48 results about "Astronauta" patented technology

The utility model provides a novel astronaut seat. The novel astronaut seat comprises a backrest assembly, a seat basin assembly, a leg support assembly, a foot support assembly, a headrest assembly, a connecting rod assembly and a handle unlocking assembly, one end of the chair basin assembly is connected with the backrest assembly through the first rotating node, and the other end of the chair basin assembly is connected with the leg support assembly through the fourth rotating node; one end of the connecting rod assembly is connected with the backrest assembly through the second rotating node, and the other end of the connecting rod assembly is connected with the leg support assembly through the third rotating node; and the handle unlocking assembly is arranged at the second rotating node and is used for relieving the rotation limitation of the second rotating node. Synchronous adjustment or locking of a plurality of joints can be achieved only by adjusting or locking one rotating joint, the stability and the convenience are high, and the requirements of astronauts for various seat postures in flight missions are met.

A preparation method of a foldable / unfoldable honeycomb structure lunar module can meet the requirements of astronauts living on extraterrestrial bodies, liquid transportation, pressure-resistant containers, etc. In the present invention, a planar circular ring sheet material is equally divided and marked, misaligned and connected, axially stretched, and then glued and cured at a specified position to obtain a foldable and telescopic hollow honeycomb structure; the structure shaping of the honeycomb structure lunar module is realized by stepwise curing of the resin coating on the honeycomb surface. The present invention proposes a new hollow honeycomb structure as the skeleton structure of the lunar module. The planar honeycomb structure has the advantages of low density and strong pressure resistance, and is applied to the sandwich of anti-theft doors, airplanes, corrugated cardboard, etc. When the planar honeycomb is bent, the honeycomb will be deformed, seriously affecting its mechanical properties. The novel hollow honeycomb structure not only has the advantages of the planar honeycomb, but also solves the problem that the planar honeycomb is difficult to be applied to curved surfaces.

The invention discloses an anti-single event upset reinforcement method based on a Transform speech recognition model, and the method is used for improving the speech recognition efficiency and accuracy of astronauts in a spaceflight task, and comprises the steps: constructing a training set, and carrying out the preprocessing of the data of the training set; the preprocessed training set is input into a Transform voice recognition model, and a trained Transform voice recognition model is obtained; parameters in the trained Transform speech recognition model are modified, a single event upset event and errors possibly occurring in a high-radiation environment are simulated, and an SEU influence model is established; and based on the SEU influence model, carrying out robustness analysis on the Transform speech recognition model, determining a sensitive module, and carrying out triple modular redundancy technology reinforcement on the sensitive module to obtain a single event upset resistant reinforced speech recognition model.

The invention relates to the technical field of space station fragment protection, in particular to a space station fragment protection device based on an initiating explosive device pressing seat, which comprises a protection assembly, a first connecting assembly and a second connecting assembly, the protection assembly is used for covering a space station cabin, preventing space debris from directly impacting the cabin and bearing the impact of the space station debris. When the fragment protection device is additionally arranged on the ascending area of the mechanical arm in an on-orbit mode, firstly, the universal handle is connected with the first connecting assembly, and an astronaut drives the protection assembly to move to the ascending area of the mechanical arm through the universal handle so as to prevent the protection assembly from drifting at will. And then, a waste initiating explosive device pressing seat is used as an installation point position of the protection assembly, so that the second connection assembly is connected with the initiating explosive device pressing seat, the fragment protection device installation task is completed, the overall fragment protection capacity of the space station is further improved, and the on-orbit service life of the space station is prolonged.

Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) may capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, may land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC may include a parachute to slow the descent of the ADC. The ADC may also include tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images may be downloaded from the ADC.

The application provides a ground zero-gravity simulation device for astronaut on-orbit maintenance, which comprises a truss support system, a maintenance tool zero-gravity support system, an astronaut suit zero-gravity support system, an astronaut foot limiting support system, a space station cabin simulator and a six-degree-of-freedom mechanical arm, and the output end of the six-degree-of-freedom mechanical arm is connected to the space station cabin simulator, and the six-degree-of-freedom mechanical arm is used for simulating different maintenance postures of a space station in orbit. The application has the beneficial effects that the working state of an astronaut for maintaining peripheral equipment of a space station in different postures of the space station is simulated on the ground. The application has important significance for training astronauts for space maintenance operation. Furthermore, the application is the first device in the world which can simulate the zero-gravity state of astronauts for maintaining different postures of a space station on the ground.

