Abstract: A bicycle derailleur includes a base member, a movable member, a link member, a chain guide, a biasing mechanism and a switching member. The link member movably couples the movable member to the base member. The chain guide is pivotally coupled to the movable member about a pivot axis. The biasing mechanism is operatively disposed between the movable member and the chain guide, and biases the chain guide with respect to the movable member about the pivot axis in a first direction in a biasing state. The switching member is configured to selectively switch the biasing mechanism between the biasing state and a releasing state. The biasing mechanism biases the chain guide less in the releasing state than the biasing state. The switching member is disengaged from the biasing mechanism in the biasing state. The switching member is engaged with the biasing mechanism in the releasing state.

Abstract: A storage boot for a bimini top including a bimini frame and a cover includes a base defining a hollow interior configured to receive a portion of the bimini top. The base includes a first support member and a base cover attached to the first support member. The base cover is formed from a fabric material. A lid is movable to selectively close the hollow interior. The lid includes a second support member and a lid cover attached to the second support member. The lid cover is also formed from a fabric material.

Abstract: A buoyant offshore platform for supporting a renewable energy system having a base portion for submerging below the surface of a body of water, a top portion, at least one mooring line for fixing the platform to a bed of the body of water, and a tensioning means for applying tension to at least one of the mooring lines. The platform further comprises a floating configuration in which the platform is positioned floating on the surface of the body of water. The platform has a deployed configuration in which the base portion is submerged and the top portion remains above the surface of the body of water. In use, the tensioning means is arranged to apply tension to the at least one mooring line fixed between the platform and the bed such that the buoyant offshore platform transitions between the floating configuration and the deployed configuration.

Abstract: The present disclosure relates to a water surface foldable emergency-built runway, including a storage box; a folding runway having an unfolding state and a folding state; a recovery apparatus, being provided in the storage box and connected with the folding runway to push the folding runway out of the storage box or recover into the storage box; a contractile apparatus, being provided on the folding runway to assist the folding runway to be unfolded or folded; an inflation and deflation apparatus, being provided in the storage box and communicated with the interior of the folding runway to inflate or deflate the folding runway; and an anchoring apparatus, being provided at a bottom face of the folding runway to fix the folding runway in water. It has advantages of low cost, convenient transportation, short construction time, strong overturning resistance, compression resistance and flex resistance.

Abstract: A pontoon boat with a motor arrangement has multiple chines on the pontoons and has a plurality of chine wedges positioned in respective reverse chines. The chine wedges providing a optimal balancing of the performance characteristics of the pontoon boat. The pontoon boat may be performance tuned by positioning the chine wedges at alternate positions or utilizing alternately shapes, sizes, or orientations of chine wedges. The chine wedge may be readily attached and detached utilizing threaded fasteners which extend into foils mounted on the pontoon, the foils partially defining the reverse chines into which the chine wedges are placed.

Abstract: Disclosed is a motorised wave-piercing ship with hull with a deck, the ship including a conning tower and, under the hull, a weighted keel, the keel being removable and being able to be placed in a low position and a high or extracted position. According to the invention, the ship can sail as a monohull or as a trimaran, the hull including a device for removable attachment of an anti-roll stabilisation system including an elongated connection arm terminated at its two lateral ends by two floats, the connection arm including an attachment member, the attachment member being configured to be removably attached on the attachment device in order to transform the ship into a trimaran, and the ship is monohull in the absence of the anti-roll stabilisation system.

Abstract: A system for a marine vessel propelled by a propulsion device includes a controller operable in an automatic navigation mode in which the controller automatically controls a thrust of the propulsion device to propel the marine vessel through a body of water. A portable device is carried on an individual on the marine vessel. The controller enables a person overboard detection algorithm in response to enablement of the automatic navigation mode. The person overboard detection algorithm disables the automatic navigation mode in response to detecting a given status of the portable device.

