Apparatus and method for a weapon attachment system

Abstract

Multiple embodiments of a payload attachment system use one or more vacuum attachment modules to secure a payload to a wing or fuselage of a drone (102) (or other type of aircraft). Each vacuum attachment module includes at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives a command corresponding to either a vacuum cup activation signal or a vacuum cup release signal.

Description

Background Art

[0001] This application claims the benefit of U.S. Provisional Patent Application No. 17 / 868,146, filed Jul. 19, 2022, and U.S. Provisional Patent Application No. 17 / 824,592, filed May 25, 2022. The entire disclosures of these documents are incorporated herein by reference for all purposes.

[0002] In various situations, it is desirable to releasably secure a weapon (which may also be referred to herein as a “payload”) to an aircraft, a drone, or the like. Typically, such a weapon is suspended from the fuselage and / or wings of an aircraft or the frame of a drone. The payload is secured to a hard point that can structurally support a pre-defined payload weighing less than a pre-defined maximum weight. The payload is fitted and secured to the aircraft or drone using a connector at the distal end of a pylon. The payload may be secured directly to the pylon. Alternatively, when multiple payloads are secured to the pylon, the multiple payloads may be secured to a rack secured to the distal end of the pylon.

[0003] FIG. 1 is a front view of an exemplary conventional military-purpose aerial drone 102. Here, a non-limiting exemplary payload 104 is an AGM-114 (air-to-ground missile) Hellfire. The AGM-114 Hellfire has a weight of just over 100 pounds and is relatively small and lightweight, and thus can be a suitable payload 104 for the drone 102. Another non-limiting example of the payload 104 is a small drone that can be used for surveillance purposes and / or weapon-dropping purposes. Such a payload 104 is suspended from the wings or fuselage of the drone 102 using a pylon 106.

[0004] The illustrated exemplary drone 102 is propelled forward by an engine and propeller 106. Some military drones are jet-propelled. For launch and landing of the drone 102 at the site (battlefield), one or more VTOL (vertical takeoff and landing) motors and propellers may be used. Alternatively, some conventional drones are equipped with landing gear for takeoff and landing on a plane such as an airfield, road, aircraft carrier, etc.

[0005] One problem encountered in the art is that radar reflections from the pylon 106 may be undesirable, especially when the drone is stealthy. That is, a stealth drone is designed with an outer skin that minimizes the reflection of incoming radar energy. However, the pylon 106 itself can be a source of unwanted radar reflections. Thus, there is a need in the field of stealth technology for improved methods, devices, and systems for reducing radar reflections from the pylon 106 used to secure weapons to a drone.

[0006] Furthermore, while the drone 102 is at a base such as an airfield or aircraft carrier, the weapon is typically secured to the pylon 106. In practice, it takes a certain amount of time (based on the speed of the drone 102 and the distance between the base and the battlefield) to move from the base to the battlefield, release (launch) the weapon from the drone 102, and then return to the base. Thus, there is a need in the art of using military drones 102 or other aircraft for improved methods, devices, and systems for quickly rearming a military drone 102 or other aircraft without the need to return to the base.

[0007] Also, attaching a weapon to the pylon 106 of a drone or other aircraft is a time-consuming task for ground personnel. Thus, there is a need in the art of releasably securing a payload 104 to a drone 102 or other aircraft for improved methods, devices, and systems for quickly securing a payload 104 to a military drone 102 or other aircraft.

[0008] Additionally, the attachment means used to secure the payload 104 to the pylon 106 (or rack) may have limitations in that both the pylon 106 (or rack) and the payload 104 need to have corresponding connectors. If the connector of the pylon 106 does not match the connector of the payload 104, the payload 104 cannot be secured to the pylon 106. Thus, there is a need for improved methods, devices, and systems for securing the payload 104 even when the connectors of the pylon 106 and the payload 104 do not correspond, or for securing a payload 104 that has no connectors at all, in the technical field of releasably securing the payload 104 to a drone 102 or other aircraft.

[0009] (Industrial Applicability) The invention described herein can be manufactured by various industrial processes, including various mechanical, electrical, and pneumatic assembly techniques. Further, the invention described herein can also be used in industrial fields including parcel delivery operations.

Summary of the Invention

[0010] Multiple embodiments of a payload attachment system use one or more vacuum attachment modules to secure a payload to the wing or fuselage of a drone 102 (or other type of aircraft). Each vacuum attachment module includes at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives a command corresponding to either a vacuum cup activation signal or a vacuum cup release signal.

[0011] The components in the drawings are not necessarily to scale with respect to each other. Like reference numerals indicate corresponding parts throughout the several views.

Brief Description of the Drawings

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DETAILED DESCRIPTION OF THE INVENTION

[0022] FIG. 2 is a front view of a conventional military-purpose aerial drone 102, with a plurality of missiles 104a fixed to the drone using a weapon attachment system 200. FIG. 3 is a front view of a conventional military-purpose aerial drone 102, with a plurality of small drones 104b fixed to the drone using a weapon attachment system 200. As defined herein, the term payload 104 refers to any target payload, such as non-limiting exemplary missiles 104a, small drones 104b, and / or other weapons. The payload 104 is releasably (removably) fixed to the drone 102 (or other types of aircraft) using one or more vacuum attachment modules 202.

[0023] Figure 4 is a diagram of four vacuum attachment modules 202. Each vacuum attachment module 202 includes a vacuum cup 204 and a vacuum control unit 206. The vacuum cup 204 is disposed outside the vacuum attachment module 202. The outer surface of the vacuum control unit 206 (the surface facing the vacuum cup 204) is configured to be permanently or semi-permanently fixed to the surface of the first object as described later.

[0024] When a vacuum is generated by the vacuum control unit 206 inside the vacuum cup 204, the vacuum attachment module 202 is releasably fixed to the surface of the second object. In practice, in response to receiving a vacuum cup activation signal from the vacuum control device 208, the vacuum control unit 206 operates one or more internal vacuum pumps to generate a vacuum at least at a predetermined vacuum level (negative atmospheric pressure) within the internal region of the vacuum cup 204.

[0025] The vacuum cup activation signal can be generated by various vacuum control devices 208 depending on a particular embodiment of the payload attachment system 100. For example, a payload installer may provide an input to the vacuum control device 208 and establish a vacuum. Here, the payload installer pairs the vacuum control device 208 with a plurality of vacuum control units 206 used to fix a particular payload 104.

