15 results about "Space suit" patented technology

This invention discloses an integrated aerospace service system for planning and processing, belonging to the field of civilian satellite observation and services. The system includes a mission coordination and integrated management subsystem, a space information management subsystem, and an information comprehensive analysis subsystem. The system is designed and implemented using a "system + service" approach, effectively achieving system iteration, stability, and resilience. The system fully utilizes multi-satellite joint mission planning algorithms and remote sensing image intelligent analysis algorithms, enabling integrated planning and processing services. This invention effectively solves the problems of slow response speed, incomplete response chains, and poor service product quality when facing major events.

The invention relates to an operation control device for a manned lunar rover. The device mainly comprises a bracket connecting rod, a control handle, a display panel and a display panel mounting bracket, the device is installed beside an astronaut seat of the manned lunar rover and provides an interaction channel for an astronaut to operate and control the lunar rover under the condition that the astronaut wears a space suit. The bracket connecting rod can be used as a handrail for getting on and off the lunar rover through rotating movement, and can also be used as a bracket for placing a control handle and a display panel; the control handle and the display panel are both detachable and are connected with the lunar rover in a wireless communication mode, and when the control handle and the display panel are installed on the lunar rover through the support connecting rod and the display panel installation support, the installation interface can charge the control handle and the display panel; the control handle is a two-degree-of-freedom handle and can provide direction and speed control when the lunar rover moves, and functional keys are arranged on the handle, so that a channel is provided for astronauts to safely and reliably control the lunar rover.

The invention relates to the field of spaceflight equipment, in particular to a telescopic multifunctional connecting device for lunar surface work, which comprises a connecting sleeve which is of an axially through hollow structure and is provided with a plurality of hollow holes in the side wall in a penetrating manner; the telescopic rod assembly penetrates through the connecting sleeve in a sliding manner; the first limiting mechanism is rotationally arranged at one end of the connecting sleeve, first limiting teeth are arranged on the side, away from the connecting sleeve, of the first limiting mechanism, and the first limiting teeth are configured to adjust the relative position of the telescopic rod assembly and the connecting sleeve; the emergency disposal mechanism is arranged at the end, away from the first limiting mechanism, of the telescopic rod assembly; the dust removal mechanism is arranged at the end, away from the emergency disposal mechanism, of the telescopic rod assembly. The telescopic multifunctional connecting device provided by the invention has a connecting function of switching between the lander and the lunar rover, an emergency disposal function and a lunar dust removal function, is light in weight, and is convenient for an astronaut to wear a spacesuit for operation.

The present application relates to a kind of distributed extravehicular spacesuit with self-repairing and resource in-situ replacement function, belong to astronaut life support and energy management technical field, the present application is set in spacesuit helmet heat control circulating system one, spacesuit ontology sets heat control circulating system two and energy and resource supply system, heat control circulating system is modularized and distributed in head, chest, abdomen and limbs, integrates two kinds of temperature control mode of carbon dioxide sublimer and phase-change radiator, can in-situ utilize carbon dioxide in Mars atmosphere and sublimate heat dissipation, significantly reduce the water heat sink resource load carried from earth, effectively disperses system weight;Abdomen and limbs are provided with standardized plug-in interface, support oxygen cylinder, battery and water tank and other key consumable modules are replaced quickly in extravehicular site, realize the real-time supply to consumable resource and the on-site replacement maintenance to failed resource storage module or phase-change temperature control component, do not need to disassemble entire system to ensure sustained cruising.

1. The name of the design product: extravehicular space suit. 2. The use of the design product: for astronauts' extravehicular activities. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view. 5. Other circumstances that need to be explained: the bottom surface of the product involved in the design patent application is a surface that is not easy to see or cannot be seen during use, and the top view is omitted.

