211results about "Cosmonautic ground equipments" patented technology

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

The invention discloses a reusable carrier rocket marine landing recovery device which comprises a tower body, a driving module, a first mechanical capturing arm, a second mechanical capturing arm, a first clamping arm and a second clamping arm. The tower body comprises first to fourth stand columns and first to eighth cross beams; the driving module comprises first to twelfth driving units; each of the first to twelfth driving units comprises a driving motor, a working track, a lead screw nut, a first bearing, a second bearing, a first bearing seat and a second bearing seat. On the premise that a simple electric control system is adopted, marine recovery of the carrier can be achieved, the structure is simple, response is rapid, good reliability and maintainability are achieved, the device is suitable for recovery tasks of carrier rockets of various models, and the launching cost is effectively reduced.

The invention discloses a mobile medium-large liquid carrier rocket capturing and recycling system, and relates to the technical field of rocket recycling. According to the mobile medium-large liquid carrier rocket capturing and recycling system, through the mobile platform design that a crane is adopted to carry a connecting truss, a switching frame and a capturing arm, rocket body information is obtained in real time in combination with a camera module, a rocket position sensor and the like, and interaction with a ground center is achieved through a data transmission module; the control module accurately controls the transmission assembly to adjust the capturing arm, the buffering assembly is matched to absorb impact, and a parachute landing mode is replaced to improve the control precision. According to the movable characteristic, the dependence on a fixed land or seaborne recovery site is reduced, the site construction and maintenance cost is reduced, the influence of environmental factors on recovery is reduced, and the problems that in an existing medium-large liquid carrier rocket recovery technology, parachute landing control is difficult, the land / seaborne recovery cost is high, and the influence of the environment is large are solved.

The invention relates to the technical field of spaceflight launching, and provides a swarm-type spaceflight launching system and method, and the system comprises a honeycomb system, a nectar source system, and a bee passage system. The honeycomb system is a technical area for spaceflight launching, is connected with the nectar source system through the bee passage system and is used for completing a satellite-rocket combination; the plurality of nectar source systems are arranged around the honeycomb system, and each nectar source system comprises a plurality of emission positions; the bee passage system is connected with the transmitting position and the honeycomb system and comprises a plurality of traffic roads. According to the scheme, a large number of satellites with different orbits can be launched in a short time, and the satellite launching efficiency is improved.

The invention discloses a reusable carrier rocket ground active recovery system and recovery method.The system comprises a landing buffer mechanism, an omnidirectional self-driven carrying platform, a rocket body posture auxiliary stabilizing mechanism and a landing structure, the landing structure comprises bearing feet, the bearing feet are located on a rocket, and a positioning device is arranged on the omnidirectional self-driven carrying platform; the rocket body posture auxiliary stabilizing mechanism comprises two pairs of clamping rods which are arranged in parallel in a staggered mode, the two ends of each clamping rod are located on a sliding table, the clamping rods are driven by the sliding table to move, and the sliding table is located on a sliding rail; the landing buffering mechanism is located on the omni-directional self-driven carrying platform and comprises a force bearing buffering base and a flexible contact pad located on the force bearing buffering base. The rocket recovery control difficulty is reduced while the carrying capacity of the rocket is guaranteed, and the rocket recovery control device is reasonable and stable in structure, capable of being applied to recovery of rockets of multiple specifications, wide in applicability and wide in application prospect.

A system and method are disclosed for softly capturing, protecting, and landing a spacecraft returning from space using a VTOL (vertical takeoff and landing) aircraft including drones and helicopters. The spacecraft is decelerated by a parachute. One or more VTOL drones transport a waterproof pocket that catches and captures the descending spacecraft in the air. In this way, the spacecraft is protected inside the pocket and, after continuing to descend, makes a soft landing in a body of water. In another embodiment, a recovery helicopter, which is a type of VTOL aircraft with heavy-lift capabilities, is used to directly catch the returning spacecraft. One or more VTOL drones are attached to the lower end of a recovery cable suspended from the helicopter. These drones carry a clutch that directly, quickly, and accurately catches the descending spacecraft without interfering with the parachute. In this way, the spacecraft is caught and protected by the helicopter while maintaining the floating function of the parachute.

