34 results about "Astronauta" patented technology

The invention discloses an assisting method and device for movements in space. According to the assisting method and device, the moving ability of astronauts can be effectively enhanced. According to the method, an external skeleton system is coupled on a space suit. The external skeleton system comprises a profiling mechanical structure, a man-machine interface system, a control system, an actuator and an energy power system. The man-machine interface system senses and sends moving states and moving intensions of the astronauts to the control system, the control system processes information and sends instructions to the actuator, and the actuator drives the profiling mechanical structure to assist in supporting of astronaut loads or providing of boosting power for movements of the astronauts, accordingly, energy consumption of the astronauts is greatly reduced, the bearing ability, the moving ability of upper and lower limbs and the information processing ability of the astronauts are improved, the adaptability of the astronauts to severe environments is enhanced, and the astronauts are assisted in completion of various space operations. Besides, by the aid of the profiling mechanical structure, astronaut bodies can be protected, the astronauts are prevented from being injured, and the assisting method and device are suitable for popularization in the of astronaut space operation devices.

The invention belongs to the field of manned aerospace engineering space station systems, and particularly relates to an in-orbit operation labor-saving device for a load supporting frame in a space station cabin. The device comprises an in-cabin load supporting frame, a fixed adapter, a labor-saving mechanism, non-disengagement screws and corner fittings, the corner fittings are arranged at the bottom and the top of the in-cabin load supporting frame, and all the corner fittings are connected with a standard interface of a space station cabin section through the non-disengagement screws; andthe labor-saving mechanism is arranged on the fixed adapter, the fixed adapter is connected with the in-cabin load supporting frame, so that the labor-saving mechanism corresponds to the non-disengagement screws on the corner pieces, and the labor-saving mechanism tightens or loosens the non-disengagement screws through torque multiplication, thereby assembly and disassembly of the in-cabin load supporting frame are achieved. Efficient torque and rotating motion transmission can be achieved, the beneficial effects of single input and two-way output are achieved, and the requirements of astronauts for on-orbit operation capacity and torque and operation space needed by screw disassembling and assembling are met.

The invention discloses an electric connector device easy to disassemble in an orbit. The electric connector device comprises an electric connector, wherein the electric connector comprises a plug anda socket, the socket is fixedly installed on the aircraft and serves as a non-on-orbit detachable part; the ratchet wheel and ratchet mechanism is used as a plug accessory to be integrated with the plug to be used as an on-track detachable part; and the ratchet mechanism swings back and forth around the shaft of the electric connector, so that the plug is screwed out of the socket. According to the electric connector device easy to disassemble on the orbit, the ratchet mechanism of the ratchet wheel and the plug of the electric connector are integrated, so that the one-way rotating action ofseparation and disassembly of the electric connector is converted into small-range reciprocating swing motion, an astronaut can conveniently operate by using a simple manual tool, and the requirementson a maintenance tool and the operation capability of the astronaut are reduced.

The invention discloses a passive self-adaptive distributed human body gravity unloading system. Modular grading is performed according to continuous mass characteristics of a human body, and the main body adopts a pure passive mechanism which is formed by combining a two-free air floating platform, a scissor type main constant force system and a self-adaptive distributed human body gravity unloading system. Horizontal two-degree-of-freedom large-range movement of the whole human body is achieved through a two-degree-of-freedom air floating platform and an air floating guide rail; a scissor type main constant force system is formed by connecting a scissor mechanism and a zero-rigidity mechanism in series, and large-range vertical movement and constant unloading force are provided in the vertical direction. According to the self-adaptive distributed human body gravity unloading system, a tree-shaped bifurcated zero-stiffness structure is combined with a scissor type auxiliary constant force system to achieve local multi-degree-of-freedom movement of the trunk of the four limbs of the human body, a multi-point distributed gravity unloading strategy is adopted, the additional joint force and the triggering muscle force during training of the astronaut are effectively reduced, and the trueness and the immersion of the micro-low gravity simulation training of the astronaut are improved.

The invention discloses an active and passive hybrid drive self-adaptive gravity unloading astronaut ground training system, which performs modular grading aiming at continuous quality characteristics of a human body, adopts a passive hybrid tree-shaped bifurcated driving mechanism, and combines a multi-point distributed gravity unloading strategy, so that additional joint force during astronaut training is effectively reduced, and the training quality of astronauts is improved. Therefore, the trueness and immersion of the micro-low gravity simulation training of the astronaut are improved. A truss vehicle two-degree-of-freedom motion platform is adopted to realize large-range space two-degree-of-freedom translation of the whole human body; and a self-adaptive gravity unloading system is combined to realize the large-range movement of the whole human body in the vertical direction and the small-range six-degree-of-freedom movement of the trunk, the four limbs and the head of the human body. Decoupling design is carried out for overall large-range movement and local small-range movement in the human body floating base state, and the training requirements of astronauts for multiple postures and multiple movement modes are met.