Abstract: This disclosure describes monitoring and operating subsea well systems, such as to perform operations in the construction and control of targets in a subsea environment. A submerisble ROV that performs operations in the construction and control of targets (e.g., well completion components) in a subsea environment, the ROV has one or more imaging devices that capture data that is processed to provide information that assists in the control and operations of the ROV and/or well completion system while the ROV is subsea.

Abstract: Described is an acceptor/adapter device for securing an outboard jet motor to a watercraft. The acceptor/adapter comprises a shrouded opening for communication with an intake of the outboard jet motor. Sidewalls of the acceptor/adapter device can form a tunnel, wherein the tunnel is configured for directing a flow of water through the tunnel, into the adapter/acceptor device, and into the intake of the outboard jet motor. Also described is a hull with a tunnel for directing a flow of water to an intake of an outboard jet motor, as well as a directional device which allows for vertical or horizontal adjustments to the jet output or reversing the jet output.

Abstract: A pedal assembly and steering assembly are disclosed for converting an inflatable, drop stitch paddle watercraft into a pedal watercraft. The pedal assembly includes a mounting plate and mounting bracket for supporting a geared drive shaft in an opening extending through the floor of the watercraft. The steering assembly includes a rudder connected to a tiller through push pull cables.

Abstract: A transportable outboard motor has a midsection and a tiller extending forwardly from the midsection. The tiller is pivotable about a lateral tilt axis into a downward tilt position in which the tiller is oriented transversely to the lateral and longitudinal directions. The tiller in the downward tilt position is configured to permit manual carrying of the transportable outboard motor.

Abstract: A marine propulsion system includes a first marine propulsion device and a second marine propulsion device. The first marine propulsion device includes an engine, a first propeller shaft to receive a driving force from the engine, and a first controller configured or programmed to control the engine. The second marine propulsion device includes an electric motor, a second propeller shaft to receive a driving force from the electric motor, an electric circuit connected to the electric motor to drive the electric motor, and a second controller configured or programmed to control the electric motor. The first controller is configured or programmed to put a limitation on an output of the engine when the electric motor is not being driven.

Abstract: A transportable outboard motor has a tiller which is pivotable about a lateral tilt axis into a plurality of tilt positions and also pivotable about an axial yaw axis into a plurality of yaw positions. The tiller is pivotable about the axial yaw axis into a straight-ahead position, into a port yaw position which is oriented towards the port side relative to the straight-ahead position, and into a starboard yaw position which is oriented towards the starboard side relative to the straight-ahead position. The tiller is pivotable downwardly about the lateral tilt axis from the port yaw position, and downwardly about the lateral tilt axis from the starboard yaw position. Pivoting the tiller into the plurality of yaw positions creates space for a user to manually grasp a swivel tube and thereby lift the transportable outboard motor from a rear-laydown position.

Abstract: A stern drive is for propelling a marine vessel in a body of water. The stern drive has a powerhead, a mounting assembly configured to affix the powerhead to the transom, inside the marine vessel, and a drive assembly coupled to the mounting assembly, the drive assembly being trimmable up and down relative to the mounting assembly, the drive assembly comprising a driveshaft and an output shaft which extends transversely to the driveshaft. The drive assembly has a driveshaft housing for the driveshaft and a gearcase housing for the output shaft, wherein the gearcase housing is steerable relative to the driveshaft housing. A universal joint couples the powerhead to the driveshaft so that operation of the powerhead causes rotation of the driveshaft, which in turn causes rotation of the output shaft.

Abstract: An autopilot system for automatically steering a marine vessel is disclosed. The marine vessel comprises two electric motors connected to respective propulsors, two rudders, a rudder steering mechanism and a navigation system for determining the vessel position with respect to an intended course. The autopilot system can operate according to one or more autopilot modes comprising at least a motor steering autopilot mode wherein the autopilot system is configured to automatically control the rudder steering mechanism in order to lock the rudders at a fixed angle, and based on a feedback from the navigation system to independently and dynamically adjust power supply to each of the propulsors by independently and dynamically regulating electric power supply to the respective electric motors in order to maintain the vessel on course.

