271results about "Cosmonautic ground equipments" patented technology

The invention relates to the field of rocket recovery, and discloses a rocket capture arm and a recovery tower. The rocket capturing arm comprises a main body; the supporting piece is arranged on the main body in a liftable mode through a first connecting rod assembly and a second connecting rod assembly and used for supporting a rocket; the first connecting rod assembly comprises at least two first connecting rods arranged in the vertical direction, one end of each first connecting rod is rotationally connected with the body, and the other end of each first connecting rod is rotationally connected with the supporting piece. The second connecting rod assembly comprises at least two second connecting rods arranged in the vertical direction, one end of each second connecting rod is rotationally connected with the body, the other end of each second connecting rod is rotationally connected with the supporting piece, and the plane where the second connecting rod assembly is located and the plane where the first connecting rod assembly is located form an angle. The buffering assembly is connected between the main body and the supporting piece and used for providing resistance in the descending process of the supporting piece. The non-coplanar layout of the two sets of connecting rod assemblies constructs a composite supporting structure in a three-dimensional space, so that the degree of freedom of an original single-plane four-connecting-rod is counteracted by rigid constraint of crossed connecting rods.

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 relates to the technical field of carrier rocket transfer, in particular to a carrier rocket transfer device which comprises a carrier and a position adjusting mechanism. The carrier is used for bearing and transporting the erecting arm carrying the carrier rocket so as to transfer the carrier rocket to the position close to the fixed launching pad. The position adjusting mechanism is installed on the carrier. The carrier can drive the position adjusting mechanism to move up and down so as to drive the erecting arm to move up and down. The position adjusting mechanism can drive the erecting arm to move or rotate in the plane where the position adjusting mechanism is located. When the rotating base arranged at one end of the erecting arm is in butt joint with the rotating base arranged on the fixed launching pad, the erecting arm is driven by the carrier to conduct position coarse adjustment, then the erecting arm is driven by the position adjusting mechanism to move or rotate in the plane where the position adjusting mechanism is located, the position of the erecting arm is accurately adjusted, the butt joint difficulty is greatly reduced, and the butt joint efficiency is improved. The butt joint precision and the butt joint efficiency are improved when the rotating seat of the erecting arm is in butt joint with the rotating seat of the fixed launching pad.

The system extracts water from lunar regolith and includes a regolith intake having a digging bucket that collects lunar regolith soil and a gravel separator that separates and discharges gravel and passes a mixture of ice-regolith powder having ice grains that are about 10-100 microns along the conveyor. A pneumatic separator receives the ice-regolith powder and pneumatically splits the ice-regolith powder into streams of different sized lithic fragments and ice particles per the ratio of inertial force and aerodynamic drag force of the lithic fragments and ice particles. Each split stream may include a magnetic separator that separates further the magnetic and paramagnetic lithic fragments from ice particles to discharge up to 80 percent of lithic fragments to slag.

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.

Systems and methods for securing an upright rocket. The rocket may be on a moveable platform, such as a landing area of a ship. The rocket may land on the deck, and the system may include cables that surround the landing area. The cables may be tightened about the rocket after the rocket has landed in an upright position. The system may include poles that telescope upward, such that the cables may tighten about the upright rocket at various heights along the body of the rocket.

The invention discloses a propellant filling system of a liquid rocket, which relates to the technical field of spaceflight and comprises movable filling equipment, a tank car / standard container for providing a propellant and a PLC (Programmable Logic Controller) system, wherein the movable filling equipment is communicated with a liquid oxygen storage tank or a kerosene storage tank of the tank car / standard container and the liquid rocket; the PLC system is in communication with the mobile filling equipment, the mobile filling equipment is controlled by the PLC system to execute a filling procedure in a corresponding filling mode, and the filling mode at least comprises a pump type filling mode and an extrusion filling mode; when the lift is larger than the preset first height, the PLC system controls the movable filling equipment to execute the filling procedure in a pump type filling mode; and when the lift is smaller than the preset second height or the flow is smaller than the preset flow, the PLC system controls the movable filling equipment to execute the filling procedure in an extrusion filling mode. The device has multiple filling modes and can be suitable for different filling occasions.

The invention discloses an offshore recovery device and method for a deep and far sea type carrier rocket, and belongs to the technical field of rocket recovery. The offshore recovery device for the deep and far sea type carrier rocket comprises a recovery platform which can float on the sea; the stabilization water cabin is arranged in the recovery platform; and the active stabilization device comprises a plurality of stabilization pieces with certain weight, one end of each stabilization piece is arranged on the recovery platform, the other end of each stabilization piece is telescopically arranged at the bottom of the recovery platform, and the active stabilization device is used for changing the gravity center of the offshore recovery device by changing the position of the other end of each stabilization piece. The anti-rolling water cabin and the anti-rolling piece are arranged on the recycling platform, the gravity center of the whole recycling device is adjusted through the telescopic anti-rolling piece, the anti-rolling piece and the anti-rolling water cabin are combined to jointly restrain the shaking angle of the recycling platform, and the inherent frequency of a rocket can be avoided by controlling the telescopic amount of the active anti-rolling device.

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.