The invention discloses a standing-type lunar surface split type spacesuit auxiliary wearing device. After an astronaut wears a split type spacesuit to fix a chest assembly to the device, arm assemblyauxiliary devices on a left arm and a right arm of a mechanism drive a clamping linkage rod to rotate through a clamping driving motor; a support and a pressing supporting rod move together to achieve pressing combination of a wrist ring of the chest assembly and a wrist ring of an arm assembly; the auxiliary wearing device enables an upper section lifting rack and a middle section lifting rack to move upwards through a middle section driving motor, and a lifting supporting plate is lifted upwards through a lower section lifting hydraulic lever to drive a trouser supporting plate to move upwards; and the planetary spacesuit is made of a hard material, after a spacesuit trouser assembly reaches the position, pressing combination of a wrist ring of the spacesuit trouser assembly and the wrist ring of the spacesuit chest assembly is achieved through acting force, then a seat middle section outer layer moves downwards, the astronaut is lowered, and then the seat middle section outer layerdeforms into a seat to be used when the astronaut wears a spacesuit shoe assembly.

The invention relates to a low-hardness and high-tear-resistance natural latex material suitable for the space environment and a preparation method thereof, an anti-aging agent DNP and an anti-aging agent 264 are introduced to serve as anti-aging agents at the same time, an accelerant ZDC and an accelerant PX are introduced to serve as accelerators at the same time, by adjusting the proportion of all the components, The obtained natural latex material has the characteristics of low hardness, high strength, high tear resistance, high and low temperature resistance, aging resistance, good air tightness, environmental protection and no toxicity, and is suitable for being worn by astronauts during out-of-cabin operation.

The invention provides an operation platform for extravehicular on-orbit maintenance of a space station. The operation platform comprises a supporting assembly and a carrying assembly. The carrying assembly comprises a frame body used for fixing an operation tool. The frame body is detachably connected with the supporting assembly; the supporting assembly comprises a supporting rod and a connecting rod; the connecting rod is detachably mounted between the frame body and the supporting rod and is used for adjusting the height of the frame body; the end, away from the connecting rod, of the supporting rod is connected with a foot limiter through a locking assembly. According to the technical scheme provided by the embodiment of the invention, the operation tool can be fixed through the object carrying assembly, and outboard maintenance is facilitated; the carrying assembly is connected with the foot limiter through the supporting assembly, the supporting assembly comprises a supporting rod connected with the foot limiter and a connecting rod for connecting the supporting rod with the carrying frame, and the connecting rods with different lengths can be adopted according to the height of the astronaut, so that the height of the carrying assembly is adjusted, and the carrying assembly is convenient to use by the astronaut.

The invention discloses a rocket launching experience system and rocket launching experience method. The rocket launching experience system comprises a rocket body comprising at least two cabin sections, one cabin section is provided with an engine cabin, and the other cabin section is provided with an astronaut activity cabin; the system further comprises an assembling assembly used for connecting the at least two cabin sections; an instruction sending assembly used for sending an instruction which at least comprises a rocket launching instruction; a transmission assembly used for receiving and transmitting the instruction and an instruction processing result; an instruction execution assembly which at least comprises a rocket launching mechanism which is used for processing the rocket launching instruction and comprises an engine or an engine equivalent device arranged in the engine compartment; a display assembly which comprises a first display arranged in a test hall; and a power assembly used for supplying power to the instruction execution assembly. The rocket launching experience system is simple in structure and good in experience effect, and has better science popularization significance.

Disclosed is an application of felt buckles to inside of a spaceflight cabin, inside of Tiangong, inside of a spaceship, and shoe soles, trousers and outside of clothes of a spaceman. The space is in a microgravity environment so that the spaceman in the spaceflight cabin in the microgravity environment floats due to weightlessness and is difficult in self-controlling and stabilizing body to get rid of weightlessness. Therefore, a principle that felt knot drawing force can be generated between two pieces of felt buckles is used so as to apply and respectively fix the felt buckles on the inner surface of the spaceflight cabin, two shoe soles, trousers and outside of clothes of the spaceman, and a spaceman seat. Thereby, the spaceman can wear shoes or boots with felt buckles fixed on the soles to step on the inner surface of the spaceflight cabin with numerous pieces of felt buckles fixed on the inner surface to move forwards, backwards, leftwards or rightwards so as to perform various scientific works or sit on the seat to work and relax without floating. The spaceman can achieve self-control, and is stabilized to get rid of weightlessness and prevented from colliding other objects in the spaceflight cabin, health and safety of spacemen are firstly guaranteed, and meanwhile, various scientific test works can be efficiently achieved.

