Abstract: The present invention provides a connecting device for connecting at least two floating bodies, in particular at least two stand-up paddle boards, side by side, comprising: a linkage having at least one rod; and a plurality of fastening means arranged on the at least one rod of the linkage, at least some of the plurality of fastening means being provided axially displaceable along the axis of the at least one rod of the linkage adapted to the respective geometry of the at least two floating bodies such that each floating body can be clamped between at least two fastening means on the at least one rod of the linkage in a positionally stable manner.

Abstract: An autonomous body of water navigation system and method uses the current of the body of water. The body of water navigation method may be asymmetric since cargo may be transported along with the current of the body of water and the navigation system can be easily transported back up the body of water.

Abstract: A self-righting sailing vessel is described. The self-righting sailing vessel may determine the occurrence of several predetermined events, such as the self-righting sailing vessel capsizing, present or imminent inclement weather, and/or a present or imminent vessel or large marine animal. Upon detection of one of these events, the self-righting sailing vessel causes at least it's hull to become partially or completely submerged beneath the water. The self-righting sailing vessel is configured such that its rig is more buoyant than the rest of the vessel when the vessel is completely submerged beneath the water, causing the vessel to move towards an upright position while underwater. When the vessel is pointing towards an upright position, the vessel may begin ascending until it surfaces and is ready to continue sailing on top of the water.

Abstract: A device for detecting a fall of and for geolocating a container that has gone overboard that includes an electronic box and a means for removably attaching the electronic box to an external part of the container is disclosed. The electronic box includes a means for detecting the container's fall, a control unit controlling the removable attachment means in the event of the detection of the container's fall and disconnecting the electronic box from the external part of the container, a flotation means for floating the electronic box on a stretch of water, a geolocation module, a data communication means, a means for powering the control unit, a link for maintaining a permanent connection between the electronic box and container when the box is disconnected from the container. This allows detection a container falling into the sea and to communicate its geographical position with a view to towing thereof.

Abstract: A lanyard system for a marine vessel propelled by at least one propulsion device includes an operator device worn by an operator of the marine vessel, a receiver device at a helm area of the marine vessel, wherein the receiver device is configured to detect whether the operator is within a permitted zone with respect to the helm area, and a control configured to generate a lanyard event when the operator is not detected within the permitted zone and, upon generating a lanyard event, reduce an rpm of the propulsion device at a pre-set reduction rate to an idle rpm.

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 fixed-pitch bolted propeller includes: a hollow hub body configured for attachment to a rotatable shaft, where the hollow hub body includes connection ports circumferentially distributed on an outer surface thereof; propeller blades, where each of the propeller blades terminates in a blade flange attached to the outer surface of the hollow hub body at one of the connection ports; retention plates positioned on an inner surface of the hollow hub body adjacent to the connection ports, where the retention plates include threaded recesses; and bolts extending through bolt holes in the blade flanges and the connection ports and into the threaded recesses of the retention plates to secure the propeller blades to the hollow hub body. The retention plates and the bolts each comprise a material having a tensile strength of at least about 125 ksi and/or a fatigue endurance limit of at least about 50 ksi.

Abstract: Various examples of a high-speed omnidirectional fully-actuated underwater propulsion mechanism are described. In one example, a propulsion system includes two decoupled counter-rotating rotors centered on a main axis, with each rotor comprising a plurality of pivotable blades projecting radially from the main axis, a servo-swashplate actuation mechanism comprising a plurality of servos and a linkage assembly connected from the servos to the pivotable blades, a blade-axis re-enforcing flap adapter comprising a plurality of stationary flaps, with the blade-axis re-enforcing flap adapter being positioned in a region between the two decoupled counter-rotating rotors centered on the main axis, and a controller.

Abstract: A hairtail-imitating high-speed soft robot driven based on chemical exergonic reaction, including a fish head module, a fish body module and a fishtail module; wherein the fish head module includes a fish head shell, the fish head shell is internally provided with a rigid exergonic reaction bin, a combustible agent storage unit, a combustion promoter storage unit, and an exergonic reaction excitation device, and a rigid push plate is in sliding fit in the rigid exergonic reaction bin; the fish body module includes a flexible fishbone, restraint assemblies, and flexible fish skin; and the fishtail module includes a fishtail fixing block.