This application relates to a satellite attitude conversion device, belonging to the field of satellite testing devices, and includes a base, a plurality of push rods installed on the base, and a mounting plate installed on the plurality of push rods. The satellite is placed on the mounting plate. The satellite includes a flange, and a plurality of mating holes are formed in the flange. The diameter of the mating holes gradually decreases from bottom to top. An installation groove is formed in the mounting plate, and a support spring is fixedly connected to the bottom wall of the installation groove. A bottom column is slidably inserted into the installation groove, and the support spring is fixedly connected to the bottom column. The diameter of the bottom column is larger than the maximum diameter of the mating holes. A support rod is fixedly connected to the bottom column, and an installation block is fixedly connected to the upper end of the support rod. A plurality of grooves are formed in the side wall of the installation block, and a fixing spring is fixedly connected to the bottom wall of the groove. A fixing block is fixedly connected to the fixing spring, and the fixing block is slidably inserted into the groove. This application has the effect of improving the efficiency of satellite attitude conversion testing.

The invention provides an offshore spaceflight launching semi-submersible platform, which belongs to the technical field of rocket offshore launching, and comprises a platform main body, a main deck, a comprehensive test room, a guarantee equipment area, a life guarantee part and a power system, the platform body is provided with an upper platform body, a lower floating body and stand columns, the top ends of the stand columns are connected with the upper platform body, and the bottom ends of the stand columns are connected with the lower floating body. The middle position of a main deck of the upper platform body is a launching area. In the sailing state, the carrier rocket is horizontally placed in a launching area, and the platform body is driven by the power system to sail autonomously on the sea; in the launching state, the carrier rocket is erected on the platform body, the comprehensive test room, the guarantee equipment area and the living guarantee part on the main deck meet the test and launching guarantee requirements, temporary deployment and refitting design is not needed, and the calling period is shortened. According to the semi-submersible platform for offshore spaceflight launching, the problem that in the prior art, the calling period is long in temporary refitting design is solved.

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.

A rocket residual fuel processing system, a recovery deck is fixed above the center of the rocket recovery platform, the rocket recovery platform is provided with a centralized control module, a connection robot is arranged on the recovery deck, the connection robot is controlled by the centralized control module, and the connection robot can move freely on the recovery deck. The kerosene recovery system is provided with a plurality of kerosene hose reels, the nitrogen supply system is provided with a plurality of nitrogen hose reels, the connection robot is provided with an auxiliary arm, a gripper is arranged at the end of the auxiliary arm, the gripper grabs the first kerosene hose or the first nitrogen hose, the first kerosene hose is connected to the kerosene discharge port of the rocket body kerosene storage tank, and the first nitrogen hose is connected to the nitrogen injection port of the rocket body kerosene storage tank. The recovery of the rocket residual fuel kerosene of the present invention is completed by remote control operation on an unmanned rocket recovery platform, avoiding the harm to personnel caused by fire caused by kerosene leakage.

The invention provides a tool module. The tool module is installed on the erecting frame, the second platform section and the third platform section are arranged at the two ends of the first platform section respectively and rotationally connected with the first platform section, and therefore the second platform section and the third platform section can be disconnected or spliced relative to the first platform section, and the tool module is in an open state or a closed state. When the tool module is in a closed state, the first platform section, the second platform section and the third platform section define a cavity structure, a first through hole is formed in a first platform of the cavity structure and connected with a rocket body of the carrier rocket in a sealed mode, and a second through hole is formed in a second platform of the cavity structure and connected with a fairing in a sealed mode. The environment conditions of the sealed plant structure are controllable, and vertical butt joint of a carrier rocket and a satellite, testing and maintenance before satellite launching and other work can be carried out in the sealed plant structure. And a service tower with a closed plant does not need to be additionally built.

1. A support device 20 for supporting a fluid circulation duct C, said support device comprising: a link 22 for supporting the duct by means of two end portions 22a of the link separated from one another in the longitudinal direction, which in cross section adopt a curved shape to support a portion Ca of the duct, the two end portions 22a being connected together by two intermediate portions of the link, each intermediate portion connecting one end 22a1, 22a2 of the two end portions 22a; two links 24, 26 for fastening the support device to an outer structure; and connection elements 28a-28d between the support link 22 and the fastening links 24, 26, each connection element having a fastening link and an intermediate portion of the support link passing through the fastening link and allowing sliding of the fastening link and the support link through the connection element.

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.

The present invention discloses a detection platform for aircraft, including a horizontal bracket, a vertical bracket, and a flip assembly, wherein the vertical bracket is perpendicular to the horizontal bracket and connected to one side of the horizontal bracket, the bottom of the horizontal bracket and the outer side of the vertical bracket are both provided with a leveling support, the flip assembly is respectively connected to the horizontal bracket and the vertical bracket, a docking flange is provided on the horizontal bracket, and a front adjustment auxiliary support is provided on the upper end of the vertical bracket. The present invention has an ingenious structure, is safe and reliable, is easy to operate and maintain, can realize the placement of the aircraft in the horizontal and vertical postures, and can ensure leveling in the horizontal and vertical postures, can realize the aerospace aircraft to flip and change its posture in the air, and can also realize the mutual conversion of the horizontal and vertical postures, providing a safe and convenient multifunctional detection platform for the detection of aircraft.

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 present invention relates to a system and method of mobile orbital launchers. The mobile launcher of the present invention mainly consists of the launch vehicle and launch related subsystems. All the systems will fit on a trailer which is capable of going anywhere via road or sea. It will carry the vehicle in a horizontal position and after reaching the required location, it will articulate and make the vehicle vertical to get ready for launch. The system and method of the present invention have all the subsystems which enable the launch without any hindrance.