The application discloses a kind of anti-impact nylon fibre for spacesuit and its preparation method, comprising: high molecular weight nylon 66 matrix 86.0-92.0wt%, multi-dimensional nano reinforcing phase 1.2-2.0wt%, multifunctional anti-impact microsphere 4.0-7.0wt%, in-situ interface compatibilizer and crosslinking point regulator 0.5-1.2wt%, aerospace-grade multifunctional stabilizing aid: 1.0-2.8wt%;The multi-dimensional nano reinforcing phase is compounded by amino graphene and amino carbon nanotube according to mass ratio 1:3-4;The multifunctional anti-impact microsphere is hollow polysiloxane-titania composite microsphere, the anti-impact nylon fibre for spacesuit and its preparation method disclosed by the application can realize the multifunctional integration of nylon fibre, meet the demand of space suit fibre.

The application discloses a manned spacecraft extravehicular activity ground in-situ suspension test verification system and method, which comprises a spacecraft cabin body, a horizontal rotation tool, a vertical support tool, an extravehicular space suit, an extravehicular space suit matching ground equipment, a suspension device and a lifting vehicle; wherein the spacecraft cabin body is parked on the horizontal rotation tool or the vertical support tool; the horizontal rotation tool controls the spacecraft cabin body to rotate along a horizontal axis to adjust the position of the equipment on the spacecraft; the extravehicular space suit is connected with the extravehicular space suit matching ground equipment; the extravehicular space suit matching ground equipment is placed on the first lifting vehicle and moves horizontally and up and down with the first lifting vehicle to cooperate with the movement of the extravehicular space suit; the suspension device lifts the extravehicular space suit and shifts to an operation position; the second lifting vehicle is used for carrying a test person to the vicinity of the extravehicular space suit to assist the test person in the extravehicular space suit to operate. The application solves the problem of verifying the feasibility of extravehicular operation during long-term on-orbit flight of the manned spacecraft.

The invention discloses a reliability test method and device for an upper limb movement assembly of a space suit under vacuum lunar dust pollution, and relates to the technical field of space environment ground simulation and spacecraft environment effect test. The problem that a comprehensive test method capable of directly associating a complex combined pollution mode of the lunar surface with dynamic performance degradation of a movable joint in a pressurized state is lacked in the industry is solved, and according to the test method, vacuum baking pretreatment is carried out on simulated lunar dust, and collaborative segmented pressure relief is carried out in the pressure relief process of a vacuum cabin; in-situ charging is carried out on the lunar dust, the assembly is driven to alternately execute contact dust sticking and multi-posture dust spraying operation, the joints are driven to move in a reciprocating mode in the lunar dust covering state, and quantitative characterization of the reliability performance degradation rule of the assembly is achieved; the device integrates the functions of vacuum environment simulation, lunar dust charging, multi-mode pollution application and dynamic performance monitoring, and provides an important test basis for long-life design and life prediction of key components of the space suit.

This invention relates to a standard device for extending the liquid circuit for easy extravehicular operation by astronauts, comprising an extension adapter and an extension housing. The extension adapter is the passive end, installed on the spacecraft cabin and launched with the spacecraft. The extension housing is the active end, installed by the astronaut after exiting the spacecraft and attached to the extension adapter. The extension adapter and the extension housing are connected mechanically, electrically, and through liquid circuits. These interfaces are all standard interfaces, and the connection method is independent of the type of liquid circuit equipment installed inside the extension housing, such as pump assemblies, valve assemblies, and working fluid replenishment assemblies. The standard device for extending the liquid circuit of this invention features standardized interface design, adaptability for astronauts operating while wearing extravehicular spacesuits, no need for auxiliary tools, simple operation, and short operation time, and can meet the requirements for pressurized, leak-free operation of the extravehicular liquid circuit.

1. Name of the product in this design: Intravesical Spacesuit (Men's). 2. Purpose of this design: for use in astronaut cabin activities. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1. 5. The top and bottom views have no design points, so the top and bottom views are omitted.

