154results about "Modular constructions" patented technology

A modular system for drones is provided. A chassis can include a coupling mechanism operable to removably couple the chassis with a drone. A plurality of modular components can be operable to be interchangeably coupled with a control component. The modular components can be operable to be detachably coupled with a payload.

Stowing systems and methods to disassemble, store, and / or protect an aircraft, and in particular a VTOL aircraft, for transportation along standard public roadways. A stowing system attaches to the aircraft in a flight-ready state, and guides, supports, and / or stabilizes sub-assemblies of the aircraft as they are removed and moved into their stowed positions in preparation for transportation. In some embodiments, the stowing system is implemented as a trailer. The trailer, in some embodiments, is towable by car, such that the aircraft can be carried on and transported with the car and trailer by road. In some embodiments, the stowing system defines landing platform for the aircraft. It may provide facilities to help direct the aircraft to a precise location allowing support elements of the stowing system to be moved to engage with sub-assemblies of the aircraft along predefined degrees of freedom.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

Disclosed here are unmanned aerial vehicle embodiments including some embodiments having a fuselage, tail, and wings including example embodiments with an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle configured with direct connection to moveable flight control surfaces.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one precondition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one precondition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one precondition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

A series of convertible aircrafts with a core with an airframe defining a first axis is described; a first, a second, a third, a fourth, a fifth and a sixth rotor which are rotatable about respective first, second, third, fourth, fifth and sixth axis, and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value independent of each other; the core comprises an electric power source and electric motors which are connected to said first, second, third, fourth, fifth and sixth rotor; each aircraft of the series comprises a module associated with a respective architecture and interfaced with said core.

An automated alert system using unmanned aerial vehicles is described where the system is configured to monitor a selected area via one or more sensors configured to monitor the selected area for an anomaly. A processor in communication with the one or more sensors may be programmed to create or alter a flight path of an unmanned aerial vehicle upon receiving an alert from the one or more sensors for investigating or verifying the anomaly.

An aircraft that is certifiable for freighter transport is disclosed herein. The aircraft can include a hybrid fuselage including a plurality of modular sections, wherein the plurality of modular sections includes a first section, a second section, and an intermediate section, and wherein the intermediate section is disposed intermediate the first section and the second section. The aircraft can further include a plurality of systems traversing the plurality of modular sections and a plurality of structural components configured to mechanically couple the intermediate section to the first section and the second section of the plurality of modular sections. The first section and the second section are configured for use with a fuselage of a passenger aircraft, and wherein the intermediate section is configured for use with a fuselage of a freighter aircraft.

A transportation system includes a body, a plurality of propulsion units, and a control unit. The body defines an interior space. The plurality of propulsion units are mounted on the body. Each of the plurality of propulsion units includes a thrust-generating mechanism and a power source. The thrust-generating mechanism is configured to produce a propulsion force. The control unit is operatively coupled to each of the plurality of propulsion units. The transportation system further includes a housing unit or a pilot attachment disposed within the interior space. The housing unit or the pilot attachment is suspended by at least one connecting element or a suspension mechanism which is configured to dampen and / or stabilize and / or actively adjust movement relative to the body.

The invention relates to a hovercar, a vehicle and an aircraft. The hovercar comprises the vehicle and the aircraft. The vehicle comprises a vehicle body and the separation and combination device, the vehicle body is fixedly provided with a land-running cabin, and the separation and combination device is arranged on the vehicle body; the aircraft comprises an aircraft body and a plurality of foldable rotors, and the aircraft body is fixedly provided with a flight cabin; the plurality of foldable rotors are arranged on the aircraft body; the aircraft can vertically take off and land on the ground, and the separation and combination device is used for pulling the aircraft to be in coupling connection with the vehicle when the aircraft is in a state of stopping on the ground. In the embodiment, the aircraft does not need to be precisely positioned with the bearing platform on the vehicle body and can rapidly and vertically stop and descend on the ground, then the separation and combination device of the vehicle is connected with the aircraft and drags the aircraft to the bearing platform, and the control difficulty of coupling of the aircraft and the vehicle is relatively low.