[0026] For example, the payload 104 can be releasably fixed to the wing or fuselage of the drone 102 (or other type of aircraft). When the payload 104 is held in place by one or more payload installers, the vacuum pump is activated. Thereby, the vacuum in each vacuum cup 204 fixes the payload 104 to the drone 102 (or other type of aircraft). During flight to the battlefield, the fixed payload 104 remains in place. In response to a vacuum cup release signal, the vacuum in the vacuum cup 204 is released. Thereby, the payload 104 falls from the drone 102 (or other type of aircraft).

[0027] In various embodiments, multiple pylons 106 are not required to removably secure a payload to the drone 102 (or other type of aircraft). One unexpected advantage provided by an embodiment of the payload attachment system 100 is that unwanted radar reflections from the pylons 106 are eliminated. Another unexpected advantage is that by reducing the weight of the pylons 106, the total payload capacity of the drone 102 (or other type of aircraft) can be increased. Also, the connectors on the payload 104 and the pylons 106 are no longer needed. Thus, the problem of connector mismatches is also resolved.

[0028] Yet another advantage provided by an embodiment of the payload attachment system 100 is that the time required to secure the payload 104 to the drone 102 (or other type of aircraft) is significantly reduced. Also, the payload installer does not need to use specially designed tools. Rather, the payload installer simply holds the payload 104 in place until a vacuum is established within the vacuum cup 204.

[0029] If the drone 102 (or other type of aircraft) has a VTOL function, the drone 102 (or other type of aircraft) can make multiple deliveries while on-site (in a battlefield). For example, if a VTOL drone 102 is being used to drop (deliver) multiple AGM-114 Hellfire missiles 104a (each weighing only 104 pounds) onto a battlefield, the VTOL drone 102 can drop the first plurality of missiles 104a onto a plurality of target targets. The VTOL drone 102 can then return to a safe location behind friendly lines (rather than a base located remotely). The VTOL drone 102 can then be quickly rearmed with a second plurality of missiles 104a and return to the battlefield.

[0030] The systems and methods of the present disclosure for securing a load 102 using a load attachment system 100 will be better understood by considering the following detailed description in conjunction with the drawings. The detailed description and the drawings provide examples of various inventions described herein. Those skilled in the art will understand that the embodiments of the present disclosure may be varied, modified, and altered without departing from the scope of the inventions described herein. Many variations are possible depending on different uses and design considerations, but for the sake of brevity, not all possible variations will be individually described in the following detailed description.

[0031] In the following detailed description, various embodiments of systems and methods for releasably securing a load to a fixture using a load attachment system 100 are provided. Related features within an embodiment may be the same, similar, or dissimilar in different embodiments. For the sake of brevity, duplicate descriptions of related features are not provided in each embodiment. Instead, the use of related feature names will inform the reader that features with the associated related feature names may be similar to the related features of the foregoing embodiments. Features specific to a given embodiment will be described in that particular embodiment. The reader should understand that a given feature need not be identical or similar to a particular depiction of related features of a given drawing or embodiment.

[0032] Unless otherwise specified, the following definitions apply throughout this document.

[0033] "Substantially" means conforming to a particular dimension, range, shape, concept, or other aspect (feature) modified by the term to some extent. A function or component need not conform exactly. For example, an object that is "substantially cylindrical" means that the object resembles a cylinder, but may have one or more deviations (differences) from a true cylinder.

[0034] The terms "comprise", "include" and "have" (and their conjugations) are used interchangeably and mean including the respective object(s) but not necessarily limited thereto, and are open-ended terms not intended to exclude additional elements or method steps not explicitly recited.

[0035] Terms such as "first", "second" and "third" are used to distinguish or identify various members of a group or the like, and are not intended to indicate a sequential, chronological, or numerical limitation.

[0036] "Coupled" means connected, either directly or indirectly through intervening components, permanently or removably. "Fixed" means connected directly without intervening components.

[0037] "Communicatively coupled" means that an electronic device is communicatively connected to another electronic device, either directly or indirectly via a communication network, wirelessly or using a wired-based connector. "Controllably coupled" means that an electronic device controls the operation of another electronic device.

[0038] Returning to FIG. 4, in a preferred embodiment, the vacuum control device 208 may be present inside the drone 102. A drone operator and / or payload installer may communicatively couple their electronic devices to the vacuum control device 208 and may generate an activation signal or a release signal.

[0039] To pair the vacuum control unit 206 with the vacuum control device 208, the payload installer simply needs to switch on (activate) the plurality of vacuum attachment modules 202 used to fix the payload 104. Other vacuum attachment modules 202 that remain switched off will not respond to the vacuum control device 208. In other embodiments, any other suitable pairing method may be used.

[0040] The vacuum control device 208 is paired with the vacuum attachment module 202, and when the payload is fixed, the drone 102 can move to the battlefield. Thereafter, the vacuum control device 208 can receive a release instruction from the drone operator who is operating the electronic device that controls the drone 102 and the vacuum control device 208.

[0041] Each vacuum attachment module 202 can maintain the target vacuum level independently within its respective vacuum cup 204, so that the payload 102 can be fixed for any period of time. That is, the vacuum control unit 206 can activate the internal vacuum pump as needed to maintain a predefined vacuum pressure between the surface and the vacuum cup 204. When the vacuum is released by the vacuum control unit 206, the vacuum cup 204 releases the object.

[0042] A selective outer seal 210 can be used to form a seal between the surface of the wing or fuselage of the drone 102 (or other type of aircraft) and the surface of the payload 104. The outer seal 210 is a suitable semi-rigid or flexible compressible material that generally follows the shape and size of the outer periphery of one or more vacuum attachment modules 202. In a preferred embodiment, the outer seal 210 is made of neoprene, rubber, rubberized foam material, etc., with a suitable thickness (height) sufficient to create a cavity between the surfaces of the two objects fixed to each other.

[0043] In various embodiments employing a selective outer seal 210, in response to activation of the payload attachment system 100, air is drawn from the plurality of vacuum attachment modules 202. The flexible vacuum cup 204 collapses (folds) somewhat and decreases in height when a vacuum is created within the vacuum cup 204. The downward collapse of the vacuum cup 204 draws the surface of the wing or fuselage of the drone 102 (or other aircraft) and the surface of the payload 104 towards each other. Thereby, the outer seal 210 is compressed, forming a friction seal between the surface of the wing or fuselage of the drone 102 (or other aircraft) and the surface of the payload 104. Since the vacuum cup 204 is present within the cavity formed by the compressed outer seal 210, it is protected from forces generated by weather and / or moving air. That is, since the outer seal 210 is made of a flexible and airtight material such as neoprene, the outer seal 210 serves to keep weather and moving air away from the vacuum cup 204 and avoid disturbing the vacuum cup 204. By protecting the seal of the vacuum cup 204, the power requirements of the vacuum pump can also be reduced. Further, the reliability of the vacuum cup 204 at the leading edge, which may experience the maximum "lift force" during the movement of the drone 102, can be increased.