Abstract: A transom saver is for supporting an outboard motor in a trim position relative to a marine vessel. The transom saver has a body that extends between a first end and a second end. The body has a first seat and a second seat that are spaced apart and configured to support a transom bracket in a first position of use. A spring is disposed on the second side and configured to resiliently support the first swivel bracket in the first position of use.

Abstract: A marine propulsion system for propelling a marine vessel includes at least two steerable rear marine drives that each generate forward and reverse thrusts, wherein each rear marine drive is independently steerable to a range of steering angles, and a lateral marine drive configured to generate starboard and port thrusts on the marine vessel. The system further includes a user input device, such as a joystick, operable by a user to provide a propulsion demand input commanding lateral movement of the marine vessel and rotational movement of the marine vessel. A control system is included that is configured to control steering and thrust of each of the at least two rear marine drives and thrust of the lateral marine drive based on the propulsion demand input so as to generate the lateral movement and/or the rotational movement commanded by the user.

Abstract: A safety system for a boat, watercraft or other vehicle includes a kill switch connected to the motor for preventing the motor from running under dangerous circumstances. The system includes at least one proximity sensor operatively connected to the kill switch, so that the motor only runs when the proximity sensor detects a person properly positioned at the captain's console. Other sensors may form an array to communicate with the kill switch, either hard-wired together or wirelessly, upon detection of dangerous situations, including proximity sensors to detect if a swimmer is near the propeller or if the captain is not in position at the helm, gate sensors to detect when gates on the boat are in an open position, and ladder sensors to detect when a ladder is in a down position. The system may also include at least one rear facing camera operatively connected to a console-mounted video screen.

Abstract: A watersports boat is equipped with a trimmable drive used to generate a virtual ballast effect. Turbulence experienced by a wake rider on startup is reduced by automatically varying the drive orientation as the watersports boat comes up to speed. A pair of water channelers are located at the stern. One of the water channelers is deployed below the running surface to redirect water across centerline and improve wake shape on the selected side.

Abstract: A method for operating a cargo door of an aircraft includes opening the cargo door inwardly in relation to an opening by pivoting the cargo door to an open position adjacent a ceiling of a cargo space. The cargo door is supported by a door frame during opening of the cargo door. The method further includes moving the cargo door in relation to the door frame to a position wherein the opening is substantially free from the cargo door. The cargo door is supported by a support frame, moveable in relation to the door frame, during this movement.

Abstract: Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine.

Abstract: An aircraft wing including a leading edge slat and a fixed aerofoil portion. The leading edge slat is moveable between a stowed position and deployed position. In the deployed position a trailing edge of the leading edge slat includes a sealed portion and an unsealed portion. The sealed portion forms a seal with the fixed aerofoil portion and the unsealed portion provides an airflow gap between the leading edge flap and the fixed aerofoil portion. The invention provides substantially the same benefits as a sealed leading edge slat whilst improving stall control behavior in local zones around the unsealed portion.

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: Various examples are provided related to flight duration enhancement for rotorcraft and multicopters. In one example, a rotorcraft or multicopter includes one or more rotors, and one or more nozzles positioned in relationship to at least one corresponding rotor. The one or more nozzles can modulate, reshape, redirect, or adjust downwash produced by the corresponding rotor. The one or more nozzles can dynamically modulate, reshape, redirect, or adjust the downwash below the rotorcraft or multicopter. The one or more nozzles can be morphed or reshaped to dynamically modulate, reshape, redirect, or adjust the downwash using, e.g., a stochastic optimization framework and/or a motif-based auto-controller.

Abstract: A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.

Abstract: An aircraft comprising a fuselage, first and second wings positioned on either side of the fuselage, wherein each wing includes an inner part connected to the fuselage and an outer part continuing the inner part, the end of each inner part connected to the fuselage having a height greater than half the height of the fuselage and extending over a length greater than or equal to half of a distance separating the nose and the tail of the fuselage.

