE / 5G cellular communication module, a wireless communication module, a wired communication module, etc.

[0054] In the body 10 of each of the first and second aircraft 100, 200, included in the first system 1000, a control module (not shown) is also placed or installed, functionally connected to the bladed air movers 20 with the ability to control their operation and connected to the communication module of the said aircraft with the ability to exchange data with it.

[0055] In particular, the control module in each of the first and second aircraft 100, 200 included in the first system 1000 may be configured to turn on (activate or put into action) at least one or each of the air movers 20, and may also be configured to turn off (deactivate) at least one or each of the air movers 20. In addition, the control module in each of the first and second aircraft 100, 200 may be configured to change the rotation speed of the blades of at least one or each of the air movers 20, and / or to change the direction of rotation of the blades of at least one or each of the air movers 20.

[0056] Thus, the communication module (not shown), installed in the body 10 of each of the first and second aircraft 100, 200, included in the first system 1000, is configured to receive external control commands and / or navigation commands from at least one of the control devices of the first system 1000, transmitted over the communication network of the first system 1000, with the ability to issue them, via the communication bus (not shown) of the said aircraft, to the control module of the said aircraft, which essentially makes it possible to remotely control the operation or functioning of at least one or each of the first and second aircraft 100, 200 using the said at least one control device of the first system 1000.

[0057] In turn, the control module in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 is configured to process control commands and / or navigation commands received by the communication module of this aircraft from one or more control devices of the first system 1000, and is additionally configured to control the operation of the said aircraft depending on the said navigation commands and / or control commands.

[0058] In particular, navigation commands and / or control commands received by the communication module of any of the first and second aircraft 100, 200 from at least one of the control devices of the first system 1000 via the communication network of the first system 1000 may correspond to a given flight program of the aircraft, so that as a result of processing said commands, the control module of this aircraft can ensure the possibility of moving said aircraft through the air or in airspace in accordance with said flight program. It should be noted that the flight program that can be implemented by the first aircraft 100 may provide for, for example, a flight of the first aircraft 100 from a given region of space to a given (target) destination, during which (i) one or more payload capture operations can be carried out in different regions of space,which can be made in the form of a payload 400 and which can be placed on any supporting surface (for example, on the surface of the earth) or placed on a second aircraft 200, which is in a state of flight in the air or is in a parked state on the supporting surface of any stationary object (for example, on the surface of the earth, a parking platform of a building, etc.) or on the supporting surface of a movable physical object (for example, in the body of a vehicle, the deck of a ship, etc.), (ii) one or more operations of moving said captured payload by the first aircraft 100 in the air and / or (iii) one or more operations of transferring said captured payload in the air from the first aircraft 100 to the second aircraft 200. In addition,in response to navigation commands and / or control commands from one or more of the control devices of the system 1000, the control module of the aircraft 100 or the aircraft 200 may provide, for example, the ability to perform at least one of the following operations: (i) changing the flight speed of the aircraft, (ii) changing the flight direction of the aircraft, (iii) directing the aircraft from a parking station (not shown) or the current airspace region by air to a target airspace region in which it is intended to transfer a payload, which may be in the form of payload 400,from one aircraft to another aircraft; (iv) directing the aircraft through the air to one of the parking stations (not shown) for placement in it or on it, ensuring the possibility of storing this aircraft in the said parking station and / or ensuring the possibility of replenishing the power reserve (charging) of this aircraft; (v) capturing the payload 400 in the air or on the supporting surface; (vi) placing the captured payload in the body 10 in a state ready for its subsequent transfer to another aircraft; (vii) transferring the payload 400 from one aircraft to another aircraft, etc.,

[0059] In some embodiments of the present invention, at least one or each of the control devices (not shown) may not be part of the first system 1000.

[0060] In some other embodiments of the present invention, the data transmission protocols and / or technical means used to transmit data between one or more control devices of the system 1000 and the first and second aircraft 100, 200 included in the first system 1000 may at least partially differ from each other and / or may at least partially coincide with each other. In addition, one or more communication protocols and, accordingly, one or more technical means of communication may be used simultaneously for the exchange of data between the first and second aircraft 100, 200 and / or with the control devices of the system 1000.

[0061] In certain embodiments of the present invention, at least one or each of the control devices of the system 1000 may be configured to ensure safety during flight or movement through the air of the first and second aircraft 100, 200, including composite aircraft formed by each of two or more aircraft 100 docked together, two or more aircraft 200 docked together, and two or more aircraft 100, 200 docked together.

[0062] It should be noted that at least one or each of the control devices of the system 1000 may be implemented in the form of a control server or a control center. In particular, the system 1000 may comprise one control device configured to issue control commands and / or navigation commands to the control module of at least one or each of the first and second aircraft 100, 200 included in the first system 1000, wherein such a control device of the system 1000 may be a single server, which may be implemented in the form of, for example, a Dell™ PowerEdge™ server, on which the Ubuntu Server or Windows Server operating system may be used.In addition, the control device of the system 1000 may have or may access at least one external (remote) database (not shown) via a communication network (not shown) or in another way, or may contain at least one local database stored on a storage device (not shown) included in such a control device, or in the memory (not shown) of such a control device.

[0063] In some embodiments of the present invention, the control device of system 1000 may be any other suitable hardware, application software, system software, or any combination thereof.

[0064] In other embodiments of the present invention, the functions of the control device of system 1000 may be divided between several computer or computing devices, for example, they may be implemented using several servers connected to each other via a communication network with the possibility of mutual data exchange.

[0065] In other embodiments of the present invention, the functions of the control device of the system 1000 may be performed by a control module of one of the first and second aircraft 100, 200 included in the first system 1000, a given group or set of control modules of the aircraft 100, 200 included in the first system 1000, a payload control unit 400 or any other suitable computing device included in the first system 1000 and configured to generate control commands and / or navigation commands and to issue said generated commands to the control module of at least one or each of the first and second aircraft 100, 200 included in the first system 1000.

[0066] In addition, the first system 1000 shown in Fig.1A-1D, includes a payload 400, which may initially be located on the surface of the earth or any other supporting surface with the possibility of its capture by the first aircraft 100 and the possibility of moving the captured payload 400 by air by this first aircraft 100 to a target region of space and which can be transferred in the air in the said target region of space from the first aircraft 100 to the second aircraft 200 with the possibility of subsequent movement of the transferred payload 400 in the air by the second aircraft 200 to another target region of space, in which this payload 400 can be placed in the place of its storage (at least in the place of its temporary installation) or can be transferred in the air from the second aircraft 200 to another aircraft, which can be made in the form of any of the first and second aircraft 100, 200.In one embodiment of the present invention, payload 400 may be removed from first system 1000.

[0067] In one embodiment of the present invention, the payload 400 included in the first system 1000 may have a frame or body in the form of a cabin configured to accommodate passengers (e.g., one or more people and / or a pilot), various living beings, and / or various cargo of any type. It should be noted that in such an embodiment of the present invention, the payload 400 may be used to deliver, transport, transport, or move people, various living beings and organisms, vehicles, equipment, medicines, and / or cargo of various types (solid, gaseous, liquid, flowable, bulk, viscous, radioactive, chemical, and / or the like) by air, which also allows the payload to be referred to as a transport module or a transport module.

[0068] In another embodiment of the present invention, a pilot seat may be installed in the payload 400, in particular in the interior space of the body or housing of the payload 400, in which a pilot (not shown) may be placed, capable of controlling the vehicle in the form of which the payload 400 may be implemented, using a dashboard and controls that may also be located in the housing of the payload 400.In addition, in this embodiment of the present invention, in the interior space of the payload body 400, in addition to the pilot, at least one passenger, at least one item of passenger baggage and / or at least one item of cargo may be additionally placed, wherein said pilot, passengers, items of cargo and items of passenger baggage may be placed in corresponding places in the common interior space or may be placed each in its own separate area, at least partially limited by one or more partitions, or in a separate compartment, at least partially limited by one or more partitions.

[0069] In another embodiment of the present invention, the pilot's seat may be located in a pilot's cabin formed in the interior space of the payload body 400 and separated by a partition from the rest of the interior space of the payload body 400, which in turn may be divided by another partition into a passenger compartment in which one or more passenger seats may be installed to accommodate passengers, and a baggage or cargo compartment in which cargo (in particular, one or more items of cargo) and / or passenger baggage (in particular, one or more items of passenger baggage) may be placed, wherein said cargo items, passenger baggage items and / or passenger seats may be placed or secured on the bottom,the floor and / or walls of the payload body 400. In one of the variations of this embodiment of the present invention, the passenger compartment, instead of or in addition to passenger seats, may be provided with: (i) handrails installed on the side walls, floor and / or ceiling of the payload body 400 for accommodating passengers in any position in the payload body 400, for example, sitting or standing on the floor of the payload body 400; (ii) couches, beds or benches fixed to the floor, walls and / or ceiling of the payload body 400 for accommodating passengers thereon in a sitting, standing and / or lying position; (iii) specialized places for accommodating disabled persons in a sitting, standing and / or lying position; (iv) specialized places for accommodating wheelchairs used by disabled persons; (v) specialized places for accommodating baby strollers used by small children; (v) specialized places for accommodating baby cradles,used by infants, and (if necessary) specialized places for accompanying persons; and / or (vi) specialized places for placing medical stretchers for transporting patients used by bedridden patients. It should be noted that the number of passengers in the passenger compartment may range from one person to several tens or even hundreds of people without introducing any restrictions, while the said number of passengers is essentially limited only by the area of ​​the passenger compartment within the interior space of the payload body 400. In another variation of this embodiment of the present invention, in the cargo compartment of the payload body 400, not only the possibility of placing cargo and / or passenger baggage on the floor may be provided, but also the possibility of securing them in the cargo compartment of the payload body 400 using standard fasteners known in the art,in addition, shelves, hangers, boxes and other supporting means may be provided in the cargo compartment of the payload body 400, secured to the floor, ceiling and / or side walls of the payload body 400 and allowing additional cargo items and / or passenger baggage items to be placed in the cargo compartment of the payload body 400. In another variation of this embodiment of the present invention, passenger baggage spaces, including shelves, hangers, boxes and other supporting means for placing passenger baggage items, may be provided only in the passenger compartment of the payload body 400 in addition to the above-described options for accommodating passengers in said passenger compartment. It should be obvious to a person skilled in the art,that cargo items and / or passenger baggage items can be at least partially secured or fastened on the outside of the payload body 400 using suitable fastening means known in the art (for example, using special closed-type attachments used in airplanes, automobiles, motorcycles, helicopters, bicycles, etc.). It should be noted that the above-described pilot cabin, passenger compartment, and cargo compartment in the payload body 400 can be designed in general similar to the corresponding compartments of airplanes, helicopters, buses, automobiles, ships, boats, etc.,

[0070] In another embodiment of the present invention, the pilot's seat may be placed in the pilot's cabin in the interior space of the payload housing 400, separated by a partition from the rest of the interior space of the payload housing 400, in which, in turn, passengers (for example, in passenger seats), cargo items, and passenger baggage items may be placed or secured on the bottom, ceiling, and / or floor of the payload housing 400.In addition, an embodiment of the present invention is possible, in which only the pilot and passengers can be accommodated in the internal space of the payload body 400; an embodiment of the present invention is possible, in which only the pilot and cargo can be accommodated in the internal space of the payload body 400; an embodiment of the present invention is possible, in which only passengers and cargo can be accommodated in the internal space of the payload body 400; an embodiment of the present invention is possible, in which only passengers can be accommodated in the internal space of the payload body 400; an embodiment of the present invention is possible, in which only the pilot in the pilot's seat can be accommodated in the internal space of the payload body 400; and an embodiment of the present invention is possible, in which only cargo can be accommodated in the internal space of the payload body 400.

[0071] In some embodiments of the present invention, controls in the payload 400, which can be installed in the interior space of the payload body 400, limited by the walls of the payload body 400 on its interior side, can essentially allow the payload 400 to be controlled in a semi-automatic mode (i.e., a combination of manual control by the pilot and automatic control by the autopilot) and can provide the possibility of manual input by the pilot, located in the pilot's seat and monitoring the readings of the instruments on the instrument panel, of at least one control command.The control elements of the payload body 400 must be connected with the possibility of exchanging data with the below-described control unit (not shown), which may also be part of the payload 400, with the possibility of issuing each of the said pilot control commands to the said payload control unit 400, wherein some of the said pilot control commands can essentially replace the corresponding control commands of the control module of the first aircraft 100, generated by the payload control unit 400 when controlling the vehicle, which is based on one or more payloads 400 docked together, in automatic mode (i.e. in autopilot mode).In one embodiment of the present invention, the participation of a pilot in the process of controlling a vehicle based on one or more payloads 400 connected to each other may not be provided for, in connection with which the above-described instrument panel, controls and pilot seat may be absent from the interior space of the payload 400 body, and the control of such a vehicle may be implemented virtually completely in automatic mode (i.e., in autopilot mode) with the help of the below-described control module of the first aircraft 100, which in turn can receive control commands from one or more control devices of the system 1000, which includes this payload 400.In another embodiment of the present invention, the above-described controls and / or the above-described instrument panel in the body of the payload 400 may be included in the control module of the first aircraft 100, which allows this control unit to simultaneously provide the ability to manually control the vehicle, which is based on one or more payloads 400 docked together, with the help of a pilot and the ability to automatically control such a vehicle in the autopilot mode.

[0072] In some embodiments of the present invention, the first system 1000 may include one or more aircraft 100 and one or more aircraft 200. In other embodiments of the present invention, the first system 1000 may comprise, for example, two, three, four, five, six, seven, eight, nine, ten, eleven, twelve or more aircraft, at least one of which may be implemented as the aircraft 100 described in this document, and at least one other of said aircraft of the first system 1000 may be implemented as the aircraft 200 described in this document.

[0073] Each of the first and second aircraft 100, 200 included in the first system 1000 can be implemented, for example, in the form of any suitable unmanned aerial vehicle (UAV) known in the art.

[0074] In other embodiments of the present invention, at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be equipped with one or more air movers 20 operating under the control of the below-described control module included in the said aircraft, ensuring the possibility of flight or movement of the said aircraft through the air or in airspace along a given trajectory to a given (target) destination.

[0075] The body 10 of at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may have any suitable shape and overall dimensions characteristic of any aircraft known in the art and may be made of any suitable material known in the art and commonly used for the manufacture of aircraft bodies, in particular from a composite material (for example, from composite sandwich panels), metal (for example, from interconnected channel beams made of metal), aluminum (for example, from interconnected aluminum load-bearing beams), plastic (for example, from a single-piece cast piece of plastic), titanium material (for example, from sandwich panels made of titanium), any other suitable material known in the art, including using any suitable combination of the listed materials (for example,from a sandwich panel or titanium panels with an aluminum honeycomb core), and / or the like. Thus, the type, shape, dimensions and material of the body 10 in each of the first and second aircraft 100, 200 included in the first system 1000 are not particularly limited in the framework of the present invention. In particular, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may have a shape generally similar to the body of a helicopter, airplane or drone, however, it should be obvious to a person skilled in the art that the body 10 may have any other shape similar to any other aircraft or air vehicle, for example, a shuttle, hang glider, paraglider, airship or any other similar aircraft known in the art.

[0076] In one embodiment of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be made in the form of a regular or irregular three-dimensional geometric figure, for example, in the form of a cube, cuboid, ball or sphere, square pyramid, tetrahedron (triangular pyramid), hexagonal pyramid, triangular prism, hexagon (octahedron), pentagonal prism, hexagonal prism, dodecahedron, ellipsoid, icosahedron, cone, cylinder or any other known three-dimensional figure.

[0077] In another embodiment of the present invention, at least a portion of the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may have a cross-section (longitudinal or transverse) in the shape of a triangle, square, circle, oval, rectangle, parallelogram, rhombus, trapezoid, quadrangle, pentagon, hexagon, heptagon, octagon, nonagon, decagon, 20-agon or any other known regular or irregular geometric figure.

[0078] In yet another embodiment of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be a skeleton, frame or supporting frame to which a skin may be attached or which may be at least partially surrounded by a shell.

[0079] In other embodiments of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be additionally provided with empennage, wings and / or a tail rotor, etc., to improve the aerodynamic characteristics of said aircraft and improve its load-bearing capacity by creating additional lift in flight.

[0080] In some other embodiments of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be additionally provided with at least one aircraft engine (not shown), and preferably two aircraft engines, to ensure the possibility of moving said aircraft through the air in the event of an emergency (for example, in the event of a failure or breakdown of at least one or each of the air movers 20) or to increase the speed of moving said aircraft through the air due to the possibility of operating the aircraft engines in addition to the movers 20 used to move said aircraft through the air in a standard situation, or instead of them).It should be noted that each such aircraft engine may be, for example, a propeller engine, a jet engine, a hybrid aircraft engine, or any other suitable aircraft engine known in the art. It should also be noted that if two aircraft engines are used in at least one or each of the first and second aircraft 100, 200, their designs and / or types may be the same or different from each other.Each such aircraft engine, which may be additionally provided with the housing 10 in at least one or each of the first and second aircraft 100, 200, may operate under the control of the control module of the said aircraft, which may issue control commands to the control driver of the aircraft engine of the said aircraft, ensuring the possibility of starting, stopping or changing the operating mode of the said aircraft engine (for example, changing the operating parameters of this aircraft engine of the aircraft).