[0044] In some embodiments, the outer seal 210 is attached to the surface of the payload 104 or the wing or fuselage of the drone 102 (or other type of aircraft) using suitable means. The payload installer need only simply hold the payload 104 in place, but preferably gently presses the payload 104 onto the outer seal 210. Once the vacuum is established and the payload 104 is fixed to the wing or fuselage of the drone 102, the payload installer can release the payload 104. The outer seal 210 can be fixed to the surface using suitable adhesives, ferromagnetic or electromagnetic strips, ferromagnetic or electromagnetic materials disposed within the outer seal 210, screws, bolts, surface fastener (loop and hook) materials, etc.

[0045] The advantage of fixing the outer seal 210 to the wing or fuselage of the drone 102 (or other types of aircraft) is that various different payloads 104 can be fixed as long as a part of the surface of the payload 104 is compatible with the outer seal 210 attached to the drone 102 (or other types of aircraft). The advantage of attaching the outer seal 210 to the payload 104 is that various different payloads 104 can be fixed at any location on the wing or fuselage of the drone 102 (or other types of aircraft).

[0046] The advantage of using a ferromagnetic material or an electromagnetic material to fix the outer seal 210 is that different outer seals 210 can be selectively used depending on the characteristics of the payload 104 and / or the drone 102 (or other types of aircraft). Further, when the magnetically fixed outer seal 210 is damaged, the damaged outer seal 210 can be easily replaced on-site by the payload installer.

[0047] In some embodiments, the outer seal 210 is not fixed to any surface of the drone 102 (or other types of aircraft) and the payload 104. In such embodiments, the payload 104 and the outer seal 210 are arranged in a predetermined position and fixed by the vacuum attachment module 202. When the payload 104 is released, the outer seal 210 is sacrificed and simply falls to the ground.

[0048] In some cases, the outer seal 210 can initially be provided as a sheet of material that can be cut by the payload installer into the desired shape and size. This embodiment can be particularly advantageous when different types of payloads 104 are to be releasably fixed to the drone 102 (simultaneously or at different times). Alternatively or additionally, a pre-cut outer seal 210 cut based on the dimensions of the payload 104 can be provided.

[0049] Figure 5 is a side view of missile 104a with four vacuum attachment modules 204, and vacuum control unit 206 is fixed to the outer surface of missile 104a using suitable releasable connectors. When missile 104a is launched by an operator of drone 102 (or other type of aircraft) by releasing the connector between the surface of missile 204a and vacuum attachment module 202, vacuum attachment module 202 remains releasably fixed to drone 102. When drone 102 returns to base, vacuum attachment module 202 can be released and the wings and / or fuselage of drone 102 can be cleaned. The released vacuum attachment module 202 can then be used for another missile 104a. After vacuum attachment module 202 is released, a payload installer can install a new missile 104a that is similarly attached. Drone 102 can return to the battlefield. Embodiments of payload attachment system 100 can enable very rapid rearming of drone 102, even within a few minutes. Also, if drone 102 (or other aircraft) has a VTOL function, drone 102 (or other aircraft) does not need to return to a base located remotely.

[0050] Figure 6 is a side view of missile 104a with four vacuum attachment modules 202, and each vacuum attachment module 202 has two opposing vacuum cups 204 that are fixed to the outer surface of the missile 104a and the wings or fuselage of drone 102 (or other type of aircraft). Here, during installation, vacuum cups 204 can first be fixed to missile 104a. Next, a payload installer holds missile 104a in a predetermined position on the wings or fuselage of drone 102. When a vacuum is established within the opposing vacuum cups 204, missile 104a is removably fixed to drone 102. This process first fixes vacuum attachment module 202 to missile 104a and then fixes vacuum attachment module 202 to the surface of the wings or fuselage of drone 102 (or other aircraft).

[0051] When the missile 104a is launched by the operator of the drone 102 (or other type of aircraft), the vacuum attachment module 202 remains releasably fixed to the drone 102. When the drone 10 returns to the base, the vacuum attachment module 202 can be released and the wings and / or fuselage of the drone 102 can be cleaned. The released vacuum attachment module 202 can then be used for another missile 104a. After the vacuum attachment module 202 is released, a payload installer can install (mount) the similarly attached missile 104a.

[0052] Alternatively, the payload installer can simply fix a new payload 104 to a previously installed (mounted) vacuum attachment module 202 on the surface of the wing or fuselage of the drone 102 (or other aircraft). However, completely removing the previously used vacuum attachment module 202 can improve reliability as the removed vacuum attachment module 202 can be inspected for damage before being reused.

[0053] After the new payload 104 is installed (mounted), the drone 102 can return to the battlefield. Embodiments of the payload attachment system 100 can enable very rapid rearming of the drone 102 and even rearming of the drone 102 in a matter of minutes. Further, the payload installer can fix the released vacuum attachment module 202 to another missile 104a while the drone 102 is on its way back from and to the battlefield.

[0054] If the drone 102 (or other aircraft) has a VTOL function, the drone 102 (or other aircraft) does not need to return to a base at a remote location. Instead, the drone 102 can return to a safe location away from the battlefield and then be rearmed and return to the battlefield immediately.

[0055] FIG. 7 is a side view of a missile 104a equipped with four vacuum attachment modules 202, with the vacuum control unit fixed to the wing or fuselage of a drone 102 (or other type of aircraft). Here, during installation, the payload installer holds the missile 104a in place on a vacuum cup 204 on the wing or fuselage of the drone 102. When a vacuum is established within the vacuum cup 204, the missile 104a is releasably fixed to the drone 102. Similar to the embodiments shown in FIGS. 5 and 6, the exemplary embodiment of FIG. 7 allows for very rapid rearming of the drone 102.

[0056] In some embodiments, the vacuum cup 204 is releasably fixed to the vacuum attachment module 202. Here, if the vacuum cup 204 is damaged during use, the payload installer can easily replace the damaged vacuum cup 204. Alternatively or additionally, different vacuum cups 204 may be suitable for different types of payloads 104. Here, the payload installer can use the vacuum cup 204 that is most suitable for the currently installed payload 104.