Abstract: Systems and methods for airspace management. One embodiment of an aerial vehicle, includes a first sensor for detecting a lateral field of view of the aerial vehicle and a vehicle computing device. The vehicle computing device may include a memory component and a processor. The memory component may store logic that, when executed by the processor, causes the aerial vehicle to calculate a detection boundary for the aerial vehicle to maintain a well clear requirement, wherein the detection boundary is based on instantaneous trajectory, planned future trajectory, and a capability of the aerial vehicle and utilize the capability of the aerial vehicle and data from the first sensor to maintain the vehicle within detection boundary. In some embodiments the logic may cause the vehicle to provide an instruction to maintain the aerial vehicle within the detection boundary.

Abstract: The embodiment is an unmanned aerial vehicle. The unmanned aerial vehicle includes: an airframe, including first mounting portions, where the first mounting portion includes a first mounting body and connecting rods formed on the first mounting body, the connecting rods extending in a pitch axis direction; and a power assembly, including a first assembling body and eccentric wheels mounted on the first assembling body, where the eccentric wheel is rotatable between a first rotation position and a second rotation position of the first assembling body around a rotation axis of the first assembling body, the rotation axis being perpendicular to the pitch axis direction.

Abstract: A passive guidance mechanism enables smooth guiding to a desired position; and a flying object landing system enables smooth guiding to and landing at a desired position. A pair of guide rails are arranged side by side with a space therebetween, and are provided so that the space increases toward one set of tips of the guide rails. One guide rail is supported so as to be rotatable about a first shaft extending in a direction perpendicular to a plane including the guide rails, at or near the tip of the guide rail. The other guide rail is supported so as to be rotatable about a second shaft extending in a direction perpendicular to the plane including the guide rails, at or near the tip of the guide rail.

Abstract: A blended wing body aircraft having an interior cabin with a usable volume of at most 4500 ft3 and a cabin aspect ratio of at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.7 and at most 2.8. Also, a blended wing body aircraft having an interior cabin with a usable volume of at least 1500 ft3 and at most 4500 ft3 and a cabin aspect ratio of at least 2 and at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.9 and at most 2.7. Also, a blended wing body aircraft wherein at least each profile section having normalized half-span values from 0 to 0.3 has a leading edge having a normalized height having a nominal value within the range set forth in Table 4.

Abstract: A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.

Abstract: A lavatory is provided which includes a plurality of walls including a first wall having a doorway, and an expandable door. The expandable door includes a main panel having dimensions that conform to the doorway and a main hinge connecting the main panel to the first wall. The lavatory further includes a latch. The main panel is configured to, in a deployed state, increase in at least one dimension to form a privacy barrier around an expansion zone located outside of the plurality of walls. The latch is configured to lock the expandable door in place in the deployed state.

Abstract: A crank assembly for extracting an inner galley trolley from a galley bay is provided. The crank assembly comprises an output shaft configured to rotate about an axis of rotation A for actuating a trolley extraction mechanism to extract an inner galley trolley from a galley trolley bay; a crank arm configured to rotate about the axis of rotation A; a handle connected to the crank arm for rotating the crank arm about the axis of rotation A; and a clutch mechanism. The clutch mechanism is operable to selectively couple the crank arm to the output shaft to selectively transfer rotational movement of the crank arm into rotational movement of the output shaft.

Abstract: A seat unit for a passenger seating arrangement provided within a vehicle cabin, wherein—the seat unit comprising at least a forward facing seat and at least a console arranged adjacent to the seat and a wall structure, wherein the seat unit is configured to link—the forward facing seat arranged in front of the wall structure, and—an angled seat arranged behind the wall structure, wherein the console provides a footwell for a passenger of the angled seat.

