Abstract: One-piece molded thermoplastic L-shaped and Z-shaped support brackets are described for supporting wiring and/or tubing. The support brackets will include a lower support flange, a backing flange, and a junction region having a concave inner surface and a convex outer surface which integrally joins the lower support flange and the backing flange to one another at a substantially right angle. The support brackets may be provided with a unitarily molded nut plate boss and a metal threaded nut cylinder which is embedded within and overmolded with the nut plate boss. Alternatively, a wire, cable or tubing mount unitarily formed as a one-piece molded unit with one of the support flanges so as to dependently extend therefrom.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) may comprise a foldable propeller blade with a locking mechanism. Foldable propeller blades may have a stowed configuration and a deployed configuration relative to the UAVDC, and the foldable propeller blades may pivot about a hinge to move between configurations. In the deployed configuration, the foldable propeller may experience forward folding forces acting upon it. The locking mechanism may lock the foldable propeller blade in the deployed configuration. The locking mechanism may keep the foldable propeller locked into place to prevent forward folding tendency.

Abstract: A rotor blade control system includes a main control valve having an inlet for receiving liquid and an outlet for issuing liquid to a rotor pitch change actuator. The main control valve is configured to control flow of liquid from the inlet to the outlet to modify pitch angle of rotor blades. A feathering system has a first conduit in fluid communication with the outlet of the main control valve, a second conduit in fluid communication with the rotor pitch change actuator, and a drain conduit in fluid communication with a liquid return system. The feathering system has a normal operation mode for supplying liquid from the main control valve to the rotor pitch change actuator, and a feathering mode for allowing drainage from the rotor pitch change actuator to the drain conduit across a range of flow rates.

Abstract: A system and a method for a battery power management system for an electric aircraft is disclosed. The system includes at least a flight component of an electric aircraft, at least a battery, wherein the at least a battery is configured power the at least a flight component of the electric aircraft, at least a sensor communicatively connected to the at least a battery and a controller communicatively connected to the at least a sensor. The controller is configured to receive sensor data from the at least a sensor, identify a battery status as a function of the sensor data and a battery threshold, and control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, further comprising reducing a torque to the at least a flight component.

Abstract: Example flap actuation systems and related methods are disclosed herein. An example control surface actuation system includes processor circuitry to cause a first actuator to generate an output to operatively couple the first actuator to a first drive arm; cause a second actuator to generate an output to operatively couple the second actuator to a second drive arm; cause the first actuator and the second actuator to move a control surface when the first actuator and the second actuator are in an operative state; detect the first actuator as in a failed state; and in response to the first actuator being in the failed state, cause first actuator to refrain from generating the output to disrupt the operative coupling between the first actuator and the first drive arm; and cause the second actuator to move the control surface via the first drive arm and the second drive arm.

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 propeller assembly including a shaft having a rotational axis; a plurality of propellers connected to the shaft; means for deploying the plurality of propellers using a centrifugal force generated from a rotation of the shaft, so as to provide vertical thrust during a vertical take-off and landing of the aircraft; and means for restoring the propellers into a stowed configuration.

Abstract: A cyclic pitch angle adjustment apparatus for a rotor or propeller and to a rotorcraft with such a rotor. The cyclic pitch angle adjustment apparatus may include levers that rotate rotor blades around associated pitch axes rods that mechanically link the levers with a bearing such that the rods are movable relative to the central point, the bearing being attached to a central rod that is movable and adapted for adjusting the cyclic pitch angle of the rotor blades from one pitch angle in one position to another pitch angle in another position.

Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

Abstract: An aircraft wing assembly including a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

Abstract: A wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

Abstract: The invention relates to a supporting structure (46) which is positioned in a fluid flow (44) and characterised in that it is configured to be elastically deformed, on at least one portion of the supporting structure (46), between a first idle state in the absence of external stress and a second deformed state in the presence of external stresses caused by the fluid flow (44) due to a change in the orientation of the supporting structure (46) and/or the fluid flow (44). The invention also relates to an aircraft comprising at least one such supporting structure (46).

Abstract: A roadable vehicle includes main wings, a fuselage, a sliding door on a lateral side surface of the fuselage, and hinge mechanisms. The hinge mechanisms connect the main wings to the fuselage. The hinge mechanisms allow the main wings to turn between a first state where the main wings are folded beside the fuselage and a second state where the main wings are opened on the lateral sides of the fuselage. In the first state, the sliding door is opened and closed by sliding the sliding door in a space formed between one of the main wings and the fuselage while an outer side of the fuselage and an inner side of the sliding door facing each other.