[0057] FIG. 8 is a block diagram of one embodiment of the vacuum attachment module 202 and shows selected exemplary electronic components. A non-limiting exemplary vacuum attachment module 202 includes a power supply 802, a vacuum pump 804 (with optional venturi and check valve), a pressure sensor 806, one or more optional environmental sensors 808, a transceiver 810, an optional user interface 812, an optional indicator light 814, a processor system 816 (also referred to as a microcontroller), and a memory 818. The memory 818 includes portions for storing a transceiver module 820, a user interface module 822, a vacuum pump and check valve module 824, and a monitoring module 826. In some embodiments, the transceiver module 820, the user interface module 822, the vacuum pump and check valve module 824, and the monitoring module 826 can be integrated together and / or integrated with other logic. In other embodiments, some or all of these memories and other data manipulation functions can be provided by using a remote server or other electronic device suitably connected to a client device via the Internet or other means. Other embodiments of the vacuum attachment module 202 can include some of the foregoing components or can omit some of them. Additionally, additional components not described herein can be included in alternative embodiments.

[0058] The power supply 802 is preferably a battery-based power supply that supplies power to the processor system 816, the vacuum pump 804 (with optional venturi and check valve), and other selected components. A replaceable battery and / or a rechargeable battery can be used. Preferably, the power obtained from the power supply is sufficient to operate the vacuum attachment module 202 for at least a predetermined semi-permanent period, which can be several weeks, several months, or more than one year. In alternative embodiments, a generator or other power source within the drone 102, any suitable power source such as solar power generation, magnetic power generation, etc. (but not limited thereto) can be used.

[0059] In a preferred embodiment, the processor system 816 monitors the power currently available from the power source 802. When the power drops below a threshold, a warning notification may be communicated from the processor system 816 to the vacuum control device 208 and / or to the remote control system of the drone operator. In some embodiments, power management recommendations may be made to the drone operator and / or payload installer so as to be able to manage the use of the vacuum attachment module 202. For example, if the power source is supplied by a battery and a low battery state occurs, or if a low battery state is predicted to occur in the near future, the drone operator and / or payload installer may be notified of the remaining power or battery life. The drone operator and / or payload installer may then choose to replace one or more batteries of the power source 802 and / or, if the battery is rechargeable, to charge the battery.

[0060] The vacuum pump 804 controllably coupled to the processor system 816 is an electric vacuum pump that establishes a vacuum (a pressure lower than the actual air pressure) sufficient to fix the vacuum cup 204 to one of the surfaces of the wing or fuselage of the drone 102 (or other aircraft) and / or the surface of the payload 104.

[0061] An optional venturi may be used with the vacuum pump 804. The venturi valve may be a mechanical valve that uses a spring or the like to operate the valve, or an active venturi valve that uses electricity to operate the valve. The pressure difference passing through the venturi, if used, improves the efficiency of the vacuum pump 804.

[0062] A processor system 816 that executes a vacuum pump and a check valve module 824 controls the operation of the vacuum pump 804. In response to receiving a vacuum cup activation signal, the vacuum pump 804 is activated to generate a vacuum, and the vacuum releasably secures the vacuum attachment module 202 to the surface of the wing or fuselage of the drone 102 (or other aircraft) and / or the payload 104. The processor system 816 activates the vacuum pump 804 to release the vacuum in response to receiving a vacuum cup release signal, releasing the surface of the wing or fuselage of the drone 102 (or other aircraft) and / or the payload 104 from the vacuum attachment module 202. It is intended that any suitable vacuum pump 804 currently known or developed in the future be included within the scope of the present disclosure and be protected by the appended claims.

[0063] Multiple vacuum pumps 804 provide reliability in the event that a single vacuum pump 804 fails. In various embodiments, any desired number of vacuum pumps 804 may be used. Also, multiple vacuum pumps 804 may be used to cooperatively (in partnership) generate a stronger vacuum. A preferred embodiment includes two vacuum pumps 804a, 804b. In a preferred embodiment, the second pump 804b can be a piezoelectric pump or other suitable micropump. Since the piezoelectric pump is very quiet during operation, the piezoelectric pump can be used to maintain the vacuum pressure while the drone 102 (or other type of aircraft) is operating in stealth mode.

[0064] Alternatively or additionally, the vacuum cup 204 may include a small vacuum canister or bottle, or a microchamber, as a source of negative pressure that can be quickly applied inside the vacuum cup 204. Alternatively, the vacuum canister or bottle may be present inside the payload 104 (see, for example, FIG. 5), and / or inside the drone 102 or other type of aircraft (see, for example, FIG. 7).

[0065] A selective pressure sensor 806 monitors the pressure within the vacuum cup 204. In an exemplary embodiment, the pressure sensor 806 is disposed within the vacuum attachment module 202 to sense the vacuum pressure. The pressure sensor 806 can be an internal component of the vacuum cup 204 or a separate component disposed at the vacuum port 408 (FIG. 4) of the vacuum pump 204. Alternatively or additionally, the pressure sensor 806 can be an integrated component of the vacuum pump 804.

[0066] The selective pressure sensor 806 is communicatively coupled to a processor system 816 (also referred to herein as a microcontroller). The microcontroller 816 executing the monitoring module 826 monitors the sensed vacuum pressure within the vacuum cup 204 in real time. Once a vacuum is established to releasably secure a payload to the vacuum cup 204, the processor system 816 executing the vacuum pump and check valve module 824 can further operate the vacuum pump 804 in response to the monitored pressure within the vacuum cup 204 falling below a predefined threshold. Accordingly, the vacuum pressure within each of the plurality of vacuum cups 204 can be controlled to any desired predetermined pressure value or pressure range.

[0067] For example, the vacuum within the plurality of vacuum cups 204 can vary depending on altitude. When the drone 102 goes to a relatively high altitude or returns to a lower altitude, the processor system 816 can operate the vacuum pump 804 to adjust and / or maintain the vacuum pressure to a desired target pressure value or target pressure range in response to the change in altitude. For example, the sensor 806 can sense the current vacuum pressure. The processor system 816 can compare the current vacuum pressure to one of a plurality of predefined thresholds. A command is communicated to the vacuum pump 804 to increase or decrease the vacuum pressure. In this way, the change in the vacuum pressure is executed so that the current vacuum pressure remains at some predefined value (or range).