Abstract: The disclosed invention describes a method for determining a lift of a gas cell of an airship. A computing device receives depth measurements of an interior surface of the gas cell comprising a lifting gas using a lidar sensor positioned outside at the top of the gas cell. The computing device performs a particular integration on the depth measurements and estimates a volume of the gas cell based on performing the particular integration. The computing device determines the lift of the gas cell comprising the lifting gas using estimated volume of the gas cell. The computing device sends the lift of the gas cell comprising the lifting gas to a control module of the airship.

Abstract: Embodiments of the present disclosure provide a wing element structure for an aircraft, comprising a plurality of wing element units, wherein adjacent wing element units are connected by airfoil control units, hydraulic units and wing element outer edge connecting members, each of the wing element units comprises a plurality of wing element edge members connected to one another and a wing support rod connecting member, and the wing support rod connecting member located in a wing leading edge in the wing element unit is connected to a support rod structure on an aircraft main body.

Abstract: An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.

Abstract: A system onboard a vehicle, an aircraft, and a method of controlling actuation of a moveable control surface of a vehicle are disclosed here. An operating method involves: obtaining a force measurement and a deflection measurement responsive to manipulation of an inceptor for the moveable control surface; determining an issue associated with the inceptor, based on the obtained force and deflection measurements and vehicle data that characterizes expected operating behavior of the vehicle under current operating conditions; and, in response to the determining, activating a temporary backup control mode for the moveable control surface. While the temporary mode is active, control surface actuation signals are generated with an onboard system that disregards deflection measurements and processes force measurements of the inceptor. While the temporary mode is active, generated control surface actuation signals are communicated to an actuation system that is coupled to the moveable control surface of the vehicle.

Abstract: A device for driving at least one wheel of an aircraft landing gear including at least one landing gear wheel, this wheel including a rim, an electric motor including a shaft, a mechanical transmission system between the shaft of the motor and the rim, this mechanical transmission system including a mechanical reducer including a sun gear secured in rotation to the shaft of the motor, a ring gear, and planet gears which are carried by a planet carrier and which each includes three external toothings, including a median external toothing which is meshed with a toothing of the sun gear, and two lateral external toothings which are respectively meshed with toothings of the ring gear.

Abstract: An aircraft comprising at least one electric drive system configured to drive a wheel of a landing gear in rotation and at least one energy receiving element configured to power the electric drive system and cooperate with an energy emitting element present on the ground, the energy receiving and emitting elements forming an electrical energy transfer device allowing, when the aircraft is moving on the ground, a transfer of electrical energy from the energy emitting element to the energy receiving element.

Abstract: A mechanical speed reducer, in particular for a device for driving at least one wheel of an aircraft landing gear, this reducer including a first sun gear including external toothing, first planet gears meshed with the external toothing of the first sun gear, these first planet gears being carried by a first planet carrier, a stationary ring gear meshed with the planet gears, and second planet gears meshed with a ring gear and with an external toothing of said first planet carrier, these second planet gears being carried by a second planet carrier.

Abstract: A device for driving at least one wheel of an aircraft landing gear is provided. The device includes at least one wheel having a rim, an electric motor having a shaft, and a mechanical transmission system for mechanical transmission between the shaft of the motor and the rim. The mechanical transmission system includes a mechanical reduction gear. The mechanical reduction gear includes a sun gear secured in rotation to the shaft and having an external toothing, a stationary ring gear with internal toothing, a movable ring gear secured in rotation to the rim and having an internal toothing, and planet gears that are meshed with the sun gear and each have two external toothing meshed respectively with the toothing of the stationary and movable ring gears.

Abstract: A propeller according to an embodiment includes a hub and a series of blades extending outward from the hub. Each blade of the series of blades includes a core and a skin covering the core. The core may be formed of a ceramic first material and the skin is formed of a second material different than the ceramic first material. The ceramic first material of the core may be ceramic Si3N4 (silicon nitride), yttria-toughened zirconia ceramic, or alumina-zirconia ceramic, and the second material of the skin may be a polymer. The polymer skin is configured to function as a shock absorber protecting the ceramic core, and the ceramic core is configured to provide rigidity to maintain the shape of the propeller blades under aerodynamic loading, which enables improved aerodynamic efficiency and reduced noise generation.