The invention discloses a method and a system for realizing continuous freezing filling of an electric propellant by controlling xenon phase change, and relates to the technical field of xenon filling control, the method comprises the following steps: connecting a full xenon bottle into equipment to be filled, and carrying out pressure equalizing operation on the equipment to be filled; introducing the residual xenon gas in the xenon gas bottle into a xenon gas liquefier, so that the residual xenon gas is liquefied into liquid xenon in the xenon gas liquefier; liquid xenon is injected into the liquid xenon collection bottles, collection is stopped when the first liquid xenon collection bottle reaches a preset liquid level, and a communication valve between the second liquid xenon collection bottle and the xenon liquefier is opened for collection; a heater at the bottom of the first liquid xenon collecting bottle is started to gasify the liquid xenon, and a pressure sensor is used for detecting internal pressure data of the first xenon collecting bottle and the to-be-filled equipment; performing temperature-controlled filling on the to-be-filled equipment; when the filling equipment reaches the rated filling amount, filling is stopped, and the filling amount is rechecked; and when the xenon filled into the equipment is detected to be unqualified, recycling the unqualified xenon into a recycling gas cylinder through a plunger pump.

A maskless touch up tool having a faceplate and handle. The faceplate is placed on a surface for touching up of a coating on the surface. The surface may be on a rocket body. The faceplate may form a seal around a target region of the surface. The faceplate has an opening configured to receive a touch up coating therethrough for application of the touch up coating to the surface. The handle may extend away from the faceplate and be configured for gripping by a user. The tool may include a reservoir, or an attachment for an external container, configured to collect excess touch up coating from the surface. The tool may be used to touch up the surface coating without the need for masking of the surface.

In a system where multiple satellites autonomously take turns acting as servers, the servers will be rotated according to instructions from a ground station. [Solution] The server, which is a satellite 200 that has obtained server rights, receives a priority notification when a ground station 300 transmits the priority notification. If the server receives the priority notification, it selects the satellite 200 specified in the priority notification as the server for the next time interval. If the server does not receive the priority notification, it selects one of the multiple satellites as the server for the next time interval based on the status information of the server and the status information of each client.

Systems and methods using VTOL (vertical take-off and landing) aircrafts including drones and helicopters for soft capture, preserving, and landing of a returning spacecraft from space are disclosed. The spacecraft is decelerated by parachutes. One or multiple VTOL drones transport a water impermeable pocket meeting and capturing the descending spacecraft in the air. The spacecraft is thus preserved inside the pocket and keeps descending and then softly lands in a body of water. In another embodiment, a recovery helicopter, one type of VTOL aircraft with heavy payload lifting capacity, is used to directly catch the returning spacecraft. One or multiple VTOL drones are coupled to the bottom end of a recovery cable hung from the helicopter. These drones bring a clutch quickly and precisely catching the descending spacecraft directly without interrupting the parachutes. The spacecraft is thus caught and preserved by the helicopter with lifting function of the parachutes maintained.

The invention is notably directed to an aircraft carrier ground vehicle (10), which comprises a chassis (102), a landing platform (104), a coupling mechanism (106), and an actuation mechanism (108). The landing platform is designed to accommodate an aircraft (20). The coupling mechanism connects the landing platform to the chassis to form a kinematic pair, in which the landing platform is rotatably mounted on the chassis. The actuation mechanism is adapted to rotate the landing platform relative to the chassis, to allow an aircraft to land on the landing platform as the vehicle moves along a landing direction of the aircraft and compensate for an inclination angle of the aircraft on landing, in operation. The aircraft carrier ground vehicles may further be designed to allow taxiing and take-off of the aircraft. The invention is further directed to related aircraft carrier ground vehicle systems, which include several vehicles that are swarmed for landing an aircraft, as well as aircraft landing and take-off methods.

The invention relates to a ground heating control method and device for an auxiliary power system of a low-temperature carrier rocket. The method comprises the steps that a first microcontroller obtains an initial parameter and a heating initial parameter of an upper computer auxiliary power system, and obtains real-time temperatures, transmitted by a second microcontroller, of an on-rocket thrust chamber, a storage box, an electromagnetic valve and a guide pipe; controlling an on-rocket heating loop according to the initial parameters, the heating initial parameters and the real-time temperatures of an on-rocket thrust chamber, a storage tank, an electromagnetic valve and a guide pipe; and / or, the second microcontroller obtains an upper computer auxiliary power system initial parameter, a heating initial parameter and a temperature measurement loop sensor resistance value, and determines the real-time temperature of the rocket heating loop based on the heating loop current, the temperature measurement loop sensor resistance value, the initial parameter and the heating initial parameter; and the heating current and the temperature measurement temperature on the rocket are sent to a first microcontroller and an upper computer. According to the application, the blank of the ground heating control device of the auxiliary power system can be filled, and unattended operation before the auxiliary power system is launched is realized.