The invention relates to the technical field of manned spacecrafts, in particular to a re-entry capsule device. The re-entry capsule capsule device comprises a capsule body, wherein an installation blind hole is formed in the bottom face of the capsule body, a containing blind hole is formed in the side wall of the installation blind hole, a first sliding groove is formed in the side wall of the installation blind hole, and a second sliding groove is formed in the side wall of the containing blind hole; an anti-impact column body inserted into the installation blind hole, wherein the lower end of the anti-impact column body abuts against an anti-heat insulation cover, the side wall of the upper end of the anti-impact column body is provided with a first protruding block, and the lower end of the first sliding groove is provided with a first limiting block; a blocking column body inserted into the containing blind hole, a spring is pressed between one end of the blocking column body and the end wall of the containing blind hole, a second convex block is arranged on the side wall of the end, and a second limiting block suitable for blocking the second convex block is arranged at the end of the second sliding groove. According to the re-entry capsule device provided by the invention, the anti-impact column body can resist the impact force borne by the anti-impact column body under the blocking force of the blocking column body, so that the damage caused by direct collision between the capsule body and the ground is avoided, and the safety of astronauts and precise instruments is ensured.

The invention discloses a three-ball instrument which comprises a foldable shell and a three-ball projection device arranged in the foldable shell. The three-ball projection device comprises a gear driving mechanism, an earth model, a moon model and a sun model; the gear driving mechanism is arranged in the foldable shell, the earth model and the moon model are arranged on the gear driving mechanism, and the sun model is arranged on one side of the gear assembly. Through the gear driving assembly, earth revolution, rotation and the motion state of the moon and the earth can be achieved; the lighting effect of simulating the sun is realized through the light of the LED lamp pole, and the day and night alternation phenomenon and the terminator line phenomenon are shown. Through a hidden upturning mechanism on the right side of the astronaut helmet, a complex gear set galaxis can be autonomously driven to move, the design is more exquisite, vast starry sky can be projected at the bottom of the base in a macro mode, projection themes are switched according to different galaxis, space style music is synchronously played through a loudspeaker, and immersive experience is provided for a user.

Lack of gravity is a cause of major health concerns for astronauts travelling or living in space. The systems, in accordance with the embodiments of the invention, provide Artificial Gravity. The users or subjects experience Artificial Gravity while exercising in an environment without gravity, such as space. Another embodiment includes chambers shielded by multilayer magnetic toroid and multilayer soft magnetic layered clothing that shields astronauts from radiation and stray magnetic fields while providing a gravitational (artificial gravity) effect.

The invention relates to an anti-fatigue and anti-radiation capsule for spaceflight and a preparation method thereof. The anti-fatigue and anti-radiation capsule for spaceflight is characterized by being prepared from the following raw materials in parts by mass: 200-300 parts of American ginseng, 800-1000 parts of Fuzhuan tea, 200-300 parts of maca powder, 30-50 parts of xylooligosaccharide, 30-50 parts of corn starch and 1-5 parts of sea cucumber peptide. The capsule provided by the invention is completely prepared from natural extracts, can improve the anti-fatigue and anti-radiation conditions of astronauts at the same time, and has no side effects.

The invention relates to a living cabin big data safety monitoring system, and the system comprises a following camera mechanism which is disposed in a space station astronaut living cabin, and is used for carrying out the following camera action of an internal scene of the living cabin, so as to obtain a corresponding living scene image; wherein the following camera mechanism is composed of a human body detection device, a holder driving device, a holder structure and a real-time camera shooting device; a big data processing node which is in network connection with the liquid detection equipment through a satellite communication link, and is used for sending a proximity alarm signal when a liquid object occupying the area of the grayscale correction image and having a distance from the human body target in the grayscale correction image lower than a preset distance threshold exists. The living cabin big data safety monitoring system is safe, reliable and stable in operation. The key operation of a customized monitoring mechanism in the space station is completed by adopting the big data processing node on the ground, so that the body health of astronauts is effectively maintained.