[0081] In some other embodiments of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be additionally provided with at least one additional rotor (not shown) or a propeller of any suitable type known in the art to ensure the possibility of moving said aircraft through the air (including in an emergency situation, for example in the event of damage, failure and / or complete discharge of this aircraft) or to increase the speed of movement of said aircraft through the air due to the possibility of operation of the rotor or propeller in addition to the propellers 20 used to move said aircraft through the air in a standard situation, or instead of them.In addition, in this embodiment of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may further comprise a power plant (not shown), which may be formed, for example, from one or two turboshaft engines and which may be operatively connected to each of the rotors of said aircraft to provide the ability to supply power to them for driving them.Each such power plant in at least one or each of the first and second aircraft 100, 200, operatively connected to the rotors of the said aircraft, with which the body 10 may be additionally provided, with the provision of transmitting a drive force to them, can operate under the control of the control module of this aircraft, which can issue control commands to the control driver of the power plant (not shown) of this aircraft with the provision of the possibility of starting, stopping or changing the operating mode of the said power plant (for example, changing the operating parameters of this power plant of the aircraft) to change the state of these rotors of the said aircraft.

[0082] In other embodiments of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be additionally provided with a chassis (not shown), which may be a system of retractable supports or at least one rigidly fixed support with which the body 10 may be provided and which may be necessary at least for the takeoff of said aircraft, the landing of said aircraft and / or the placement of said aircraft in one of the parking stations to replenish its power reserve.In particular, the chassis in at least one or each of the first and second aircraft 100, 200 may be of a skid type, a wheel type, a track type, a float type, or any other type known in the art, and the type, shape, dimensions, and material of the chassis of this aircraft are not particularly limited in the framework of the present invention.It should be noted that in this embodiment of the present invention, the chassis in at least one or each of the first and second aircraft 100, 200 can at least ensure (i) the perception of a static load from its own weight when said aircraft is parked; and (ii) the cushioning of dynamic loads that occur during landing of said aircraft (including an emergency landing) on ​​the surface of the earth, water, or the surface of another physical object, at least partially located in airspace, on land, in water, and / or in underwater space, depending on the specific embodiment of the present invention.

[0083] In some other embodiments of the present invention, the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may not be provided with a chassis of any type. In one variation of such an embodiment of the present invention, the bottom of the body 10 in at least one or each of the first and second aircraft 100, 200 included in the first system 1000 may be provided with a shock-absorbing pad (not shown) made of an elastic material (for example, rubber), which can be fastened to said bottom on its outer side, or any other suitable support known in the art and used in the art for known aircraft (in particular, for drones or other unmanned aerial vehicles).

[0084] In addition, in the body 10 of each of the first and second aircraft 100, 200, included in the first system 1000, a power source (not shown) is placed or installed, connected via a power supply circuit (not shown) to both air movers 20, a control module and a communication module with the ability to supply power to them or with the ability to supply power to them under the control of the said control module.

[0085] In Fig. 1A on the left, the first system 1000 for moving a payload according to the present invention is in its first (initial or initial) state, in which the first aircraft 100 for moving a payload is in the air in a given region of space at a given distance from the target payload 400 located on the surface of the earth, wherein the first aircraft 100 can end up in the said region of space, for example, when executing its individual flight program, which can be received by the first aircraft 100 via a communication network from at least one of the control devices of the first system 1000 and which can contain, among other things, the coordinates of the location of the payload 400, which must be captured by the first aircraft 100 for its movement through the air to the target region of airspace or to a ground destination.

[0086] As shown in Fig. 1A-1D, the first aircraft 100 is provided with a gripping ring 300 connected to the body 10 by means of two flexible connecting elements 350, each made in the form of a cable or rope, with the possibility of moving the gripping ring 300 in a substantially vertical direction with respect to the body 10 with a corresponding change in the extension or length of these flexible connecting elements 350, i.e. with the possibility of lowering the gripping ring 300 (i.e. moving away from the body 10 or moving away from it) with an increase in the length of the flexible connecting elements 350 or with the possibility of raising the gripping ring 300 (i.e. moving towards the body 10 or approaching it) with a decrease in the length of the flexible connecting elements 350.Thus, the gripping ring 300 in the first aircraft 100 is essentially suspended on two flexible connecting elements 350, that is, it has two suspension points to the body 10 in the first aircraft 100.

[0087] In some embodiments of the present invention, the gripping ring 300 in the first aircraft 100 may be suspended from at least one flexible connecting element 350 (e.g., one, two, three, four, five, six, seven, eight, nine, ten or more such flexible connecting elements 350), that is, it may have at least one suspension point.

[0088] The housing 10 in the first aircraft 100 is provided with a winding module (not shown) that operates under the control of the control module of the first aircraft 100 and is operatively connected to both flexible connecting elements 350 to provide the possibility of changing the length of at least one or each of these two flexible connecting elements 350 and, therefore, to provide the possibility of a corresponding change in the distance of the gripping ring 300 from this housing 10. As an example, the winding module of the housing 10 can be made in the form of a drive winch or a drive winding drum.It should be noted that the increase in the length of the flexible connecting elements 350 as a result of the issuance by the control module of the first aircraft 100 of the corresponding control commands to the winding module of the first aircraft 100 leads to the lowering of the gripping ring 300 in relation to the body 10, as a result of which the gripping ring 300 moves away from the body 10 or as a result of which the distance between the body 10 and the gripping ring 300 increases.It should also be noted that the reduction in the length of the flexible connecting elements 350 as a result of the issuance by the control module of the first aircraft 100 of the corresponding control commands to the winding module of the first aircraft 100 leads to the lifting of the gripping ring 300 towards the housing 10, as a result of which the gripping ring 300 approaches the housing 10 or as a result of which the distance between the housing 10 and the gripping ring 300 decreases, wherein the said process of lifting the gripping ring 300 can occur until the contact of the gripping ring 300 with the said housing 10 or until the entry of the gripping ring 300 into interaction with the said housing 10.

[0089] In some embodiments of the present invention, each of the flexible connecting elements 350, on which the gripping ring 300 can be suspended from the housing 10, can be operatively connected to a separate winding module, made similar to the above-described winding module of the housing 10.

[0090] In one embodiment of the present invention, in which the winding module with which the body 10 in the first aircraft 100 is provided is made in the form of a winding drum, the body 10 is provided with a drive drum (not shown), operatively connected to both flexible connecting elements 350 with the possibility of winding them onto this drum when rotating / turning said drum in one direction of rotation or with the possibility of unwinding them from this drum when rotating / turning said drum in the opposite direction of rotation.In addition, in such an embodiment of the present invention, the housing 10 in the first aircraft 100 is also provided with a drive device or actuator (not shown) operating under the control of a drive driver having a wired or wireless connection with the control module of the first aircraft 100 for receiving control commands from it, and operatively connected to the winding drum of the housing 10 to ensure the possibility of controlling its operation depending on the said control commands received by the drive driver.In turn, the control module of the first aircraft 100 in such an embodiment of the present invention is further configured with the possibility of issuing control commands to the driver of the drive of the housing 10 via a wired or wireless communication network, ensuring the possibility of activating the said drive, changing the rotation speed of the said drive, changing the direction of rotation of the said drive, or stopping (switching off) the said drive, wherein the said control commands of the control module of the first aircraft 100 can be generated by the control module of the first aircraft 100 in response to the corresponding control instructions received by the control module of the first aircraft 100 from the control device of the first system 1000.

[0091] The gripping ring 300, suspended from the body 10 by means of two flexible connecting elements 350, is designed with the possibility of detachably gripping the payload 400 by entering into tight interaction with this payload 400, tightly gripping this payload 400 along its entire perimeter, tightly gripping a part of the perimeter of this payload 400, or fitting onto this payload 400 with tension.

[0092] In one embodiment of the present invention, the body 10 in the first aircraft 100 may be provided with a gripper that implements the functions of the gripper ring 300. In such an embodiment of the present invention, the gripper of the body 10 may be configured to grip the payload 400, in particular by entering into tight interaction with this payload 400, grasping this payload 400 along its entire perimeter, grasping a part of the perimeter of this payload 400, or landing on this payload 400 with interference.

[0093] In another embodiment of the present invention, the body 10 in the first aircraft 100 may be provided with an annular gripper that implements the functions of the gripping ring 300. In such an embodiment of the present invention, the annular gripper of the body 10 may be designed to grip the payload 400 by entering into tight interaction with this payload 400, grasping this payload 400 along its entire perimeter, grasping a part of the perimeter of this payload 400, or landing on this payload 400 with interference.

[0094] In one of the variations of the embodiment of the present invention, in which the body 10 in the first aircraft 100 is provided with an annular gripper that implements the functions of the gripping ring 300, the annular gripper itself can be formed from two or more rings of the same diameter (for example, two, three, four, five, six, seven, eight, nine, ten or more similar rings), flexibly or rigidly connected to each other to ensure their placement or arrangement in height (vertically) at a given distance from each other and each made with the possibility of entering into tight interaction with the payload 400, the possibility of embracing the payload 400 or the possibility of landing on the payload 400 with tension for its capture in two places located at a distance from each other, essentially corresponding to the specified distance between the rings of the annular gripper.It should be noted that this variation of the embodiment of the present invention, in which the ring grip is formed from two or more rings of the same diameter nested inside each other, is well suited for gripping a payload 400 having a cylindrical body shape.

[0095] In yet another variation of the embodiment of the present invention, in which the body 10 in the first aircraft 100 is provided with a ring gripper that implements the functions of the gripping ring 300, the ring gripper itself can be formed from two or more rings nested within each other (for example, two, three, four, five, six, seven, eight, nine, ten or more similar rings) of different diameters, connected to each other to ensure the possibility of their extension, unfolding or deployment under the control of the control module of the first aircraft 100, which activates the said ring gripper by issuing a corresponding control command to it, thus,that these rings of the annular grip are arranged / spaced vertically (vertically) at a given distance from each other with an increase or decrease in the diameter of said rings in the direction from top to bottom (i.e., as they move away from the body 10, the rings have an increasingly larger diameter or an increasingly smaller diameter, respectively). In particular, in this variation of the embodiment of the present invention, in which the annular grip is formed from two or more rings of different diameters nested inside each other, the annular grip may be additionally provided with a drive device (not shown) operating under the control of the control module of the first aircraft 100 and operatively connected to the rings of the annular grip or configured to interact with the rings of the annular grip to ensure the possibility of their at least partial or complete return extension, unfolding or deployment with respect to each other,wherein the control module of the first aircraft 100 may be further configured to issue control commands to the driver of the drive device of the ring gripper for activating this ring gripper with the possibility of at least a partial or complete return extension, unfolding or deployment of the rings of the ring gripper. In this variation of the embodiment of the present invention, in which the ring gripper is formed from two or more rings of different diameters nested inside each other, said rings of the ring gripper are each configured to enter into tight interaction with the payload 400, to grasp the payload 400 or to land on the payload 400 with interference for its capture in two or more places corresponding in number to said rings of the ring gripper. It should be noted that this variation of the embodiment of the present invention,in which the ring grip is formed from two or more rings of different diameters nested inside each other, is well suited for gripping a payload 400 having a conical body shape.,

[0096] In yet another embodiment of the present invention, the gripping ring 300 may be formed from separate arcuate segments connected to each other with the possibility of reciprocal extension from each other under the control of the control module of the first aircraft 100 to increase the diameter of the gripping ring 300, wherein the gripping ring 300, which makes it possible to adapt the diameter of the gripping ring 300 to a specific shape of the payload 400 that must be captured with the help of such a gripping ring 300. In one of the variations of this embodiment of the present invention, the arcuate segments of the gripping ring 300 may be made telescopic.

[0097] In another embodiment of the present invention, the gripping ring 300 may be further provided with a drive device or actuator (not shown) operating under the control of the control module of the first aircraft 100 and operatively connected to the gripping ring 300 with the possibility of changing its diameter in response to control commands of the control module of the first aircraft 100, received by the driver of the drive of the gripping ring 300 using a wired or wireless communication network (not shown), to which the said driver of the drive of the gripping ring 300 may be connected.In one of the variations of this embodiment of the present invention, the gripping ring 300 may be additionally provided with a sensor module (not shown) connected with the possibility of exchanging data with the control module and configured with the possibility of determining the size of the payload 400 when the first aircraft 100 is in the target region of space at a given distance from the said payload 400, with the possibility of issuing data on the size of the payload to the control module of the first aircraft 100, and the control module of the first aircraft 100 in turn may be additionally configured with the possibility of issuing control commands to the driver of the drive of the gripping ring 300 with the possibility of changing the diameter of the gripping ring 300 depending on the said determined size of the payload 400.

[0098] In another embodiment of the present invention, the gripping ring 300 may be inflatable or capable of being inflated with a fluid (e.g., air, water, any suitable gas, any suitable liquid, or a mixture thereof) with the ability to change its diameter, in particular the ability to increase its diameter upon inflation and decrease its diameter upon deflating. As an example, such an inflatable gripping ring 300 in such an embodiment of the present invention may be an air cushion.In such an embodiment of the present invention, the gripping ring 300 may be operatively connected, via a fluid supply line (for example, a fluid supply tube), to a pump (not shown), which may be provided with the gripping ring 300 itself or the housing 10 and which may be operatively connected, via a fluid intake line (for example, a fluid intake tube), to a container (not shown) for a fluid, which may be additionally provided with the housing 10, wherein the control module of the first aircraft 100 may be additionally connected to the pump with the possibility of exchanging data with it and is configured to control the operation of said pump.Thus, in such an embodiment of the present invention, the control module of the first aircraft 100 can issue control commands to the pump driver to provide the ability to supply under pressure a fluid taken by the pump in a predetermined amount from the fluid container through the fluid intake line into the interior of the gripping ring 300 through the fluid supply line for inflating it (i.e. increasing in diameter) until the inner diameter of the inflated gripping ring 300 is suitable for tightly grasping the payload 400. In addition, in such an embodiment of the present invention, the pump can be switched to the aspirator mode in response to the corresponding control commands of the control module of the first aircraft 100 to provide the ability to pump or suck out the fluid from the previously inflated gripping ring 300 for at least partially or completely returning it to its original state (i.e.i.e., in essence, its deflating), in which this gripping ring 300 has its original (non-enlarged) internal diameter.

[0099] In another embodiment of the present invention, the gripping ring 300 in the first aircraft 100 may be provided on its inner side with an annular pneumatic cushion, which is capable of being inflated with air, gas, a mixture of gases, or any suitable gaseous medium known in the art, thereby increasing its diameter, and which is capable of being deflated by drawing in or releasing said gaseous medium from it, thereby decreasing its diameter, wherein such annular pneumatic cushion may be attached to the inner side of the gripping ring 300, ensuring its tight fit to the gripping ring 300 along the entire perimeter of its inner wall. In the first variation of this embodiment of the present invention, such annular pneumatic cushion may be divided into several separate inflatable segments,hermetically isolated from each other by partitions and connected to each other by means of a common channel communicating with the interior space of each of the said inflatable segments of the air cushion by means of a functional opening made in the body of the said inflatable segment of the air cushion, wherein the said common channel can be connected to a controlled pump operating under the control of the control module of the first aircraft 100 and operatively connected, by means of a fluid intake line (for example, a tube for fluid intake), to a container (not shown) for a fluid, with which the housing 10 in the first aircraft 100 or the housing of the gripping ring 300 can be additionally provided,wherein the control module of the first aircraft 100 may be further connected to said controlled pump with the ability to exchange data with it and is configured to control the operation of said pump by issuing corresponding control instructions to it for changing its operating mode (switching on, switching off, fluid supply mode, fluid intake mode, etc.). Thus, in such a first variation of this embodiment of the present invention, the control module of the first aircraft 100 may issue control commands to the pump driver to ensure its activation in the fluid supply mode, which provides the possibility of substantially simultaneous supply of fluid under pressure, taken by the pump in a given (target) amount from the fluid tank along the fluid intake line,through a common channel into the interior space of all the inflatable segments of the air cushion for inflating this air cushion (i.e. increasing its diameter) under the control of the control module of the first aircraft 100, in particular until the internal diameter of such an inflated annular air cushion of the gripping ring 300 is suitable for tightly enveloping the target payload 400. In addition, in such a first variation of this embodiment of the present invention, the control module of the first aircraft 100 can issue control commands to the pump driver to ensure its activation in the fluid intake mode (i.e., essentially in the aspirator mode), which makes it possible to create a negative pressure (vacuum) in the common channel, sufficient for essentially simultaneously pumping or sucking out the fluid from the segments of the inflated air cushion of the gripping ring 300,for their at least partial or complete return to their original states (i.e., in essence, for their partial or complete deflating), upon reaching which the gripping ring 300 takes its original (non-increased) size (i.e., acquires the original internal diameter as a whole) or acquires a limitedly reduced internal diameter sufficient for the gripping ring 300 to exit tight interaction with the payload 300. In the second variation of this embodiment of the present invention, the annular air cushion may have a common internal space (i.e., an internal space not divided into segments), communicating through a functional opening with a functional channel connected to a controlled pump that operates and is designed similarly to the controlled pump,described above in relation to the first variation of this embodiment of the present invention. In the third variation of this embodiment of the present invention, the annular air cushion can be similarly divided into several separate inflatable segments, each of which communicates through a functional opening formed therein with a corresponding one of the functional channels connected through a distribution module operating under the control of the control module of the first aircraft 100 and connected to a controlled pump operating and designed as a whole similar to the controlled pump described above in relation to the first variation of this embodiment of the present invention, with the possibility of alternately or selectively connecting said controlled pump to one of said functional channels.