The present invention discloses a method for enhancing the resistance to single event upset of a Transformer speech recognition model, which is used to improve the efficiency and accuracy of speech recognition for astronauts in space missions, including: constructing a training set and preprocessing the data in the training set; inputting the preprocessed training set into the Transformer speech recognition model to obtain a trained Transformer speech recognition model; modifying the parameters in the trained Transformer speech recognition model to simulate single event upset events and possible errors in a high-radiation environment, and establishing a SEU impact model; based on the SEU impact model, performing a robustness analysis on the Transformer speech recognition model to determine sensitive modules, and strengthening the sensitive modules with triple modular redundancy technology to obtain a speech recognition model with enhanced resistance to single event upset.

Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) is configured to capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, is configured to land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC includes a parachute to slow the descent of the ADC and tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images are downloadable from the ADC.

1. The name of the product of this design: Inflatable Castle (20373 Astronaut Rocket). 2. Purpose of this design product: for amusement equipment. 3. The design key point of this appearance design product lies in the shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture. 5. The bottom surface of this design product is a part that is not easily visible or cannot be seen when in use, so the top view is omitted.

The invention provides a space truss assembly connector and a using method, and relates to the technical field of aerospace. The space truss assembly connector comprises a supporting seat and variable structures, the variable structures are made of shape memory composite materials, the multiple variable structures are distributed in the circumferential direction of the supporting seat, the connecting end of each variable structure is connected with the supporting seat, and the connecting end of each variable structure is connected with the supporting seat. The deformation end of each variable structure extends away from the supporting base, and the multiple deformation ends are used for getting close to each other through external excitation to form a connector connected with a truss rod piece in an inserted mode. In the assembling process of the truss rod piece, only external excitation needs to be applied to the variable structure, and special connecting parts do not need to be additionally carried. According to the technology, a light-weight and low-cost assembly mode is provided for large-scale on-orbit facility construction, and dependence on a high-precision mechanical arm and out-of-cabin operation of astronauts is remarkably reduced.

1. Name of the product in this design: Lunar Rover. 2. Purpose of this design: As a vehicle for astronauts to travel, explore, and conduct research on the lunar surface. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

The present invention provides a manual arm folding and unfolding device for use in a space environment, comprising a ratchet input assembly, a transmission box assembly and an arm connecting assembly, wherein one side of the transmission box assembly is connected to the ratchet input assembly, and the other side of the transmission box assembly is connected to the arm connecting assembly. The present invention has the following beneficial effects: the invention adopts a gear and worm gear transmission combination mode, occupies a small space, is easy to operate, and can reliably lock the arm at any position; adopts a gear rack composite structure, realizes the function of first rotating and then translating by an astronaut's one-time input operation; and meets the astronaut's on-orbit one-handed operation and low-operation-force on-orbit operation requirements.

Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) is configured to capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, is configured to land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC includes a parachute to slow the descent of the ADC and tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images are downloadable from the ADC.

1. Name of the designed product: cup cover (third generation of astronauts). 2. Use of the designed product: cup cover. 3. Design points of the designed product: in shape. 4. Picture or photo that best shows the design points: design 1 perspective view 1. 5. Design 1 is designated as the basic design.

This application relates to the fields of positioning, navigation, semantic segmentation, and target detection technologies, and particularly to a method and system for collaborative positioning of astronauts and scientific targets on the lunar surface. The method includes: constructing a feature point map by collecting visual and inertial data, and using VIO sliding window optimization to estimate the astronaut's pose, generating a 3D environmental point cloud; further performing 3D target detection on the point cloud, distinguishing between scientific targets and lunar base station objects, and using prior information of scientific targets and a random sampling consensus algorithm for screening and constraint, constructing geometric constraints by fitting a geometric model of the targets and feeding them back into the pose optimization process, introducing iterative optimization to achieve pose correction; simultaneously calculating the relative pose of the astronaut and each target, and updating the environmental map. This method improves positioning accuracy and robustness in the absence of GPS and is suitable for autonomous navigation and mission execution in the complex lunar environment.