[0068] As another example, the vacuum pressure can be varied as a function of the speed of the drone. Here, as the speed of the drone 102 increases, a higher vacuum pressure can be generated to ensure that the vacuum attachment module 202 does not become detached from the drone 102 and / or the payload 104 due to the increased wind caused by the increased speed of the drone 102. A speed sensor (not shown), such as a speedometer, provides current speed information to the processor system 816. The processor system 816 compares the current vacuum pressure to a predefined vacuum pressure associated with the speed. A command is communicated to the vacuum pump 804 to increase or decrease the vacuum pressure to a new vacuum pressure corresponding to the current speed. In this way, the vacuum pressure is adjusted so that the current vacuum pressure value (or range) is appropriate for the current speed.

[0069] In various embodiments, a predetermined vacuum pressure or pressure range can be maintained within the vacuum cup 204. For example, a slow leak between the edge of the vacuum cup 204 and the surface of the payload that is releasably fixed thereto may result in a loss of vacuum pressure. The sensor 806 can sense the decreasing current vacuum pressure due to the slow leak. The processor system 816 compares the current vacuum pressure to one of a plurality of predefined thresholds. A command is communicated to the vacuum pump 804 to increase or decrease the vacuum pressure. In this way, the vacuum pressure is adjusted so that the current vacuum pressure remains at some predefined value (or range). Thus, the vacuum control unit 206 can automatically activate when the vacuum pressure goes outside a predetermined threshold or threshold range and re-establish the vacuum pressure.

[0070] As another example, changing environmental conditions such as temperature and / or altitude can vary the vacuum pressure, whereby the control unit 206 can automatically activate in response to the vacuum pressure dropping or rising beyond a predetermined threshold or threshold range and can re-establish the vacuum pressure. Here, the sensor 806 can sense the current vacuum pressure that changes due to the changing environmental conditions. The processor system 816 can compare the current vacuum pressure with one of a plurality of predefined thresholds. A command is communicated to the vacuum pump 804 to increase or decrease the vacuum pressure. In this way, the vacuum pressure is changed so that the current vacuum pressure remains at some predefined value (or range).

[0071] The environmental sensor 808 can be used to monitor external environmental conditions such as humidity, rainfall, wind speed, ambient air pressure, temperature, etc. Based on the sensed environmental conditions, the processor system 816 can execute the vacuum pump and check valve module 824 to change a predefined minimum vacuum pressure so that the vacuum pressure maintained within the vacuum cup 204 is appropriate for the changing environmental conditions. For example, when the altitude increases and the ambient air pressure decreases, or when the altitude decreases and the ambient air pressure increases, the actual vacuum pressure can be automatically adjusted by the vacuum control unit 206 and / or the vacuum control device 208 to maintain a predefined minimum vacuum pressure and / or a maximum vacuum pressure within the vacuum cup 204 or the vacuum attachment module 202. Alternatively, some embodiments can maintain a predetermined pressure difference between the vacuum within the vacuum cup 204 and the current ambient air pressure.

[0072] The transceiver 810 is configured to wirelessly receive and / or transmit radio frequency (RF) communication signals to other transceivers 810 within other vacuum attachment modules 202 and / or the drone 102. In such embodiments, the wireless communication transceiver 810 can be a low-power communication system such as a short-range communication system. An exemplary short-range wireless communication is Bluetooth. Any suitable low-power and / or short-range wireless communication system known currently or developed in the future can be used in various embodiments. Since multiple vacuum attachment modules 202 and / or drone transceivers are in proximity to each other, a low-power short-range wireless communication system is suitable.

[0073] Alternatively or additionally, other wireless-based communication networks and / or hybrid communication networks can be communicatively coupled to the transceiver 810. Exemplary communication systems include, but are not limited to, cellular phone systems, Wi-Fi systems, satellite systems, radio frequency (RF) systems, and / or telephone systems. In such embodiments, the transceiver 810 can be communicatively coupled to a wireless communication system. Accordingly, the transceiver 810 enables communication between a remote electronic device such as a drone operator's remote control system and the vacuum attachment module 202. In some applications, the transceiver 810 is communicatively coupled to an operator's portable handheld electronic device such as a smartphone, notebook, etc. In such embodiments, the operator can use the portable handheld electronic device and / or another control system while in the battlefield to operate the vacuum attachment module 202 (initiate a vacuum cup release signal) and / or monitor the performance of the vacuum attachment module 202.

[0074] In one embodiment, a processor system 816 that executes a transceiver module 820 receives and / or transmits communications from other vacuum attachment modules 202, drone transceivers, or other remote electronic devices. As disclosed herein, the vacuum attachment module 202 activates the vacuum pump 804 to establish a vacuum within the vacuum cup 204 in response to the transceiver 810 receiving a vacuum cup activation signal from one of the other vacuum attachment modules 202, a drone transceiver, and / or other remote electronic device. Conversely, the processor system 816 that executes the transceiver module 820 can deactivate the vacuum pump 804 to terminate the vacuum within the vacuum cup 204 in response to the transceiver 810 receiving a vacuum cup release signal from one of the other vacuum attachment modules 202, a drone transceiver, and / or other remote electronic device such as an operator's drone remote control system.

[0075] An optional user interface 812 can be provided to enable manual control of the vacuum attachment module 202 by a payload installer. Buttons, switches, or other controllers can enable the payload installer to manually activate the vacuum control unit 206. A processor system 816 that executes a user interface module 822 can activate the vacuum pump 804 to establish and / or release a vacuum within the vacuum cup 204 based on control signals generated by the user interface 812 in response to a manual operation of the user interface 812 by the payload installer.

[0076] For example, after the payload 104 is first fixed to the drone 102 (or other types of aircraft), there may be a case where the payload installer wants to relocate and / or reorient the fixed payload 104. For example, the position and / or orientation of the missile 104a fixed to the surface (fixture) of the wing or fuselage of the drone 102 can be changed to adjust the orientation of the missile. The payload installer can manually deactivate one or more vacuum attachment modules 202 to perform the adjustment, and then can restart (activate) those vacuum attachment modules 202 to re - establish the vacuum within the vacuum cups 204.