[0100] In some embodiment of the present invention, the body 10 in the first aircraft 100 may be provided with a gripper that implements the functions of the gripper ring 300, wherein such a gripper may have any shape and any dimensions suitable for gripping the payload 400, in particular for gripping the payload 400 by entering into a tight interaction with this payload 400, grasping this payload 400 along its entire perimeter, grasping a part of the perimeter of this payload 400 or landing on this payload 400 with interference, wherein such a gripper may be additionally configured with the possibility of changing its shape and / or its dimensions under the control of the control module of the first aircraft 100 before using such a gripper to grip the target payload 400, which makes it possible to adapt this gripper to the shape and / or overall dimensions of the payload 400, which must be gripped with the help of such a gripper.

[0101] In some other embodiment of the present invention, the body 10 in the first aircraft 100 may be provided with a gripper that implements the functions of the gripper ring 300, wherein such a gripper may have a variable shape and / or variable dimensions and may be additionally provided with a drive device or actuator (not shown) operating under the control of the control module of the first aircraft 100 and operatively connected to the gripper with the possibility of its extension, unfolding or deployment in response to the corresponding commands issued by the control module of the first aircraft 100 to the gripper drive driver, in order to give said gripper a shape and / or overall dimensions suitable for gripping the payload 400.

[0102] In some other embodiment of the present invention, the gripping ring 300 may be configured to be releasably connected or secured to the payload 400 to be gripped.

[0103] In other embodiments of the present invention, the gripping ring 300 may be configured to be releasably connected or secured to at least one or each of the flexible connecting elements 350.

[0104] In other embodiments of the present invention, the payload 400 or the gripping ring 300 may be further provided with a docking module configured to enable the formation of an additional detachable connection between the payload 400 and the gripping ring 300 when the payload 400 is gripped by the gripping ring 300.

[0105] In some embodiments of the present invention, the gripping ring 300 may be further provided with two or more docking modules (e.g., two, three, four, five, six, seven, eight, nine, ten or more docking modules), wherein said docking modules may be mounted on the same side of the gripping ring 300 body or on different sides of the gripping ring 300 body (e.g., on opposite or adjacent sides of the gripping ring 300 body). In one variation of this embodiment of the present invention, at least one of the docking modules with which the gripping ring 300 body may be provided may be mounted inside said gripping ring 300 body or may be partially embedded in the gripping ring 300 body.In another variation of this embodiment of the present invention, at least one first docking module of the docking modules with which the body of the gripping ring 300 may be provided may be installed inside this body of the gripping ring 300, and at least one second docking module of said docking modules may be installed outside this body of the gripping ring 300.

[0106] In embodiments of the present invention in which the body of the gripping ring 300 may be further provided with one or more docking modules, each of such docking modules may be designed as one of the following connecting / fastening means or any suitable combination thereof: (i) a mechanical connecting or fastening element (e.g., a hook, bracket, grip, fastener, mounting groove, hook or clasp, latch, bracket, eye, clamp, etc.) for mating with corresponding mating mechanical elements (i.e., with the mating part), (ii) an electromechanical gripper, operating under the control of the control module of the first aircraft 100 and configured to grip the mating gripping element (i.e., the mating part), (iii) an electromagnetic gripper, operating under the control of the control module of the first aircraft 100 and configured to grip the mating gripping element (i.e.,(iv) a vacuum gripper operated by a control module of the first aircraft 100 and configured to grip a mating gripping element (i.e., a mating part), etc. In one of the variations of such embodiments of the present invention, the mating part, with which the mating module of the gripping ring body 300 can be releasably engaged, can be mounted on a movable element or mechanism (for example, on a carriage), which can be mounted on the payload body 400 with the ability to move along it or can be mounted in the payload body 400 with the ability to move in it. In another variation of this embodiment of the present invention, the mating part, with which the mating module of the gripping ring 300 can be releasably engaged, can be mounted in the payload body 400 or on such a payload body 400.

[0107] In embodiments of the present invention, in which the body of the gripping ring 300 may be additionally provided with one or more docking modules, each of such docking modules may be a fixed connecting / fastening means (including a fixed connecting / fastening mechanism or a fixed connecting / fastening structure), which may be made with the possibility of entering into a detachable interaction with the corresponding counterpart, wherein said fixed fastening means may be rigidly or removably fixed to the body of the gripping ring 300 from its outer side or may be partially embedded / built into this body of the gripping ring 300, providing the possibility of access to it from the outer side of said body.It should be noted that in such embodiments of the present invention, the mating part, in detachable interaction with which the mating module of the gripping ring 300, made in the form of such a fixed fastening means, can be made fixed and can be installed in the body of the payload 400 or on such a body of the payload 400.

[0108] In embodiments of the present invention in which the body of the gripping ring 300 may be further provided with one or more docking modules, each of such docking modules may be a movable connecting / fastening means (including a movable connecting / fastening mechanism or a movable connecting / fastening structure), which may operate under the control of the control module of the first aircraft 100 (for example, a controlled carriage) or which may not operate under the control of the control module of the first aircraft 100 (for example, one or more running rollers or rollers), wherein said fastening means may be configured to enter into a detachable interaction with the corresponding counterpart,wherein said movable fastening means may be rigidly or removably fixed to the body of the gripping ring 300 from its outer side or may be partially embedded / built into this body of the gripping ring 300, providing the possibility of access to it from the outer side of said body of the gripping ring 300. It should be noted that in such embodiments of the present invention, the counter part, in detachable interaction with which the mating module of the gripping ring 300, made in the form of such a movable fastening means, may enter, must be made stationary and can be installed in the body of the payload 400 or on such a body of the payload 400.

[0109] In some other embodiments of the present invention, the body 10 in the first aircraft 100, which is part of the first system 1000, may be provided with a gripper that implements the functions of the gripper ring 300 and operates under the control of the control module of the first aircraft 100 with the ability to grip the payload 400, wherein such a gripper may be secured to the said body 10 on its outer side, connected to the body 10, partially embedded in the body 10, completely embedded in the body 10 with the ability to at least partially exit from it, or the like.In such embodiments of the present invention, the gripper, which can be provided with the body 10 in the first aircraft 100, can be made with the possibility of its at least partial deployment, unfolding, extension or sliding under the control of the control module of the first aircraft 100, ensuring the possibility of placing the said gripper or its part at a given distance from the body 10 for capturing the payload 400 and can be made with the possibility of its return to the initial state or position under the control of the control module of the first aircraft 100, ensuring the possibility of attracting the captured payload 400 to the body 10.In one of the variations of such embodiments of the present invention, the gripper, which can be provided with the body 10 in the first aircraft 100, can be completely installed or secured in the body 10 (that is, in the interior space of the body 10 in the first aircraft), and can also be made with the possibility of its at least partially extending from said body 10 and / or the possibility of its deployment outside of said body 10 under the control of the control module of the first aircraft 100 with the possibility of capturing the payload 400 and can be made with the possibility of its return to the original state or position under the control of the control module of the first aircraft 100 with the possibility of attracting the captured payload 400 to the body 10.In another variation of such embodiments of the present invention, the gripper, which can be provided with the body 10 in the first aircraft 100, can be partially embedded or built into this body 10, and can also be made with the possibility of its at least partial deployment, unfolding or extension from said body 10 under the control of the control module of the first aircraft 100 with the provision of the possibility of capturing the payload 400 and can be made with the possibility of its return to the initial state or position under the control of the control module of the first aircraft 100 with the provision of the possibility of attracting the captured payload 400 to the body 10.In another variation of such embodiments of the present invention, the gripper, which can be provided with the body 10 in the first aircraft 100, can be initially installed or secured on the outside of said body 10, and can also be made with the possibility of its at least partially extending, unfolding or deploying, ensuring its removal to the side of this body 10 under the control of the control module of the first aircraft 100, ensuring the possibility of capturing the payload 400, and can be made with the possibility of its return to the original state or position under the control of the control module of the first aircraft 100, ensuring the possibility of attracting the captured payload 400 to the body 10.

[0110] In some variation of such embodiments of the present invention, in which the body 10 in the first aircraft 100 can be provided with a gripper that implements the functions of the gripper ring 300, such a gripper can be a controlled gripper that can be secured to the body 10 in the first aircraft 100 on its outer side, secured inside the body 10 in the first aircraft 100 or partially embedded / built into this body 10 and that can operate under the control of the control module of the first aircraft 100, wherein access to such a controlled gripper can be provided by, for example, opening a covering or enclosing structure that can be rigidly secured to the body 10 on its outer side or partially embedded / built into this body 10 and that can operate under the control of the control module of the first aircraft 100,wherein such a barrier structure may be, for example, (i) a hatch, door or flaps formed in the body of the housing 10, or (ii) a hatch, door or flaps formed in a separate protective housing surrounding or covering the said at least one free docking module 130, or (iii) an element or plate fixed to the housing 10 and preventing the possibility of performing an operation of deploying, extending, unfolding or extending the gripping structure, or an opening protective cover, casing or housing preventing access to the controlled gripping means from the outside of the housing 10, or (iv) a combination of the above alternative embodiments of such a barrier structure. In this variety of embodiments of the present invention, the possibility of deploying, extending, unfolding or extending the gripping structure can be provided under the control of the control module of the first aircraft 100 by, for example,opening, unfolding, swinging open, shifting, sliding or removing such a barrier structure under the control of the control module of the first aircraft 100 with the provision of the possibility of its subsequent return to its original state or position under the control of the control module of the first aircraft 100 (as such a need arises, in particular after the return of the controlled gripping means to its original state or position).,

[0111] The housing 10 in each of the first and second aircraft 100, 200 included in the first system 1000 is provided with a through channel or passage (not shown) extending generally vertically through the said housing 10, wherein the said through passage opens with an inlet (not shown) providing communication of this through channel with the environment on one side of the housing 10, on which the gripping ring 300 is located, suspended on flexible connecting elements 350, and having a shape and dimensions suitable for the entry or insertion of the gripping ring 300 into it, and opens with an outlet (not shown) providing communication of this through channel with the environment on the other (opposite) side of the housing 10, on which the bladed air movers 20 are located, and having a shape and dimensions suitable for the exit or withdrawal of the gripping ring 300 from it,placed or inserted into the through passage of the housing 10 through the inlet opening of the housing 10, ensuring its advancement along this through passage of the housing 10 to the specified outlet opening of the channel of the housing 10.,

[0112] Thus, the gripping ring 300 is configured to move substantially in a vertical direction in the through passage of the housing 10 in the first aircraft 100 under the control of the control module of the first aircraft 100, which allows the gripping ring 300 to advance the captured payload 400 through the through passage of the housing 10 (i.e., to move between the inlet opening of the passage of the housing 10 and the outlet opening of the housing 10, in particular to move along the through passage of the housing 10 from the inlet opening of the passage of the housing 10 towards the outlet opening of the passage of the housing 10), with the possibility of at least a partial or complete extension of the captured payload 400 from the through passage of the housing 10.

[0113] In particular, the through passage of the housing 10 in the first aircraft 100 is provided with one or more guides (not shown) secured or installed in said through passage of the housing 10, and the gripping ring 300 is further configured to engage with at least one or each of said guides of the housing 10 when entering the inlet opening of the passage of the housing 10, ensuring the possibility of moving the gripping ring 300 together with the payload 400 captured by it along said guide of the housing 10 in said through passage of the housing 10. Thus, the guides of the housing 10 in the first aircraft 100 ensure the possibility of moving the gripping ring 300 together with the payload 400 captured by it along the through passage of the housing 10 from the inlet opening of the passage of the housing 10 to the outlet opening of the passage of the housing 10.It should be noted that in order to introduce or insert the gripping ring 300 together with the payload 400 captured by it into the inlet opening of the passage of the housing 10, the control module of the first aircraft 100 issues corresponding control commands to the winding module of the housing 10, operatively connected to the flexible connecting elements 350, in order to activate it in the winding mode, which leads to the winding of the flexible connecting elements 350 on the winding module of the housing 10 with the provision of a decrease in the extension or length of the flexible connecting elements 350 outside the housing 10, that is, to the approach or attraction (pulling) of the gripping ring 300 together with the payload 400 captured by it to the housing 10, until the moment of entry of the gripping ring 300 itself into the inlet opening of the passage of the housing 10, at which time the said gripping ring 300 enters into a detachable interaction with the guides of the housing 10.It should also be noted that the flexible connecting elements 350 are connected to the housing 10 and the gripping ring 300 in such a way that the gripping ring 300 itself and, consequently, the payload 400 that can be gripped by this gripping ring 300 are precisely positioned or centered with respect to the inlet opening of the passage of the housing 10.

[0114] In addition, to ensure the detachable interaction of the gripping ring 300 with the guides of the housing 10, the housing of the gripping ring 300 is provided on its outer side with one or more docking modules made with the possibility of entering into a detachable interaction with the guides of the housing 10 and operating under the control of the control module of the first aircraft 100, wherein at least one or each of the said docking modules of the gripping ring 300 can be made, for example, in the form of (i) a controlled mechanical connecting or fastening element (for example, a hook, bracket, grip, fastener, mounting groove, hook or hook, latch, bracket, eye, clamp, etc.) for detachable docking with the guides of the housing 10 (i.e.with a corresponding counter part formed on at least one or each of the guides of the housing 10), (ii) an electromechanical gripper, operating under the control of the control module of the first aircraft 100 and configured to grip a counter gripping element on at least one or each of the guides of the housing 10 (i.e. a counter part formed on at least one or each of the guides of the housing 10), (iii) an electromagnetic gripper or electromagnet, operating under the control of the control module of the first aircraft 100 and configured to interact with a counter element on at least one or each of the guides of the housing 10 (i.e.with a counter part formed on at least one or each of the guides of the housing 10), (iv) a vacuum gripper operating under the control of the control module of the first aircraft 100 and configured to grip a counter gripping element on at least one or each of the guides of the housing 10 (i.e. a counter part formed on at least one or each of the guides of the housing 10), or the like.

[0115] In addition, to move the gripping ring 300 together with the payload 400 captured by it along the guides of the body 10 from the inlet opening of the passage of the body 10 to the outlet opening of the passage of the body 10, the gripping ring 300 is additionally provided with one or more modules for moving the gripping ring, secured or installed on the body of the gripping ring 300 on its outer side, made with the possibility of interacting with the guides of the body 10 and operating under the control of the control module of the first aircraft 100.In particular, when the gripping ring 300 enters into detachable interaction with the guides of the body 10, the control module of the first aircraft 100 issues corresponding control commands to at least one or each of the said modules for moving the gripping ring to activate them, ensuring their interaction with the guides of the body 10 to advance the gripping ring 300 together with the payload 400 captured by it in the through passage of the body 10.For example, at least one or each of the gripping ring movement modules with which the gripping ring housing 300 is provided may be implemented in the form of a driven wheel module provided with rotating rollers, shafts or wheels (including toothed wheels) driven into rotation by a controlled drive connected with the possibility of exchanging data with the control module of the first aircraft 100, wherein the control module of the first aircraft 100 may be further implemented with the possibility of issuing corresponding control commands to said drive for controlling the operation of said driven wheel module of the gripping ring 300, in particular for changing the speed and / or direction of rotation of said wheels of the driven wheel module of the gripping ring 300 and, consequently, changing, accordingly, the speed and / or direction of movement of the gripping ring 300 in the through passage of the housing 10.Thus, each of the gripping ring movement modules, with which the gripping ring housing 300 is equipped, essentially implements the function of a drive carriage, configured with the possibility of simultaneously moving along at least one or each of the guides of the housing 10 in the through passage of the housing 10 from the inlet opening of the passage of the housing 10 to the outlet opening of the passage of the housing 10.