Disclosed are specialized airframe structures for mission-adaptable unmanned aerial vehicles (UAVs) that are fabricated by rapid, low-cost additive manufacturing techniques. In some embodiments, an integral fastening system for a mission-adaptable aerial vehicle includes a first airframe section, a second airframe section, and a bayonet mount system that comprises one or more passageways produced on a first end region of the first airframe section to include a first channel and second channel, and one or more protrusions produced on a second end region of the second airframe section, such that, when the first and second airframe sections being assembled, the one or more protrusions are first aligned with an entry region of the first channel to be translated and then aligned with the second channel of the one or more passageways to be rotated to securely connect the first and second airframe sections together.

A case for carrying loads by an Unmanned Aerial Vehicle (UAV) comprises a first end comprising a first cap and a first opening and a second end comprising a second cap and a second opening, the second opening being smaller than the first opening. The case also comprises a rechargeable battery pack that, when the case is secured to the UAV, is configured to provide a power source for the UAV and the first cap and the second cap each comprising at least one metal connector for providing power to the UAV.

A computing device may generate a command for performing inventory management of a storage site based on inventory management data. The computing device may cause the inventory aerial robot to perform an inventory management trip based on the command. The inventory management trip may include receiving an input that includes coordinates of a plurality of target locations in the storage site, departing from a base station, navigating through the storage site to the plurality of target locations, capturing an image associated with an inventory item location at the one of the target locations, and returning to the base station. The computing device may perform an analysis of the image captured by the inventory aerial robot. The base station may perform swapping of a battery pack of the inventory aerial robot at the base station to prepare the inventory aerial robot for another inventory management trip.

The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes a mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a center wing, and causing the second wing to be extended relative to the center wing.

Disclosed are specialized airframe structures for mission-adaptable unmanned aerial vehicles (UAVs) that are fabricated by rapid, low-cost additive manufacturing techniques. In some embodiments, an integral fastening system for a mission-adaptable aerial vehicle includes a first airframe section, a second airframe section, and a bayonet mount system that comprises one or more passageways produced on a first end region of the first airframe section to include a first channel and second channel, and one or more protrusions produced on a second end region of the second airframe section, such that, when the first and second airframe sections being assembled, the one or more protrusions are first aligned with an entry region of the first channel to be translated and then aligned with the second channel of the one or more passageways to be rotated to securely connect the first and second airframe sections together.

The invention relates to the technical field of unmanned operation, and discloses an active deformation multi-aircraft integrated operation platform, which comprises a first aircraft, a second aircraft and a controller, one ends of the two fixed connecting rods are connected with the first aircraft, and steering engines are fixed to the other ends of the two fixed connecting rods; one ends of the two swing connecting rods are fixedly connected with the driving ends of the two steering engines respectively, a second aircraft and a third aircraft are connected to the two swing connecting rods respectively, the first aircraft, the second aircraft and the third aircraft are arranged in a triangular shape, and then a triangular collaborative architecture operation platform is formed; a first arc-shaped contact plate and a second arc-shaped contact plate are detachably arranged at the other ends of the two swing connecting rods respectively, a first clamping jaw is detachably arranged at one end of the first arc-shaped contact plate, and a second clamping jaw is detachably arranged at one end of the second arc-shaped contact plate. The platform can adapt to stable contact of diversified contact surfaces (flat / non-flat / corrugated wall surfaces, stand columns and the like), and the scene adaptation cost is reduced.

