Abstract: A system includes a surface, an actuator, and processing circuitry. The surface includes one or more non-actuating zones and one or more actuatable zones. The actuator is configured to a flow property of a fluid that flows over the one or more actuatable zones of the surface. The processing circuitry is configured to obtain a value of a parameter of the fluid that flows over the surface, and operate the actuator to adjust the flow property of the fluid that flows over the one or more actuatable zones based on the value of the parameter of the fluid.

Abstract: An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.

Abstract: In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.

Abstract: A linking member between a first and a second structural member of a fuselage of an aircraft allowing improved dissipation of stresses. The linking member has a first part made of a solid structure and at least one second part made of a lattice structure. The first part made of the solid structure is configured to dissipate static stresses and to withstand fatigue up to a predetermined maximum stress and fatigue threshold. This configuration allows improved dissipation of the stresses exerted on the linking member.

Abstract: The left and right main landing gears on an aircraft are normally controlled by separate hydraulic power packs (HPP). Each HPP is sized for the load of the respective main landing gear. During failure of one of the HPP, a backup valve actuates to allow the other HPP to operate both main landing gears. With the backup valve actuated, the pump of the functioning HPP is coupled to the reservoirs of both HPPs and to the load paths to both main landing gears.

Abstract: A device includes hauling means for the movement of a payload while suspended from one or more lines. The or each line is suspended or suspendable from one end, the hauling means being provided at or in the region of the other end of the line/s and at which end the payload is situated in use.

Abstract: A rotatable thruster aircraft includes an airframe, which includes an aircraft body and a fixed wing; rotatable thruster assemblies, each including first and second thrusters that provide rotation via differential thrust; a rotatable shaft with torsional flexibility; an inertial measurement unit; optionally vertical lift thrusters; and an aircraft control unit, including a processor, a non-transitory memory, an input/output component, and a power manager that controls specific power applied to the thrusters.

Abstract: An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

Abstract: A method according to certain embodiments generally involves operating a system including an unmanned aerial vehicle (UAV) and a base station. The base station includes a nest including an upper opening having an upper opening diameter and a lower opening having a lower opening diameter less than the upper opening diameter. The lower opening is accessible from within the base station. The method generally includes landing the UAV within the nest such that a portion of the UAV is accessible via the lower opening, releasably attaching a load to the UAV, and operating the UAV to deliver the load to a destination.

Abstract: An unmanned aerial vehicle (UAV) storage and launch system, including: a UAV pod having an interior; and a telescoping UAV landing surface disposed in the interior of the UAV pod; where the telescoping UAV landing surface may translate up toward a top opening of the UAV pod, translate down into an interior of the UAV pod, or rotate relative to the UAV pod.

Abstract: The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

Abstract: An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a control system, and at least one rotor. The chassis includes a first battery compartment configured to receive sliding insertion of a first battery, and a second battery compartment configured to receive sliding insertion of a second battery. The control system is operable to receive power from the first battery and the second battery when the first battery is received in the first battery compartment and the second battery is received in the second battery compartment. The at least one rotor is operable to generate lift under control of the control system when both the first battery and the second battery are installed to the chassis. The control system is configured to remain at least partially active under power supplied by the first battery when the second battery is removed from the second battery compartment.

Abstract: A method is provided for operating a hybrid-electric propulsion system having a first engine, a second engine, a first electric machine coupled to the first engine, and a second electric machine coupled to one of the first engine or the second engine. The method includes: receiving data indicative of a first engine operating parameter, a second engine operating parameter, or both; determining a first engine operating parameter margin, a second parameter operating margin, or both; determining a load share for the first engine, the second engine, or both, or between the first engine and the second engine based on the first engine operating parameter margin, the second engine operating parameter margin, or both; and transferring a first amount of power to or from the first electric machine and a second amount of power to or from the second electric machine in response to the determined load share.

Abstract: A base station for an unmanned aerial vehicle (UAV) is disclosed that includes: an enclosure; a slide mechanism; and a cradle. The slide mechanism is repositionable between a retracted and extended positions and is secured in relation to the enclosure via first and second mounts, which are located between the slide mechanism and the enclosure so as to separate the slide mechanism from the enclosure and thereby reduce vibration of the slide mechanism during repositioning between the retracted and extended positions. The cradle is connected to the slide mechanism and is configured for docking with the UAV such that the UAV is movable into and out of the enclosure during repositioning of the slide mechanism between the retracted and extended positions.

Abstract: An on-orbit servicing spacecraft includes an engagement system to engage a space vehicle or object to be serviced or tugged, so as to form a space system, and an electronic reaction control system to cause the spacecraft to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft to carry out given maneuvers.

Abstract: An easy extention of a telescopic rod. The telescopic rod extends in the axial direction by a gas forcibly fed to the inside and is provided with a posture control means.

Abstract: A method for collecting orbital debris comprises detecting a piece of orbital debris approaching a front end of a debris collecting apparatus. An electromagnet is activated and acts to slow or stop rotation of the orbital debris and to attract the orbital debris to the collecting zone. The orbital debris is secured and the orbit of the debris collecting apparatus is changed to a decaying orbit in order to move the debris collecting apparatus out of LEO and closer to Earth. The debris collecting apparatus remains in the decaying orbit until a predetermined altitude is reached at which point the orbital debris is released from the collecting zone to continue along the decaying orbit such that it enters Earth's atmosphere. The debris collecting apparatus is then moved out of the decaying orbit and returned to a stable LEO.

Abstract: The present disclosure provides a device for detecting carbon emission of a passive house. The device for detecting carbon emission of a passive house is arranged on a metal rain cap at a top of a chimney. The device for detecting carbon emission of a passive house includes an unmanned aerial vehicle, a guide assembly, and two landing gear assemblies. The two landing gear assemblies are arranged at a bottom of the unmanned aerial vehicle, the guide assembly is arranged at a bottom of the two landing gear assemblies, and the guide assembly includes two split assemblies. The two split assemblies correspond one-to-one to the two landing gear assemblies, and the split assemblies are in linked connection to the landing gear assemblies. In the device for detecting carbon emission of a passive house, the unmanned aerial vehicle, the guide assembly and the two landing gear assemblies are arranged to cooperate with each other.

Abstract: A base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: an enclosure; a slide mechanism that is connected to the enclosure and which is repositionable between a retracted position and an extended position; a cradle that is connected to the slide mechanism and which is configured for docking with the UAV such that the UAV is movable into and out of the enclosure during repositioning of the slide mechanism between the retracted position and the extended position; and a charging hub that is connected to the slide mechanism and which is configured for electrical connection to a power source of the UAV to charge the power source.

Abstract: A device and a method for introducing a drone to an area of interest are presented. The delivery system may include a housing, a drone, either a timer or a receiver, a lock mechanism, and a biasing mechanism. The housing further includes a pair of parts with or without subparts. At least one sensor is attached to the drone. The timer or the receiver is secured to the housing and communicable with the lock mechanism to control function thereof. The lock mechanism is adapted to releasably secure the parts or the subparts. The drone is enclosed within the housing in a CLOSED configuration when the lock mechanism is locked. The biasing mechanism separates the parts or the subparts to an OPEN configuration when the lock mechanism is unlocked. The drone is introducible to the area of interest in the CLOSED configuration and separable from the housing in the OPEN configuration.