Abstract: A method for transmitting power based on aerodynamic deceleration, a structure and an application thereof; a method for transmitting power based on aerodynamic deceleration is to propel a large rotor wing without driving force to rotate using an airflow generated by the rotation of small rotor wings with driving force; a structure for transmitting power based on aerodynamic deceleration, includes a large rotor wing, a small rotor wing, a main shaft and a power assembly; the large rotor wing is rotatably connected to the main shaft, and the large rotor wing rotates around the main shaft; the small rotor wing is connected to the power assembly.

Abstract: A portion of a vertical structure is determined for inspection by an unmanned aerial vehicle. A flight plan including safe locations around the vertical structure is determined. Each of the safe locations is associated with a respective column of waypoints. The unmanned aerial vehicle navigates according to the flight plan by navigating to a first safe location of the safe locations, navigating vertically along a first column associated with the first safe location, activating sensors to obtain respective sensor information at at least some of the waypoints associated with the first safe location, navigating to a second safe location of the safe locations, navigating vertically along a second column associated with the second safe location, and activating the sensors to obtain respective sensor information at at least some of the waypoints associated with the second safe location.

Abstract: A tilt prop aircraft is provided, including a first longeron and a second longeron capable of tilting relatively to each other, a tilt actuator disposed on the second longeron, a first power transmission member rotated by the tilt actuator, a second power transmission member fixed to the first longeron and coupled to the first power transmission member to transmit a rotational movement of the first power transmission member by turning 90 degrees in different planes, a crank fixed to the second longeron and extending through a slot in the first longeron and protruding inwardly from the first longeron, and a connecting rod connected to the crank so as to be relatively rotatable to the crank, and connected to the pitch control rod.

Abstract: A method for enhancing movement or autonomy, including movement or flight of vehicles or flight vehicles in communication and or GPS degraded and or denied and or non-optimal environments is presented, where 3D area maps and or area maps may be employed, and 3D area maps and or area maps employed may include embedded position, location or GPS date, where the location or GPS data may be used in the present invention to determine vehicle location through image recognition, and using the GPS coordinates or location from the 3D area map of the image recognized, or measuring distance to other know aspects of a 3D area map in the real world, and context or system level information may also be used to estimate obstacle shapes and optimal routes in a potential route of travel or for understanding an area.

Abstract: A method for emitting a fluid from a fluid dispersal system includes determining a desired distribution profile for the fluid, identifying a plurality of sections of the desired distribution profile, and determining, for each section of the plurality of sections of the desired distribution profile, an amount of fluid required from each nozzle assembly of the plurality of nozzle assemblies needed to deposit fluid according to the desired distribution profile within the corresponding section. The method also includes determining a target emission rate of the fluid from each nozzle assembly of the plurality of nozzle assemblies based on the determined amount of fluid required from each nozzle assembly, and controlling an operating parameter of a valve assembly of each nozzle assembly to obtain the respective target emission rate from each nozzle assembly.

Abstract: Provided are an unmanned aerial vehicle and a method that enable mounting work for a package and a battery to be efficiently performed. The unmanned aerial vehicle includes a package-chamber tray, a package-chamber cover attached to the package-chamber tray from above, a battery provided on an upper surface of the package-chamber cover, and a body capable of flying, the body being attachable and detachable to and from a package chamber formed by the package-chamber tray and the package-chamber cover. First, packages are placed on the package-chamber tray. Next, the package-chamber cover is attached to the package-chamber tray. Next, the battery is placed on the package-chamber cover. At this time, the mounting position of the battery is adjusted in accordance with the center of gravity position of the entirety of the packages. Then, the body is attached to the package chamber.