Abstract: A system of connectable aerial vehicles. The system includes a plurality of aerial vehicles that each include a platform, one or more rotors operatively connected to the platform, and a power source that supplies power to the one or more rotors. The plurality of aerial vehicles are configured to operate in air, and operate in water while connected to form a floating platform. The floating platform is configured to support an object with at least a portion of each of the plurality of aerial vehicles configured to form a segment of the floating platform.

Abstract: An integrated engineering system including multiple drones and an Electro-Mechanical drone transportation system for a new method of aviation flight transportation by the drones. These drones can be used either for passenger transportation or for parcel delivery. These drones may fly to land onto or fly to attach to carriers of the Electro-Mechanical drone transportation system then travel a distance with the carriers as unified objects. This integrated engineering system facilitates a novel method of aviation flight transportation by drones by uplifting a limit of maximum travel distance of the drones, hence making those drones a more practical tool for future aviation transportation within a city or between the cities. The Electro-Mechanical drone transportation system may include multiple routes to form a complicated transportation network to increase the number of potential destinations for the drones.

Abstract: A UAV having a wireless-front end including propellers that are dual purposed to function as ground communication antenna elements. This design reduces weight and size of the UAV, hence enabling a compact design with the capability of handling a heavier payload.

Abstract: The present invention discloses an unmanned aerial vehicle and a method for controlling a gimbal thereof. The method for controlling a gimbal includes: generating, by a flight control system, a yaw angular speed instruction of the unmanned aerial vehicle; and controlling, by a gimbal control system, a yaw axis motor of the gimbal according to the yaw angular speed instruction of the unmanned aerial vehicle. In the present invention, the yaw axis motor of the gimbal is jointly controlled by the flight control system and the gimbal control system, so that advantages of high-precision control and quick response of the gimbal control system are maximized. The advantages are used for compensating for deficiencies of the flight control system in yaw control, thereby improving the stability of a yaw channel of the gimbal, and completely resolving frame freezing of an aerial video when the unmanned aerial vehicle yaws at a low speed.

Abstract: A sunshade device and management system for mitigating the effects of climate change to help reduce the risk of extinction of plants, animals, and humans. The sunshade device has a canopy, which will collapse when lifted into the atmosphere by lifting devices, and open when the lifting devices are turned down or off, to provide shade. The canopy is preferably formed of a flexible lightweight solar panel film containing solar cells, which charge a battery power system which operates electrically powered propeller-driven lifting devices attached to a central portion of the canopy. The sunshade management device controls the lifting devices to manage the sunshade device elevation, angle and geolocation. The sunshade management device is provided with artificial intelligence and machine learning whereby it is able to make determinations regarding sunshade device takeoff and shutdown, and positioning of the elevation and angle of the canopy relative to the ground below, to maximize the shade effects of the canopy.

Abstract: A queue system for a lavatory of an aircraft can include an infotainment system configured to receive a user input and to output a request to use the lavatory associated with a seat or occupant, and a queue module operatively connected to the infotainment system. The queue module can be configured to receive the request from the infotainment system and to create and/or modify a virtual lavatory queue based on a request hierarchy of the request to position the request in the virtual lavatory queue, and output a vacancy indicator signal to the infotainment system when the request is at a front of the virtual lavatory queue. The infotainment system can be configured to receive the vacancy indicator signal and display an indication to indicate to a user of the infotainment system that it is the user's turn in the queue.

Abstract: A support configured to be reversibly installed on an upper part of an uncovered backrest of a seat. The support includes a plate configured to bear, completely or partly, against a rear face of the backrest, three clamping mechanisms, a Li-Fi technology data communicator connected to the plate, and a connector. Each clamping mechanism includes a bearing member and a clamping screw that are configured to cooperate with the plate so as to clamp a structural frame of the backrest between the bearing member and the plate. The connector being connected to the data communicator by a cable and being connectable an electronic equipment item.

