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 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: 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 (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: 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: 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: 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: 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: 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: 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: An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

Abstract: A method for extracting a rescue subject from a surface position includes lowering a rescue pod having an enclosed compartment with a door from an aircraft, the rescue pod having a parachute and a control system, the rescue pod connected by a tether to a winch in the aircraft, controllably releasing the tether from the winch while maneuvering the aircraft into an orbit at altitude, diameter and airspeed, creating a gravity well in which the tether describes a spiral configuration with the pod descending along a vertical centerline, lowering the pod to the surface position, loading the rescue subject into the enclosed compartment, and lifting the rescue pod from the surface position by retrieving the tether with the winch or altering the path and speed of the aircraft, in a manner to gradually increase tension in the tether lifting the rescue pod from the ground point.

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.

Abstract: An aircraft includes a fuselage, a main entry door with an associated passenger loading zone, an auxiliary power unit (APU) in the fuselage, and an APU inlet assembly. The APU inlet assembly has an inlet duct, and inlet door, and means for redirecting sound waves coupled to or integrated with an interior side of the inlet door. The inlet duct has a first end coupled to the APU, and a second end associated with the inlet door. The inlet door moves between a closed position and an open position. The means for redirecting sound waves is positioned at a particular location on the interior side of the inlet door, and includes certain acoustic features and characteristics. The particular location and the acoustic features and characteristics cooperate to redirect sound waves generated by the APU away from the passenger loading zone when the inlet door is in the open position.

Abstract: A multiple hold-down and release device for spacecraft includes a central structure including a central section with a cylindrical inner hole, an inner axial shaft insertable into the inner hole. A release bolt aligns with the inner axial shaft. A main bushing is partially arranged inside the inner hole and axially guided by guiding bushings on the main bushing and the inner hole. The main bushing includes a protrusion and internal retainer spring. Arms protruding from the central section are axially preloaded by a pusher opposite the central section. Connecting levers each connect to the end of the corresponding arm by the pusher. Hold-down assemblies on the periphery of the device each include a hold-down support and a fastener with conical contact surfaces, a torsion spring around a torsion spring shaft, and articulated with the corresponding hold-down support by the corresponding torsion spring shaft.

Abstract: Flying body including body portion and a plurality of propellers radially disposed to be laterally symmetrical from body portion is provided with: a plurality of motors respectively rotating the plurality of propellers; a plurality of power storage packs respectively supplying currents to the plurality of motors; and sub power storage pack connected to the plurality of power storage packs by power wirings, respectively. The same number of motors of the plurality of motors are installed on each of the left and right sides, and the same number of power storage packs of the plurality of power storage packs are installed on each of the left and right sides. Sub power storage pack is installed on a lateral center line of body portion.

Abstract: A vertical take-off and landing aircraft using a hybrid electric propulsion system, according to an embodiment of the present invention, includes: a first control step (S1) of changing a destination when an engine (10), a power generator (20), an engine control unit (30), a power management device (40), a control unit (50), a battery management system (60), a main battery (62) and the like malfunction, thereby causing a normal flight to be difficult; a second control step (S2) of performing control so that an aerial vehicle (1) glides to a point (T), at which same has entered a first space (CEP-1) required for landing or a wider second space (CEP-2) considered safe, and maintains lift and has minimized flight air resistance after passing through the point (T); a third control step (S3) of performing control so that lift is increased and performing control so that a nose cone is switched into an upward direction; and a fourth control step (S4) of performing control so that lift is gradually reduced, and contro

Abstract: A robot includes a housing including a first shell and a second shell and having a first configuration and a second configuration, a rack disposed in an inner cavity of the housing, a telescopic assembly disposed on the rack and connected between the first shell and the second shell, and a rotary wing assembly disposed on the rack and having a folded configuration and a flight configuration. The rotary wing assembly includes: a folding arm with one end rotatably connected to the rack, a rotary wing, and a tilting arm connected between the rotary wing and the folding arm, the tilting arm and the rotary wing are extended to an outside of the housing to be adapted to drive the robot to fly in the flight configuration, and the tilting arm is rotatable relative to the folding arm to adjust a rotation direction of the rotary wing.