34 results about "Astronauta" patented technology

Disclosed is an interplanetary rocket propulsion to Mars and the Moons of the nearer outer Planets by means of 6000° K temperature, 100 atmosphere pressure, power generation and propulsion systems that utilize a gas cooled nuclear reactor and metal powder combustion, in combination with water wherein dissociation into oxygen to react with certain metals to form on board retained metal oxides, and to heat the hydrogen from dissociated water as well as on-board liquid hydrogen that is seeded with an alkali metal for use in a linear, Faraday magnetohydrodynamic (MHD) generator that is coaxial with a MHD accelerator for propulsion, wherein water and probable metal sources on planetary bodies would provide rocket fueling by metal oxide reprocessing to metal and for manned permanent life support bases, and for search of high value minerals, gold, silver, aluminum, rare minerals, diamonds, for transport with their lesser gravity back to Earth.

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 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 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 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 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 discloses a rocket launch experience system and a rocket launch experience. The rocket launch experience system includes: a rocket body, including at least two compartments, one of which has an engine compartment, and one of which has an astronaut activity compartment; an assembly component, used to connect the at least two compartments; The command sending component is used to launch the command, and the command includes at least a rocket launch command; the transmission component is used to receive and forward the command and the command processing result; the command execution component includes at least a rocket launch mechanism for processing the rocket launch command , the rocket launching mechanism includes an engine or an engine equivalent arranged in the engine compartment; a display assembly includes a first display arranged in the test and launch hall; a power assembly is used to supply power to the command execution assembly. The rocket launching experience system of the present invention is not only simple in structure, but also has good experience effect and has better popular science significance.

The invention discloses a measuring device for hand-transmitted vibration of an electric tool for space on-orbit maintenance, comprising a subject, an on-orbit maintenance electric tool, a suspension system and a measurement system; the suspension system includes a bracket and is connected with the bracket The balancer, the screw test interface board fixed on the bracket, and the non-disengagement fastening device installed on the screw test interface board; the measurement system includes a data acquisition device and a computer, and one end of the data acquisition device passes through the data acquisition device line. cable to connect to the computer. In this application, one end of the data acquisition device is connected to the computer through a data acquisition cable, and the other end is connected to a mechanical sensor with an output axonometric point, a measurement point on the right side of the handle, and a measurement point on the left side of the handle through a sensor cable. The mechanical sensors at the measuring point on the right side of the handle and the measuring point on the left side of the handle are used to measure the vibration data of the three positions, which can assist the astronauts to better operate the on-orbit maintenance power tools.

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.