The electrical connector device that is easy to be disassembled on the rail of the present invention includes an electrical connector; the electrical connector includes a plug and a socket, and the socket is fixedly installed on the aircraft as a part that cannot be disassembled on the rail; the ratchet and ratchet mechanism is used as a plug accessory and The plug is integrated as an on-rail detachable part; the ratchet and ratchet mechanism swings back and forth around the axis of the electrical connector to unscrew the plug out of the socket. The electrical connector device that is easy to disassemble on rail of the present invention integrates the ratchet mechanism with the plug of the electrical connector, and converts the one-way rotation movement of the electrical connector separation and disassembly into a small-scale reciprocating swing motion, so that astronauts can use it easily. Hand tool operation reduces the need for maintenance tools and astronaut operating capabilities.

The invention discloses a spacecraft environment light control system based on attitude recognition, and relates to the field of attitude detection and the field of image processing. The system comprises at least one electronic chip processor and more than one image sensing device. Compared with a wearable dynamic capture device, the spacecraft environment light control system adopts a camera shooting and recording image type dynamic capture device which is more convenient, the process of pasting motion capture sensors one by one is avoided, and meanwhile the cost is relatively low under the condition that the spacecraft environment light control system is used by multiple persons in spaceflight. The system aims at a use environment where a human body is inconvenient to move in a spacecraft environment, can help an astronaut to quickly and automatically adjust light with related light emitting parameters according to a human body posture, is high in intelligent degree, improves the psychological comfort of the astronaut, improves the working efficiency of the astronaut in a mode of changing ambient light, and improves the working efficiency of the astronaut. Therefore, a certain auxiliary effect on the life of the astronaut in the spacecraft is achieved.

The invention provides an exoskeleton type man-machine back frame system for astronaut micro-low gravity simulation, which comprises a three-dimensional rotating mechanism, an exoskeleton bracket mechanism and a gravitational torque compensation mechanism, and is characterized in that the exoskeleton bracket mechanism is rotationally connected with the three-dimensional rotating mechanism; the gravitational torque compensation mechanism is arranged on the three-dimensional rotating mechanism and connected with the exoskeleton support mechanism. According to the exoskeleton type man-machine back frame system for astronaut micro-low gravity simulation, the gravitational torque compensation mechanism is arranged on the three-dimensional rotating mechanism to connect the three-dimensional rotating mechanism with the exoskeleton support mechanism and is used for compensating gravitational torque when the exoskeleton support mechanism rotates along with three axes of the astronaut; therefore, the weightlessness of the astronaut in the directions of three rotational degrees of freedom is simulated, so that the somatosensory of the astronaut in a micro-low gravity environment is truly simulated.

The invention discloses a motion mapping method based on a CyberForce teleoperation mechanical arm, belongs to the technical field of robot teleoperation, and aims to solve the problem that the control mapping effect of a conventional control method for robot astronauts is poor as working spaces of the mechanical arm and human arms are inconsistent. The motion mapping method comprises the steps that a motion space of the mechanical arm is divided into a free moving space and a fine operation space; bulges are utilized to represent an outer contour of a reachable working space in a corresponding space; in a bulge outer contour of the free moving space, the position is controlled through set zoom factor mapping and the posture is controlled through posture adjustment mapping according to thereachable working space of the mechanical arm; and in a bulge outer contour of the fine operation space, the position is controlled through variable zoom factor mapping and the posture is controlledthrough posture adjustment mapping according to a set posture space of the mechanical arm. The motion mapping method is used for control of the position and posture of the tail end of the mechanical arm.

The invention provides an outboard workbench for an astronaut. The outboard workbench comprises a frame body, wherein a butt joint mechanism, a first tool storage mechanism and a second tool storage mechanism are arranged on the frame body; the butt joint mechanism is fixedly installed on the frame body and used for being in butt joint with a space suit; and the first tool storage mechanism and the second tool storage mechanism are respectively provided with tool interfaces at positions corresponding to tools, are rotatably connected with the frame body and are respectively positioned on two sides of the butt joint mechanism. According to the above technical scheme, the first tool storage mechanism and the second tool storage mechanism are arranged on the two sides of the frame body respectively, the tool interfaces are arranged in correspondence to the tools, so the tools can be placed on the two tool storage mechanisms; and the frame body is provided with the butt joint mechanism, so the frame body can be installed on the space suit, and the astronaut can thus carry a large number of tools without being affected when performing out-cabin maintenance.

