An aircraft body and a method of making an aircraft body are provided. In one embodiment, an aircraft body may be molded from a single layer of carbon fiber stock, producing curved sections of single layer molded carbon fiber by molding pliable carbon fiber stock, and heat curing the carbon fiber stock to form a rigid, molded wing section.

The present disclosure relates to the manufacture of battery packs/assemblies and more specifically, the manufacture of battery packs/assemblies for use in aircraft. A lightweight battery assembly with cell compression and/or pressure management system is disclosed herein. The battery assembly can employ a composite battery enclosure impregnated with a plurality of primary fibers that define a direction of the composite battery enclosure's tensile strength. A cell-stack can be positioned in the composite battery enclosure such that the composite battery enclosure applies a predetermined pressure upon the cell-stack to compress the cell-stack in the direction of the composite battery enclosure's tensile strength.

Disclosed herein is a distributed pressure sensor system that quickly detects and counters changes in lift, onset of stall, and flutter. The distributed pressure sensor system may employ a plurality of integrated pressure ports distributed across the span of a wing's leading edge to gather differential pressure measurements. Based on the differential pressure measurements, the distributed pressure sensor system can estimate torque on the fuselage to provide a more efficient estimate for changes in lift, onset of stall, and/or flutter. These estimates may be applied as feedback to the aircraft's control system, thereby eliminating the latency in the existing platform dynamics.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

The present invention is aimed to provide a multi-functional flying platform with a simple structure, which is easy to operate and can achieve the mounting of different functional equipment. It includes rotor arm system and mounting plate (1). A plurality of evenly distributed fixing devices (2) are provided on the mounting plate (1). Mounting plate (1) is fixedly connected to rotor arm (3) of the rotor arm system by fixing device (2). A plurality of mounting positions (4) are provided on the lower side of the mounting plate (1). The present invention can be used in the field of agricultural aviation.

Methods of making a composite structure comprise compression molding a fiber reinforced, thermoplastic component having a web and at least one flange integral with the web; laying up a fiber reinforced, thermoplastic cap; placing the fiber reinforced, thermoplastic cap on the flange; and joining the fiber reinforced, thermoplastic cap with the flange.

An unmanned aircraft system having a flying wing orientation includes an airframe having leading and trailing edges, a two-dimensional thrust array coupled to the leading edge, a power system and a flight control system operable to independently control the speed of each propulsion assembly of the two-dimensional thrust array. In the flying wing orientation, the two-dimensional distributed thrust array provides airspeed control responsive to collectively changing the speed of each propulsion assembly, pitch authority responsive to differentially changing the speed of the propulsion assemblies above the airframe relative to the propulsion assemblies below the airframe, roll authority responsive to differentially changing the speed of the propulsion assemblies rotating clockwise relative to the propulsion assemblies rotating counterclockwise and yaw authority responsive to differentially changing the speed of the propulsion assemblies on a port side of the airframe relative to the propulsion assemblies on a starboard side of the airframe.

Disclosed herein is a distributed pressure sensor system that quickly detects and counters changes in lift, onset of stall, and flutter. The distributed pressure sensor system may employ a plurality of integrated pressure ports distributed across the span of a wing's leading edge to gather differential pressure measurements. Based on the differential pressure measurements, the distributed pressure sensor system can estimate torque on the fuselage to provide a more efficient estimate for changes in lift, onset of stall, and/or flutter. These estimates may be applied as feedback to the aircraft's control system, thereby eliminating the latency in the existing platform dynamics.

Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.

Modular unmanned aerial vehicles (UAVs) are disclosed. A disclosed example UAV includes a fuselage that extends along a longitudinal axis, a wing support frame extending from the fuselage and along a wingspan of the UAV. The wing support frame includes distal ends to support a releasably couplable wing, the releasably couplable wing to extend along the wingspan when coupled to the wing support frame, and a motor boom that extends parallel to the longitudinal axis, the motor boom to support a motor that is oriented to generate lift for the UAV.