Abstract: A system for tracking passenger behaviors of passengers on a commercial passenger vehicle is provided. The system comprises: media playback devices located on the commercial passenger vehicle, the media playback devices being associated with passenger seats and configured to operate in an onboard check-in mode, and an onboard server in communication with the media playback devices and configured to receive, from a media playback device associated with a passenger seat of a passenger, passenger identification information of the passenger and update passenger boarding information to indicate a completion of a boarding process of the passenger. The onboard server is further configured to provide, to at least one of a ground terminal or a crew terminal, passenger boarding information that enables determination of a time interval between a start of the boarding process by each passenger and an end of the boarding process as indicated from the media playback devices.

Abstract: Alterable aircraft lavatory configurations for improving access for Persons of Restricted Mobility are disclosed comprising incorporating an expandable aircraft lavatory wall-door that can convert from a configuration as a wall in a lavatory having an aircraft lavatory first footprint into a configuration as an expanded door in an expanded aircraft lavatory having an aircraft lavatory second footprint that is larger than the aircraft lavatory first footprint.

Abstract: A system and method for replacing or retrofitting aircraft galley monuments that include standard inserts therein with monuments that include at least some spaces for larger non-standard inserts.

Abstract: A portable and adjustable workstation to be used for working or laying one's head when travelling in vehicles such as planes, trains, buses, and the like attachable to a seat back tray table on a vehicle. A platform is connected to a pair of legs and wherein the pair of legs are adjustable to accommodate a width of a seat back tray table by angling outward or angling inward at the connection to the platform. Additionally, the point at which the one or more legs connect to the platform includes a textured feature that prevents the one or more legs from slipping at the connection point once locked into position. The one or more legs may be configured to be telescoping to allow a height of the platform to be adjusted to a desired position. A padding may also be included which fits onto a top surface of the platform.

Abstract: The present invention describes an arrangement and method for Programmable, Periodic, Substantial increase in the standard leg room provided in Airline seating for a planned limited duration, this is achieved by having the standard airline chair rows being mounted on specially designed sliding base assembly fixed on to the aircraft cabin floor, which allows the seat rows to be moved in a fore and aft directions in relation to each other in a programmable periodic manner by Hydraulic means and in a sequential manner covering all seat rows with the condition that at all times and under no circumstances the standard leg room already provided is reduced or compromised for any of the seats, thereby serving the express purpose of giving periodic relief from discomfort, mental and physical stress to airline passengers on long duration flights now being seated in compact rows with absolute minimum leg room.

Abstract: A clockable articulation insert for a seat is disclosed. The clockable articulation insert includes a base portion that inserts into a cavity within the frame or spreader bar of the seat. The clockable articulation insert further includes a face that comprises a guide slot that couples to a cross piece of the seat that is itself coupled to a seat pan. Movement of the cross piece within the guide slot changes the tilt, extension, and/or rake of the seat pan. Clocking the clockable articulation insert to a different position alters the articulation profile of the clockable articulation insert, resulting in a different set of ranges of tilt, extension, and/or rake that can be accomplished by sliding the cross piece within the guide slot. The set of articulation profiles may be further changed by replacing the clockable articulation insert with another clockable articulation insert configured with a differently designed guide slot.

Abstract: The invention relates to a seat, in particular for an aircraft, including: a seat support, a seat base, a backrest hinged relative to the seat base by means of a pivot link, a leg rest hinged relative to the seat base by means of a pivot link, the seat being able to move between a sitting position and a bed position in which the backrest and the leg rest are situated in a continuation of the seat base, the seat base being mounted so as to be able to slide relative to the seat support, the seat comprising at least one connecting rod, referred to as the backrest pivot connecting rod, comprising a first end connected in rotation relative to the backrest and a second end connected in rotation relative to the seat support, the leg rest being mechanically connected to the backrest by means of a connecting rod deployment device, the seat further comprising a single actuator capable alone of moving a set of components of the seat formed at least by the seat base, the backrest, and the leg rest in order to move the

Abstract: A system for controlling airflow from a galley compartment to a plenum chamber is disclosed. The system includes an actuating assembly. The actuating assembly includes a cylinder, a heat-expanding material disposed in the cylinder, and a piston disposed in the cylinder, wherein the heat-expanding material is configured to actuate the piston when the heat-expanding material is heated. The system includes a valve assembly. The valve assembly may include a louver assembly coupled to the actuating assembly. The louver assembly includes a louver frame, one or more louver blades and bracket and a connecting rod that couples the actuating assembly to the valve assembly. The valve assembly may also include a poppet valve. The poppet valve includes a poppet body element, a poppet stem coupled to the actuating assembly that is inserted into a channel within the poppet body element, and a poppet head coupled to the poppet stem.