[0077] One or more optional indicator lights 814 may be provided outside the vacuum attachment module 202 and / or the vacuum control device 208 to indicate the operating state of the device and / or the system. For example, the processor system 816 can cause the indicator light 814 to emit light when the vacuum attachment module 202 is functioning properly. Alternatively or additionally, when the vacuum attachment module 202 is not operating properly, a light of a different color and / or another indicator light can emit light. Thus, the payload installer can visually determine whether the vacuum attachment module 202 is operating properly based on the visible output of the indicator light 814. In some embodiments, the indicator light 814 can be remotely located. In this case, the indicator light 814 can be communicatively coupled to another remote transceiver. A light control signal generated by the processor system 816 can be communicated from the transceiver 810 to the other transceiver. Then, the light control signal can be received by the remote indicator light 814.

[0078] FIG. 9 is a side cross-sectional view of a vacuum attachment module 202 with a non-limiting exemplary cover member 902. The vacuum control unit 206 is preferably defined by a rigid or semi-rigid body member 904 (such as, but not limited to, a monocoque body), which defines a cavity that encompasses various components within the vacuum control unit 206. Some embodiments may be formed as a monocoque body. The body member 904 protects the various components within the body cavity from damage. In a non-limiting exemplary embodiment, the monocoque body member 904 defines a monocoque cavity that fixes and protects the components of the vacuum control unit 206, and the vacuum cup 204 is coupled to the monocoque body member 904.

[0079] The vacuum cup 204 is preferably manufactured from a flexible or semi-flexible material that is air-impermeable. In various embodiments, the vacuum cup 204 is permanently fixed to the body member 904 in an airtight manner. In some embodiments, the body member 904 and the vacuum cup 204 are formed as an integral part.

[0080] Ports 906 fluidly couple vacuum pumps 204a, 204b to the internal cavity of the vacuum cup 204. A check valve 908 may be used to maintain the vacuum pressure established within the vacuum cup 204. The check valve 908 has a cracking pressure corresponding to a predetermined vacuum pressure within the vacuum chamber such that a predetermined vacuum pressure is maintained within the vacuum cup 204 when the vacuum cup attachment system 100 is fixed to the surface of an object. The check valve 908 can be a mechanical check valve that uses a spring or the like to operate the valve, or an active check valve that uses electricity to operate the check valve 908.

[0081] The exemplary embodiment illustrated in FIG. 9 includes one or more optional manual release tabs 910. The manual release tab 910 is a member that protrudes outwardly on the outside of the vacuum cup 204. The tab 910 can be gripped by the user to lift the bottom of the flexible vacuum cup 204 from the surface of the load after the vacuum is released. When the user grips and pulls the manual release tab 910, ambient air flows into the interior of the vacuum cup 204, the remaining vacuum pressure is released, and the vacuum attachment module 202 is released from the load. In various embodiments, any desired number of manual release tabs 910 can be provided at any location.

[0082] A plurality of openings 912 (holes) are shown as being manufactured in the body member 904 of the vacuum control unit 206. These openings 912 are used to secure the cover member 902 to the upper surface of the body member 904. The openings 912 can be screw holes that receive threaded bolts or screws 918 (FIG. 4) that engage through corresponding openings 912 in the cover member 902. When the bolts or screws 918 are screwed and tightened in place, the cover member 902 is secured to the top of the body member 904. Alternatively, the openings 912 may not be threaded, and nuts and bolts 918 can be used to secure the cover member 902 to the body member 904 of the vacuum control unit 206. Alternatively or additionally, other fastening means such as screws, clamps, magnets, adhesives, etc. can also be used to secure the cover member 902 to the top of the vacuum cup 204. In some embodiments, the cover member 902 can be secured to or made part of the body member 904 of the vacuum control unit 206 during manufacture.

[0083] A non-limiting exemplary cover member 902 may include a selective outward protruding member 914 that protrudes outward from the outer surface of the cover member 902. A selective opening 916 may be disposed through the outward protruding member 912. Bolts or screws 918 are used to fix the cover member 902 to a fixture. In this non-limiting exemplary embodiment, the height of the outward protruding member 914 is high enough to allow access to the opening 912 when the bolts or screws 918 are used to fix the cover member 902 to the upper part of the vacuum control unit 206.

[0084] Alternatively, the outer edge of the cover member 902 may be threaded. The inner surface near the top of the body member 904 may have mating threads. When the cover member 902 is fixed to the surface of the wing or fuselage of the drone 102 (or other aircraft) and / or the surface of the payload 104, the body member 904 may be screwed to the fixed cover member 902.

[0085] Alternatively, tabs or other protrusions (not shown) may extend outward from the body member 904 and / or the cover member 902. At this time, screws 918, bolts 918, etc. may be used to fix the vacuum attachment module 202 to the surface of the wing or fuselage of the drone 102 (or other aircraft) and / or the surface of the payload 104. Clips, snaps, rails, etc. may also be used to fix the vacuum attachment module 202 to the surface of the wing or fuselage of the drone 102 (or other aircraft) and / or the surface of the payload 104.

[0086] After considering the present disclosure, those skilled in the art will understand that various types of fixing means may be used to fix the cover member 902 to the upper part of the vacuum control unit 206 without departing from the novel features of the present invention. Similarly, those skilled in the art will understand that various types of fixing means may be used to fix the cover member 902 to any type of fixture without departing from the novel features of the present invention. All such embodiments are within the scope of the present disclosure and are intended to be protected by the appended claims.

[0087] Figure 10 is a side cross-sectional view of a vacuum attachment module 1002 with two opposing vacuum cups 204. The components and operating functions of the vacuum attachment module 1002 can be similar or identical to those of the vacuum attachment module 202. For the sake of brevity, the same components and / or operating functions will not be described again here. A practical application example of the vacuum mount module 1002 is shown in FIG. 6.

[0088] The exemplary embodiment shown in FIG. 10 shows two vacuum pumps 804a that establish and maintain a vacuum within each respective vacuum cup 204. Alternative embodiments may use any suitable number and / or any suitable type of vacuum pump 804.

[0089] Figure 11 is a block diagram of a vacuum attachment module control system 1102 that employs a designated vacuum control device 208 to control a plurality of vacuum attachment modules 202. Each of the vacuum attachment modules 202 (slave devices) is controllably coupled to the vacuum control device 208 (master device). Preferably, the master / slave control system enables the vacuum control device 208 to generate a vacuum cup activation signal and a vacuum cup release signal using an appropriate short-range or wired-based communication signal and transmit them to the plurality of vacuum attachment modules 202. In some embodiments, one of the selected vacuum attachment modules 202 is designated as the vacuum control device 208.