Abstract: An assembly for an energy attenuation system is described. The assembly offers a lower profile configuration that fits better into tight spaces that exist in the compact seats that are required for military helicopters. The assembly includes a cable that is oriented and positioned to work with the profile. The assembly includes an actuator which ejecting the pins in a multi-stage sequence. The design of the assembly also ensures the pins cannot back drive when the pins are in the ejected position. Additionally, the pins may have part commonality reducing a unique part of the assembly.

Abstract: An environmental control system of a vehicle includes a first inlet configured to receive a flow of a first medium, a second inlet configured to receive a flow of a second medium, and a thermodynamic device including a compressor and at least one turbine operably coupled by a shaft. The compressor and the at least one turbine are fluidly coupled to the first inlet. The compressor and the at least one turbine are arranged in parallel relative to the flow of the first medium such that a first portion of the first medium is receivable at the compressor and a second portion of the first medium is receivable at the at least one turbine.

Abstract: A canopy attachment yoke, comprising: first and second support bars, each having a first end and a second end, wherein the respective first ends are configured for attachment to at least one support line of a canopy and the respective second ends are configured for attachment to a vehicle; and at least one spreader bar having a first end and a second end, the first end of the spreader bar connected to the first support bar and the second end of the spreader bar connected to the second support bar, wherein the spreader bar is slidably mounted on the first and second support bars.

Abstract: Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

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 (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 a first aspect, described herein is a direct drive electric aircraft propulsion wherein the propulsion rotor torque is decoupled from the primary proprotor mast moment forces. A hub shaft locates the propulsion proprotor assembly in space relative to the aircraft nacelle, while a motor torque coupler transfers torque from the electric motor to the propulsion rotor while resolving a negligible amount of mast moment through the electric motor.

Abstract: A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

Abstract: An assembly is provided for an aircraft. This assembly includes a variable area inlet for an aircraft propulsion system. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage and an outer inlet passage. The inlet door is configured to move outward from a closed position to an open position. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends into the inlet structure to the inner inlet passage.

Abstract: An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.

Abstract: Propulsion system (2) for a helicopter (1) comprising a main engine (9), a main rotor (3), a main gearbox (4) including an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an assistance device (10). The assistance device (10) comprises a first electric machine mechanically coupled to the reduction gearbox (13) and configured to operate as an electric generator to take off energy produced by the main engine (9), and a second electric machine mechanically coupled to a second input of the main gearbox (4), the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox (4).

Abstract: In one embodiment, systems and methods include using an evaporator coil with a solid oxide fuel cell generator to generate energy for an aircraft vehicle. The system comprises a solid oxide fuel cell generator operable to generate energy. The system further comprises a first tank fluidly coupled to the solid oxide fuel cell generator configured to discharge a fluid to the solid oxide fuel cell generator and to receive the fluid from an evaporator coil coupled to the solid oxide fuel cell generator. The system further comprises a second tank fluidly coupled to the first tank and having a volume of the fluid, wherein the second tank is configured to discharge the fluid to the first tank, wherein the evaporator coil receives the discharged fluid from the second tank and increases the temperature of the discharged fluid prior to the first tank receiving the discharged fluid.

Abstract: A method of recovering fuel vapour from a fuel tank of an aircraft, is disclosed. The aircraft includes a fuel tank; a wing with an upper surface and a lower surface; and an opening in the lower surface of the wing. The method includes coupling an inlet of a vapour recovery system to the opening; capturing fuel vapour from the fuel tank which flows out of the opening with the inlet of the vapour recovery system; and collecting the captured fuel vapour in a vapour storage tank of the vapour recovery system.

Abstract: Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for receiving data related to a first flight risk factor and a second flight risk factor where the first and second risk factors include one of: a proficiency risk factor, an equipment risk factor, an environmental risk factor, or a performance risk factor. Applying a first weighting to the first flight risk factor to generate a first weighted flight risk factor, and applying a second weighting to the second flight risk factor to generate a second weighted flight risk factor. Assessing a flight risk level for a flight based on the first weighted flight risk factor and the second weighted flight risk factor. Providing data indicating the assessed flight risk level for the flight for display to a user.