Abstract: Air distribution nozzles, aircraft that include air distribution nozzles, and methods of utilizing air distribution nozzles are disclosed herein. The air distribution nozzles include an elongate inlet chamber, an elongate outlet chamber, and an elongate slot that extends between, and fluidly interconnects, the elongate inlet chamber and the elongate outlet chamber. The air distribution nozzles also include a suction inlet chamber that extends from a suction inlet port to the elongate inlet chamber. The suction inlet port opens into the suction inlet chamber. The air distribution nozzles further include a motive fluid inlet port that extends into the elongate inlet chamber. The air distribution nozzles also include a sensor port that extends into the suction inlet chamber. The air distribution nozzles further include an elongate outlet port that extends from the elongate outlet chamber.

Abstract: An environmental control system for use in an aircraft includes at least one component positioned along a length of the aircraft and a decompression panel assembly comprising an array of apertures. The array of apertures is based on a location of the decompression panel assembly along the length of the aircraft relative to the at least one component.

Abstract: Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger.

Abstract: A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit.

Abstract: The present disclosure relates to a hydrogen electric hybrid power plant for a hovercar. The hydrogen electric hybrid power plant comprises a first-stage duct, a transition duct and a second-stage duct. An air outlet end of the first-stage duct is connected to the second-stage duct through the transition duct. A hydrogen reactor is arranged in the first-stage duct, and the hydrogen reactor is fixed with the first-stage duct through a plurality of supporting pieces A. A primary filter screen is arranged at a front end of the first-stage duct and fixed on the first-stage duct through a hoop, so that low-altitude sundries and dust are prevented from entering the reactor. A return pipe is arranged, and the problems of oxygen supply, heat dissipation and cooling and the like of the hydrogen reactor are solved through ducted airflow. A motor power supply requirement of a ducted fan is met.

Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

Abstract: A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.

Abstract: A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a carrier, a first gear system, a second gear system and an idler. The first gear system includes a first sun gear, a first ring gear and a plurality of first intermediate gears. Each of the first intermediate gears is between and is meshed with the first sun gear and the first ring gear. Each of the first intermediate gears is rotatably mounted to the carrier. The second gear system includes a second sun gear, a second ring gear and a plurality of second intermediate gears. Each of the second intermediate gears is between and is meshed with the second sun gear and the second ring gear. Each of the second intermediate gears is rotatably mounted to the carrier. The idler gear couples the first ring gear to the second ring gear.

Abstract: A cryogenic fuel tank for retrofitting a conventional fossil-fuel-powered aircraft, or for a purposely built aircraft to run on hydrogen has an aerodynamically shaped outer surface including an ogive shaped nose cone, and a tapered tail cone, wherein the tapered tail cone includes actively adjustable elements for adjusting aerodynamic characteristics of the cryogenic fuel tank. The cryogenic fuel tank is configured to be attached below wings of the aircraft, through support pylons, which include sensors configured to measure forces applied by the cryogenic fuel tank to the airframe. The cryogenic fuel tank includes a nozzle and valve configured to vent gas from the cryogenic fuel tank by expansion through the nozzle in the event that the cryogenic fuel tank is jettisoned from the aircraft.

Abstract: An aircraft has a first principles takeoff processor (PCE), a predictive flight envelope protection processor (PFEP), and a maximum takeoff weight processor. The PCE is programmed to predict a liftoff location and an energy state of the aircraft at a liftoff on a runway. The PFEP is programmed to assess each of a plurality of potential trajectories for compliance with or violation of a predetermined flight envelope. The maximum weight processor is programmed to: indicate that the aircraft may takeoff at the aircraft weight when any one of the plurality of potential trajectories is in compliance with the predetermined flight envelope; iteratively reduce an input of the aircraft weight to the PCE until the PCE indicates that any one of the plurality of potential trajectories is in compliance with the predetermined flight envelope; and indicate that the input of the aircraft weight as reduced is a maximum allowable takeoff weight.