Abstract: The invention relates to a seat assembly for a cabin of a means of transportation, having an aisle which is arranged in the longitudinal direction of the cabin, two mutually spaced cabin walls which are oriented parallel to the aisle at least in some regions and laterally delimit the cabin, two outer passenger seat regions which are separated from one another by the aisle and each of which adjoins one of the two cabin walls, wherein the outer passenger seat regions have at least one row of seats with a respective inner first seat module which faces the aisle, a central second seat module adjoining the first module, and an outer third seat module adjoining the respective cabin wall.

Abstract: A seat extension apparatus for a cabin dividing element, in particular of an aircraft cabin, the seat extension apparatus comprising at least an extension device having a mounting side and a bed surface side, wherein the extension device is movable between a vertical stowed position and a horizontal use position, and a support structure coupled to the extension device to pivotably support the extension device, wherein the support structure comprises at least one pivotable strut element having at least one end pivotably coupled to the mounting side of the extension device and at least one free end.

Abstract: An aircraft air conditioning system includes a lower cooling zone and an upper cooling zone. The lower cooling zone includes a lower recirculation heat exchanger configured to receive cabin air from a cabin and convert the cabin air into lower cooled recirculated cabin air. The upper cooling zone includes an upper recirculation heat exchange configured to receive the cabin air from the cabin and convert the cabin air into upper cooled recirculated cabin air. A power system selectively delivers power to the lower cooling zone and the upper cooling zone. A controller is in signal communication with the power system. The controller determines a target temperature of the cabin and invokes a recirculation ground maintenance mode that commands the power system to deliver power to one or both of the lower cooling zone and the upper cooling zone so that a temperature of the cabin reaches the target temperature.

Abstract: A water extractor for an environmental control system of an aircraft includes a separation mechanism configured to divide an airflow into a first airflow and a second airflow. The separation mechanism includes an inlet conduit, a body in fluid communication with the inlet conduit, and at least one coalescing feature arranged within an interior of the body. A water extraction vessel is arranged in fluid communication with the separation mechanism. The water extraction vessel includes a first portion for receiving the first airflow and a second portion for receiving the second airflow. The first portion is configured to collect and remove water from the first airflow.

Abstract: A device for disconnection by a mechanical action includes at least one mechanical connection part, in particular a buckle held closed by spring action, linked to at least one trigger via at least one connecting member, and a release lever configured to be triggered by application of a force according to a predefined opening direction. The disconnect device also includes at least one guide for the connecting member configured to redirect an effort applied on the trigger, when opening is required, towards the mechanical connection part linked to the connecting member, according to the predefined opening direction.

Abstract: Actuation assemblies for emergency devices (e.g., inflatable life rafts carried on-board an aircraft) are provided with enhanced (preferably multiple) levels of security to preclude inadvertent unlatching and/or deployment but also allow access to an on-board emergency device removably positioned within a device bay of the vehicle which is normally covered by an access panel. The actuation assembly may be provided with a rotatable actuation shaft, a manually operated actuation lever fixed to the actuation shaft so as to rotate the actuation shaft in response to movement of the actuation lever between stowed and deployed conditions thereof, and a safety locking system operably connected to the rotatable shaft and having a locked condition which prevents operation of the actuation lever to thereby maintain the actuation assembly in a safe mode during normal vehicle operation, and an armed mode which allows the actuation lever to be moved into the deployed condition thereof.

Abstract: A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred thirty (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft.

Abstract: In an aspect this disclosure is directed at a propulsor assembly powered by a dual motor system. The aircraft may comprise a propulsor. The electric aircraft may also include a driveshaft that is mechanically coupled to the propulsor, wherein a driveshaft is configured to provide mechanical power to the propulsor. The aircraft includes a plurality of electric motors. The electric motors may be configured to impart rotational energy to the driveshaft. Wherein each electric motor includes a stator and a rotor. Each electric motor is selectively engaged to the driveshaft by a freewheel clutch.

Abstract: An aircraft that includes a fuselage, an electric motor driven propulsion system, and a fuel cell system configured to provide electricity to the electric motor. The fuel cell system includes a fuel cell, a hydrogen tank, an oxygen tank, an air channel, and a cathode switch. The cathode switch being configured to convert between an air mode, wherein the fuel cell operates utilizing air from the air channel, and an oxygen mode, wherein the fuel cell operates utilizing oxygen from the oxygen tank.