According to the pure oxygen testing device and method for the space suit circulating pump, the testing device has the functions of simulating the pure oxygen environment, conducting medium filling and circulating and the like, and the actual working state of the circulating pump in a space suit can be fully simulated. The pure oxygen test device comprises a pure oxygen test main body device, a medium supply device, a high-pressure nitrogen supply device, an oxygen supply device, a vacuumizing device and a pump control device, a circulating pump in the pure oxygen test main body device is connected with a pump control device; the circulating pump is connected with a medium supply device through a filter and a medium return valve; the medium supply device is connected with the high-pressure nitrogen supply device through a nitrogen supply valve and a high-pressure nitrogen pressure reducing valve; the pure oxygen test main body device is connected with a vacuumizing device through a test box ventilation nozzle and a vacuumizing hand valve; and the pure oxygen test main body device is connected with the oxygen supply device through the other test box body ventilation nozzle, the oxygen supply hand valve and the oxygen pressure reducing valve.

The application discloses a kind of humanoid soft body finger with rigid-flexible coupling structure, it is related to the technical field of soft body robot, solve the existing soft body finger in space suit glove interactive force test working condition, when overcoming pressurized space suit glove high impedance load, lateral instability, motion trajectory deviation and low control precision and other problems are prone to occur, rigid support skeleton is assembled in soft body base, the proximal end and distal end of soft body base are respectively equipped with one positioning ring, the both sides of rigid support skeleton are equipped with high-strength plastic tube that is penetrated into driving line, auxiliary reset spring is sleeved on rigid support skeleton and two ends are respectively connected with two positioning rings, the application is constrained by discrete rigid skeleton and cylindrical pin, by weaving artificial tendon sheath at joint through hole, arch string effect is radically cured and driving arm constant is ensured, independently arranged high-strength plastic tube effectively protects soft body base from being cut by driving line, and the cavity formed by heat shrink tube ensures the dexterity of joint movement.

The application relates to a portable astronaut extravehicular auxiliary mechanical arm system, and relates to a mechanical arm system.The application is used for solving the problem that the operation object and execution efficiency of an astronaut extravehicular operation are influenced due to the reachability space and pose limitation of an existing space station mechanical arm, and the flexibility of single-hand operation of the astronaut.The one end of a modular joint is rotationally connected with the one end of a fixed clamp jaw, the other end of the fixed clamp jaw is connected with a space station extravehicular handrail;the other end of the one modular joint is connected with the one end of a power transmission chain to form a roll freedom degree unit;an azimuth freedom degree unit and a pitch freedom degree unit are sequentially connected to form a mechanical arm unit;the roll freedom degree unit is sequentially connected with at least one mechanical arm unit from right to left, a quick plug-in buckle is connected with the tail end of the mechanical arm unit, and the quick plug-in buckle is connected with a waist central fixed hanging point of a space suit.The application is used for assisting an astronaut extravehicular operation.

1. The name of the design product: cabin space suit (female). 2. The use of the design product: for astronauts' cabin activities. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1. 5. The top view and bottom view have no design points, and the top view and bottom view are omitted.

The invention discloses a foot joint movement life testing device for an extravehicular spacesuit. A lifting pressure applying assembly is arranged on a frame assembly; the torsion force application assembly is arranged on the frame assembly and located below the lifting pressure application assembly. The lower posture adjusting and reversing assembly is arranged on the torsion force applying assembly; the upper posture adjusting reversing assembly is arranged on the lifting pressure applying assembly and located above the lower posture adjusting reversing assembly. The spacesuit feet are arranged between the lower posture adjusting and reversing assembly and the upper posture adjusting and reversing assembly. The rigid binding assembly is arranged between the foot of the spacesuit and the lower posture adjusting and reversing assembly; the flexible binding assembly is arranged between the foot of the spacesuit and the rigid binding assembly. The extravehicular spacesuit foot motion trail simulation device can adapt to extravehicular spacesuit feet of different sizes and different models, simulation of spacesuit foot ankle joint motion trails can be achieved by matching external driving with binding belt fixing, downward pressure can be applied to the spacesuit feet during testing, the working pressure during spacesuit foot ankle joint motion is simulated, and the test efficiency is improved. The device has the characteristics of high test precision, good test safety and high test reliability.