[0116] According to one embodiment of the present invention, at least on one or each of the guides of the housing 10 in the first aircraft 100, a drive carriage (not shown) may be movably mounted, configured to move along said guide of the housing 10 under the control of the control module of the first aircraft 100, or any drive functional mechanism performing the function of such a drive carriage may be movably mounted.Thus, in this embodiment of the present invention, the gripping ring 300 is further configured to enter into a detachable interaction with at least one or each of the guides of the housing 10 by means of a carriage movably mounted on said guide of the housing 10, when entering the inlet opening of the housing 10, ensuring the possibility of moving the gripping ring 300 together with the payload 400 captured by it along said guide of the housing 10 under the control of the control module of the first aircraft 100, issuing control commands to the drive of said drive carriage for at least setting it in motion, stopping it, changing the speed of its movement or changing the direction of its movement.

[0117] According to another embodiment of the present invention, the gripping ring 300 may be further provided with one or more driven working elements or working bodies that operate under the control of the control module of the first aircraft 100 and are configured to interact with at least one or each of the guides of the housing 10 or the wall of the through passage of the housing 10 in response to the corresponding control commands of the control module of the first aircraft 100, ensuring the possibility of moving or advancing the gripping ring 300 together with the payload 400 captured by it along at least one or each of the guides of the housing 10, installed in the through passage of the housing 10, from the inlet opening of the passage of the housing 10 towards the outlet opening of the passage of the housing 10.

[0118] According to another embodiment of the present invention, in the first aircraft 100, the gripping ring 300 may be initially or initially mounted on one or more guides of the housing 10, and for mounting the gripping ring 300 on said guides of the housing 10, at least one drive carriage may be used, configured to move along said guides of the housing 10 under the control of the control module of the first aircraft 100, so that the movement of said at least one drive carriage of the housing 10 in said through passage of the housing 10 in response to corresponding control commands of the control module of the first aircraft 100, setting the operating mode of said at least one drive carriage of the housing 10 (i.e. at least (i) activation or switching on to start the movement, (ii) switching off to stop or complete the movement,(iii) changing the direction of movement or changing the speed of movement, (iv) setting the stopping point), provides the possibility of moving the gripping ring 300 itself with the payload 400 captured by it on the said at least one drive carriage of the housing 10 along the said guides of the housing 10. In addition, in such an embodiment of the present invention, at least one or each of the guides of the housing 10 in the first aircraft 100 can be movably mounted on the side wall of the through passage of the housing 10 and is made with the possibility of return unfolding, deploying or extending from the housing 10 under the control of the control module of the first aircraft 100 with the provision of placing its free end at a predetermined distance from the housing 10 on either of the two opposite sides of the housing 10,that (i) provides the possibility of extending the guides of the housing 10 together with the gripping ring 300 installed thereon from the inlet opening of the housing 10 under the control of the control module of the first aircraft 100 to a predetermined distance from the housing 10 (i.e. beyond the housing 10), sufficient to ensure the possibility of entering said gripping ring 300 into releasable interaction with the payload 400, and (ii) provides the possibility of extending the guides of the housing 10 together with the gripping ring 300 installed thereon, holding or grasping the payload 400, from the outlet opening of the housing 10 under the control of the control module of the first aircraft 100 to a predetermined distance from the housing 10 (i.e. beyond the housing 10),sufficient to ensure the possibility of said payload 400 leaving the interaction with the gripping ring 300 and the possibility of gripping this payload 400 by the gripping ring of the second aircraft 200. It should be noted that in the first variation of such an embodiment of the present invention, when the guides of the housing 10 together with the gripping ring 300 installed on them are extended from the inlet of the housing 10 under the control of the control module of the first aircraft 100 to a predetermined distance from the housing 10, the gripping ring 300 may already be on said extended guides of the housing 10 in the target area or in the target place suitable for using this gripping ring 300 to grip the payload 400 (i.e. it may initially or initially be located at the ends of the guides of the housing 10, which turn out to be extended beyond the housing 10),wherein the gripping ring 300 may be additionally suspended from the body 10 by means of flexible connecting elements 350, holding the gripping ring 300 in the specified target location on these extended guides of the body 10, or it may not be additionally suspended from the body 10 by means of flexible connecting elements 350 (i.e. the flexible connecting elements 350 may not be engaged or may be absent altogether). In the second variation of such an embodiment of the present invention, when the guides of the body 10 together with the gripping ring 300 mounted thereon are extended from the inlet opening of the body 10 under the control of the control module of the first aircraft 100 by a predetermined amount of extension beyond the body 10, the gripping ring 300, initially or initially located on the guides of the body 10 within the through passage of the body 10,can be moved on at least one drive carriage of the housing 10 along said extended guides of the housing 10 in response to corresponding control commands issued by the control module of the first aircraft 100 to said at least one carriage of the housing 10, to a target location on said extended guides of the housing 10 (in particular, to a target location at the ends of these guides of the housing 10 extended beyond the housing 10, located at a distance from the housing 10, generally corresponding to the degree of extension of the guides of the housing 10), suitable for using this gripping ring 300 to grip the payload 400, wherein the gripping ring 300 can be additionally suspended from the housing 10 by means of flexible connecting elements 350 holding the gripping ring 300 in said target location on these extended guides of the housing 10,and may not be additionally suspended from the body 10 using flexible connecting elements 350 (i.e. flexible connecting elements 350 may not be used, or may be absent altogether). In addition, in the above-described first or second variation of such an embodiment of the present invention, after using the gripping ring 300 extended from the housing 10 when the guides of the housing 10 on which this gripping ring 300 is mounted are extended from it, to grip the payload 400, such a gripping ring 300 with the payload 400 captured by it can remain in the same target place on the guides of the housing 10, and the guides of the housing 10 themselves can be pushed back into the through passage of the housing 10 under the control of the control module of the first aircraft 100, so that the gripping ring 300 with the payload 400 captured by it, installed with the help of the carriages of the housing 10 on the pushed-in guides of the housing 10,may end up inside the through passage of the housing 10, wherein before the start of the extension of said guides from the opposite side of the housing 10 under the control of the control module of the first aircraft 100, such a gripping ring 300 with the payload 400 captured by it, pushed inside the through passage of the housing 10, may remain in the same target location on the pushed-in guides of the housing 10, but as an alternative, may also be moved on said carriages of the housing 10 along said guides of the housing 10 within the through passage of the housing 10 under the control of the control module of the first aircraft 100, in particular, may be moved or advanced within the through passage of the housing 10 to the outlet opening of the passage of the housing 10, generally corresponding to the target location at the opposite ends of the guides of the housing 10,which, after the extension of these guides of the housing 10 beyond the housing 10 on its opposite side by a given extension value, will be suitable for capturing the payload 400 extended together with the gripping ring 300 beyond the housing 10, with the help of the gripping ring of the second aircraft 200. In addition, in the above-described first or second variation of such an embodiment of the present invention, the guides of the housing 10, which were previously pushed inside the through passage of the housing 10 and on which the gripping ring 300 with the payload 400 captured by it is located, can be extended beyond the housing 10 on its opposite side (i.e., from the side of the housing 10 on which the bladed air movers 20 are located, and which is opposite the other side of the housing 10 from which the capture of the payload 400 was carried out) by a given extension value under the control of the control module of the first aircraft 100. It should be noted,that in the above-described first or second variation of such an embodiment of the present invention, in the case where the gripping ring 300 together with the payload 400 captured by it remains positioned in the same target location on the guides of the housing 10 when they are pushed inside the through passage of the housing (that is, in the target location on the guides of the housing 10, in which the gripping ring 300 was used to grip the payload 400), after these guides of the housing 10 have been extended beyond the housing 10 on its opposite side by a given amount of extension, the said gripping ring 300 can be moved on at least one carriage, on which the said gripping ring 300 is mounted on the said guides of the housing 10, along the said guides of the housing 10 under the control of the control module of the first aircraft 100 to the target location on these extended guides of the housing 10,which is essentially located at the opposite ends of the guides of the housing 10, extended beyond the housing 10 from the said opposite side of the housing 10, at a given distance from the housing 10, generally corresponding to the amount of extension of these guides of the housing 10, and which is suitable for capturing the payload 400, which turns out to be removed together with the gripping ring 300 from the housing 10 by the said distance when this gripping ring 300 is moved together with the payload 400 captured by it to the said target location on the extended ends of the guides of the housing 10, with the help of the gripping ring of the second aircraft 200. It should also be noted that in the above-described first or second variation of such an embodiment of the present invention, in another case, when after retracting the guides of the housing 10 together with the gripping ring 300 installed on them, holding the payload 400 captured by it,this gripping ring 300 together with the payload 400 captured by it was moved along the guides of the housing 10 within the through passage of the housing 10 to the outlet opening of the passage of the housing 10, after these guides of the housing 10 have been extended beyond the housing 10 from its opposite side by a given amount of extension, the said gripping ring 300 may already be located on the said extended guides of the housing 10 in a target location, which will essentially be located at the opposite ends of the guides of the housing 10, extended beyond the housing 10 from the said opposite side of the housing 10, at a given distance from the housing 10, generally corresponding to the amount of extension of these guides of the housing 10, and which will be suitable for capturing the payload 400,which turns out to be removed together with the gripping ring 300 from the body 10 by the specified distance when this gripping ring 300 is moved together with the payload 400 captured by it to the specified target location on the extended ends of the body 10 guides, with the help of the gripping ring of the second aircraft 200. In the above-described first or second variation of such an embodiment of the present invention, when the body 10 guides are extended from the body 10 from its opposite side by a given amount of extension suitable for the subsequent capture of the payload 400 with the help of the gripping ring of the second aircraft 200, the flexible connecting elements 350 can continue to hold the gripping ring 300, which, after the body 10 guides are extended from the body 10, can already immediately be in the target location suitable for the subsequent capture of the payload 400 with the help of the gripping ring of the second aircraft 200,or can be moved on at least one carriage of the housing 10 along the extended guides of the housing 10 to the specified target location under the control of the control module of the first aircraft 100, but may no longer be involved in this (or may be initially absent altogether). It should be noted that the use of flexible connecting elements 350 to ensure the retention of the extended gripping ring 300 together with the payload 400 captured by it in the target location on the extended guides of the housing 10, suitable for the subsequent capture of this extended payload 400 with the help of the gripping ring of the second aircraft 200, additionally stabilizes the spatial position of the specified extended payload 400,which in turn simplifies and accelerates the process of its capture with the help of the capture ring of the second aircraft 200. In such an embodiment of the present invention, the payload 400 can come out of interaction with the capture ring 300, with which the body 10 in the first aircraft 100 is provided and which continues to hold it after the extension of this capture ring 300 together with the payload 400 captured by it beyond the body 10 on its opposite side, when the said payload 400 is captured by the capture ring of the second aircraft 200 with the subsequent pulling or attracting of this capture ring of the second aircraft 200 to the body of the second aircraft 200 under the control of the control module of the second aircraft 200.

[0119] Further, when the gripping ring 300 reaches the outlet opening of the passage of the housing 20 together with the payload 400 captured by it, which can be controlled using, for example, an infrared line crossing sensor (not shown), with which the housing 10 can be additionally equipped and which can be connected with the possibility of exchanging data with the control module of the first aircraft 100, the control module of the first aircraft 100 can receive a signal from the said infrared line crossing sensor, indicating that the gripping ring 300 has reached the level of the outlet opening of the passage of the housing 20, with the possibility of issuing control commands to the guide extension modules (not shown),with which the body 10 is additionally provided and each of which is operatively connected to the corresponding one of the guides of the body 10 with the provision of the possibility of its movement or displacement by a given amount and in a given direction in response to the said control commands of the control module of the first aircraft 100. In particular, in response to the control commands of the control module of the first aircraft 100, the guides of the body 10, on which the gripping ring 300 with the payload 400 captured by it is mounted, can be extended, by means of the guide extension modules of the aircraft 100, operatively connected to the said guides of the body 10, from the through passage of the body 10 on the side of the bladed air movers 20 by a given amount beyond the body 10,so that the gripping ring 300 is positioned at a given distance from the housing 10 (i.e., it completely exits the through passage of the housing 10 and is removed from the housing 10 by a given distance), and the payload 400 captured by said gripping ring 300 is only partially extended from the through passage of the housing 10 by a distance suitable for capturing said payload 400 by its said partially extended portion using the gripping ring of the second aircraft 200. Alternatively, as a result of the complete exit of the gripping ring 300 from the through passage of the housing 10, the payload 400 captured by said gripping ring 300 may be completely extended from the through passage of the housing 10 by a given distance (i.e., it may be removed from the housing 10 by a given distance),suitable for capturing said payload 400 using the capturing ring of the second aircraft 200. It should be noted that the payload 400 can be removed from interaction with the capturing ring 300, with which the body 10 in the first aircraft 100 is provided, as a result of capturing said payload 400 by the capturing ring of the second aircraft 200, followed by pulling or attracting this capturing ring of the second aircraft 200 to the body of the second aircraft 200 under the control of the control module of the second aircraft 200.

[0120] It should be noted that when the gripping ring 300 is advanced together with the payload 400 captured by it along the guides of the body 10 with the help of the gripping ring movement modules with which the gripping ring 300 is provided, and when the said guides of the body 10 are subsequently extended together with the gripping ring 300 installed thereon, which envelops or holds the payload 400, by a given amount beyond the body 10, the flexible connecting elements 350 connecting the body 10 and the gripping ring 300 essentially remain connected to the said gripping ring 300 all the time, but can be removed from interaction with this gripping ring 300 in response to the corresponding control signals of the control module of the first aircraft 100, which can be issued to the controlled docking modules,by means of which the said flexible connecting elements 350 are docked or connected to the gripping ring 300 and with which the gripping ring 300 may be further provided. In particular, the control module of the first aircraft 100 may be further configured to issue corresponding control signals to the controlled docking modules of the gripping ring 300 for detaching or disconnecting the flexible connecting elements 350 from the gripping ring 300 when, for example, the following two conditions are met: (1) the guides of the housing 10 together with the gripping ring 300 installed thereon, which embraces or holds the payload 400, are extended by a predetermined amount beyond the housing 10, controlled by the control module of the first aircraft 100, and (2) the control module of the first aircraft 100 has received a signal from the second aircraft 200,indicating that the second aircraft 200 has occupied the proper spatial position with respect to the first aircraft 100, or a signal indicating that the gripping ring of the second aircraft 200 has been properly positioned in space with respect to said payload 400 held by the gripping ring 300, or a signal indicating that said payload 400 held by the gripping ring 300 has been captured by the gripping ring of the second aircraft 200.

[0121] In some embodiments of the present invention, the flexible connecting elements 350 connecting the housing 10 and the gripping ring 300 may be removed from interaction with this gripping ring 300 when the gripping ring 300 with the payload 400 captured by it enters into interaction with the guides of the housing 10.

[0122] In some other embodiments of the present invention, the flexible connecting elements 350 connecting the housing 10 and the gripping ring 300 may be removed from interaction with this gripping ring 300 upon partial extension of the gripping ring 300 with the payload 400 captured by it from the through passage of the housing 10 or upon reaching the outlet opening of the passage of the housing 10 by the gripping ring 300 with the payload 400 captured by it.

[0123] Thus, as described above, the gripping ring 300 in the first aircraft 100, which is part of the first system 1000, is configured to come out of interaction with the payload 400, previously captured by this gripping ring 300, at least upon partial extension of this payload 400 from the through passage of the housing 10 (i.e., when a part of the payload 400 is located or placed outside the housing 10, and the remaining part is still in the through passage of the housing 10) and the capture of said extended payload by the gripping ring of the second aircraft 200.In particular, the force with which the gripping ring of the second aircraft 200 is pulled or attracted to the body of the second aircraft 200 under the control of the control module of the second aircraft 200 must at least exceed the force with which the gripping ring 300, with which the body 10 in the first aircraft 100 is provided, continues to hold the said gripping ring 300 (i.e. the force of pulling the payload 400, captured by the gripping ring of the second aircraft 200, must be sufficient for this payload 400 to leave the interaction with the gripping ring 300), which will allow the gripping ring of the second aircraft 200 to remove the payload 400 from the interaction with the gripping ring 300 and, therefore, to transfer this payload 400 from the first aircraft 100 to the second aircraft 200.It should also be noted that the flexible connecting elements 350 can continue to additionally hold the payload 400 until it is captured by the gripping ring of the second aircraft 200, thereby additionally stabilizing the spatial position of the payload 400 extended beyond the body 10, which in turn simplifies the process of its capture by the gripping ring of the second aircraft 200 and / or accelerates the process of its transfer from the first aircraft 100 to the second aircraft 200.

[0124] It should be noted that in the first system 1000 for the primary capture of the payload 400, initially installed on the surface of the earth or any other supporting surface of a moving or stationary physical object, a second aircraft 200 can be used instead of the first aircraft 100, wherein the payload 400 can be transferred in the air not only from the first aircraft 100 to the second aircraft 200, but can also be transferred in the air from one first aircraft 100 to another first aircraft 100 or from one second aircraft 200 to another second aircraft 200.