Disclosed are specialized airframe structures for mission-adaptable unmanned aerial vehicles (UAVs) that are fabricated by rapid, low-cost additive manufacturing techniques. In some embodiments, an integral fastening system for a mission-adaptable aerial vehicle includes a first airframe section, a second airframe section, and a bayonet mount system that comprises one or more passageways produced on a first end region of the first airframe section to include a first channel and second channel, and one or more protrusions produced on a second end region of the second airframe section, such that, when the first and second airframe sections being assembled, the one or more protrusions are first aligned with an entry region of the first channel to be translated and then aligned with the second channel of the one or more passageways to be rotated to securely connect the first and second airframe sections together.

A mounting structure 200 has a first component 201 with a body with a connection structure 205 to couple it to an aerial vehicle 203, and an interface 207 for coupling to a second component 209 which

The embodiments relate to an air mobility structure, the air mobility structure comprising an upper module allowing the air mobility structure to fly and a lower module that can couple with the upper module, wherein the upper module comprises: a body comprising a fuselage including a seating space and an entrance, and wings connected to the fuselage; a flight module for generating lift for the air mobility structure to fly; and a control unit for controlling the flight module, and the lower module comprises: an energy module for supplying driving energy to the flight module so that lift is generated for the air mobility structure to fly; and one or more application modules for executing preset functions.

- AIRCRAFT SAFETY DEVICE - This aircraft safety device transforms the fuselage into an emergency module in the event of damage [Fig.42]. There are three parts, the fuselage, the wings, and the elevator, [Fig.26]. They can be separated from each other, each of its parts grouping sub-devices which ensure this transition. The first part of this assembly, (the fuselage) represents the emergency module. This one has a Sigma device [Fig.30] which is composed of two ailerons. They have the particularity of blending into the mass of the wings of the aircraft of part 2 [Fig.28][Fig.29]. This emergency module integrates an Alpha device, [Fig.7] of two stabilizers which have the role of relay elevator. In the fuselage, there is a Theta device [Fig.30] composed of four fans distributed judiciously on each side of it hidden inside a dedicated compartment; and whose main function is to slow the fall of this rescue module, if necessary, but we can attribute other possibilities to it. This rescue module includes an Iota device [Fig.38][Fig.40], hatches which serve as landing gear, to cushion the impact on the ground and guarantee a horizontal plane whatever the type of terrain encountered. The second part of this assembly serves as a reception base for the rescue module. As for the third part of this assembly (the elevator) [Fig.41] [Fig.53] it is a drone whose mission is to tow this rescue module or to participate in rescue searches. FIGURE FOR ABBREVIATION: [Fig.3].

An aircraft (100), an aircraft system (1000), a battery (600), a movable platform. The aircraft (100) can communicate with external equipment through the first communication device (200) and / or the second communication device (300), the aircraft (100) can access a first communication network through the first communication device (200) and can access a second communication network through the second communication device (300), and the first communication network is different from the second communication network; the aircraft (100) comprises a containing space (120) arranged in the aircraft shell (110), at least part of the first communication device (200) can be arranged in the containing space (120) in a quick-release mode, and therefore the first communication device (200) does not have a large influence on the appearance of the aircraft (100), the aesthetic feeling of the appearance of the aircraft (100) can be guaranteed, and the influence of the first communication device (200) on the flight performance of the aircraft can be reduced.

A repair device and method for repairing damage around the leading edge of a wind turbine blade (20) are provided. The repair device includes a robotic maintenance device (40) and an unmanned aerial vehicle (UAV) (62) that can move the maintenance device (40) between a storage position and an operation position, the former being mounted on a blade (20) of the wind turbine (10). The UAV (62) hovers and remains connected to the maintenance device (40) during operations at the blade (20) to minimize a total operational downtime needed to conduct the repair actions. The UAV (62) is secured to the maintenance device (40) by at least one support line (68) that carries the weight load of the maintenance device (40) and at least two control lines (72) that prevent undesired rotations of the maintenance device (40), thereby improving precision and accuracy of UAV-driven movements of the maintenance device (40). A transport container (24) may also be provided to define the storage position, the transport container (24) including an elongated slot (70) for guiding movement of the lines (68, 72) and the maintenance device (40) during movements into and out of a storage space within the container (24).