The invention discloses an active compensation method for a somatosensory micro-low gravity simulation device, and the somatosensory micro-low gravity simulation device comprises a gravity balance assembly, and a buffer assembly which provides buffer potential energy for the gravity balance assembly to at least partially balance the gravity of a human body. The active compensation method comprises the following steps: S1, acquiring an additional torque generated by a micro-low gravity simulation device; and S2, outputting compensation torque in the opposite direction to the somatosensory micro-low gravity device according to the additional torque. The reverse compensation torque is output according to the obtained additional torque, so that the walking effect of the astronaut in the training system is consistent with or close to the actual walking effect on the moon surface and the Mars surface, the active compensation efficiency is improved, and the simulation precision of the device is improved.

The invention discloses a positioning and locking device for replaceable electronic equipment outside the cabin, which comprises a replaceable electronic equipment body outside the cabin and a mounting bracket for the deck; the mounting bracket for the deck is fixed on the outer wall of the spacecraft; the body of the replaceable electronic equipment outside the cabin There are lugs on both sides of the side; the body of the replaceable electronic equipment outside the cabin is provided with a first positioning mechanism and a second positioning mechanism; the first positioning mechanism includes a first positioning hole set on the lug and a hole set on the mounting bracket The first positioning pin, the first positioning pin is a coarse and fine two-stage positioning pin; it is also provided with at least one holding mechanism, and the holding mechanism includes a reed on the lug, a reed bracket and a reed on the deck mounting bracket. Holding pin; thus, the positioning and locking device of the external replaceable electronic device of the present invention realizes rapid positioning and fixing of the body of the external replaceable electronic device, frees the hands of the astronauts, and improves the work efficiency of the astronauts. The invention also discloses a method for astronauts to replace equipment outside the cabin.

The invention relates to an upper limb limiting mechanism of a space suit, a shoulder joint limiting mechanism is formed by connecting two semispherical thin shells in series and has three degrees of freedom which are respectively convergence / abduction, forward extension / backward extension and inward rotation / outward rotation, an elbow joint mechanism is formed by connecting a hinge pair mechanism and a cylindrical pair mechanism in series and has two degrees of freedom, and the elbow joint mechanism has two degrees of freedom. The wrist joint mechanism is composed of a wrist extension plate, a wrist plate, a palm plate and a hinge pair and has two degrees of freedom. Movement of the upper limbs is decomposed into movement of the shoulder joints, the wrist joints and the elbow joints, and the movement range of the joints is limited by designing limiting mechanisms of the shoulder joints, the wrist joints and the elbow joints, so that the upper limbs of the astronaut can be forced to move in the simulated astronaut device; the problem that when the astronaut is in the earth environment, the movement limitation on the upper limbs of the astronaut cannot meet the requirements in the space environment state is solved.

The invention provides a lithium-ion storage battery for an outboard power tool used in aerospace, including a lithium-ion storage battery cell, a pressure plate, an outer cylinder, a support rod, an insulating ring, a top cover, a bottom plate, and an electrical connector. The structure of this example is characterized in that : The circular outer cylinder is good for astronauts to grasp with one hand; the floating in-line electrical connector and the guide groove of the battery shell are convenient for astronauts to blindly insert and dock; the metal sealing structure can shield space radiation; the in-line shape can realize the astronaut cabin It can be quickly replaced outside to provide sufficient battery life for electric tools and to deal with emergencies outside the cabin. The structure provided by the invention is simple in layout, less in parts, low in cost, small in size, easy to carry, high in output voltage, and easy to replace. It can also be used as a supporting battery product for electric tools and can be used in civilian products, especially in the field of space.

A device for preventing amyotrophy of an astronaut during space weightlessness mainly comprises mesh belt type joint elastic force conjoined clothes, permanent magnet torque sole shoes and magnetic lining plates. The astronauts are dressed in a space cabin, and the tension force of the corresponding part of the mesh belt type joint tightness conjoined clothes and the magnetic attraction force distance generated by the permanent magnetic moment sole shoe and the magnetic lining plate arranged in the space cabin are overcome as long as the astronauts move or walk, the force intensity is similar to the force intensity of muscles of corresponding parts of limbs such as cervical vertebra, shoulder elbow, waist, leg, foot and the like when the astronauts move on the ground, the muscle atrophy of the parts can be prevented when the astronauts work or live in the space cabin, and the problems of extreme discomfort and low working efficiency caused by the floating state of the bodies of the astronauts are solved. Meanwhile, a body forward and reverse transposition bracelet and a forward and reverse instrument interpretation operation device are mounted in the space capsule, so that the utilization rate and the cost performance of the inner surface of the space capsule can be multiplied.