[0090] In addition, the vacuum control device 208 is configured to receive information from a plurality of vacuum attachment modules 202. Operating state information can be communicated to the vacuum control device 208. For example, when one of the vacuum attachment modules 202 fails or begins to lose vacuum pressure, the vacuum control unit 206 can be notified of the failure and / or vacuum pressure loss by the specific vacuum attachment module 202. Optionally, the vacuum control device 208 can increase the vacuum pressure in the remaining vacuum attachment modules 202 to compensate for the failed vacuum attachment module 202. As another non-limiting example, the vacuum pressure of one or more of the vacuum attachment modules 202 can be selectively changed by the vacuum control device 208.

[0091] Optionally, the vacuum control device 208 can be communicatively coupled to a remote control and command center 1104. The control and command center 1104 can communicate with the vacuum control device 208 using an appropriate wireless communication signal 1106 format, such as a satellite signal or a cellular phone communication signal. In response to receiving a command from the control and command center 1104, which is controlled by a drone operator, the vacuum control device 208 can generate and transmit a vacuum cup activation signal and a vacuum cup release signal. In some embodiments, a wired-based communication format can be used. Additionally or alternatively, the vacuum control device 208 can communicate operating state information and / or vacuum pressure information to the control and command center 1104. Accordingly, the drone operator can grasp the operating state of the payload attachment system 100. When the control and command center 1104 is a smartphone or the like, an app that facilitates communication between the smartphone and the vacuum control device 208 can be installed on the smartphone.

[0092] FIG. 12 is a block diagram of a vacuum attachment module control system 1202 employing a mesh network 1204, where a plurality of vacuum attachment modules 202 cooperate to control the operation of the payload attachment system 100. Here, the individual vacuum attachment modules 202 are communicatively coupled together. Each of the vacuum attachment modules 202 communicates information such as its operating state and / or vacuum pressure to each of the other vacuum attachment modules 202. Thus, the plurality of vacuum attachment modules 202 operate in cooperation (collaboration) to fix the object. Some embodiments may employ an artificial intelligence algorithm to more effectively control the operation of the payload attachment system 100.

[0093] Optionally, one or more of the vacuum attachment modules 202 may be communicatively coupled to the control and command center 1104 using a format (form) of a suitable wireless communication signal 1106 such as a satellite signal or a cellular phone communication signal. When one or more of the vacuum attachment modules 202 receive a command from the remote control and command center 1104, the vacuum attachment module 202 responsible for the reception communicates a vacuum cup activation signal and a vacuum cup release signal to the other vacuum attachment modules 202. In some embodiments, a wired-based communication format may be used. Additionally or alternatively, the said one or more of the vacuum attachment modules 202 may communicate operating state information and / or vacuum pressure information to the control and command center 1104. Thus, the drone operator can grasp the operating state of the payload attachment system 100. When the remote control and command center 1104 is a smartphone or the like, an app that facilitates communication between the smartphone and the vacuum control device 208 may be installed on the smartphone controlled by the drone operator.

[0094] After considering this disclosure, one of ordinary skill in the art will understand that the plurality of vacuum attachment modules 202 can be implemented using any suitable mono Internet of Things (IOT) technology. All such IOT embodiments currently known or developed in the future are within the scope of this disclosure and are intended to be protected by the appended claims.

[0095] It should be emphasized that the foregoing embodiments of the payload attachment system 100 are merely possible examples of the implementation of the present invention. Many variations and modifications can be made to the foregoing embodiments. All such modifications and changes are within the scope of this disclosure and are intended to be protected by the appended claims.

[0096] Furthermore, the foregoing disclosure encompasses a plurality of distinguishable inventions having independent utility. Each of these inventions is disclosed in a specific form, but the specific embodiments described and illustrated above should not be considered in a limiting sense since numerous variations are possible. The subject matter of the present invention includes all novel and non-obvious combinations and sub-combinations of various elements, features, functions, and / or characteristics that are described above and are inherent to one of ordinary skill in the art in connection with such inventions. The present disclosure or the claims subsequently filed thereto describe "a" element, "a first" element, or any such equivalent, but it should be understood that the present disclosure or claims may incorporate one or more such elements and do not require or exclude two or more such elements.

[0097] The applicant for this application reserves the right to submit claims directed to combinations and sub - combinations of the disclosed invention that are considered novel and non - obvious. Inventions embodied in other combinations and sub - combinations of features, functions, elements, and / or characteristics may be claimed by amending their claims or presenting new claims in this application or related applications. Such amended or new claims should be considered to be within the scope of the subject matter of the invention described herein, whether they are directed to the same invention or a different invention, and whether they differ in scope from, are broader than, are narrower than, or are equal to the original claims.

Claims

1. A payload attachment system using at least one vacuum attachment module, wherein the vacuum attachment module comprises a cover member having an outer surface fixable to the surface of the wing or fuselage of a drone, a body member defined by a cavity covered by the cover member during use of the object attachment system by vacuum, a vacuum cup coupled to the body member, the vacuum cup being disposed outside the body member on the side of the body member opposite to the cover member, a microcontroller present in the cavity of the body member, a vacuum pump present in the cavity of the body member, the vacuum pump being controllably coupled to the microcontroller and fluidly coupled to the vacuum cup, a power supply controllably coupled to the microcontroller and connected to the vacuum pump, and the power supply supplies power to the vacuum pump in response to an activation signal received by the microcontroller, causing the vacuum pump to generate a predetermined vacuum pressure between the surface of the payload and the vacuum cup A payload attachment system characterized by the above.

2. The cover member has attachment means configured to attach the outer surface of the cover member to the surface of the wing or the fuselage. The payload attachment system according to claim 1, characterized by the above.

3. The vacuum attachment module further comprises a vacuum chamber in fluid communication with the vacuum pump and the vacuum cup, a check valve disposed between the vacuum chamber and the vacuum cup, and the microcontroller activates the vacuum pump to maintain the predetermined vacuum pressure in the vacuum chamber, the check valve has a cracking pressure corresponding to the predetermined vacuum pressure, and when the vacuum cup attachment system is fixed to the surface of the payload, the predetermined vacuum pressure is maintained in the vacuum cup. The payload attachment system according to claim 1, characterized by the above.

4. The vacuum attachment module further comprises a pressure sensor communicably connected to the microcontroller, and the pressure sensor senses the vacuum pressure in the vacuum cup, and the pressure sensor communicates pressure sensor information corresponding to the sensed vacuum pressure to the microcontroller. In response to the sensed vacuum pressure becoming greater than a first predetermined vacuum pressure or in response to the sensed vacuum pressure becoming less than a second predetermined vacuum pressure, the microcontroller activates the vacuum pump to maintain the predetermined vacuum pressure between the load and the vacuum cup. The load attachment system according to claim 1, characterized in that.