[0125] The first and second aircraft 100, 200, included in the first system 1000, are preferably designed to be identical or the same in terms of design and functionality, in particular, they have identical shapes and dimensions and are equipped with the same functional technical means described in this document with respect to the first aircraft 100, included in the first system 1000. Thus, the description given above in this document with respect to the design features and operational features of the functional technical means of the first aircraft 100, included in the first system 1000, should essentially be considered a description of both the corresponding functional technical means and the second aircraft 200, included in the same first system 1000.

[0126] According to various embodiments of the present invention, the body 10 in the first aircraft 100 may be provided with two or more driven working elements, wired working elements or driven robotic manipulators operating under the control of the control module of the first aircraft 100, which issues corresponding control commands to the drive drivers of the said driven robotic manipulators, and holding the gripping ring 300 with the possibility of its movement relative to the body 10 of the first aircraft 100. In one of the varieties of such embodiments of the present invention, the driven robotic manipulators can be connected to the gripping ring 300 with the possibility of its rotation or tilt at a given angle under the control of the control module of the first aircraft 100. Thus,in such embodiments of the present invention, the driven robotic manipulators of the first aircraft 100 can move the gripping ring 300 in the airspace to change its spatial position and / or its spatial orientation with respect to the payload 400 that needs to be captured with the help of this gripping ring 300, ensuring the possibility of a tight fit of this gripping ring 300 on the said payload 400 (including by inflating the pneumatic cushion of such a gripping ring to a degree of inflation sufficient to tightly grasp and hold this payload 400) for its capture and movement in the airspace under the control of the control module of the first aircraft 100. In addition,in such embodiments of the present invention, the driven robotic manipulators of the first aircraft 100 may be further configured with the ability to pull the payload 400 captured by them to the body 10 and the ability to advance the payload 400 captured by them through a through passage of the body 10, ensuring its installation or placement in this through passage of the body 10 using one or more docking modules that can be installed inside this through passage of the body 10 or with which the gripping ring 300 itself can be equipped, as a result of which part of this payload 400 is extended from the body 10 from the side on which this body is equipped with bladed air movers 20,wherein after the installation of the payload 400 in the through passage of the body 10, these driven robotic manipulators of the first aircraft 100 can exit interaction with the gripping ring 300 or can continue to hold this payload 400 until the moment it is captured by the gripping ring of the second aircraft 200 by its extended part.

[0127] In particular, as shown in Fig. 1A on the left, in the first (i.e. initial or initial) state of the first system 1000, both flexible connecting elements 350, connecting the gripping ring 300 and the housing 10 with each other with the setting of a distance between them, depending on the degree or amount of unwinding of these flexible connecting elements 350, have a minimum extension or length (i.e. they are wound on the winding module of the housing 10 in the first aircraft 100), so that the gripping ring 300, suspended from the housing 10 on these two flexible connecting elements 350, is pulled to the housing 10 with the provision of a minimum permissible distance between them or with the provision of contact between them and faces the side of the payload 400 to be captured (target), which is located on the surface of the earth and at a distance from which this first aircraft 100 is located, while the bladed air movers 20 operate in a given operating mode,controlled by the control module of the first aircraft 100, with the provision of hovering of this first aircraft 100 in the air in a given region of space at a distance from the indicated payload 400 (i.e. above this payload 400), sufficient for its subsequent capture with the help of the capture ring 300.,

[0128] In Fig. 1A, the second state of the first system 1000 is shown in the center, into which this first system 1000 passes from its first state, shown in Fig. 1A on the left. In particular, in the second state of the first system 1000, shown in Fig. 1A in the center, the first aircraft 100 maintains its spatial location in the air (i.e., is in the air in the same region of space as when the first system 1000 was in its first state), wherein both flexible connecting elements 350, which are in the unwound state, have a maximum extension or length, and the gripping ring 300, which is removed from the body 10 at a distance that generally corresponds to the length of the unwound flexible connecting elements 350, is brought into interaction with the payload 400, ensuring its capture for its subsequent detachment from the ground surface and rise into the air.

[0129] It should be noted that in order to transfer the first system 1000 from the first state shown in Fig. 1A on the left to the second state shown in Fig.1A in the center, the control module of the first aircraft 100 issues the corresponding control commands to the winding module of the body 10 to activate it in a given operating mode with the provision of unwinding the flexible connecting elements 350 from this winding module of the body 10 (for example, from the opposite ends of the bobbin of this winding module) and, consequently, with the provision of approaching the gripping ring 300 with the payload 400 to provide the possibility of interaction of the gripping ring 300 with the payload 400, which can be realized, for example, manually by the user by placing the gripping ring 300 on the payload 400 with tension on it or automatically / semi-automatically using one or more docking modules with which the gripping ring 300 or the payload 400 itself can be equipped and which can operate under the control of the control module of the first aircraft 100.

[0130] In Fig. 1A on the right, a third state of the first system 1000 is shown, into which this first system 1000 passes from its second state, shown in Fig. 1A in the center. In particular, in the third state of the first system 1000, shown in Fig. 1A on the right, the first aircraft 100 is in the air in substantially the same region of space, wherein both flexible connecting elements 350, which are in a partially wound state, have a limited length, the value of which is in the range from a minimum length corresponding to the wound / coiled state of the flexible connecting elements 350, to a maximum length corresponding to the unwound state of the flexible connecting elements 350, and the gripping ring 300 together with the payload 400 captured by it are in the air at a given distance from the body 10, on the whole corresponding to the remaining length of the unwound flexible connecting elements 350, and are removed from the surface of the earth,on which the payload 400 was initially placed at a distance generally corresponding to the amount by which the length of the flexible connecting elements 350 was reduced as a result of their partial unwinding or by which these flexible connecting elements 350 were unwinded.

[0131] It should be noted that in order to transfer the first system 1000 from the second state shown in Fig. 1A in the center to the third state shown in Fig. 1A on the right, the control module of the first aircraft 100 issues corresponding control commands to the winding module of the housing 10 to activate it in a given operating mode with the provision of winding the flexible connecting elements 350 on this winding module of the housing 10 (for example, on the opposite ends of the bobbin of this winding module of the housing 10) and, consequently, with the provision of attracting the gripping ring 300 with the payload 400 captured by it to the housing 10 under the control of the control module of the first aircraft 100 for the subsequent entry of the payload 400 into the inlet opening of the passage of the housing 10.

[0132] Fig. 1B shows on the left the fourth state of the first system 1000, into which this first system 1000 transitions from its third state shown in Fig. 1A on the right. In particular, in the fourth state of the first system 1000 shown in Fig. 1B on the left, the first aircraft 100 continues to be in the air in essentially the same region of space, while both flexible connecting elements 350, which are in the coiled state, have a minimum (minimum permissible) length, the gripping ring 300 is in contact with the body 10 with the provision of entry into a detachable interaction with the guides of the body 10 in the input passage of the body 10, and the payload 400, advanced through the through passage of the body 10, continues to be held by the gripping ring 300 and is partially extended from the body 10 on the side on which this body 10 is equipped with bladed air movers 20 and which is opposite the other side of the body 10,with which this payload 400 was captured by means of the capture ring 300 and with which the capture ring 300 is in contact with this body 10, for the subsequent transfer of this payload 400 from the first aircraft 100 to the second aircraft 200, which can fly up to this first aircraft 100.,

[0133] It should be noted that in order to transfer the first system 1000 from the third state shown in Fig. 1A on the right to the fourth state shown in Fig. 1B on the left, the winding module of the housing 10 continues to operate under the control of the control module of the first aircraft 100 in the same operating mode previously set by the control module of the first aircraft 100 when the first system 1000 transitions to its third state, with the provision of the maximum permissible winding of the flexible connecting elements 350 on this winding module of the housing 10 (for example, on the opposite ends of the bobbin of this winding module of the housing 10) and, consequently, with the provision of the maximum permissible attraction of the gripping ring 300 with the payload 400 captured by it to the housing 10 under the control of the control module of the first aircraft 100, in which the gripping ring 300, still held by the wound flexible connecting elements 350,comes into contact with the housing 10 or adjoins the housing 10 with the provision of entry, by means of the docking modules of the gripping ring 300, operating under the control of the control module of the first aircraft 100, into detachable interaction with the guides of the housing 10 in the input passage of the housing 10, and the payload 400 is advanced through the through passage of the housing 10 with the provision of its partial entry beyond the limits of the housing 10 from the side from which this housing 10 is equipped with air blade propellers 20, so that a part of this payload 400 remains protruding beyond the limits of the housing 10 from its side from which this housing 10 is in contact with the gripping ring 300, and the other part of the payload 400 from its opposite end is extended from the outlet opening of the passage of the housing 10 by an amount sufficient for its subsequent capture by the second aircraft 200 for the specified extended part payload 400,

[0134] In Fig. 1B, the fifth state of the first system 1000 is shown in the center, into which this first system 1000 passes from its fourth state, shown in Fig. 1B on the left. In particular, in the fifth state of the first system 1000, shown in Fig. 1B in the center, the first aircraft 100 has moved through the air to another region of space in accordance with its flight program under the control of the control module of the first aircraft 100, wherein the gripping ring 300 in the first aircraft 100 and the payload 400, held by this gripping ring 300 and placed in the through channel 10 in this first aircraft 100, have essentially the same states as when the first system 100 is in the fourth state. In addition, in this fifth state of the first system 1000, shown in Fig. 1B in the center, the second aircraft 200 is in the area of ​​space,into which the first aircraft 100 has moved through the air in accordance with its flight program, at a given distance from this first aircraft 100, wherein both flexible connecting elements 350 connecting the gripping ring 300 and the housing 10 in the second aircraft 200 have a minimum extension or length (that is, they are wound on the winding module of the housing 10 in the second aircraft 200), so that the gripping ring 300, suspended from the housing 10 in the second aircraft 200 on these two flexible connecting elements 350, is pulled to the housing 10 in this second aircraft 200 and faces the side of the payload 400 to be captured (target), which is partially extended from the housing 10 in the first aircraft 100, wherein the bladed air movers 20 in the second aircraft 200 operate in a given operating mode controlled by the control module of the second aircraft 200,with the provision of hovering of this second aircraft 200 in the air in the specified region of space above the first aircraft 100, and the blade air movers 20 in the first aircraft 100 operate in a given operating mode, controlled by the control module of the first aircraft 100, with the provision of hovering of this first aircraft 100 in the air in the specified region of space, which ensures stabilized spatial positions of the first and second aircraft 100, 200 in relation to each other and, therefore, simplifies and accelerates the process of transferring the payload 400 from the first aircraft 100 to the second aircraft 200.,

[0135] Fig. 1B shows on the right the sixth state of the first system 1000, into which this first system 1000 transitions from its fifth state shown in Fig. 1B in the center. In particular, in the sixth state of the first system 1000 shown in Fig.1B on the right, the first aircraft 100 and the second aircraft 200 continue to be in the air as a whole in the same regions of space as in the fifth state of the first system 1000, wherein both flexible connecting elements 350 in the second aircraft 200, which are in the unwound state, have a maximum extension or length, and the gripping ring 300 in the second aircraft 200, removed from the body 10 of the second aircraft 200 by a distance that generally corresponds to the length of the unwound flexible connecting elements 350 of this second aircraft 200, is brought into interaction with the payload 400, partially extended from the body 10 of the first aircraft 100, with the provision of its capture by the extended part for its further lifting towards the body 10 of the second aircraft 200.

[0136] It should be noted that in order to transfer the first system 1000 from the fifth state shown in Fig. 1B in the center to the sixth state shown in Fig. 1B on the right, the control module of the second aircraft 200 issues appropriate control commands to the winding module, with which the housing 10 in the second aircraft 200 is provided, for activating this winding module of the housing 10 in a given operating mode with the provision of unwinding the flexible connecting elements 350 from this winding module of the housing 10 (for example, from the opposite ends of the bobbin of this winding module of the housing 10) and, consequently, with the provision of approaching the gripping ring 300 of the second aircraft 200, suspended by the said flexible connecting elements 350 to the housing 10 in the second aircraft 200, with the payload 400, still held by the gripping ring 300, with which the housing 10 in the first aircraft 100 is provided,to ensure the possibility of said gripping ring 300 of the second aircraft 200 entering into interaction with this payload 400, which can be implemented, for example, automatically / semi-automatically using one or more docking modules with which the gripping ring 300 of the second aircraft 200 can be equipped (as an alternative, the payload 400 itself) and which can operate under the control of the control module of the second aircraft 200.,

[0137] In Fig. 1C on the left, a seventh state of the first system 1000 is shown, into which this first system 1000 passes from its sixth state shown in Fig. 1B on the right. In particular, in the seventh state of the first system 1000, shown in Fig. 1C on the left, the first aircraft 100 and the second aircraft 200 continue to be in the air in the same regions of space as in the sixth state of the first system 1000, wherein both flexible connecting elements 350 in the second aircraft 200, which are in a partially wound / wound state, have a limited length, the value of which is in the range from a minimum length corresponding to the wound / wound state of the flexible connecting elements 350 of the second aircraft 200, to a maximum length corresponding to the unwound state of the flexible connecting elements 350 of the second aircraft 200,and the gripping ring 300 of the second aircraft 200 together with the payload 400 captured by it are in the air at a given distance from the body 10 of the first aircraft 100, generally corresponding to the length of the flexible connecting elements 350 of the second aircraft 200 remaining after the above-described operation of their partial or limited winding, and are removed from the first aircraft 100, from the body 10 of which the payload 400 was partially extended, at a distance generally corresponding to the value by which the length of the flexible connecting elements 350 of the second aircraft 200 was reduced as a result of their partial winding or by which these flexible connecting elements 350 of the second aircraft 200 were wound. In addition, in the seventh state of the first system 1000, shown in Fig. 1C on the left, the capture ring 300 of the first aircraft 100, still holding the payload 400,captured by the capture ring 300 of the second aircraft 200, and still connected to the body 10 of the first aircraft 100 by means of both flexible connecting elements 350 of the first aircraft 100, partially or limitedly unwound from the winding module of the first aircraft 100, is partially or limitedly extended on the guides of the body 10 of the first aircraft 100 beyond the body 10 of the first aircraft 100 from the side on which this body 10 of the first aircraft 100 is equipped with bladed air movers 20.

[0138] It should be noted that in order to transfer the first system 1000 from the sixth state shown in Fig. 1B on the right to the seventh state shown in Fig. 1C on the left, the control module of the second aircraft 200 issues corresponding control commands to the winding module with which the body 10 in the second aircraft 200 is provided, in order to activate this winding module of the body 10 of the second aircraft 200 in a given operating mode with ensuring limited winding of the flexible connecting elements 350 of the second aircraft 200 on this winding module of the body 10 of the second aircraft 200 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the second aircraft 200) and, therefore,with ensuring the attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200. In addition, the control module of the first aircraft 100 issues corresponding control commands to the modules for moving the gripping ring of the first aircraft 100 to activate them in a given operating mode with ensuring the limited extension of the guides of the body 10 of the first aircraft 100 together with the gripping ring 300 of the first aircraft 100 installed on them beyond the body 10 of the first aircraft 100 from the side on which this body 10 of the first aircraft 100 is equipped with bladed air movers 20; and essentially simultaneously issues corresponding control commands to the winding module with which the body 10 in the first aircraft 100 is equipped,for activating this winding module of the body 10 of the first aircraft 100 in a given operating mode with ensuring a limited unwinding of the flexible connecting elements 350 of the first aircraft 100 from this winding module of the body 10 of the first aircraft 100 (for example, from the opposite ends of the reel of this winding module of the body 10 of the first aircraft 200) and, therefore, with ensuring the possibility of extending the gripping ring 300 of the first aircraft 100, still holding the payload 400, on the guides of the body 10 of the first aircraft 100 towards the second aircraft 200 under the control of the control module of the first aircraft 100. It should be noted,that the above-described operation of limited attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200, the operation of limited extension of the guides of the body 10 of the first aircraft 100 together with the gripping ring 300 of the first aircraft 100 installed thereon beyond the body 10 of the first aircraft 100 under the control of the control module of the first aircraft 100 and the operation of limited unwinding of the flexible connecting elements 350 of the first aircraft 100 under the control of the control module of the first aircraft 100 are carried out essentially simultaneously, in particular in response to the corresponding control commands,received by the control module of the first aircraft 100 and the control module of the second aircraft 200 from the control device of the first system 1000.,

[0139] In Fig. 1C, the eighth state of the first system 1000 is shown in the center, into which this first system 1000 transitions from its seventh state shown in Fig. 1C on the left. In particular, in the eighth state of the first system 1000 shown in Fig. 1C in the center, the first aircraft 100 and the second aircraft 200 continue to be in the air in the same regions of space as in the seventh state of the first system 1000, wherein both flexible connecting elements 350 in the second aircraft 200, which are in an additionally or to a greater extent wound / wound state (in particular, in comparison with the amount of their winding when the first system 1000 is in the previous seventh state), have an additionally or to a greater extent reduced length, the value of which is still in the range from the minimum length corresponding to the wound / wound state of the flexible connecting elements 350 of the second aircraft 200, to the maximum length,corresponding to the unwound state of the flexible connecting elements 350 of the second aircraft 200, but already additionally shifted towards the specified minimum value of the range in comparison with the value of the length of these flexible connecting elements 350 of the second aircraft 200 when the first system 100 is in the seventh state, and the gripping ring 300 of the second aircraft 200 together with the payload 400 captured by it are in the air at an additionally increased or greater distance from the body 10 of the first aircraft 100 (in particular, in comparison with their positions in relation to the body 10 of the first aircraft 100 when the first system 1000 is in the previous seventh state), on the whole corresponding to the length of the flexible connecting elements 350 of the second aircraft 200 remaining after the above-mentioned additional winding has been carried out, and are additionally removed from the first aircraft 100,from the body 10 of which the said payload 400 was further removed, by a distance generally corresponding to the value by which the length of the flexible connecting elements 350 of the second aircraft 200 was reduced in total as a result of their partial unwinding in the seventh state of the first system 1000 and additional unwinding in the eighth state of the first system 1000, or by which these flexible connecting elements 350 of the second aircraft 200 were wound in total when the first system 1000 was in the seventh and eighth states. In addition, in the eighth state of the first system 1000, shown in Fig. 1C in the center, the gripping ring 300 of the first aircraft 100, still holding the payload 400, captured by the gripping ring 300 of the second aircraft 200, and still connected to the body 10 of the first aircraft 100 by means of both flexible connecting elements 350 of the first aircraft 100,additionally or to a greater extent unwound from the winding module of the first aircraft 100 (in particular, in comparison with the amount of their unwinding when the first system 1000 is in the above-described seventh state), is additionally or to a greater extent extended on the guides of the body 10 of the first aircraft 100 beyond the body 10 of the first aircraft 100 from the side on which this body 10 of the first aircraft 100 is equipped with bladed air movers 20.

