435results about "Systems for re-entry to earth" patented technology

The disclosed methods, systems, and kits provide the ability to deliver entire clean sheet designs from concept to first hot fire in under six weeks with instant specific impulses above 330 seconds in some of our engines. In examples, thrusters can be delivered that are at less than half of the mass budget allowable for them and they can be delivered in weeks.

The invention relates to a phase change sweating cooling porous structure and application thereof in an aircraft reentry capsule, the porous structure comprises a porous layer comprising a plurality of densely arranged porous units; the liquid separation cavity is connected with the porous layer; the liquid storage cavity is used for storing a cooling agent; the coolant conveying pipeline is connected with the liquid storage cavity and the liquid separation cavity; the regulating valve is arranged on the coolant conveying pipeline; each porous unit comprises a small-porosity porous part as well as a large-porosity porous part and a liquid channel which are respectively connected with the small-porosity porous part, and a gas channel is formed between the small-porosity porous part and the large-porosity porous part; and a coolant is introduced from the liquid channel, permeates into the small-porosity porous part, escapes from the large-porosity porous part along the gas channel after being gasified, and forms a gas film for heat insulation. Compared with the prior art, rapid gas-liquid separation and partitioned flow regulation and control of the coolant in the sweating cooling porous layer can be effectively achieved, and the phase change sweating cooling efficiency and reliability are effectively improved.

Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

This patent belongs to the field of spacecraft recovery and landing, and relates to a combined cushion airbag active exhaust control system. By building an active exhaust control system composed of a controller, a power supply, a landing sensor, a pressure sensor, an exhaust port cutter, an exhaust port fixing rope, etc., and cooperating with a preset exhaust control strategy, active control of the airbag landing cushioning process is achieved, and the airbag landing cushioning effect is improved. The present invention is mainly composed of a load, a cushion airbag, a controller, a power supply, a landing sensor, an exhaust port, a pressure sensor, an exhaust port cutter, and an exhaust port fixing rope. It has a wide range of applications and a fast actuator response speed. It can be used as a landing cushioning protection for various loads to achieve non-destructive landing of various large-mass aircraft and spacecraft.

The invention relates to the technical field of space flight and aviation, in particular to a recoverable rocket landing supporting mechanism which comprises a plurality of folding, unfolding and folding mechanisms. Each folding, unfolding and folding mechanism comprises an on-arrow locking mechanism, an auxiliary air cylinder, a telescopic assembly, a supporting assembly and a buffering device. The upper end of the telescopic assembly is hinged to the rocket body, the lower end of the telescopic assembly is hinged to the bottom end of the supporting assembly through a buffering device, the top end of the supporting assembly is hinged to the rocket body through a left hinge joint and a right hinge joint, and the left hinge joint and the right hinge joint are coaxial and located below the upper end of the telescopic assembly. The locking mechanism on the rocket is located on the rocket body and locks the edge of the supporting assembly after the supporting assembly is tightly attached to the rocket wall; one end of the auxiliary air cylinder is fixed to the arrow body, the other end of the auxiliary air cylinder extends outwards and downwards, the auxiliary air cylinder is located below the telescopic assembly, and when the supporting assembly is tightly attached to the arrow wall, the other end of the auxiliary air cylinder makes contact with the supporting assembly. The invention has the characteristics of large folding-unfolding ratio, reliable locking, high landing stability, small impact peak value and small aerodynamic resistance.

The invention relates to the technical field of cosmic sailing, and particularly discloses an offshore rocket recovery system and method, and the system comprises a floating body which floats on the sea surface; the inclination measuring unit is arranged on the floating body and is used for measuring the inclination angle between the floating body and the sea surface and generating an inclination signal; the recovery unit comprises a recovery deck, a rocket fixing device and a plurality of lifting devices, the rocket fixing device is installed on the recovery deck, the lifting devices are arranged on the periphery of the bottom of the recovery deck and installed on the floating body, and the lifting devices are used for driving the recovery deck to move up and down; and the control unit is arranged on the floating body, the control unit is in signal connection with the inclination measuring unit and the lifting device, and the control unit is configured to receive an inclination signal of the inclination measuring unit and control the lifting device to drive the recovery deck to move up and down. According to the offshore rocket recovery system and method, the rocket can be stably recovered, the recovery efficiency is improved, and the cost is reduced.