Abstract: A takeoff location and a landing location are received for an autonomous vertical takeoff and landing (VTOL) vehicle that includes a plurality of rotors. An autonomous and noise-reduced flight trajectory for the autonomous VTOL vehicle is determined based at least in part on the takeoff location, the landing location, a jerk function, and a noise function, including by minimizing the jerk function and minimizing the noise function. A set of one or more desired forces or moments is determined for the autonomous VTOL vehicle based at least in part on autonomous and noise-reduced flight trajectory. A plurality of motor control signals is determined for the plurality of rotors based at least in part on the set of one or more desired forces or moments.

Abstract: An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.

Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

Abstract: An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.

Abstract: Aspects of the disclosure provide solutions for automated air-to-air refueling (A3R) and assisted air-to-air refueling. Examples include: receiving a video frame; identifying an aircraft to be refueled from within the video frame; segmenting the video frame to generate a segmentation mask matching the aircraft within the video frame; based on at least the segmentation mask, determining a position of a fuel receptacle on the aircraft; determining a position of a boom tip of the aerial refueling boom; and controlling the aerial refueling boom to engage the fuel receptacle based on at least the position of the fuel receptacle and the position of the boom tip.

Abstract: An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

Abstract: A charge dissipation plate for aircraft electronic systems having a metal plate with machined through openings. A collar is integrally formed with each through opening. The collar extends upwardly from the plane of the plate and includes a threaded outer surface for receiving an electronic connector.

Abstract: A method for establishing a runway safety area adjacent a runway, wherein the runway safety area is a cement matrix having a plurality of foamed glass aggregate bodies suspended therein, including mixing cement and foamed glass aggregate bodies to define a composite material, forming the composite material into a runway safety area defining a plurality of foamed glass aggregate bodies suspended in a cement matrix, taxiing an aircraft over the runway safety area and crushing at least a portion of the runway safety area with the aircraft to bleed off the aircraft's kinetic energy, wherein the runway safety area has a crushing failure mode.

Abstract: A moveable wing gantry for servicing a wing of an aircraft is configured to be positioned around a wing of an aircraft to provide access to overwing and underwing surfaces of the wing of the aircraft. The wing gantry includes a service deck positioned underneath the wing of the aircraft. An operator platform is moveably attached to the service deck and operable to move along the length of the service deck. A chair support is moveably attached to the operator platform and operable to move across the operator platform in a direction substantially perpendicular to the length of the service deck. The wing gantry includes a pivotable span platform positioned above the wing of the aircraft and pivotable between a raised position and a lowered position. The wing gantry is customizable to different aircraft wing types and styles.

Abstract: A method of testing an aircraft landing gear is disclosed including: a) generating a test signal with the first tachometer, wherein the first wheel is not rotating during the generation of the test signal; b) receiving the test signal via one of the tachometer output lines; c) issuing a braking command in response to the receipt of the test signal, wherein the braking command is issued via the braking command line which is associated with the one of the tachometer output lines; and d) monitoring a response of the first or second braking system to the braking command to test for a cross-connection between the first and second braking systems. The landing gear includes first and second wheels; a first braking system having a first tachometer mounted to the first wheel and configured to generate a first tachometer signal indicating rotation of the first wheel, and a first brake configured to brake the first wheel.

Abstract: Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

Abstract: An antenna assembly has a solar layer having one or more solar cells generating solar power, an antenna layer connected to the solar layer and having electronic components utilizing the solar power generated by the solar layer, and a thermal dissipation device dissipating heat locally at the antenna assembly. A large number of antenna assemblies are connected to form an antenna array in which heat is generated locally at each antenna assembly and dissipated locally at each antenna assembly.

Abstract: A disclosed spacecraft is provided with: an attitude control actuator configured to control an attitude of the spacecraft; an imaging device configured to receive an optical communication signal from another spacecraft; and an attitude controller configured to control the attitude control actuator, based on a position of the optical communication signal in an image obtained by the imaging device.