1. Name of the Design Product: Lower Limb Assistive Exoskeleton for Astronauts. 2. Use of the Design Product: For assisting astronauts in walking. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photograph that Best Illustrates the Design Key Points: Perspective view.

Systems and methods for operating a vehicle in an environment that requires an astronaut in the vehicle to wear a spacesuit, are presented. The vehicle may be a lunar rover or a rover to be used on Mars. An astronaut will be in a spacesuit while in the vacuum of the Moon. This vacuum or thin atmosphere will give rise to a pressure differential between the inside and the outside of the spacesuit. This pressure differential reduces the flexibility of the spacesuit, such that the joints of the spacesuit resist bending or flexing. Spacesuit stiffness is substantially reduced while an astronaut is in a pressurizable cabin of the vehicle, where the pressure differential can be reduced or eliminated. The spacesuit may provide all necessary life support while the cabin of the rover provides a cabin pressure that is substantially the same as the pressure in the spacesuit.

The present invention relates to a pneumatic arm, device and method that can be repeatedly extended and retracted for docking with the lunar surface, and belongs to the technical field of repeatable connection and separation of aerospace equipment. The invention solves the problem that the work is seriously affected by the special external environment. The invention comprises a rigid rod and a soft driver, the rigid rod and the soft driver are alternately arranged, the interior of the rigid rod has an air duct, the soft driver comprises a soft shell and an elastic metal sheet, the soft shell has a cavity, one side of the soft shell is corrugated, the other side of the soft shell is in contact with the elastic metal sheet in the cavity, and the air duct is connected to the cavity. The present invention can adapt to certain position and posture deviations between fixed equipment, facilitates docking, and has good adaptability; the present invention can be repeatedly extended and retracted, has a good load-bearing capacity, reduces the difficulty of operation, provides sufficient operating space for astronauts, and reduces the impact of the external environment.

The invention relates to a globe at a scale of 1:100,000, where 1 cm represents 1 km, and therefore has a radius of 63.71 m. A first sphere made of screens represents the surface of this globe. A second, even larger sphere, also made of screens, represents the space around the Earth. The objective of this invention is to welcome the public and immerse them in the experience of being an astronaut traveling around the Earth, able to move from pole to pole, and to admire the Earth on one side and the Universe in which it exists on the other. This invention allows its visitors to travel all around the Earth and to appreciate the upheavals it has undergone, is still undergoing today, and will continue to undergo in the future.

The invention relates to the technical field of positioning, navigation, semantic segmentation and target detection, in particular to an astronaut and scientific target cooperative positioning method and system suitable for the lunar surface, and the method comprises the steps: achieving the position and posture estimation of an astronaut through the collection of visual and inertial data, the construction of a feature point map, and the combination of VIO sliding window optimization, and generating a three-dimensional environment point cloud; further performing three-dimensional target detection on the point cloud, distinguishing a scientific target from a lunar base station object, performing screening and constraint by using scientific target prior information and a random sampling consistency algorithm, constructing a target fitting geometric model into geometric constraint, feeding back the geometric constraint to a pose optimization process, and introducing iterative optimization to realize pose correction; meanwhile, the relative poses of the astronaut and the targets are calculated, and the environment map is updated. According to the method, the positioning precision and robustness are improved under the condition of no GPS, and the method is suitable for autonomous navigation and task execution in the complex lunar environment.

The invention relates to the technical field of space operation assistance, in particular to a computer-based space operation auxiliary device which comprises a manned frame. The device further comprises a supporting assembly and an auxiliary assembly, the supporting assembly used for assisting supporting is installed at the rear end of the manned frame, the auxiliary assembly used for assisting walking is installed on the manned frame, the supporting assembly comprises an installation box, a fixing ring, a triangular support and an open groove, and the installation box is installed at the rear end of the manned frame. Fixing rings are magnetically connected to the left and right sides of the bottom end of the mounting box, triangular brackets are movably connected to the outer sides of the fixing rings, slots are formed in the left and right sides of the bottom end of the manned frame, and the fixing rings are centrally symmetric to the bottom ends of the slots; through cooperation of the triangular support and the telescopic air cylinder, the height of the triangular support can be adjusted, the device is suitable for astronauts of different heights, the best supporting and comfort degree is provided, the astronauts can better complete tasks, and inconvenience in operation or potential safety hazards caused by improper height are avoided.