[0140] It should be noted that in order to transfer the first system 1000 from the seventh state shown in Fig. 1C on the left to the eighth state shown in Fig. 1C in the center, the winding module of the body 10 of the second aircraft 200 continues to operate or function in the operating mode specified by the control module of the second aircraft 200 when the first system 1000 is in the above-described seventh state, with the provision of additional or even greater winding of the flexible connecting elements 350 of the second aircraft 200 on this winding module of the body 10 of the second aircraft 200 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the second aircraft 200) and, therefore,with the provision of additional or even greater attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200. In addition, the modules for moving the gripping ring of the first aircraft 100 continue to operate in the operating mode specified by the control module of the first aircraft 100 when the first system 1000 is in the above-described seventh state, with the provision of additional or even greater extension of the guides of the body 10 of the first aircraft 100 together with the gripping ring 300 of the first aircraft 100 installed thereon beyond the body 10 of the first aircraft 100 from the side on which this body 10 of the first aircraft 100 is equipped with bladed air movers 20,under the control of the control module of the first aircraft 100; and simultaneously with the modules for moving the gripping ring of the first aircraft 100, the winding module of the body 10 of the first aircraft 100 continues to operate in the operating mode specified by the control module of the first aircraft 100 when the first system 1000 is in the above-described seventh state, with the provision of an additional or even greater unwinding of the flexible connecting elements 350 of the first aircraft 100 from this winding module of the body 10 of the first aircraft 100 (for example, from the opposite ends of the bobbin of this winding module of the body 10 of the first aircraft 200) and, consequently, with the provision of the possibility of an additional or even greater extension of the gripping ring 300 of the first aircraft 100, still holding the payload 400,on the guides of the body 10 of the first aircraft 100 towards the second aircraft 200 under the control of the control module of the first aircraft 100. It should be noted that the above-described operation of additional or even greater attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200,the operation of additionally or further extending the guides of the body 10 of the first aircraft 100 together with the gripping ring 300 of the first aircraft 100 installed thereon beyond the body 10 of the first aircraft 100 under the control of the control module of the first aircraft 100 and the operation of additionally or further unwinding the flexible connecting elements 350 of the first aircraft 100 under the control of the control module of the first aircraft 100 are carried out essentially simultaneously, in particular in response to the corresponding control commands received by the control module of the first aircraft 100 and the control module of the second aircraft 200 from the control device of the first system 1000.

[0141] In Fig. 1C, the ninth state of the first system 1000 is shown on the right, into which this first system 1000 transitions from its eighth state shown in Fig. 1C in the center. In particular, in the ninth state of the first system 1000 shown in Fig. 1C on the right, the first aircraft 100 and the second aircraft 200 are in the air in generally the same regions of space as in the previous eighth state of the first system 1000, while both flexible connecting elements 350 in the second aircraft 200, which are in an even greater degree of wound / wound state (in particular, in comparison with the amount of their winding when the first system 1000 is in the previous eighth state), have an even greater degree of reduced length, the value of which is still in the range from the minimum length corresponding to the wound / wound state of the flexible connecting elements 350 of the second aircraft 200, to the maximum length,corresponding to the unwound state of the flexible connecting elements 350 of the second aircraft 200, but is already even more shifted towards the specified minimum value of the range in comparison with the value of the length of these flexible connecting elements 350 of the second aircraft 200 when the first system 100 is in the previous eighth state, and the gripping ring 300 of the second aircraft 200, holding the payload 400 captured by it, removed from interaction with the gripping ring 300 of the first aircraft 100, are in the air at an even greater distance from the body 10 of the first aircraft 100 (in particular, in comparison with their positions in relation to the body 10 of the first aircraft 100 when the first system 1000 is in the previous eighth state), on the whole corresponding to the length of the flexible connecting elements 350 of the second aircraft 200 remaining after implementation of their above-mentioned even greater winding,and accordingly further removed from the first aircraft 100, from the body 10 of which the said payload 400 was further removed, by a distance generally corresponding to the value by which the length of the flexible connecting elements 350 of the second aircraft 200 was reduced in total as a result of their partial unwinding in the seventh state of the first system 1000, additional unwinding in the eighth state of the first system 1000 and even greater unwinding in the ninth state of the first system 1000 or by which these flexible connecting elements 350 of the second aircraft 200 were wound in total when the first system 1000 was in the seventh, eighth and ninth states.

[0142] In addition, in the ninth state of the first system 1000 shown in Fig. 1C on the right, the gripping ring 300 of the first aircraft 100, which has come out of interaction with the payload 400 captured by the gripping ring 300 of the second aircraft 200, and is still connected to the body 10 of the first aircraft 100 by means of both flexible connecting elements 350 of the first aircraft 100, limitedly wound back onto the winding module of the first aircraft 100 (that is, they have a smaller unwinding value in comparison with the value of their unwinding when the first system 1000 is in the above-described eighth state), turns out to be limitedly extended on the guides of the body 10 of the first aircraft 100 beyond the body 10 of the first aircraft 100 (i.e.the gripping ring 300 of the first aircraft 100 is brought closer to the body 10 of the first aircraft 100 in comparison with the position of the gripping ring 300 of the first aircraft 100 when the first system 1000 is in the previous eighth state) from the side on which this body 10 of the first aircraft 100 is equipped with bladed air movers 20.

[0143] It should be noted that in order to transfer the first system 1000 from the eighth state shown in Fig. 1C in the center to the ninth state shown in Fig. 1C on the right, the winding module of the body 10 of the second aircraft 200 continues to work or function in the operating mode specified by the control module of the second aircraft 200 when the first system 1000 is in the above-described seventh state and maintained by the control module of the second aircraft 200 when the first system 1000 is in the above-described eighth state, with the provision of additional or even greater winding of the flexible connecting elements 350 of the second aircraft 200 on this winding module of the body 10 of the second aircraft 200 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the second aircraft 200) and, therefore,with providing additional or even greater attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 (in comparison with their state when the first system 1000 is in the previous eighth state) under the control of the control module of the second aircraft 200. In particular, when performing the operation of even greater attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200, the payload comes out of interaction with the gripping ring 300 of the first aircraft 100 and moves or is displaced in the air in a substantially vertical direction towards the body 10 of the second aircraft 200 due to the pulling of the gripping ring 300 of the second aircraft 200, holding a payload of 400,to the body 10 of the second aircraft 200. In addition, the modules for moving the gripping ring of the first aircraft 100 begin to operate in a different operating mode specified by the control module of the first aircraft 100, ensuring a limited retraction of the guides of the body 10 of the first aircraft 100 back into the through passage of the body 10 of the first aircraft 100 under the control of the control module of the first aircraft 100 and, consequently, ensuring a corresponding limited displacement of the gripping ring 300 of the first aircraft 100, removed from interaction with the payload 400, towards the body 10 of the first aircraft 100; and simultaneously with the modules for moving the gripping ring of the first aircraft 100, the winding module of the body 10 of the first aircraft 100 also begins to operate in a different operating mode specified by the control module of the first aircraft 100,with ensuring limited winding of flexible connecting elements 350 of the first aircraft 100 on this winding module of the body 10 of the first aircraft 100 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the first aircraft 200) and, consequently, with ensuring the possibility of limited displacement of the gripping ring 300 of the first aircraft 100, released from the payload 400, on the sliding guides of the body 10 of the first aircraft 100 towards the body 10 of the first aircraft 200 under the control of the control module of the first aircraft 100. It should be noted that the above-described operation of further attracting the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200,the operation of limited pushing of the guides of the body 10 of the first aircraft 100 back into the through passage of the body 10 of the first aircraft 100 with ensuring the corresponding displacement of the gripping ring 300 of the first aircraft 100 installed thereon towards the body 10 of the first aircraft 100 under the control of the control module of the first aircraft 100 and the operation of limited winding of the flexible connecting elements 350 of the first aircraft 100 back onto the winding module of the first aircraft 100 under the control of the control module of the first aircraft 100 are carried out essentially simultaneously, in particular in response to the corresponding control commands received by the control module of the first aircraft 100 and the control module of the second aircraft 200 from the control device of the first system 1000.

[0144] Fig. 1D shows the tenth state of the first system 1000, into which this first system 1000 passes from its ninth state shown in Fig. 1C on the right. In particular, in the tenth state of the first system 1000, shown in Fig. 1D, the first aircraft 100 and the second aircraft 200 are in the air in the same regions of space as in the previous ninth state of the first system 1000. Moreover, in the tenth state of the first system 1000, shown in Fig. 1D, both flexible connecting elements 350 of the second aircraft 200, which are in the coiled state, have a minimum length, the gripping ring 300 of the second aircraft 200 is in contact with the body 10 of the second aircraft 200, and the payload 400, partially advanced through the through passage of the body 10 of the second aircraft 200,continues to be held by the gripping ring 300 of the second aircraft 200 and is partially extended from the body 10 of the second aircraft 200 on the side opposite to the other side of the body 10 of the second aircraft 200, from which this payload 400 was captured with the help of the gripping ring 300 of the second aircraft 200, and from which this body 10 of the second aircraft 200 is equipped with bladed air movers 20, for subsequent capture of this payload 400 by its extended part with the help of the gripping ring of another aircraft, which may be another first aircraft 100, which is part of this first system 1000, or another second aircraft 200, which is part of this first system 1000.

[0145] Furthermore, in the tenth state of the first system 1000 shown in Fig. 1D, the gripping ring 300 of the first aircraft 100, still connected to the body 10 of the first aircraft 100 by means of both flexible connecting elements 350 of the first aircraft 100, limitedly unwound from the winding module of the first aircraft 100 (that is, they can maintain unchanged the previous unwinding value specified by the winding module of the first aircraft 100 when the first system 1000 is in the above-described ninth state, or can be maximally wound on the said winding module of the first aircraft 100 with the provision of their subsequent unwinding from this winding module of the first aircraft 100 by the said unwinding value after the gripping ring 300 of the first aircraft 100 passes through the through passage of the body 10 of the first aircraft 100),is located at a limited distance from the body 10 of the first aircraft 100 at a given distance from the side opposite the other side of the body 10 of the first aircraft 100, from which this body 10 of the first aircraft 100 is equipped with bladed air movers 20.,

[0146] It should be noted that in order to transfer the first system 1000 from the ninth state shown in Fig. 1C on the right to the tenth state shown in Fig. 1D, the winding module with which the body 10 in the second aircraft 200 is provided continues to operate under the control of the control module of the second aircraft 200 in the same operating mode specified by the control module of the second aircraft 200 when the first system 1000 is in the above-described seventh state and maintained by the control module of the second aircraft 200 when the first system 1000 is in the above-described eighth state and the above-described ninth state, with the provision of the maximum permissible winding of the flexible connecting elements 350 of the second aircraft 200 on this winding module of the body 10 of the second aircraft 200 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the second aircraft 200) and, therefore,with ensuring the maximum permissible attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200, in which the gripping ring 300 of the second aircraft 200, still held by the coiled flexible connecting elements 350 of the second aircraft 200 and attracted by the gripping ring of the second aircraft 200 to the body 10 of the second aircraft 200, comes into contact with the body 10 of the second aircraft 200 or tightly adjoins the body 10 of the second aircraft 200, and the payload 400, held by the attracted gripping ring 300 of the second aircraft 200,enters into the through passage of the body 10 of the second aircraft 200 through the inlet opening of the passage of the body 10 of the second aircraft 200, ensuring its partial exit beyond the body 10 of the second aircraft 200 from the side from which this body 10 of the second aircraft 200 is equipped with bladed air movers 20, upon contact of the gripping ring 300 of the second aircraft 200 with the body 10 of the second aircraft 200.

[0147] In addition, the modules for moving the gripping ring of the first aircraft 100 continue to operate in another operating mode specified by the control module of the first aircraft 100 when the first system 1000 is in the previous ninth state, with the provision of complete retraction of the guides of the body 10 of the first aircraft 100 back into the through passage of the body 10 of the first aircraft 100 under the control of the control module of the first aircraft 100 and, consequently, with the provision of advancement of the gripping ring 300 of the first aircraft 100 through the through passage of the body 10 of the first aircraft 100,wherein, when the guides of the body 10 of the first aircraft 100 are pushed back to the maximum into the through passage of the body 10 of the first aircraft 100, the docking modules of the gripping ring 300 of the first aircraft 100 come out of interaction with these guides of the first aircraft 100, ensuring that this gripping ring 300 of the first aircraft 100 comes out of interaction with the body 10 of the first aircraft 100, as a result of which the gripping ring 300 is in its initial or starting state, in which it is suspended from the body of the first aircraft 100 on two flexible connecting elements 350 of the first aircraft 100 and is located at a limited distance from the body 10 of the first aircraft 100 or is adjacent to it.

[0148] Thus, after the transition of the first system 1000 completely to the above-described tenth state, shown in Fig. 1D, the payload 400 is transferred from the first aircraft 100 to the second aircraft 200, ensuring its placement on this second aircraft 200, wherein this second aircraft 200 in turn can carry out the movement or transportation of the payload 400 captured by it by air to another region of space in accordance with its flight program.

[0149] According to other embodiments of the present invention, the drive gripper or drive gripping ring 300 in the first aircraft 100, operating under the control of the control module of the first aircraft 100, may be further configured to extend the captured payload 400 from the through passage of the housing 10 to a predetermined distance from this housing 10 and to exit interaction with the extended payload 400 when this extended payload 400 enters into interaction with the second aircraft 200, in particular when this extended payload 400 is captured by the gripping ring of the second aircraft 200. It should be noted that in such embodiments of the present invention, the gripping ring of the second aircraft 200, which may be made similar to the above-described gripping ring 300, may be further provided with one or more contact sensors,configured to establish or detect the payload 400 captured by the gripping ring of the second aircraft 200 and connected with the ability to exchange data with the control module of the second aircraft 200, ensuring the ability to transmit data to it about the captured payload 400, and the control module of the second aircraft 200 can be further configured to establish a wireless communication channel over the communication network with the control module of the first aircraft 100, ensuring the ability to transmit to it the said data about the captured payload 400, as a result of processing which the control module of the first aircraft 100 issues the corresponding control commands to the drive of the gripping ring 300, ensuring the ability to exit this gripping ring from interaction with the captured payload 400.

[0150] According to other embodiments of the present invention, the gripping ring 300 in the first aircraft 100 may be configured to grip the payload 400 from either of the two opposite sides of the body 10, connected to each other by the above-described through passage of the body 10.

[0151] According to some embodiments of the present invention, the housing 10 in the first aircraft 100 may be additionally provided with a robotic manipulator, working element or working element operating under the control of the control module of the first aircraft 100 and configured to capture a payload 400 extended from the through channel of the housing 10, with the ability to remove the captured payload 400 from interaction with the gripping ring 300 and the ability to move it towards the second aircraft 200 to capture this payload 400 with the gripping ring of the second aircraft 200.

[0152] According to another embodiment of the present invention, the guides of the housing 10 in the first aircraft 100, into interaction with which the gripping ring 300 can be brought into contact when it is inserted into the inlet opening of the passage of the housing 10, can be made with the possibility of their at least partially returning extension together with the gripping ring 300 installed on them from the through passage of the housing 10 through the outlet opening of the passage of the housing under the control of the control module of the first aircraft 100, ensuring the possibility of at least partial entry of this grip into contact with the payload or the possibility of extending the grip together with the payload to a predetermined distance from the body of the aircraft.

