Abstract: An electromagnetic lock release mechanism includes: a frame, an ejection unit, a satellite unit, a lock release unit, and a lock release drive unit; the ejection unit includes an ejection spring, an ejection jack, and a spring sleeve; the lock release unit includes a locking pin, a locking slider, an unlocking spring, and a base; the lock release drive unit includes an electromagnet limit nut, an electromagnet moving core, and an electromagnet. Advantages of the present invention are as follows. The present invention is a point positioning lock release mechanism that can be used to separate micro-satellites and rockets and repeatedly tested, which provides reliable locking and separating of satellites and rockets in a complex mechanical environment, and can be repeatedly tested on the ground. The separation is entirely a mechanism action without pollution.

Abstract: An embodiment of the present disclosure relates to an unmanned flying robotic object that contains a wheeled mechanism that encircles its spherical exoskeleton. This feature allows the flying spherical vehicle to readily transform into a ground maneuverable vehicle. A robotic motor with differential speed capability is used to operate each wheel to provide effective ground maneuverability. There are examples provided herein of wheel configurations suitable for use with an embodiment. One is the straight- (or parallel) wheel design, and another is tilted-wheel design as are illustrated and discussed hereinafter. One embodiment of an unmanned flying robotic object taught herein is foldable.

Abstract: A cycloidal rotor air vehicle includes an airframe, a first cycloidal rotor assembly supported by the airframe and configured to rotate about a first axis of rotation relative to the airframe, the first cycloidal rotor assembly including a blade having a longitudinal axis oriented parallel to the first axis of rotation, a first motor configured to rotate the first cycloidal rotor assembly about the first axis of rotation, a first servo coupled to the blade of the first cycloidal rotor assembly and configured to adjust the pitch of the blade, and a control system supported on the airframe and configured to control the operation of the first motor and the first servo.

Abstract: A device for catching and launching a guided UAV, the device comprises a supporting post, a horizontal shaft mounted on the post, and a lever is mounted on the horizontal shaft and can make a full revolution around a horizontal axis within a vertical plane, the lever is equipped with an engagement/disengagement device a means for interaction with the UAV catching device and an optical member, preferably arranged on the lever, for determining a location of the lever interaction means by an optical guidance system of the UAV. The lever comprises two coaxial portions, one is the engagement/disengagement device, and the second is a bar, wherein one end of the bar is coupled to the horizontal shaft, while another end thereof is connected to the engagement/disengagement device.

Abstract: A hybrid unmanned aerial vehicle (10) is provided which comprises a multicopter frame (14) having a plurality of operable multicopter propulsion units (22) thereon, and an airframe body (16) which is connected to the multicopter frame (14). There is also a pair of wings (34) positioned on opposite sides of the airframe body (16) and a wing control means for manipulating the pair of wings (34) with respect to the airframe body (16) to alter an angle-of-attack of the pair of wings (34). In a first wing condition, the angle-of-attack of the pair of wings (34) is alterable with respect to a relative airflow so as to produce zero lift, and, in a second wing condition, the angle-of-attack of the pair of wings (34) is alterable with respect to the relative airflow so as to produce an optimum or near optimum lift. A method of improving the manoeuvrability of the hybrid unmanned aerial vehicle (10) is also provided, as is a method of improving the operational range of unmanned aerial vehicles.

Abstract: In one embodiment, a drone is provided with several inflatable tubes that each connect a propeller component to a body of the drone. In order to increase the handling of the drone, a patch is placed on the top surface of each inflatable tube that includes some number of shape memory alloy wires. The shape memory alloy wires shrink and become rigid when an electric current is applied to them. The optimal locations on each tube to place the patches, and the shape of the patches, is determined using a topology optimization. Later, the wires in the patches can be selectively activated or deactivated by an operating entity to provide an additional means to control the drone. Additionally, the drone is equipped with several landing arms which may include a shape memory alloy torsion coil spring to help the arm deployment during landing.

