Abstract: A system architecture for operation of aircraft flaps. The system architecture includes a first pair of motor drive units, the first pair comprising a first motor drive unit (MD1) and a second motor drive unit (MD3), and a second pair of motor drive units, the second pair comprising a third motor drive unit (MD2) and a fourth motor drive unit (MD4). The system further includes a first plurality of switches connected between the first motor drive unit (MD1) and the second motor drive unit (MD3), the first plurality of switches configured to operate a first electric motor and a second electric motor, and a second plurality of switches connected between the third motor drive unit (MD2) and the fourth motor drive unit (MD4), the second plurality of switches configured to operate a third electric motor and a fourth electric motor.

Abstract: A base station is disclosed for use with an unmanned aerial vehicle (UAV). The base station includes: an enclosure; a cradle that is configured to charge a power source of the UAV during docking with the base station; and a temperature control system that is connected to the cradle and which is configured to vary temperature of the power source of the UAV. The temperature control system includes: a thermoelectric conditioner (TEC); a first air circuit that is thermally connected to the TEC and which is configured to regulate temperature of the TEC; and a second air circuit that is thermally connected to the TEC such that the TEC is located between the first air circuit and the second air circuit. The second air circuit is configured to direct air across the cradle to thereby heat or cool the power source of the UAV when docked with the base station.

Abstract: A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting of a strut used to connect a structural element to a payload. The end fitting may include outer and inner cylindrical hubs, with a space between the outer and inner cylindrical hub at least partially filled with a viscoelastic material. In a further example, the passively damped mechanical system includes legs used to connect a structural element to a bracket configured to support a payload. Each leg may include a hollow interior having a lattice structure to add strength and a viscoelastic material to provide passive damping.

Abstract: In some embodiments, systems are provided to determine distances to one or more objects, and comprise an image capture system; an angular movement system; an illumination source providing illumination having a time varying amplitude; and a range measurement circuit configured to: obtain, based on at least one of measured and induced LOS angular displacement changes relative to the image capture system, a set of candidate point-spread-functions (PSFs) corresponding to different possible ranges; deconvolve, using the candidate PSFs, at least a region of interest (ROI) in an evaluation image to obtain at least a set of deconvolved ROIs of the evaluation image, each corresponding to one of the candidate PSFs; identify a first candidate PSF that produces a deconvolved ROI resulting in a determined artifact power that is lower than a corresponding artifact power determined from the other candidate PSFs; and determine a distance corresponding to the first candidate PSF.

Abstract: Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.

Abstract: A release system for the release of satellites from a launch vehicle is provided that includes: (i) a torsion bar, having a first end which is fixed by means of support means to a launch vehicle and is locked in rotation around a longitudinal axis of the torsion bar, and a second end which is connected by means of hinge means to the launch vehicle and is free to rotate around the longitudinal axis; (ii) at least one launch arm extending perpendicularly from the torsion bar and comprising (a) a torsion lever having a first end which is fixed to the torsion bar in an integral manner, and (b) a guide having a first end connected to a second end of the torsion lever, and a second free end; (iii) at least one slider which is fixed in an integral manner to a satellite to be launched and arranged to engage the guide in a sliding manner; and (iv) and a limit stop element designed to act upon the torsion lever to stop the rotation of the launch arm around the longitudinal axis.

Abstract: A surface assembly and related method of constructing a surface assembly are used as part of a landing platform. The surface assembly includes a modular structure having an upper surface with a plurality of discrete elements. Each discrete element has a body of metal material defining at least one anchor aperture for receiving a hook or like anchor device for anchoring a helicopter or other powered light aircraft to the surface assembly. The surface assembly is configured to define an array of the plurality of discrete elements in which at least two of the anchor apertures are provided side-by-side. The body of each discrete element has a periphery, and each anchor aperture of the array is inboard of the periphery of a respective body of a discrete element in the array.

Abstract: An internal cabin of a vehicle includes a vehicle control area. A first door is coupled to the vehicle control area. The first door is moveable between a first open position and a first closed position. An aisle extends between the vehicle control area and a passenger seating area. A forward section of the aisle is disposed between a first monument and a second monument. A second door is disposed within the aisle between the first monument and the second monument. The second door is moveable between a second open position and a second closed position. A privacy vestibule is defined between the second door in the second closed position, the first monument, the second monument, and the vehicle control area.

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: 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: 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: 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: An unmanned aerial vehicle, having a main body comprising at least an elongate backbone with a forward end piece and a rearward end piece. The end pieces are wider than the backbone and comprise coupling facilities for respective rotor arms, each said rotor arm configured for supporting motor and propeller assemblies. The unmanned aerial vehicle further comprises a pair of elongated batteries. The end pieces and at least a portion of the backbone form receptacles on both sides of the backbone for releasably receiving respective electric batteries, wherein the batteries, backbone and end pieces form an elongate and substantially rectangular body assembly.

Abstract: Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

Abstract: A super first-class cabin includes a monitor disposed in the ceiling structure, a controller to render images on the monitor, and cameras to capture real-time streaming environmental images and renders them on the monitor. At the passenger's request, or when the passenger reclines, the controller may render a selection of mood affective images, for example to promote sleep if desired. Such mood affective images may be organized into a schedule associated with phases of flight to gently wake the passenger and prepare them for the end of the flight. The monitor may be employed to reduce the effects of flight-base time-disassociation by varying a daylight color scheme over the course of long flights, simulating a day/night routine to align the time of day at the origin of the flight with the time of day at the destination.

Abstract: Technology is disclosed herein for deploying stacked spacecraft. When the spacecraft are stacked corresponding z-axis magnetic torque rods of the spacecraft will align with each other along a z-axis. Thus, collectively the stack of spacecraft have one or more sets of magnetic torque rods aligned with the z-axis. Just prior to deploying the spacecraft the one or more sets of magnetic torque rods are operated to hold the stack of spacecraft together. For example, the north magnetic pole of the magnetic torque rod in one spacecraft may face the south magnetic pole of the magnetic torque rod in an adjacent spacecraft. To deploy the top spacecraft, the polarity of the z-axis magnetic torque rod(s) in the top spacecraft is/are reversed. After the spacecraft is clear of the stack the magnetic torque rod(s) in the deployed spacecraft may be de-activated. Then another spacecraft may be deployed in a similar manner.

Abstract: The present technology is directed to thrusting rails for launch vehicles, and associated systems and methods. Certain embodiments of the thrusting rails can include a first rail housing portion having a cavity and a second rail housing portion having a projection positioned at least partially within the cavity. The rails can include a bellows positioned within the cavity and an elongated tube positioned within the bellows. The elongated tube can include a vent opening in a lateral wall of the elongated tube. A shield can be positioned between the vent opening at the bellows and a sleeve can be positioned within the elongated tube. The sleeve can be constructed from a fibrous material and positioned to retain an ordnance within the elongated tube.

Abstract: Systems and methods for providing a spacecraft are provided. The spacecraft includes a main structural member that extends between end panels of the spacecraft, and that defines a first interior volume. A fuel tank is disposed within and conforms to at least a portion of the first interior volume. The fuel tank can itself include a central void that defines a second interior volume. The main structural member and the fuel tank can be cylindrical. Payload items or components of the spacecraft can be disposed within the second interior volume.