5. The vacuum attachment module further comprises a manual actuator disposed on an outer surface of the object attachment system by the vacuum and communicatively coupled to the microcontroller. and The load installer activates the manual actuator to release the object attachment system by the vacuum from the surface of the load, The manual actuator communicates a release signal to the microcontroller in response to activation by the load installer, In response to receiving the release signal, the microcontroller activates the vacuum pump to release the object attachment system by the vacuum from the surface of the load, The load installer further activates the vacuum pump to fix the object attachment system by the vacuum to the surface of the load, The manual actuator communicates the activation signal to the microcontroller in response to further activation by the load installer, In response to receiving the activation signal, the microcontroller activates the vacuum pump to fix the vacuum cup attachment system to the surface of the load. The load attachment system according to claim 1, characterized in that.

6. The vacuum attachment module further comprises an indicator light disposed on an outer surface of the object attachment system by the vacuum and communicatively coupled to the microcontroller. and In response to fixing the object attachment system by the vacuum to the surface of the load, the microcontroller activates the indicator light, The indicator light lights up in response to fixing the vacuum cup attachment system to the surface of the load, The load installer can intuitively understand whether the object attachment system by the vacuum is fixed to the surface of the load by looking at the indicator light. The load attachment system according to claim 1, characterized in that.

7. The object attachment system by vacuum is one of a plurality of object attachment systems by vacuum, each of the plurality of object attachment systems by vacuum further includes a transceiver communicably connected to a respective microcontroller and each of the microcontrollers of the plurality of object attachment systems by vacuum communicates with a vacuum control device, each of the vacuum pumps of the plurality of object attachment systems by vacuum operates to generate the vacuum between the surface of the load and the vacuum cup in response to the respective microcontroller receiving the activation signal from the vacuum control device via the respective transceiver The load attachment system according to claim 1, characterized in that.

8. The load is an aerial drone released by the drone The load attachment system according to claim 1, characterized in that.

9. further includes an outer seal corresponding to a selected part of the shape and size of the load, and a plurality of vacuum attachment modules are configured to cooperate to fix the load to the drone The load attachment system according to claim 1, characterized in that.

10. The outer seal further has one of a ferromagnetic strip or an electromagnetic strip, and the ferromagnetic strip or the electromagnetic strip is configured to hold the outer seal at a selected position of one of the drone or the load while the load installer fixes the load to the drone The load attachment system according to claim 9, characterized in that.

11. The vacuum attachment module further includes at least one environmental sensor communicably coupled to the transceiver and sensing environmental conditions, and the at least one environmental sensor communicates environmental information corresponding to the sensed environmental conditions to the transceiver, the received environmental information is communicated from the transceiver to the vacuum control device, and the vacuum control device determines an adjustment to the predetermined vacuum pressure based on the received environmental information The load attachment system according to claim 1, characterized in that.

12. A plurality of vacuum attachment modules further includes a transceiver, and the corresponding microcontroller communicates adjustment information corresponding to the adjustment to the predetermined vacuum pressure to the corresponding transceiver When the corresponding transceiver broadcasts the adjustment information, transceivers in other multiple vacuum cup units receive the adjustment information broadcasted, and the corresponding microcontroller executes the adjustment to the predetermined vacuum pressure based on the received adjustment information The load attachment system according to claim 1, characterized in that.

13. A load attachment system using at least one vacuum attachment module, wherein the vacuum attachment module comprises a cover member having an outer surface fixable to a load, a main body member defined by a cavity covered by the cover member during use of the object attachment system by the vacuum, a vacuum cup coupled to the main body member, the vacuum cup being disposed outside the main body member on the side opposite to the cover member of the main body member, a microcontroller present in the cavity of the main body member, a vacuum pump present in the cavity of the main body member, the vacuum pump being controllably coupled to the microcontroller and fluidly coupled to the vacuum cup, a power supply controllably coupled to the microcontroller and connected to the vacuum pump, and the power supply supplies power to the vacuum pump in response to a startup signal received by the microcontroller, causing the vacuum pump to generate a predetermined vacuum pressure between the surface of the wing or fuselage of the drone and the vacuum cup The load attachment system characterized by that.

14. The cover member has attachment means configured to attach the outer surface of the cover member to the drone The load attachment system according to claim 13, characterized in that.

15. The attachment means is configured to detachably attach the outer surface of the cover member to the drone The load attachment system according to claim 14, characterized in that.

16. The load further comprises an outer seal corresponding to a selected part of the shape and size of the load and a plurality of vacuum attachment modules are configured to cooperate to fix the load to the drone The load attachment system according to claim 13, characterized in that.

17. The outer seal further has one of a ferromagnetic strip or an electromagnetic strip, While the payload installer is fixing the payload to the drone, the ferromagnetic strip or the electromagnetic strip is configured to hold the outer seal at a selected position of either the drone or the payload. The payload attachment system according to claim 16, characterized in that.

18. A payload attachment system using at least one vacuum attachment module, The vacuum attachment module includes A cover member having an outer surface that can be fixed to the surface of the wing or fuselage of the drone, A body member defined by a cavity covered by the cover member during use of the vacuum object attachment system, A first vacuum cup coupled to the body member, the vacuum cup being disposed outside the body member, A second vacuum cup coupled to the body member, the vacuum cup being disposed outside the body member on the side opposite to the first vacuum cup of the body member, A microcontroller present in the cavity of the body member, A first vacuum pump present in the cavity of the body member, the first vacuum pump being controllably coupled to the microcontroller and fluidly coupled to the first vacuum cup, A second vacuum pump present in the cavity of the body member, the second vacuum pump being controllably coupled to the microcontroller and fluidly coupled to the second vacuum cup, A power supply controllably coupled to the microcontroller and connected to the first vacuum pump and the second vacuum pump, Comprising The power supply supplies power to the first vacuum pump in response to a first activation signal received by the microcontroller, causing the first vacuum pump to generate a predetermined vacuum pressure between the surface of the wing or fuselage of the drone and the first vacuum cup. The power supply supplies power to the second vacuum pump in response to a second activation signal received by the microcontroller, causing the second vacuum pump to generate a predetermined vacuum pressure between the surface of the payload and the second vacuum cup. The payload attachment system, characterized in that.

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