1. The name of the design product: manned lunar rover. 2. The use of the design product: used as manned lunar rover, supporting the tasks of rapid transfer between different locations, living cabin and functional areas, emergency rescue and material transportation of lunar astronauts. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view.

The application relates to the technical field of space activity mechanisms, in particular to an unlocking device with an on-orbit manual unlocking function, which comprises a fixed frame, a base mechanism, a cover plate mechanism, a heat release unlocking device and a base spring assembly, wherein the base mechanism is arranged in the fixed frame and comprises the heat release unlocking device and the base spring assembly, the heat release unlocking device is arranged on the base spring assembly, the cover plate mechanism comprises an unlocking assembly, a transmission assembly and an unlocking screw rod, the unlocking assembly is connected with the transmission assembly, and the unlocking screw rod is located below the transmission assembly; the unlocking assembly drives the transmission assembly to rotate and move until the transmission assembly is inserted into the inside of the unlocking screw rod and drives the unlocking screw rod to rotate together, so that the cover plate mechanism is separated from the base mechanism, and unlocking is completed. The application has the advantages that the on-orbit manual unlocking function is added on the basis of the traditional heat release unlocking device, astronauts can perform on-orbit unlocking through a manual unlocking driving shaft, and the reliability of the cover plate unlocking is improved.

The present invention belongs to the field of space application, specifically, a stepper motor controller and control method in a space station cabin. It includes: a power conversion unit, a main control unit, a motor drive unit, a communication unit and an external IO unit; the power conversion unit is used to detect the current data flowing through the driver; the main control unit is used to check and analyze the control instructions sent by the host computer, and send the analyzed control instructions to the motor drive unit to control the driver; it also analyzes the control instructions that pass the verification, and judges the state of the stepper motor at the same time, and combines the analyzed control instructions with the state of the stepper motor, and sends the motor drive unit to control the driver to drive the stepper motor to work; the present invention has high reliability and strong safety. The present invention takes into account the complex space particle radiation environment, and the product has been verified by reliability experiments to ensure that the system continues to work reliably and stably. At the same time, multiple operation methods ensure the safety of cabin equipment and astronauts. It has strong versatility.

1. Name of this design product: Name tag (astronaut). 2. Purpose of this design: This design is intended to add fun and is suitable for children's activities or themed venues. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

The invention discloses a multifunctional comprehensive special cable for astronauts to simulate space training, and belongs to the field of cables. The invention discloses a multifunctional comprehensive special cable for simulating space training of astronauts. The multifunctional comprehensive special cable is characterized by comprising a bearing rope arranged in the center of the cable, three pairs of braided shielding wire pairs which are uniformly distributed, a plurality of insulated conductive wire cores, a radial waterproof layer, a longitudinal waterproof layer, an overall shielding layer and an outer protection layer. In the cable manufacturing process, the viscous water-blocking material is applied to the cable, the viscous water-blocking material is changed into an elastic solid through crosslinking to fill gaps of the cable core, once the waterproof isolation protection layer outside the cable is damaged, water entering the cable can be effectively prevented from flowing, normal operation of the cable is protected, and the service life of the cable is prolonged. Meanwhile, the force bearing rope is made of high-strength fibers instead of a common rigid material, so that the flexibility of the cable is improved.

An object of a system according to an embodiment is to efficiently perform space mission planning, support for astronauts, space education, and space data analysis.SOLUTION: A system includes a collection part, a proposal part, a monitoring part, a support part, a generation part, a provision part, an analysis part, and a summarization part. The collection unit collects past mission data and a current technical status. The proposal section analyzes the data collected by the collection section and proposes an efficient mission plan. The monitoring unit monitors a health condition and a work situation of the astronaut. The support unit provides necessary support based on the data obtained by the monitoring unit. The generation unit generates educational content related to space. The provision unit provides the content generated by the generation unit. The analysis unit analyzes a large amount of space data. The summarization unit summarizes and provides important information obtained by the analysis unit.SELECTED DRAWING: Figure 1