[0153] According to one embodiment of the present invention, the body 10 in the first aircraft 100 may be configured to tilt or rotate at a given angle under the control of the control module of the first aircraft 100 when capturing the payload 400 using the gripping ring 300, which provides the ability to adapt the spatial orientation of the through passage of the body 10 to a specific spatial orientation or shape of the captured payload 400 that must be inserted into the inlet opening of the passage of the body 10. In particular, in such an embodiment of the present invention, the gripping ring 300 may be further equipped with a scanner or scanning module known in the art, configured to scan the payload 400 that must be captured using this gripping ring 300, to obtain three-dimensional images (scans) of this payload, accurately determining the shape,geometric dimensions and design features of the implementation of this payload 300, and connected with the possibility of exchanging data with the control module of the first aircraft 100, ensuring the possibility of issuing said scans of the payload 400 to it, and the control module of the first aircraft 100 in turn can be further configured with the possibility of processing said scans of the payload 400 received from the scanning module of the gripping ring 300, to obtain a 3D model of the payload 400 and is configured to provide the possibility of changing the angle of inclination of the body 10 or the possibility of rotating the body 10 by a given angle depending on said obtained 3D model of the payload 400. In addition, in such an embodiment of the present invention, the body 10 in the first aircraft 100 can be a structure with the above-described through passage of the body 10, pivotally mounted in a supporting frame (not shown),equipped with the above-described air blade propellers 20, installed by means of beams on the specified supporting frame of the first aircraft 100, wherein the specified frame of the first aircraft 100 can be additionally equipped with drives for rotating the body 10, operating under the control of the control module of the first aircraft 100 and operatively connected to the body 10 with the possibility of tilting it or rotating it at a given angle in response to the corresponding control commands of the control module of the first aircraft 100, generated by this control module of the first aircraft 100 depending on the above-described 3D model of the payload 400, which must be captured with the help of the gripping ring 400, operatively connected to the body 10.,

[0154] According to another embodiment of the present invention, the housing 10 in the first aircraft 100 may be configured to change its shape and / or its dimensions under the control of the control module of the first aircraft 100 when capturing the payload 400 using the gripping ring 300, which provides the ability to adapt the shape of the through passage of the housing 10 to the specific dimensions and / or shape of the captured payload 400, which must be inserted into the inlet opening of the passage of the housing 10. In particular, in such an embodiment of the present invention, the gripping ring 300 may be additionally provided with a scanner or scanning module known in the art, configured to scan the payload 400, which must be captured using this gripping ring 300, to obtain three-dimensional images (scans) of this payload, accurately determining the shape,geometric dimensions and design features of the implementation of this payload 300, and connected with the possibility of exchanging data with the control module of the first aircraft 100 with the ability to issue said scans of the payload 400 to it, and the control module of the first aircraft 100 in turn can be further configured with the ability to process said scans of the payload 400 received from the scanning module of the gripping ring 300 to obtain a 3D model of the payload 400 and is configured to provide the ability to change the shape and / or geometric dimensions of the body 10 and, consequently, the shape and / or geometric dimensions of the through passage of the body 10 depending on said obtained 3D model of the payload 400. In addition, in such an embodiment of the present invention, the body 10 in the first aircraft 100 can be a composite structure with the above-described through passage of the body 10,at least partially or completely formed from a plurality of interconnected drive elements configured to extend, unfold, deploy in response to the corresponding control commands of the control module of the first aircraft 100, which can be generated by this control module of the first aircraft 100 depending on the above-described 3D model of the payload 400, which must be captured with the help of the capture ring 400, operatively connected to the body 10, and which can be issued by this control module of the first aircraft 100 to at least one or each of the controlled drives of the said drive elements with the ability to change the shape and / or dimensions of those drive elements that are operatively connected to the said controlled drives, to which the said control commands of the control module of the first aircraft 100 were issued.

[0155] According to another embodiment of the present invention, at least one or each of the guides with which the through passage of the body 10 in the first aircraft 100 may be provided may be at least partially or completely made bendable or flexible.

[0156] According to another embodiment of the present invention, at least one or each of the guides with which the through passage of the body 10 in the first aircraft 100 may be provided may be at least partially or completely made rectilinear or curvilinear.

[0157] According to some embodiment of the present invention, at least one or each of the guides with which the through passage of the housing 10 in the first aircraft 100 may be provided may consist of two or more parts, at least one of which may be made movable, wherein the housing 10 may additionally contain a drive device (not shown) operating under the control of the control module of the first aircraft 100 and operatively connected to the said at least one movable part of the guide with the possibility of its displacement or tilting in relation to the remaining parts of the said guide to change the shape of this guide. Second system for moving payload

[0158] Fig. 2A-2C schematically illustrate one of the illustrative embodiments of the second system 2000 for moving the payload, which in general has a structure and functionality identical to the above-described first system 1000 for moving the payload, shown in various states in Fig. 1A-1D. In particular, similar to the first system 1000, the second system 2000 comprises a first aircraft 100 for moving a payload and a second aircraft 200 for moving a payload, each of which has a body 10 equipped with bladed air movers 20, and also contains one or more control devices (not shown) configured to create a wireless communication channel over a communication network (not shown) with at least one or each of the first and second aircraft 100, 200 included in this second system 2000, and a payload 400 that must be captured using a capture ring 300,with which the body 10 in the first aircraft 100 is provided, and transfer it in the air from the first aircraft 100 to the second aircraft 200 by capturing the payload 400, at least partially extended from the through passage of the body 10 in the first aircraft 100, with the help of the capturing ring 300, with which the body 10 in the second aircraft 200 is provided. It should be noted that the main differences of the second system 2000 from the above-described first system 1000 consist in the below-described features of advancing the captured payload 400 through the through passage of the body 10 in the first aircraft 100 or the second aircraft 200. It should also be noted that in the second system 2000 for the primary capture of the payload 400, initially installed on the ground surface or any other supporting surface of a movable or fixed physical object,a second aircraft 200 may be used instead of the first aircraft 100, wherein the payload 400 may be transferred in the air not only from the first aircraft 100 to the second aircraft 200, but may also be transferred in the air from one first aircraft 100 to another first aircraft 100 or from one second aircraft 200 to another second aircraft 200.

[0159] In particular, in the second system 2000, the through passage of the body 10 in the first aircraft 100 may be additionally provided with a payload movement module (not shown), which may be mounted on the guides of the body 10 described above in relation to the first system 1000, with the possibility of movement along them under the control of the control module of the first aircraft 100, connected with the possibility of exchanging data with the said payload movement module.

[0160] The payload handling module installed in the through passage of the housing 10 in the first aircraft 100 may be configured to enter into releasable interaction with the payload 400 captured by the gripping ring 300 described above in relation to the first system 1000 and attracted / pulled toward the housing 10 as a result of winding the flexible connecting elements 350 described above in relation to the first system 1000 and connecting the housing 10 and said gripping ring 300 to each other onto the winding module of the housing 10 described above in relation to the first system 1000, under the control of the control module of the first aircraft 100 with the possibility of contact between the gripping ring 300 and the housing 10 and the possibility of partial entry of the payload 400 held or captured by this gripping ring 300 into the inlet opening of the passage of the housing 10. It should be noted that in the second system 2000 fact of at least partial insertion of payload 400,captured by the capture ring 300, into the through passage of the housing 10 can be monitored or controlled using, for example, one or more contact sensors or line crossing sensors known in the art and each connected with the possibility of exchanging data with the control module of the first aircraft 100 with the possibility of issuing an information signal to it indicating the entry or insertion of the payload 400 into the through passage of the housing 10, wherein the control module of the first aircraft 100 generates control commands in response to said information signal of the sensor and issues them to the payload movement module, and the payload movement module, with which the housing 10 in the first aircraft 100 is additionally provided,in turn, in response to the specified control commands of the control module of the first aircraft 100, it can interact with the specified payload 400, ensuring the possibility of its advancement in the through passage of the body 10 towards the outlet opening of the passage of the body 10.,

[0161] In addition, in the second system 2000, the payload movement module, with which the housing 10 in the first aircraft 100 is additionally provided, is configured to exit interaction with the payload 400 at least upon partial or complete extension of this payload 400 from the through passage of the housing 10 beyond the limits of this housing 10, wherein such at least partial extension of the payload 400 from the through passage of the housing 10 beyond the limits of the housing 10 can be implemented using the said payload movement module or in any other way described in this document with respect to the first system 1000 or which is obvious to a person skilled in the art after his familiarization with the description in this document.

[0162] In one embodiment of the present invention, the payload handling module in the second system 2000, which the body 10 in the first aircraft 100 is additionally equipped with, may be a robotic manipulator or gripper, configured to releasably grip the payload 400 in the through passage of the body 10 under the control of the control module of the first aircraft 100, ensuring the possibility of moving the captured payload 400 in this through passage of the body 10, wherein such a robotic manipulator or gripper can be installed in the through passage of the body 10 on one or more guides of the body 10 with the possibility of moving along them in this through passage of the body 10 under the control of the control module of the first aircraft 100.In particular, in such an embodiment of the present invention, the robotic manipulator or gripper can be mounted on the guides of the housing 10 with the help of at least one drive carriage, configured to move along the said guides of the housing 10 under the control of the control module of the first aircraft 100, wherein the control module of the first aircraft 100 in turn can be further configured to issue corresponding control commands to the drive of the said carriage for its movement together with the robotic manipulator or gripper mounted on it to the target location on the guides of the housing 10.

[0163] In another embodiment of the present invention, the payload movement module, with which the body 10 in the first aircraft 100 is additionally provided, may be a controlled working element or working member, made with the possibility of entering into a detachable interaction with the payload 400 in the through passage of the body 10 under the control of the control module of the first aircraft 100, ensuring the possibility of moving the said payload 400 in this through passage of the body 10, wherein such a controlled working element or working member may be installed in the through passage of the body 10 on one or more guides of the body 10 with the possibility of moving along them in this through passage of the body 10 under the control of the control module of the first aircraft 100.In particular, in such an embodiment of the present invention, the working element or working member can be mounted on the guides of the housing 10 with the help of at least one drive carriage, configured to move along the said guides of the housing 10 under the control of the control module of the first aircraft 100, wherein the control module of the first aircraft 100 in turn can be additionally configured to issue corresponding control commands to the drive of the said carriage for its movement together with the working element or working member mounted on it to the target location on the guides of the housing 10.

[0164] In yet another embodiment of the present invention, the gripping ring 300 in the first aircraft 100 may be further configured to be removably mounted on the guides of the housing 10 of a payload 400, which is captured by means of this gripping ring 300 and pulled / pulled towards the housing 10 as a result of winding flexible connecting elements 350 connecting the housing 10 and said gripping ring 300 to each other, onto a winding module of the housing 10 under the control of the control module of the first aircraft 100, ensuring the possibility of this gripping ring 300 entering, together with the payload 400 captured by it, into the inlet opening of the passage of the housing 10, wherein the payload movement module may be a pusher operating under the control of the control module of the first aircraft 100 and configured to act on the payload 400 mounted on the guides of the housing 10 in the through passage of the housing 10,with the provision of the possibility of moving this payload 400 along the guides of the housing 10 (for example, to the outlet opening of the passage of the housing 10 or beyond the housing 10 at a given distance from it).,

[0165] It should be noted that the flexible connecting elements 350 in the second system 2000 can continue to additionally hold the payload 400 until the moment of its capture by the gripping ring of the second aircraft 200, thereby additionally stabilizing the spatial position of the payload 400 extended beyond the body 10, which in turn simplifies the process of its capture by the gripping ring of the second aircraft 200 and / or accelerates the process of its transfer from the first aircraft 100 to the second aircraft 200 in this second system 2000.

[0166] The first and second aircraft 100, 200, included in the second system 2000, are preferably designed to be identical and functional or the same, in particular they have identical shapes and dimensions and are equipped with the same functional technical means described in this document with respect to the first aircraft 100, included in the first system 1000. Thus, the description given above in this document with respect to the design features and operational features of the functional technical means of the first aircraft 100, included in the first system 1000, should essentially be considered a description of the corresponding functional technical means of the first aircraft 100 and the second aircraft 200, both included in the second system 2000.

[0167] In some embodiments of the present invention, the first and second aircraft 100, 200 included in the system 1000 may have different shapes and sizes and may be equipped with different functional technical means, but these functional technical means, which differ from each other, must provide the ability to perform the above-described operations necessary for capturing the payload 400 by the first aircraft 100 and transferring such captured payload 400 from the first aircraft 100 to the second aircraft 200.

[0168] As shown in Fig. 2A on the left, in the first (initial or initial) state of the second system 2000, both flexible connecting elements 350 connecting the gripping ring 300 and the housing 10 in the first aircraft 100 have a minimum extension or length (that is, they are wound on the winding module of the housing 10 in the first aircraft 100), so that the gripping ring 300, suspended from the housing 10 on these two flexible connecting elements 350, is pulled to the housing 10 and faces the side of the payload 400 to be captured (target), which is located on the surface of the earth and at a distance from which this first aircraft 100 is located, while the bladed air movers 20 operate in a given operating mode, controlled by the control module of the first aircraft 100, ensuring that this first aircraft 100 hangs in the air in a given area of ​​space at a distance from the specified payload 400 (i.e.above this payload 400), sufficient for its further capture using the capture ring 300.

[0169] In Fig. 2A on the right, a second state of the second system 2000 is shown, into which this second system 2000 passes from its first (initial or initial) state, shown in Fig. 2A on the left. In particular, in the second state of the second system 2000, shown in Fig. 2A on the right, both flexible connecting elements 350, which are in the unwound state, have a maximum extension or length, and the gripping ring 300, removed from the body 10 at a distance generally corresponding to the length of the unwound flexible connecting elements 350, is brought into interaction with the payload 400, ensuring its grip for its subsequent detachment from the ground surface and lifting into the air.

[0170] It should be noted that in order to transfer the second system 2000 from the first state shown in Fig. 2A on the left to the second state shown in Fig.2A on the right, the control module of the first aircraft 100 issues the corresponding control commands to the winding module of the housing 10 to activate it in a given operating mode with the provision of unwinding the flexible connecting elements 350 from this winding module of the housing 10 (for example, from the opposite ends of the bobbin of this winding module) and, consequently, with the provision of approaching the gripping ring 300 with the payload 400 to provide the possibility of interaction of the gripping ring 300 with the payload 400, which can be realized, for example, manually by the user by placing the gripping ring 300 on the payload 400 with tension on it or automatically / semi-automatically using one or more docking modules with which the gripping ring 300 or the payload 400 itself can be equipped and which can operate under the control of the control module of the first aircraft 100.

[0171] In Fig. 2B on the left, a third state of the second system 2000 is shown, into which this second system 2000 passes from its second state shown in Fig. 2A on the right. In particular, in the third state of the second system 2000, shown in Fig. 2B on the left, the first aircraft 100 is in the air in substantially the same region of space, both flexible connecting elements 350, which are in a partially wound state, have a limited length, the value of which is in the range from a minimum length corresponding to the wound / coiled state of the flexible connecting elements 350, to a maximum length corresponding to the unwound state of the flexible connecting elements 350, and the gripping ring 300 together with the payload 400 captured by it are in the air at a predetermined distance from the body 10, on the whole corresponding to the remaining length of the unwound flexible connecting elements 350, and are removed from the surface of the earth,on which the payload 400 was initially placed at a distance generally corresponding to the amount by which the length of the flexible connecting elements 350 was reduced as a result of their partial unwinding or by which these flexible connecting elements 350 were unwinded.

[0172] It should be noted that in order to transfer the second system 2000 from the second state shown in Fig. 2A on the right to the third state shown in Fig. 2B on the left, the control module of the first aircraft 100 issues corresponding control commands to the winding module of the housing 10 to activate it in a given operating mode with the provision of winding the flexible connecting elements 350 on this winding module of the housing 10 (for example, on the opposite ends of the bobbin of this winding module of the housing 10) and, consequently, with the provision of attracting the gripping ring 300 with the payload 400 captured by it to the housing 10 under the control of the control module of the first aircraft 100 for the subsequent entry of the gripping ring 300 into the inlet opening of the passage of the housing 10.

[0173] In Fig. 2B, the fourth state of the second system 2000 is shown in the center, into which this second system 2000 transitions from its third state shown in Fig. 2B on the left. In particular, in the fourth state of the second system 2000 shown in Fig. 2B in the center, the first aircraft 100 is in the air in essentially the same region of space, both flexible connecting elements 350, which are in the coiled state, have a minimum length, the gripping ring 300 is in contact with the body 10, and the payload 400, advanced through the through passage of the body 10, continues to be held by the gripping ring 300 and is partially extended from the body 10 on the side opposite to the other side of the body 10, from which this payload 400 was captured with the help of the gripping ring 300, for subsequent capture of this payload 400 by its extended part with the help of the gripping ring of the second aircraft 200.