A propulsion-based payload transporter (PPT) and methods of its operation are provided. The PPT may operate in a gravitational field such as that on the lunar surface. Via rocket engines that produce thrust, the PPT is configured to descend onto and over a payload to be moved. Once in position with respect to the payload, latches engage with the payload so as to secure the payload in a payload holding bay of the PPT. The rocket engines produce thrust with an exhaust plume that is angled away from the payload to avoid payload damage. The rocket engines, which are located at the sides of the payload holding bay, produce thrust to propel the PPT and the payload in a substantially horizontal trajectory with respect to gravity and toward a landing destination.

This invention is embodied in a system and device for transporting assets (small satellites, commodities, or other payloads) in space. The preferred system comprises a scaffold of relay stations strategically orbiting one or more celestial bodies. The orbits are complimentary to each other so that the relay stations can transfer mass from one station to another. In this way, the system can support different logistical networks connecting the space between orbits such as Low Earth orbit (LEO), geostationary orbit (GEO), and Low Lunar orbit (LLO), and even between Earth and Mars.

A Z-shaped layout fixed-length dual-rope-grouped closed force system capture and recovery net system, comprising: a capture and interception assembly, which comprises a rope group a (1), a rope group b (2), a rope group c (3) and a rope group d (4), wherein the rope group a (1), the rope group b (2), the rope group c (3) and the rope group d (4) are each wound around two movable pulley blocks (5), the two movable pulley blocks (5) being arranged opposite each other, and the rope group a (1) between the two movable pulley blocks (5) is an interception section a (6), the rope group b (2) between the two movable pulley blocks (5) is an interception section b (7), the rope group c (3) between the two movable pulley blocks (5) is an interception section c (8), and the rope group d (4) between the two movable pulley blocks (5) is an interception section d (9); and a support assembly which comprises four stand columns (10), wherein the four stand columns (10) are fixedly connected to a base (11), a guide rail (12) is fixedly connected between every two adjacent stand columns (10), the movable pulley blocks (5) are slidably connected to the guide rails (12), and are in transmission connection with a traction device (15), a plurality of fixed pulleys (13) are provided on the stand columns (10), and the rope group a (1), the rope group b (2), the rope group c (3) and the rope group c (4) are each wound around a different fixed pulley (13). The capture and recovery net system can effectively reduce the length of the rope group a (1), the length of the rope group b (2), the length of the rope group c (3) and the length of the rope group d (4), and can also reduce the force and work of the traction device.

The application relates to a detachable guide rail type launch vehicle pre-launch heating and keeping warm device, which comprises a detaching mechanism and a heating and keeping warm mechanism; in a storage state, the detaching mechanism and the heating and keeping warm mechanism are independent of each other and are stored separately; in a heating working state, the heating and keeping warm mechanism is lifted by the detaching mechanism, and the heating and keeping warm mechanism heats and keeps warm the vehicle; and in a launch separation state, the detaching mechanism takes the heating and keeping warm mechanism away from the guide rail type launch device of the guide rail type launch vehicle, so that the vehicle can normally leave the rail. The application can ensure normal heating and keeping warm functions before and after the small and medium-sized vehicle is erected, and can make the heating and keeping warm device reliably detach through manual or electric ways 5 minutes before the vehicle is launched, so that the normal launch of the vehicle is not affected.

The present invention is embodied in systems and devices for transporting assets (small satellites, goods, or other payloads) in outer space. A preferred system comprises a scaffold of relay stations strategically orbiting one or more celestial bodies. Since the orbits are complementary to each other, the relay stations can transport mass objects from one station to another. In this way, the system can support various logistics networks connecting space between orbits such as low Earth orbit (LEO), geostationary orbit (GEO), and low lunar orbit (LLO), as well as space between Earth and Mars.

The invention relates to a multi-source electromagnetic matrix aircraft take-off and landing system and a waste heat utilization and building integration method thereof, and belongs to the technical field of aircraft take-off and landing. The system comprises at least three electromagnetic emission units which are arranged in a space array, and each electromagnetic emission unit comprises an independent controllable excitation coil; the central controller is used for independently adjusting current parameters of each electromagnetic emission unit; the at least three electromagnetic emission units act together to form at least four independent and controllable electromagnetic stress action points in a predetermined space area. The system comprises a building facade integration system, a waste heat recovery system and a military application system (space debris cleaning and aerospace vehicle launching). The system has the multiple advantages of high control dimension, high magnetic field intensity, low cost, mobility, building embeddability, comprehensive energy utilization, military and civilian dual-purpose, military defense value and the like, and can be used as a general take-off and landing infrastructure in the fields of urban air traffic, military aviation, spaceflight launching, military defense and the like.