The invention relates to the field of rocket recovery, in particular to an ignition reverse thrust deceleration landing system for a recoverable rocket, which designs a reverse thrust engine module, defines a propellant and a plurality of parameters, perfects a fuel supply system, and covers solutions to storage, vaporization, collapse, vortexes and other problems. According to the accurate control algorithm, the trajectory and speed of a rocket are predicted through multi-sensor data, a reverse thrust engine is dynamically adjusted through complex steps including target setting, control strategy, ignition, thrust adjustment and the like, and real-time feedback and landing stage control are further achieved. The integrated sensor system comprises various types of sensors and is responsible for collecting and processing data and transmitting the data to the control system. System integration involves hardware, software and debugging, and test plans include ground, simulation and flight testing. The safety and redundancy design comprises a redundancy control path, a fault detection mechanism and countermeasures when an engine and a sensor have faults. According to the scheme, the rocket recovery accuracy and safety can be improved, and the cost is reduced.

A satellite constellation forming system forms a satellite constellation (20) including two orbital planes each having a different normal direction and in each of which the same number of satellites fly. A satellite constellation forming unit gradually changes an orbital altitude of at least one orbital plane of the two orbital planes from a state in which satellite passage timings of satellites flying in the two orbital planes do not coincide with each other at an intersection neighborhood point (Pc) between the two orbital planes in each of the two orbital planes, while maintaining the state in which the satellite passage timings do not coincide with each other.

The invention discloses a rocket power landing phase guidance control method, system and device and a medium, and relates to the technical field of rocket guidance recovery. The method comprises the following steps: in a current control period, obtaining a state quantity according to a control parameter and a rocket power landing section motion model; taking the minimum guidance control comprehensive target mathematical model as a target, and updating the to-be-adjusted parameter value according to the parameter updating period and the state quantity; according to the guidance cycle, the updated partial to-be-adjusted parameter values, partial parameters in the state quantity, the flight time and the guidance model, a thrust amplitude and a channel expected attitude are obtained; and according to the attitude control period, the updated part of parameter values to be adjusted, the attitude, the attitude angular rate, the thrust amplitude, the channel expected attitude and the attitude control model, obtaining a channel engine swing angle, and entering the next control period for control. According to the method, the problems of low terminal constraint satisfaction precision, fuel consumption loss, poor attitude control quality and the like can be solved, and the reliability of recoverable rocket power landing is improved.

Container for collecting space debris. Space debris ingress through container's openable access port. A barrier deployment mechanism has a rotatable roll of flexible material on a frame assembly. A barrier translation mechanism translates the frame assembly towards or away from the access port to adjust the size of the compartment. When unwound, the roll forms a compartment for containing the space debris within the interior of the container, thus forming an obstruction between the compartment and access port.

A tiered spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. A first tier includes a first frame enclosing a first area. A first net-like mesh is coupled to the first frame and fills the first area enclosed by the first frame. A second tier includes a second frame enclosing a second area. A second net-like mesh is coupled to the second frame and fills the second area enclosed by the second frame. A plurality of support beams attach the first frame to the second frame. A lander is used to slow and stop a spacecraft on a celestial body. The lander includes a first and a second webbed structure and a decelerator coupled to the first webbed structure and / or the second webbed structure. The decelerator maintains a tension in the first and / or second webbed structure below a predetermined threshold.

The invention relates to a low-cost parachute landing recovery system for a microgravity load return capsule, and aims to realize an efficient, reliable and economical recovery scheme through modular design, all modules are connected through standard interfaces, and assembly, maintenance and upgrading are facilitated. The structure module is used for assembling the parachute module and providing necessary shock resistance; the parachute module is used for pneumatic deceleration and attitude stabilization of the system and adopts a multi-stage unfolding structure; and the initiating explosive device module is used for bouncing the brake parachute, releasing the brake parachute and releasing a parachute closing opening. According to the system, the production and maintenance cost is remarkably reduced through modular design, meanwhile, the reliability and adaptability of the system are improved, and the system is suitable for various microgravity load return scenes and has wide market application prospects.