[0174] It should be noted that in order to transfer the second system 2000 from its third state shown in Fig. 2B on the left to the fourth state shown in Fig. 2B in the center, the winding module of the housing 10 continues to operate under the control of the control module of the first aircraft 100 in the same operating mode specified by the control module of the first aircraft 100 when the second system 2000 transitions to its third state, with the provision of the maximum permissible winding of the flexible connecting elements 350 on this winding module of the housing 10 (for example, on the opposite ends of the bobbin of this winding module of the housing 10) and, consequently, with the provision of the maximum permissible attraction of the gripping ring 300 with the payload 400 captured by it to the housing 10 under the control of the control module of the first aircraft 100, in which the gripping ring 300, still held by the wound flexible connecting elements 350,comes into contact with the housing 10 or adjoins the housing 10, and the payload 400 partially enters into the through passage of the housing 10 through the inlet opening of the passage of the housing 10, thereby exiting the interaction with the gripping ring 300 that previously held it and essentially simultaneously entering into interaction with the payload movement module installed in this through passage of the housing 10. In addition, the control module of the first aircraft 100 additionally issues appropriate control commands to the payload movement module, into interaction with which the payload 400 was brought into interaction, having exited the interaction with the gripping ring 300 that held it, ensuring that it is activated in a given operating mode, so that this payload 400 is advanced, by means of the said payload movement module,through the through passage of the housing 10, ensuring its partial extension from this through passage of the housing 10, as a result of which its part ends up being located outside the housing 10 or ends up being extended outside the housing 10 by a given distance.

[0175] Fig. 2B shows on the right the fifth state of the second system 2000, into which this second system 2000 transitions from its fourth state shown in Fig. 2B in the center. In particular, in the fifth state of the second system 2000 shown in Fig. 2B on the right, the second aircraft 200 is located in the region of space into which the first aircraft 100 has moved through the air in accordance with its flight program, at a given distance from this first aircraft 100. In particular, in the fifth state of the second system 2000, both flexible connecting elements 350 connecting the gripping ring 300 and the housing 10 in the second aircraft 200 have a minimum extension or length (that is, they are wound on the winding module of the housing 10 in the second aircraft 200), so that the gripping ring 300, suspended from the housing 10 in the second aircraft 200 on these two flexible connecting elements 350,attracted to the body 10 in this second aircraft 200 and facing the side of the payload 400 to be captured (target), which is partially extended from the body 10 in the first aircraft 100, wherein the bladed air movers 20 in the second aircraft 200 operate in a given operating mode, controlled by the control module of the second aircraft 200, with the purpose of hovering this second aircraft 200 in the air in the specified region of space above the first aircraft 100, and the bladed air movers 20 in the first aircraft 100 operate in a given operating mode, controlled by the control module of the first aircraft 100, with the purpose of hovering this first aircraft 100 in the air in the specified region of space, which ensures stabilized spatial positions of the first and second aircraft 100, 200 in relation to each other and thereforesimplifies and accelerates the process of transferring payload 400 from the first aircraft 100 to the second aircraft 200.,

[0176] Fig. 2C on the left shows the sixth state of the second system 2000, into which this second system 2000 transitions from its fifth state shown in Fig. 2B on the right. In particular, in the sixth state of the second system 2000 shown in Fig. 2C on the left, the first aircraft 100 is in the same state in which it was in the above-described fifth state of the second system 2000, wherein both flexible connecting elements 350 in the second aircraft 200, which are in the unwound state, have a maximum extension or length, and the gripping ring 300 in the second aircraft 200, removed from the body 10 at a distance generally corresponding to the length of the unwound flexible connecting elements 350, is brought into interaction with the payload 400, partially extended from the body 10 in the first aircraft 100, with the provision of its capture for its subsequent withdrawal from interaction with the first aircraft 100 in the second system 2000.

[0177] It should be noted that in order to transfer the second system 2000 from the fifth state shown in Fig. 2B on the right to the sixth state shown in Fig. 2C on the left, the control module of the second aircraft 200 issues the corresponding control commands to the winding module, with which the housing 10 in the second aircraft 200 is provided, for activating this winding module of the housing 10 in a given operating mode with the provision of unwinding the flexible connecting elements 350 from this winding module of the housing 10 (for example, from the opposite ends of the bobbin of this winding module of the housing 10) and, consequently, with the provision of approaching the gripping ring 300, suspended by the said flexible connecting elements 350 to the housing 10 in the second aircraft 200, with the payload 400, still held by the gripping ring 300, with which the housing 10 in the first aircraft 100 is provided,to ensure the possibility of said gripping ring 300 of the second aircraft 200 entering into interaction with this payload 400, which can be implemented, for example, automatically / semi-automatically using one or more docking modules with which the gripping ring 300 of the second aircraft 200 or the payload 400 itself can be equipped and which can operate under the control of the control module of the second aircraft 200.,

[0178] In Fig. 2C, the seventh state of the second system 2000 is shown in the center, into which this second system 2000 passes from its sixth state, shown in Fig. 2C on the left. In particular, in the seventh state of the second system 2000, shown in Fig. 2C in the center, the first aircraft 100 is in the air in substantially the same region of space as in the above-described fifth or sixth state of the second system 200, wherein both flexible connecting elements 350 in the second aircraft 200, which are in a partially wound state, have a limited length, the value of which is in the range from the minimum length, corresponding to the wound / coiled state of said flexible connecting elements 350, to the maximum length, corresponding to the unwound state of said flexible connecting elements 350,and the gripping ring 300 of the second aircraft 200 together with the payload 400 captured by it are in the air at a given distance from the body 10 of the first aircraft 100, generally corresponding to the remaining length of the unwound flexible connecting elements 350 of the second aircraft 200, and are removed from the first aircraft 100, from the body 10 of which the payload 400 was partially extended, at a distance generally corresponding to the value by which the length of the flexible connecting elements 350 of the second aircraft 200 was reduced as a result of their partial unwinding or by which these flexible connecting elements 350 of the second aircraft 200 were wound.

[0179] It should be noted that in order to transfer the second system 2000 from the sixth state shown in Fig. 2C on the left to the seventh state shown in Fig.2C in the center, the control module of the second aircraft 200 issues the corresponding control commands to the winding module, with which the body 10 in the second aircraft 200 is equipped, to activate it in a given operating mode with the provision of winding the flexible connecting elements 350 of the second aircraft 200 on this winding module of the body 10 of the second aircraft 200 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the second aircraft 200) and, consequently, with the provision of attracting the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200 for the subsequent contact of the gripping ring 300 of the second aircraft 200 with the body 10 of the second aircraft 200 (i.e.similar to the first aircraft 100, which is part of the second system 2000) or the subsequent entry of the gripping ring 300 of the second aircraft 200 into the inlet opening of the passage of the body 10 of the second aircraft 200 (i.e. similar to the first aircraft 100, which is part of the first system 1000).

[0180] Fig. 2C shows on the right the eighth state of the second system 2000, into which this second system 2000 transitions from its seventh state shown in Fig. 2C in the center. In particular, in the eighth state of the second system 2000 shown in Fig. 2C on the right, the first aircraft 100 is in the air in essentially the same region of space in which it was in the above-described fifth, sixth and seventh states of the second system 200, wherein both flexible connecting elements 350 of the second aircraft 200, which are in the coiled state, have a minimum length, the gripping ring 300 of the second aircraft 200 is in contact with the body 10 of the second aircraft 200, and the payload 400, advanced through the through passage of the body 10 of the second aircraft 200, continues to be held by the gripping ring 300 of the second aircraft 200 and is partially extended from the body 10 of the second aircraft 200 from the side,opposite the other side of the body 10 of the second aircraft 200, from which this payload 400 was captured with the help of the capture ring 300 of the second aircraft 200, for the subsequent capture of this payload 400 by its extended part with the help of the capture ring of another aircraft, which can be another first aircraft 100, which is part of this second system 2000, or another second aircraft 200, which is part of this second system 2000.,

[0181] It should be noted that in order to transfer the second system 2000 from its seventh state shown in Fig. 2C in the center to the eighth state shown in Fig. 2C on the right, the winding module with which the body 10 in the second aircraft 200 is provided continues to operate under the control of the control module of the second aircraft 200 in the same operating mode specified by the control module of the second aircraft 200 when this second system 2000 is transferred to its above-described seventh state, with the provision of the maximum permissible winding of the flexible connecting elements 350 of the second aircraft 200 on this winding module of the body 10 of the second aircraft 200 (for example, on the opposite ends of the bobbin of this winding module of the body 10 of the second aircraft 200) and, therefore,with ensuring the maximum permissible attraction of the gripping ring 300 of the second aircraft 200 with the payload 400 captured by it to the body 10 of the second aircraft 200 under the control of the control module of the second aircraft 200, in which the gripping ring 300 of the second aircraft 200, still held by the coiled flexible connecting elements 350 of the second aircraft 200, comes into contact with the body 10 of the second aircraft 200 or adjoins the body 10 of the second aircraft 200, and the payload 400 partially enters into the through passage of the body 10 of the second aircraft 200 through the inlet opening of the passage of the body 10 of the second aircraft 200, thereby exiting the interaction with the gripping ring 300 of the second aircraft that previously held it 200 and essentially simultaneously entering into interaction with the payload movement module,installed in this through passage of the body 10 of the second aircraft 200. In addition, the control module of the second aircraft 200 additionally issues corresponding control commands to the payload movement module of the second aircraft 200, into interaction with which the payload 400 was brought into interaction, having come out of interaction with the gripping ring 300 of the second aircraft 200 holding it, ensuring that it is activated in a given operating mode, so that this payload 400 is advanced, by means of the said payload movement module of the second aircraft 200, through the through passage of the body 10 of the second aircraft 200 ensuring its partial extension from this through passage of the body 10 of the second aircraft 200,as a result of which its part is located outside the body 10 of the second aircraft 200 or is extended beyond the body 10 of the second aircraft 200 by a given distance.

[0182] Thus, after the transition of the second system 2000 completely to the above-described eighth state, shown in Fig. 2C on the right, the payload 400 is transferred from the first aircraft 100 to the second aircraft 200, ensuring its placement on this second aircraft 200, while this second aircraft 200 in turn can carry out the movement or transportation of the payload 400 captured by it by air to another region of space in accordance with its flight program. Method of moving the payload

[0183] A block diagram is shown illustrating the main operations of the method 500 for moving a payload, wherein the method 500 for moving a payload shown in can be performed using the above-described first system 1000 or the above-described second system 2000 for moving a payload, which can be performed in accordance with any of the relevant embodiments of the present invention described above in this document.

[0184] In particular, the method 500 for moving a payload shown in includes the following two main operations or two main steps 510 and 520, wherein at step 510, a payload 400 is releasably captured, by means of a capture ring 300 of the first aircraft 100 according to any of the embodiments of the present invention described in this document, with the possibility of its advancement through a through passage of the body 10 of the first aircraft 100 under the control of a control module of the first aircraft 100 or under the control of a control device included in the first system 1000 or the second system 2000.At the end of the method 500, at step 520, the payload 400 is captured by means of the capture ring 300 of the second aircraft 200, when it is at least partially extended from the body 10 of the first aircraft 100, ensuring the transfer of said captured payload 400 to this second aircraft 100 under the control of the control module of the first aircraft 100 or under the control of a control device included in the first system 1000 or the second system 2000.

[0185] The illustrative embodiments, examples, and descriptions presented herein serve merely to provide an understanding of the essence of the claimed invention and are not limiting. Other possible embodiments of the present invention, or modifications or improvements to the above-described embodiments of the present invention, will be apparent to those skilled in the art from the description provided above. The scope of the present invention is limited only by the appended claims.

Claims

An aircraft comprising: a body with a through passage, a control module with which the body is provided and which is configured to control the operation of the aircraft, and a gripper connected to the body with the capability of detachably gripping a payload with the capability of advancing the captured payload through said through passage and configured to disengage from interaction with said payload at least upon partial extension of this payload from said through passage of the body. An aircraft according to claim 1, in which the gripper is a gripping ring, designed with the possibility of entering into tight interaction with the payload, the possibility of embracing the payload or the possibility of landing on the payload with tension for its gripping and suspended on at least one flexible connecting element, and the body of the aircraft is additionally provided with a winding module, operating under the control of a control module and operatively connected to the said at least one flexible connecting element with the possibility of changing its length. An aircraft according to claim 2, in which the gripper is additionally provided with a drive operating under the control of a control module and functionally connected to the gripper with the ability to change its diameter. An aircraft according to claim 3, in which the gripper is additionally provided with a sensor module connected with the ability to exchange data with the control module and configured to determine the size of the payload with the ability to output data on the size of the payload to the control module, and the control module is additionally configured to output control commands to the gripper drive for changing the diameter of the gripper ring depending on the specified size of the payload. An aircraft according to claim 1, wherein the gripper is designed with the possibility of detachable connection or fastening with the payload. An aircraft according to claim 1, in which the gripper is designed with the possibility of deployment or extension from the body, ensuring its placement at a given distance from the body. An aircraft according to claim 1, in which the gripper is additionally configured to move in the through passage of the body together with the captured payload. An aircraft according to claim 7, in which the body is additionally provided with one or more guides installed in said through passage, and the gripper is additionally configured to engage with at least one of said guides, ensuring the possibility of movement along said at least one guide together with the captured payload. An aircraft according to paragraph 7, in which the body is additionally provided with one or more guides installed in the said through passage, and the gripper is installed on the said guides with the possibility of movement along them. An aircraft according to claim 9, in which the gripper is mounted on the said guides of the body by means of a drive carriage, configured to move along the said guides under the control of a control module. An aircraft according to paragraph 9, in which the said guides are designed with the possibility of retracting from the body of the aircraft together with the gripper installed thereon under the control of a control module, ensuring the possibility of this gripper interacting with the payload or the possibility of extending the gripper together with the payload to a specified distance from the body of the aircraft. An aircraft according to any one of paragraphs 7-9, in which the gripper is additionally configured to extend the gripped payload from the through passage of the body to a predetermined distance from the body of the aircraft. An aircraft according to claim 12, in which the gripper is additionally configured to exit interaction with the extended payload when this extended payload enters into interaction with another aircraft. An aircraft according to claim 1, in which the gripper is designed to grip a payload from either of two opposite sides of the aircraft body, connected to each other by the said through passage. An aircraft according to paragraph 1, in which the body is additionally provided with a robotic manipulator, working element or working element operating under the control of a control module and designed with the ability to capture a payload extended from a through channel of the body, with the ability to move the captured payload towards another aircraft. An aircraft comprising: a body with a through passage, a control module with which the body is provided and which is configured to control the operation of the aircraft, a gripper connected to the body with the ability to detachably grip a payload with the ability to install the captured payload in said through passage, a payload movement module operating under the control of the control module and installed in the through passage of the body with the ability to enter into detachable interaction with said installed payload with the ability to advance this payload in the through passage of the body and the ability to exit interaction with this payload at least during partial extension of this payload from said through passage of the body. An aircraft according to claim 16, in which the payload movement module is a robotic manipulator or gripper, configured to releasably grip a payload in a through passage of the body under the control of a control module, ensuring the ability to move the captured payload in this through passage of the body. An aircraft according to claim 17, in which the robotic manipulator or gripper is installed in the through passage of the body on one or more guides with the possibility of movement along them in this through passage of the body. An aircraft according to claim 18, in which the robotic manipulator or gripper is mounted on the said guides of the body by means of a drive carriage configured to move along the said guides under the control of a control module. An aircraft according to claim 18, in which the payload movement module is a working member or working element designed with the possibility of entering into a detachable interaction with the payload in a through passage of the body under the control of a control module, ensuring the possibility of moving said payload in this through passage of the body. An aircraft according to paragraph 20, in which the working member or working element is installed in a through passage of the body on one or more guides with the possibility of movement along them in this through passage of the body. An aircraft according to paragraph 21, in which the working element or working member is mounted on the said guides of the body by means of a drive carriage, configured to move along the said guides under the control of a control module. An aircraft according to claim 16, in which the body is additionally provided with one or more guides installed in said through passage, and the gripper is additionally configured to install the captured payload in said through passage of the body on at least one of said guides of the body. An aircraft according to claim 23, in which the payload movement module is a pusher operating under the control of a control module and designed with the ability to act on the payload in a through passage of the body, ensuring the ability to move this payload along the guides of the body. A system for moving a payload, comprising: two or more aircraft, at least one of which is a first aircraft according to any one of paragraphs 1-24, one or more control devices configured to control the operation of said aircraft, wherein at least one second aircraft of said aircraft is configured to capture a payload extended from the body of the first aircraft. A method for moving a payload, according to which: the payload is detachably captured, by means of capturing the first aircraft according to any of paragraphs 1-24, with the possibility of its advancement through a through passage of the body of the first aircraft under the control of a control device and the payload is captured, by means of a second aircraft, during its at least partial extension from the body of the first aircraft with the possibility of its transfer to this second aircraft under the control of a control device.

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