Abstract: A landing gear system for an aircraft is presented. The landing gear system comprises a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches; and a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.

Abstract: Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

Abstract: A space launch system includes a launch track and an elevating platform for horizontally launching aerospace vehicles at a takeoff velocity. The launch track includes a first portion horizontally oriented with respect to the horizon, a second portion positioned after the first portion and horizontally oriented with respect to the horizon, and a third curved transition portion disposed between the first portion and the second portion. The elevating platform is coupled to the launch track and is configured to receive and position an aerospace vehicle upon the launch track. A magnetic accelerator is disposed along the launch track for propelling the aerospace vehicle down the launch track to reach the takeoff velocity. The magnetic accelerator includes magnetic levitation trains, each comprising a respective plurality of carriers that couple to the aerospace vehicle.

Abstract: A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

Abstract: A method for the flying of a vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

Abstract: A flight propulsion system for Vertical Take-Off and Landing (VTOL) and Short Take-Off and Landing (STOL) aircraft, having a two cyclorotors, installed in the front and rear portions of a pair-wings mechanism involving top wing and bottom wing, three degree-of-freedom DOF adjusting mechanism for pair-wings, a dielectric barrier discharge (DBD) plasma actuators, a bar mechanism for pitching oscillation and rotation speed controls and rear cyclorotor, a yawing mechanism for rear cyclorotor, all on each side of the flight vehicle. This propulsion system is particularly useful for VTOL aircraft. The main features are: high controllability and manoeuvrability, low noise and environmental pollutions, VTOL, STOL, hover state flights, marine and ground take-off and landing, high safety, suitable for different aircraft scales and for different missions and purposes, instant altering the flight direction.

Abstract: A method of flight control including having a vertical takeoff and landing aerial vehicle that has a plurality of lift propellers disposed on two linear support pieces, and there are two vertical stabilizers disposed at the rear of the two linear support pieces. A rotating shaft of each lift propeller from among the multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the aerial vehicle perpendicular to a horizontal plane of the aerial vehicle. The aerial vehicle of the present disclosure improves the heading axis control capacity of the aerial vehicle and reduces the restriction to the design size of the aerial vehicle.

Abstract: A vibratory motion reduction system for a pylon assembly includes an inner member having an opening extending therein that receives a first end of the pylon assembly, an outer member moveably attached to the inner member, a tuning mass attached to the inner member and the outer member such that a vibratory motion of the pylon assembly accelerates the tuning mass, a spring member that couples to a second end of the pylon assembly, and the spring member and the tuning mass reduce the vibratory motion of the pylon assembly.

Abstract: A main body of an unmanned vehicle is provided. The main body comprises a propulsion-receiving module having a mount point for removably mounting a propulsion source, a payload-receiving module having a mount point for removably mounting a payload, and a damper interposed between the payload-receiving module and the propulsion-receiving module to inhibit transmission of vibrations from the propulsion-receiving module to the payload-receiving module when the payload-receiving module and the propulsion-receiving module are in mechanical communication.

Abstract: An unmanned aerial vehicle is provided, including an airframe including a fuselage and at least one stowable wing. The unmanned aerial vehicle can further include a radar panel positioned on the fuselage such that the radar panel is angled downward and extends longitudinally along a ventral region of the fuselage. The unmanned aerial vehicle can further include a drop-away rocket engine that is configured to detachably mount to the airframe adjacent the radar panel.

Abstract: The present disclosure concerns an electric aircraft propulsion system. Example embodiments include an aircraft propulsion system (200) comprising: a fan (213) mounted on a central shaft (214); a first electric motor (215) mounted on the central shaft (214) and arranged to drive rotation of the fan (213) via the central shaft; and a second electric motor (216) arranged to drive rotation of the fan (213) via the central shaft (214), wherein the second electric motor (216) is coaxially mounted downstream of the first electric motor (215) and an outer diameter (D2) of the second electric motor (216) is smaller than an outer diameter (D1) of the first electric motor (215).

Abstract: Various mechanisms and methods for altering sound output from an unmanned aerial vehicle (UAV) are disclosed. The UAV can have a drive system comprising a motor or a plurality of motors, and a processor operatively coupled to the drive system to control operation of the drive system. The UAV can further have a plurality of propellers that are rotatably drivable by the drive system, the plurality of propellers having physical characteristics such that, when drivingly rotated to maintain the UAV in stable flight, a first of the plurality of propellers emits a first note, and a second of the plurality of propellers emits a second, different note, a combination of the first and second notes producing a consonant sound.

Abstract: A tail for a projectile includes a body having a longitudinal axis. A steering assembly is secured to the body. The steering assembly includes a flap movable from a first position in which the flap does not extend radially beyond the body to a second position in which the flap extends radially beyond the body and at an angle relative to the longitudinal axis, and a flap release mechanism. A projectile including a tail according to the present disclosure is also provided.

Abstract: The disclosure provides a fixed-wing UAV, with two pull propellers or two push propellers arranged parallel to each other and providing thrust for the UAV. Wherein the thrust ratio provided by the two pull propellers or the two push propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV.

Abstract: A vertical takeoff and landing unmanned aerial vehicle and a cooling system for the unmanned aerial vehicle. Heat dissipation in an arm of an unmanned aerial vehicle is achieved by providing a forward-facing opening at the front end of each of a left linear support and a right linear support of the unmanned aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

Abstract: Systems and method for active vibration control on an aircraft. An active vibration control system (AVCS) is configured for an aircraft having an aircraft structure and a gun. The AVCS includes at least one control sensor on the aircraft, at least one force generator on the aircraft, and at least one controller in electronic communication with the sensor and the force generator. The controller is configured for determining, using the at least one control sensor, force generating commands for controlling vibrations acting on the aircraft structure, sending the force generating commands to the at least one force generator, causing the at least one force generator to produce a vibration canceling force, determining that the gun is firing, and in response to determining that the gun is firing, determining different force generating commands and sending the different force generating commands to the at least one force generator.

Abstract: A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

Abstract: A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.

Abstract: A rotorcraft includes a body and a plurality of rotary-wing parts. The body has a front-end portion, a rear-end portion, two side portions, and a reference plane passing through the front-end portion, the rear-end portion, and the two side portions. The plurality of rotary-wing parts are disposed to the body. Each of the rotary-wing parts includes at least one blade and a shaft coupled to the at least one blade. The at least one blade is rotated around an axis of the shaft. An angle between the axis of the shaft and a normal line of the reference plane is between 5 and 30 degrees. The rotorcraft can provide additional lift force, to help reduce the weight of the rotorcraft.

Abstract: An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.