Various embodiments comprise a multi-agent spacecraft system for rendezvous and proximity operations. The spacecraft system comprises a chief spacecraft and a deputy spacecraft. The chief spacecraft maneuvers to the orbit of a Resident Space Object (RSO) and deploys a deputy spacecraft to rendezvous with the RSO. The deputy spacecraft maneuvers to the RSO and senses the RSO during the rendezvous and proximity operations maneuver. The deputy spacecraft generates a Three-Dimensional (3D) surface reconstruction of the RSO based on the sensing. The deputy spacecraft determines a roll rate and a relative trajectory of the RSO based on the sensing. The deputy spacecraft returns to the chief spacecraft.

The invention relates to the technical field of aerospace, and provides a multi-stage pneumatic telescopic mechanism and a rocket recovery landing leg device.The multi-stage pneumatic telescopic mechanism comprises a plurality of barrels which are arranged in a sliding and sleeving mode from inside to outside; the outermost cylinder is connected with an end cover, and the end cover is provided with an unfolding inflation hole; in every two adjacent barrels, a vent hole is formed in the end, away from the end cover, of the outer barrel, a locking groove is formed in the inner wall of the outer barrel, and a locking component is arranged at the end, close to the end cover, of the inner barrel. The locking component is switched from the locking state to the unlocking state through the vent hole of the outermost cylinder, the inner cylinder can slide to contract, and when the two adjacent cylinders are in the contraction state, the vent holes of the two adjacent cylinders communicate with each other, so that the locking state of the locking component is changed, and the service life of the locking component is prolonged. The corresponding locking grooves are unlocked by all the locking parts by means of the vent holes of the outermost cylinder body; the extension of the multi-stage barrel body is realized by unfolding the inflation hole, so that the extension and retraction of the multi-stage barrel body can be realized through the vent hole in the outermost barrel body and the unfolding inflation hole, and the design complexity of an air path is reduced.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

A method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. A system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

The invention relates to the technical field of aerospace, and provides a multi-stage pneumatic telescopic mechanism and a rocket recovery landing leg device.The multi-stage pneumatic telescopic mechanism comprises a plurality of barrels which are arranged in a sliding and sleeving mode from inside to outside, and the barrel on the outermost side is provided with an unfolding inflation hole; in every two adjacent barrels, the outer barrel is provided with a vent hole, and the inner side of the outer barrel is provided with a locking part; a locking groove is formed in the inner side barrel body; the locking member has a locked state and an unlocked state. The locking component can be switched from the locking state to the unlocking state through the vent hole of the outermost cylinder body, so that the inner cylinder body slides to contract, and the vent holes of the two adjacent cylinder bodies are communicated under the condition that the two adjacent cylinder bodies are in the contraction state, so that the locking component is locked. The corresponding locking grooves are unlocked by all the locking parts by means of the vent holes of the outermost cylinder body; and extension of the multi-stage cylinder body is realized through the unfolding inflation hole, so that extension and retraction of the multi-stage cylinder body can be realized through the vent hole in the outermost cylinder body and the unfolding inflation hole, and the complexity of air path design is reduced.

A rocket stage for a multistage space launch vehicle, wherein the rocket stage includes a main engine and is configured for stage separation from remaining parts of the space launch vehicle such that the rocket stage returns to the surface of the earth, wherein rocket stage includes an inflatable hull configured to retain lifting gas from a pressure tank, an inflation unit, a propulsion and steering unit configured to provide thrust and attitude control to the rocket stage, and a control unit configured to initiate inflation of the hull by controlling the inflation unit after the stage separation and to control the propulsion and steering unit to maneuver the rocket stage to a specified landing site on the surface of the earth.

To solve the problem that there is a case in which it is difficult to recover a flying object.SOLUTION: A recovery device has an engine part which burns supplied propellant to obtain a thrust in a predetermined direction, and is configured to be mounted on an airframe of a recovery object such that the recovery device can obtain, with the engine part, the thrust in a direction opposite to a direction in which the airframe of the recovery object obtains a thrust.SELECTED DRAWING: Figure 1

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

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.