The application provides a rocket erecting frame overturning docking device and a docking method thereof, and the device comprises an overturning docking base, overturning docking blocks, a rotating assembly, an erecting oil cylinder assembly and a hydraulic chuck mechanism; the overturning docking base is a main torsion-resistant mechanism during the overturning process of the erecting frame, and high-strength steel is selected as the material; the overturning docking blocks are arranged on the left and right sides of the overturning docking device and are symmetrically arranged, the bottom of the overturning docking block is connected with the overturning docking base; the upper surface of the overturning docking block is reserved with connecting hole positions of the erecting frame and the hydraulic chuck mechanism, and the inner cavity is provided with an interface connected with the upper fulcrum of the erecting oil cylinder. The adjustment and positioning of the erecting frame are completed through the expansion of the hydraulic chuck. The docking method can realize the accurate posture positioning of the erecting frame in a short time, increases the reliability and efficiency of the docking, reduces the docking time and the participation degree of manpower, and reduces the safety risk to a certain extent.

The application relates to a modular quick-assembly and opening type launching station aircraft protection device scheme and belongs to the technical field of launching protection devices. The device is composed of a plurality of basic modules, each basic module is designed by using quick-guiding positioning, quick hoisting positioning can be realized, a plurality of groups of quick-assembly mechanisms are arranged to be connected with quick locking / unlocking, quick fixing between the modules can be realized after installation, an integrated protection device is formed, and the protection device is convenient for quick assembly and opening.

Orbital Elevator with Magnetic Rail Propulsion System: The invention relates to an orbital elevator designed to transport payloads between Earth and geostationary orbit. The system uses an ultra-strong, multi-strand cable made of carbon nanotubes to withstand gravitational and centrifugal forces. A transport module (climber) equipped with magnetic rails is in continuous contact with the cable, enabling stable, frictionless propulsion and precise control of movement along the cable. An integrated emergency braking system allows the climber to be stopped if necessary, thus enhancing transport safety. The ground base, which anchors the cable, includes a control center to monitor the movement of the modules and maintain structural tension. An orbital counterweight completes the system, stabilizing the cable through dynamic equilibrium.

The invention provides a rocket launching pad hydraulic system. The rocket launching pad hydraulic system comprises an oil source, a plurality of sets of control valve sets and a plurality of execution hydraulic motors. The oil source is connected with a plurality of execution hydraulic motors through a plurality of sets of control valve groups; each set of control valve group is connected with one or more execution hydraulic motors; each set of control valve group is used for controlling one or more execution hydraulic motors connected with the control valve group; the oil source outputs high-pressure oil, and the high-pressure oil is conveyed to the execution hydraulic motor through the control valve set and used for driving the execution hydraulic motor to rotate. The execution hydraulic motor is connected with the supporting disc or the windproof pressing device on the launching pad and drives the supporting disc or the windproof pressing device to act. The operation convenience of the hydraulic system controlled by the multiple hydraulic motors is improved, simultaneous action or independent action of the multiple hydraulic motors can be achieved, variable torque output control or high and low speed rotation control of the single hydraulic motor can be achieved, and all redundant backup is achieved from the angle of safety.

Disclosed is a Z-shaped layout fixed-length double-rope grouped closed force system capturing and recycling net system. The system includes a capturing and intercepting assembly which includes a rope group a, a rope group b, a rope group c, and a rope group d that are each wound with two movable wheel groups oppositely arranged, the rope group a between the two movable wheel groups is an intercepting section a, the rope group b between the two movable wheel groups is an intercepting section b, the rope group c between the two movable wheel groups is an intercepting section c, and the rope group d between the two movable wheel groups is an intercepting section d. The disclosure can effectively decrease the lengths of the rope group a1, the rope group b2, the rope group c3 and the rope group d4 and the force and work of traction devices.

The invention provides a multi-load observation task planning method, which comprises the following steps of: after any load on a satellite triggers an observation task, converting the position of an observation target into a position in a reference load view field, then calculating a constraint condition according to the position of the observation target in the reference load view field, comparing the constraint condition with a preset condition, and if the preset condition is met, determining that the observation target is a target. If not, the task is cancelled. By setting the reference load and calculating the constraint condition based on the reference load, it can be ensured that all loads in the observation task can observe the target, and then the task success rate and the observation accuracy are ensured.