The invention relates to a multi-architecture modular drone system, and discloses a modular aerial vehicle system having a fuselage module configured to couple with a plurality of lift generating modules. A modular aerial vehicle system may include a fuselage module and a lift generating module. The fuselage module may include a first attachment interface, an avionics system operably coupled with a power unit (e.g., via an ESC), and a communication system operably coupled with a flight controller. The lift generating module may include a second attachment interface and a plurality of propellers. The fuselage module may be configured to be removably coupled with the lift generating module via the first and second attachment interfaces. The first and second attachment interfaces may include (1) a plurality of electrical contacts to facilitate electrical communication between the fuselage module and the lift generating module, and / or (2) one or more retention devices to structurally couple the lift generating module with the fuselage module.

The robot includes an image sensor that captures the environment of the storage site. The robot navigates the storage site by visually recognizing regularly shaped structures using various object detection and image segmentation techniques. In response to receiving a target location of the storage site, the robot moves along a path to the target location. The robot receives images as the robot moves along the path. The robot determines its current position along the path by analyzing the images captured by the image sensor and tracking the number of regularly shaped structures in the storage site that the robot has passed. The regularly shaped structures may be racks, horizontal bars on racks, and vertical bars on racks. The robot can determine the target location by counting the number of rows and columns that the robot has passed.

A motor vehicle hub station configured to function as a terminal for an air motor vehicle, a ground motor vehicle, or a water motor vehicle, the motor vehicle hub station including a plurality of levels by a combination of a water surface level connected to a water surface and having an entrance for a water motor vehicle, a port level having a takeoff and landing field for an air motor vehicle, or a ground level configured to be connected to a ground and having an entrance for a ground motor vehicle, wherein a lift passage having an internal space extending in an up-down direction of the motor vehicle hub station is provided between the levels, the internal space is connected to each of the water surface level, the port level, and the ground level, and the air motor vehicle, the ground motor vehicle, or the water motor vehicle is lifted or lowered through the internal space.

A modular VTOL drone aircraft can include a primary processor, a plurality of propellers, one or more line replacement modules (“LRMs”) and one or more line replacement units (“LRUs”). LRMs can include a fuselage, a center wing, two booms, two outer wings, two vertical tails, a horizontal tail, and / or an engine. LRUs can include an avionics module, a radio communications assembly, a sensor package assembly, an ISR assembly, and / or a deployable payload assembly. Each LRM and LRU can be self-contained and removably attached to the remainder of the VTOL drone. Each LRM can be readily interchanged with another similar LRM, which can be of a different size. LRM interfaces can include a blind mate electric connector and / or a floating connector.

A line assembly for installation in an aircraft fuselage comprises a first line section having a first diameter, at least one second line section having a second diameter, a set of first line brackets, and a set of second line brackets, wherein the first line brackets comprise a first receiving space designed for holding the first line section and a first support portion for attaching the first line brackets to a structural part of the fuselage, wherein the second line brackets comprise a second receiving space designed for holding the at least one second line section and a second support portion for attaching the second line brackets to the first line section, wherein at least one second line section comprises a higher flexibility than the first line section, and wherein the at least one second line section is attached to the first line section through a plurality of second line brackets that are arranged at a distance to and are independent from the first line brackets.

An unmanned aerial vehicle (UAV) includes a fuselage assembly, a further portion that attaches with the fuselage assembly, and a propulsion assembly coupled with the further portion. The propulsion assembly is constructed and arranged to provide propulsion for the UAV. The fuselage assembly includes a fuselage body constructed and arranged to operate as a forward portion of the UAV, lateral stringers coupled with the fuselage body and extending laterally along the fuselage body, and a set of interchangeable covers to cover at least a portion of a payload bay opening defined by the fuselage body. Utilizing such a fuselage assembly offers a highly configurable mounting architecture to accommodate a wide variety of payloads.