The invention discloses a space parallel mechanism type landing buffering and moving integrated variable-configuration suspension. A suspension assembly comprises a support, a movable platform, a four-degree-of-freedom space parallel mechanism and a wheel assembly. The support is composed of a horizontal installation plate and a vertical installation plate, and the horizontal installation plate is used for achieving installation with the bottom of a vehicle body. The four-degree-of-freedom spatial parallel mechanism comprises four branch chains, three branch chains are UPS branch chains of universal hinges, linear pairs and spherical hinges, and the other branch chain is a PPU branch chain of linear pairs, linear pairs and universal hinges; universal hinges of the three UPS branch chains are mounted on the inner side of the vertical mounting plate, and spherical hinges of the three UPS branch chains are mounted on the movable platform; universal hinges and spherical hinges on the vertical mounting plate and the movable platform are arranged in a triangular manner; universal hinges of the PPU branch chains are mounted on the movable platform and located in the triangular layout formed by the spherical hinges, and linear pairs of the PPU branch chains are mounted on the horizontal mounting plate; the wheel assembly is installed on the movable platform.

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.

Tether-based reaction control systems for spacecraft undergoing atmospheric entry or reducing orbital energy, including systems that use atmospheric drag on one or more tethers to alter the angle of attack of the spacecraft during its atmospheric transit to reduce the thermal and mechanical loads on the spacecraft during the reentry process. Systems may include tethers that together generate a force that functionally acts on the spacecraft at a point that is offset from the spacecraft's center of mass. Such systems may be either actively or passively controlled.

A composite article comprises a body comprising a radial region, a tapered region, and a cavity region. The cavity region comprises a cylindrical shape and an inner diameter of the cylindrical shape decreases between the radial region and the tapered region. A nosecone region is adjacent to the tapered region of the body and at an opposing end of the body to the cavity region. A thermal protection structure is on the body and comprises a base layer, an insulating layer is on the base layer, and an erosion resistant layer is on the insulating layer. The insulating layer exhibits a specific gravity of from about 0.01 to about 1.0. Methods of forming the thermal protection structure and of thermally protecting an article are also disclosed.

The invention discloses a rocket sublevel active rotor pneumatic deceleration recovery system and a control method, and aims to solve the problems of low recovery precision, large fuel consumption, large landing impact and the like. The recovery process is divided into five stages of reentry, rotor wing unfolding, main pneumatic deceleration, accurate approaching and soft landing. Fine adjustment of the descending speed and the horizontal position is achieved through cooperative control of aerodynamic resistance of the body and the rotor wing system. And a multi-source sensor and a trajectory tracking algorithm are fused, so that stable soft landing at the sub-level zero horizontal speed and the minimum vertical speed is finally ensured. According to the invention, the recovery precision is obviously improved, the fuel consumption is reduced and the landing impact is reduced.

To enable making a rocket ultra-small-sized, a robot body light-weighted, a rocket manufacturing cost significant reduced, so as to facilitate capture of space debris.SOLUTION: An entire outer wall of a rocket body, including a fairing at a head of a space rocket, is made of wood. In order to use wood material for the entire outer wall of the rocket body, the wood material must be treated to be tougher in terms of heat resistance than conventional aluminum veneer. In an inner wall of the rocket body, all of inner wall surfaces are lined with fireproof fabric that can withstand fires up to 1700°C, or heat insulating fabric, and toughened wood technology is used to ensure that rocket inner wall will not have any problems with heat resistance until the rocket ascends and reaches outer space. Further, in order to reduce weight of the rocket, the wood materials to be used is to be selected from those having a low specific gravity, such as cedar or hinoki.SELECTED DRAWING: None

The invention provides a system device for core-level offshore recovery of a carrier rocket and a control method. The system device comprises an offshore recovery platform body, a core-level recovery capture rotary locking device, a dumping thrust reverser, an anti-dumping damping device, an auxiliary holding device and a locking device moving platform. The locking device moving platform can move to any position on the offshore recovery platform body; the core-level recycling, capturing and rotating locking device is used for receiving core-level position signals and supporting vertically descending cores; the dumping thrust reverser is used for holding the core; the anti-toppling damping device is matched with the toppling thrust reverser to enable the core to topple to a horizontal state; the auxiliary clasping device is used for clasping a core in a horizontal state. According to the invention, the carrier rocket core-level can be converted from a vertical fixed state to a horizontal fixed state after being recovered on the offshore recovery platform, the core-level mass center is reduced, the overturning risk of the core-level and the offshore recovery platform body is greatly reduced, and the harbor returning safety after core-level offshore recovery is improved.