The invention provides a supporting device. The supporting device is used for a carrier rocket sub-stage power system test run and comprises a supporting frame, a first supporting frame and a second supporting frame, the multiple stand columns are detachably connected to the lower portion of the first platform assembly. The first platform assembly comprises a first platform and a bearing frame; a first through groove is formed in the center of the first platform, and the bearing frame is detachably connected with the inner circumferential wall of the first through groove; the lower surface of the transfer frame is detachably connected with the bearing frame, and the upper surface of the transfer frame is configured to be detachably connected with the bottom end of the carrier rocket sub-stage power system; one end of the mooring tool is detachably connected with the first platform, and the other end of the mooring tool is constructed to be detachably connected with the top end of the carrier rocket sub-stage power system; therefore, the supporting device can be quickly disassembled and assembled and is convenient to transport. Moreover, the mooring tool provides a downward pulling force, so that the phenomenon that the carrier rocket sub-stage is out of control and flies off due to accidents in the test run process of the carrier rocket sub-stage power system can be avoided.

The invention discloses an equipment six-degree-of-freedom automatic posture-adjusting docking device applying a binocular vision system, belongs to the technical field of cabin docking, and solves the problems that the mounting effect of a cabin docking device in the prior art depends on the experience of operators, and the mounting stability is poor. The invention discloses an equipment six-degree-of-freedom automatic posture adjusting and docking device applying a binocular vision system. The equipment six-degree-of-freedom automatic posture adjusting and docking device comprises a horizontal walking mechanism, a binocular vision camera, a first docking section posture adjusting mechanism and a second docking section posture adjusting mechanism. The binocular vision camera can shoot the postures of the butt joint sections on the first butt joint section posture adjusting mechanism and the second butt joint section posture adjusting mechanism in real time. The positions of the first butt-joint section and the second butt-joint section are recognized through the binocular vision camera, butt joint of the first butt-joint section and the second butt-joint section is achieved by controlling the horizontal walking mechanism, the first butt-joint section posture adjusting mechanism and the second butt-joint section posture adjusting mechanism, and dependence on experience and level of operators is avoided; and the butted cabin sections have good stability and consistency.

A space transportation system (1) intended to be mounted on a space launcher (100) comprising a re-ignitable propulsion device (2), steerable flaps (3) arranged at a second end (12), and a monitoring unit (4), each flap (3) comprising an actuation means configured to change the orientation of said flap (3), said monitoring unit (4) being configured to: · a launch step in which the propulsion device (2) is off and the flaps (3) are in the retracted position; a return step in which the monitoring unit (4) deploys the flaps (3) and individually controls the orientation of the flaps (3) to slow down the system (1), while the propulsion device (2) is off; A landing step in which the monitoring unit (4) controls the propulsion device (2) and the actuation means to orient and slow down the flaps (3) and roll over the system (1). In order to carry out the above, the activation of the propulsion device (2) is controlled and the orientation of the flap (3) is individually controlled.

The present invention is a recovery system for recovering a spacecraft that drops a fuselage while generating thrust when landing. The recovery system includes: a plurality of cable members connected to the fuselage and extending toward the outside of the fuselage at the time of fuselage dropping; a plurality of unmanned aircraft that respectively seize the cable members and fly; and a recovery structure that is provided at a landing location of the spacecraft, and that supports the spacecraft in a suspended state as a result of the seized / released plurality of cable members being latched to the unmanned aircraft. At the time of fuselage dropping, the recovery system executes: a step in which the plurality of unmanned aircraft latch the seized plurality of cable members to the recovery structure; a step in which the plurality of unmanned aircraft releases the seizing of the cable members; and a step in which, after thrust stoppage of the spacecraft, the recovery structure suspends and supports the spacecraft.

Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process.

The invention provides a flexible solar wing unfolding test device and test method, and relates to the technical field of spacecrafts, the flexible solar wing unfolding test device comprises a one-dimensional unfolding unloading mechanism and a two-dimensional unfolding unloading mechanism; in the one-dimensional unfolding unloading mechanism, a first air floating sliding block is arranged on a transverse guide rail in a sliding mode, and the first air floating sliding block is connected with the flexible solar wing through a lifting assembly. In the two-dimensional unfolding unloading mechanism, a second air floating sliding block of a first tackle assembly is arranged on a first longitudinal guide rail in a sliding mode. The first connecting pieces of the first tackle assembly are correspondingly connected with the flexible solar wings respectively; a sliding block of the second pulley assembly is slidably arranged on the second longitudinal guide rail through a rolling piece. And the second connecting pieces of the second pulley assembly are correspondingly connected with the flexible solar wings respectively. According to the flexible solar wing unfolding test device, continuous verification of the solar wing in one-dimensional and two-dimensional unfolding processes can be realized, so that the unfolding reliability and safety of the solar wing are ensured.