Abstract: A buoyancy method for deploying a plurality of floats of a buoyancy system of an aircraft. The plurality of floats comprises a plurality of main floats and a plurality of secondary floats that are folded in flight. The method comprises a step of deploying the main floats in flight prior to ditching, and a step of deploying the secondary floats after ditching.

Abstract: Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

Abstract: A drogue parachute assembly may comprise a canopy housing and a mortar. The mortar may include an inner mortar tube and an outer mortar tube configured to telescope relative to the inner mortar tube. The canopy housing may be coupled to the outer mortar tube. A guide plate may be configured to contact an interface surface of the canopy housing and pivot the mortar about a pivot joint.

Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).

Abstract: A secondary payload bridge for a payload adapter is disclosed and includes a body portion, plurality of payload ports, and a secondary payload port. The plurality of attachment points are connected to the body portion of the secondary payload bridge. The plurality of attachment points are configured to removably attach the secondary payload bridge to the payload adapter to allow for clockable positioning of the secondary payload bridge around a circumference of the payload adapter. The secondary payload port is connected to the body portion. The secondary payload port is configured to releasably attach to a corresponding secondary payload.

Abstract: The invention discloses a propeller-driven helicopter or airplane which comprises a fuselage and a propeller comprising a plurality of blades, wherein a plurality of pressure pipes are uniformly distributed between windward sides and leeward sides of the blades; a plurality of first inlets are formed in the windward sides and are communicated with outside via first channels in the blades and second outlets at tails of the blades; a high-pressure fluid of a low-speed fluid layer formed when a fluid flows through the leeward sides in a widthwise direction flows towards a low-pressure fluid of a high-speed fluid layer formed when the fluid flows through the first inlets, the first channels and the second outlets; and an upward pressure generated by the high-pressure fluid is opposite to a downward pressure generated by an external fluid above the windward sides, so that a fluid pressure above the propeller is decreased.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: An assembly for manual control of an HSTA for controlling the position of a moveable surface, the assembly comprising a user-operated manual control element (1?) e.g. a trim wheel in the cockpit, a first motor and a first resolver connected to the manual control element and a second motor and a second resolver arranged to communicate with the first motor and the first resolver and to cause corresponding movement of the actuator, in use.

Abstract: The invention relates to a separation device for a spacecraft or launcher. The separation device includes an inner housing divided into at least two portions locked to each other by a locking device in a locking position. The locking device is arranged to move between a locking position and a releasing position. The separation device includes an initiator including means for providing high pressure fluid to an expansion chamber when the separation device is switched from a locked state to a released state. The high pressure fluid in an expansion chamber moves the locking device from the locking position to the releasing position when the separation device is switched from the locked state to the released state. The separation device comprises a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state.

Abstract: A motor mounted on a drone includes a rotor including a propeller mounting portion with a propeller detachably attached, the rotor being rotatable about a central axis, a stator radially facing the rotor with a gap therebetween, and an auto-balancer capable of automatically correcting dynamic balance of the rotor.

Abstract: A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.

Abstract: Embodiments herein describe mitigating flexible modes in an airframe of an aircraft by operating a battery for the aircraft as a tuned mass damper. One embodiment comprises an Unmanned Aerial Vehicle (UAV). The UAV includes a flexible airframe, a plurality of propulsors coupled to the flexible airframe that generate thrust for the UAV, a battery that provides electrical power for the plurality of propulsors, and a suspension system that suspends the battery from the flexible airframe and operates the mass of the battery as a tuned mass damper to dampen flexible modes generated in the flexible airframe during flight.

Abstract: Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

Abstract: An air and land multimodal vehicle comprises a frame, a propeller engine attached to a first location of the frame supplying power and torque to a propeller, a ground engine attached to a second location of the frame supplying power and torque to one or more ground traction elements, and a flexible wing releasably connectable to the frame, wherein the propeller engine is vertically and horizontally spaced from the ground engine.