Abstract: An aircraft is described. The aircraft includes an avionics management system including one or more control display units. The control display units include an alphanumeric keyboard. By the alphanumeric keyboard, an operator within the aircraft may input a personal identification number (PIN). The input PIN is received from the alphanumeric keyboard and compared with a PIN stored in memory. When the input PIN is validated, the avionics management system changes a system state from not validated to validated, thereby permitting the control display unit to access otherwise unavailable mobile user objective system (MUOS) feature sets, such as viewing MUOS presets or tuning to the MUOS presets.

Abstract: An aircraft beacon light includes a plurality of primary light sources for emitting light into at least two spatial sectors, wherein the at least two spatial sectors include a forward sector and at least one of an aft sector, a starboard lateral sector, and a portside lateral sector; and a light transmissive cover, which covers the plurality of primary light sources. The plurality of primary light sources are arranged and configured for providing an FAR-compliant aircraft beacon light output of the aircraft beacon light, in case of the light transmissive cover being in a non-eroded state. The aircraft beacon light also includes at least one booster light source for selectively emitting a booster light output into the forward sector. The at least one booster light source is controllable independently of the plurality of primary light sources.

Abstract: A removable canopy, such as for placement above an entry into a vehicle, includes a brace having releasable mounting features for mounting to the vehicle. The canopy further includes a linkage extending from the brace and convertible from a folded configuration to an extended configuration and a cross bar connected to the linkage so as to be nearer the brace when the linkage is in the folded configuration than when the linkage is in the extended configuration. A sheet is connected to the cross bar and the linkage so as to be folded when the linkage is in the folded configuration and extended when the linkage is in the extended configuration.

Abstract: A system for positioning vehicle components relative to each other on a floor to prepare an assembly. A plurality of carriers receive a vehicle component. A plurality of positioning tables have a lower portions which can be fixed to the floor and a upper portions which receive a carrier. A location device having at least one base and mobile units moveable relative to the base. At some of the positioning tables moves the respective upper portion along at least two movement axes relative to the respective lower portion to position a carrier located thereon. A transport device guides the carriers from an external position to a positioning table and to place them on the upper portion. The location device determines the positions of the respective mobile units relative to the at least one base. A position control unit controls a movement of the upper portions to a predetermined target position.

Abstract: A system for scanning or inspecting an aircraft or spacecraft surface. A ground vehicle has a first inspection device, a hovering platform has a second inspection device. The first inspection device is on a first arm of the ground vehicle. The ground vehicle comprises a vertical pole and a transverse holding element extends therefrom. The hovering platform is electrically connected to the ground vehicle through a cable for transferring electrical power and/or data to the hovering platform. The vertical pole and/or transverse holding element carry the cable. The hovering platform is flexibly held on the vertical pole and/or the transverse holding element through the cable or an additional component. The inspection devices determine a characteristic of the surface and identify points of shape deviation by comparison with an intended characteristic. The system successively inspects the surface through the inspection devices being arranged in different heights at the same time.

Abstract: A surveillance satellite (100) of a surveillance system (310) transmits flying object information, which is generated by monitoring a flying object (520), to a coping system (330) via a communication satellite (200) of a communication system. A defense information integration center (350) includes a communication route search device (470) for satellite information, a flight path prediction device (5490) predicting a flight path of a flying object, and a coping asset selection device (333). The defense information integration center (350) transmits an instruction command to a surveillance satellite group included in the surveillance system (310), a communication satellite group included in the communication system (320), and a coping asset (332).

Abstract: A monitoring system (404) includes a plurality of monitor satellites (307) and a monitoring ground center (810). A satellite information transmission system (403) includes a plurality of communication satellites including communication devices. A coping system (405) includes land, sea, and air coping assets to cope with a flying object. A flying object coping system (401) transmits flying object information, generated by the monitoring system (404) that monitors a flying object (601), to the coping system (405) via the satellite information transmission system (403). The monitoring ground center (810) includes a communication route search device (811) and a flight path prediction device (803) and transmits order commands to a communication satellite cluster included in the satellite information transmission system (403).