Abstract: The invention relates to a method of determining the relative positions of components of a munitions system, the munitions system comprising a first component (331) and at least one second component (333). The method comprises monitoring the output of a resonant circuit (305) provided on a first component (331), the resonant circuit (305) having a resonant frequency, detecting a change in the output due to a change in the resonant frequency caused by a change in the relative positions of the first component (331) and the at least one second component (333), and using the detected change to determine that the at least one second component (333) has moved relative to the first component (331).

Abstract: A method for self-assessing components of a cargo handling system configured for autonomous control by a processor is disclosed. In various embodiments, the method includes receiving by the processor a sensor database from a plurality of sensing agents in operable communication with the processor; testing by the processor the plurality of sensing agents by comparing the sensor database against a sensor assessment; and performing by the processor a first calibration assessment of the plurality of sensing agents to assess whether a compromised operational status of the cargo handling system has occurred due to a failure of one or more of the plurality of sensing agents.

Abstract: Described herein is an elevated unmanned aerial vehicle (UAV) station. The elevated UAV station includes an elevated platform and a conveyance device configured to raise a payload to the elevated platform. The elevated unmanned UAV station may further include a launch device configured to cause a takeoff of a UAV from the elevated platform. The elevated UAV station may further include a recovery device configured to cause a controlled landing of the UAV at the elevated platform. The elevated UAV station may be associated with a payload housing structure to establish a system for payload storage and launch.

Abstract: Aspects of the present disclosure include an aircraft with auxiliary components that are powered by an external power supply. Auxiliary components may include components that are used while the aircraft is grounded. Auxiliary components may be off while the aircraft is in flight.

Abstract: A data processing system for generating predictive maintenance models is disclosed, including one or more processors, a memory, and a plurality of instructions stored in the memory. The instructions are executable to receive a historical dataset relating to each system of a plurality of systems, the historical dataset including maintenance data and operational data. The instructions are further executable to evaluate correlation between each of a plurality of operational data features and maintenance events of the maintenance data, using a supervised machine learning classification model. The instructions are further executable to display a quantitative result of the evaluation for each operational data feature in a graphical user interface, receive a selection of one or more operational data features of the plurality of operational data features, and generate a predictive maintenance model using the selected one or more operational data features according to a machine learning method.

Abstract: The present technology relates to an artificial satellite and a control method thereof that enable to ensure quality of a captured image while suppressing battery consumption. An artificial satellite includes: an imaging device configured to perform imaging of a predetermined region on the ground; and a management unit configured to change accuracy of attitude control in accordance with a remaining battery amount at an instructed imaging time, and configured to change an imaging condition in accordance with accuracy of the attitude control. The present technology can be applied to, for example, an artificial satellite or the like that performs satellite remote sensing by formation flight.

Abstract: A constellation planning system receives a request, from a client, to plan an optimal set of tasks for one or more satellites in a constellation of satellites and at least one ground station in a constellation of ground stations. The request includes a planning problem object. The system generates a status of the planning task describing a progress of the planning task, and returns the status to the client. If the status of a task is successful, then the client may retrieve the resulting schedule and publish it to the constellation.

Abstract: A dual solution candidate searcher receives an input of information about a constraint coefficient matrix and a cost vector, determines a dual problem of a linear programming problem being a primal problem and all active sets representing combinations of active formulas in constraints of the dual problem, finds, for each of the active sets, a feasible dual solution candidate meeting constraints, and stores the dual solution candidate into a storage in a manner associated with a corresponding one of the active sets. An optimal solution calculation device receives an input of a constraint vector as, selects an optimal one of the active sets as an optimal active set based on an inner product of the constraint vector and the dual solution candidate stored in the storage, and finds and outputs a basic feasible solution corresponding to the selected active set as an optimal solution.

Abstract: In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

Abstract: A gyromesh solar sail spacecraft having a gyromesh of solar sail panel assemblies, each with a reflective solar sail. The gyromesh of solar sail panel assemblies distributed around a hub and rim with a cable structure, the cable structure having a plurality of radial cables and plurality of circular cables, the radial cables extending from the hub linearly and the plurality circular cables encircling the hub. The solar sail panels assemblies attached to at least one of the plurality of circular cables, at least a portion of the solar sail panel assemblies attached to the circular cables by a plurality of actuators, respectively, wherein centrifugal force keeps the plurality of radial cables, plurality of circular cables, and solar sail panels extended from the rim.