219 results about "Micro gravity" patented technology

The invention relates to the technical field of intelligent robots, in particular to a mechanical arm-dexterous hand system tool intelligent grabbing strategy generation method oriented to a space microgravity environment. Based on installation configuration of a mechanical arm-dexterous hand system, gravity coefficients are set for a tool to be grabbed and an environment scene, and a simulation environment under space microgravity is constructed; on the basis of configuration of a tool to be grabbed and the dexterous hand, a grabbing configuration of the dexterous hand is generated, and a fixed grabbing test is carried out in the simulation environment; and on the basis of the simulation environment, the pose information of the tool to be grabbed and the real-time states of the mechanical arm and the dexterous hand serve as input of neural network training, actions of the mechanical arm and the dexterous hand serve as output of neural network training, and a grabbing strategy is obtained through neural network training. According to the scheme, an intelligent grabbing strategy of a mechanical arm-dexterous hand system tool can be generated for the space microgravity environment.

A space robot ground microgravity crawling test system is characterized in that the lower end of an outer frame is fixed on the ground, the upper end of the outer frame is provided with an X / Z-axis gravity compensation module and a Y-axis gravity compensation module, the upper surface of a centroid following module is fixedly connected with a suspension rope in the X / Z-axis gravity compensation module through a tension sensor, and the lower surface of the centroid following module is fixedly connected with a space crawling robot through a universal joint and a spherical hinge; the space crawling robot conducts a space microgravity crawling test on the target simulator, the target simulator is placed on the ground through universal wheels, and when the robot crawl, the target simulator moves in an X / Y mode and rotates around the Z axis under the counter-acting force, so that three-degree-of-freedom space microgravity simulation conditions are provided. Meanwhile, the X / Z-axis gravity compensation module and the Y-axis gravity compensation module can realize micro-gravity compensation autonomous following of the space crawling robot in the X / Y / Z directions, and the mass center following module can realize that the mass center of the robot is always on a suspension point extension line when the posture and the configuration of the robot are changed.

The invention provides an astronaut working load relieving implementation method based on a virtual reality technology in a microgravity environment, and belongs to the field of microgravity environment psychological recovery. The problems that an existing working load relieving system is difficult to provide higher immersion and interactivity for astronauts in a microgravity environment, and is poor in individuation and intervention effect are solved. According to the method, physiological state data and psychological state data of astronauts are collected, task execution data are integrated, workloads are quantified, workload types are identified after comprehensive evaluation, preliminary matching is carried out according to defined matching conditions, a virtual scene is selected through machine learning and multi-dimensional data analysis, and a virtual scene is obtained. And performing continuous fine adjustment in the loaded and presented optimized virtual scene, and recording the process. According to the method, an effective pressure relieving means can be flexibly and accurately provided according to the real-time state of the astronaut and the requirements of the working environment, and the cognitive reconstruction and psychological recovery process is enhanced through the immersion of the virtual reality technology.

The utility model discloses a microgravity experimental instrument which comprises a vertical framework, and a plurality of friction plates are installed on the front outer wall and the rear outer wall of the vertical framework in the vertical direction. The rising and falling platform body is installed at one end in the vertical framework in a sliding mode, and an experiment cabin is installed at the top end of the rising and falling platform body; and the belt wheel lifting units are installed on the two sides of the interior of the vertical framework and used for driving the lifting platform body to do accelerated lifting motion. According to the utility model, the active brake mechanism and the friction plate are matched to work to control the accelerated rising of the rising and falling platform body and the deceleration of the free falling body, experiment parameters are ensured to be within a required range, meanwhile, the active brake mechanism can increase the safety of an experiment, and especially in an emergency, the active brake mechanism and the friction plate can be used for an emergency stop experiment. And unnecessary damage or danger is avoided.

The invention relates to a three-dimensional microgravity simulation system, and belongs to the field of spaceflight mechanism ground tests. According to the three-dimensional microgravity simulation system, ground six-degree-of-freedom microgravity simulation can be realized, the aircraft simulator and accessories thereof have a five-degree-of-freedom motion state on an air floating plane through the five-degree-of-freedom air floating platform, and the aircraft simulator can have a three-dimensional space six-degree-of-freedom motion state through the magnetic air suspension assembly. In the process of a ground microgravity experiment, the gravity of the movement of the aircraft and accessories thereof is unloaded by the magnetic suspension assembly, so that the movement interference of the aircraft simulator and the microgravity simulation tool is avoided, and the problem of dynamic high-precision gravity unloading is solved.

The invention belongs to the technical field related to robot motion control, and provides a robot motion control method and system in a microgravity environment in order to solve the problems of stability and sand blowing of robot motion under existing microgravity. A robot swing stage is divided into three sub-stage motions, and a robot foot end expected track is generated for each sub-stage motion; the robot state information, the historical track and the environment information are input into a pre-constructed joint control model, and a joint control instruction of the robot in the microgravity environment is obtained through prediction; the joint control model is a strategy network model trained in a reinforcement learning mode; the trajectory tracking reward is determined by the actual position of the robot and the expected position of the foot end of the robot. Stable, low-disturbance and high-efficiency movement of the robot in the microgravity environment is achieved, and meanwhile the sand blowing phenomenon is effectively restrained.

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.

The invention provides a navigation method and system for a flying robot in a microgravity-normal air environment, and belongs to the technical field of autonomous navigation of robots. The problem that a robot collides with experimenters and floating objects in the environment in a near space is solved. The method comprises the following steps: acquiring navigation positioning information based on point cloud data of a depth vision camera carried by a robot and attitude angle sensing data acquired by an IMU module; determining point cloud distribution and voxelization space size; and constructing an environment map based on the acquired accurate positioning information. According to the invention, position and attitude stable control, autonomous navigation target identification and tracking in a complex environment in the cabin, and motion planning and collision avoidance can be realized, high-level and more complex tasks such as efficient interaction with experimenters, cooperative operation and the like are further realized, higher-level autonomous operation capability is realized, and the technical advantages of high safety and high reliability are realized.

The invention discloses a drag-free spacecraft ground experiment system for a gravitational wave detection task, and belongs to the technical field of spacecraft dynamics and control, and the drag-free spacecraft ground experiment system comprises a smooth flat platform, a non-contact real-time position attitude measurement system and a drag-free spacecraft simulator; the non-dragging spacecraft simulator is located on a smooth flat platform and simulates a microgravity environment; the smooth and flat platform provides a friction-free and flat plane, and is preferably a smooth granite platform; the non-contact real-time position and attitude measurement system is used for measuring position and attitude information of the drag-free spacecraft simulator and the two test masses in real time, and sending the position and attitude information to the airborne calculation module of the drag-free spacecraft ground simulator through the wireless information transmission system; when the system is applied to a ground experiment, the problem that complex dynamic coupling and control between a drag-free spacecraft and a test mass cannot be simulated in the ground experiment can be solved; and the system provided by the invention has a higher degree of freedom.

The invention relates to a ground test gravity unloading device for simulating a space microgravity environment. A base is fixedly arranged at the bottom of a fixed frame; a suspension system is arranged above the base and comprises a fixed pulley block mounted on the fixed frame, a pull rope is wound on the fixed pulley block, the bottom of one end of the pull rope is connected with a dynamometer through a tension spring, and the bottom of the other end of the pull rope is wound on a winch mounted on the base; the hoisting system comprises an external excitation device which is suspended right above the detected object; the displacement sensing system comprises a displacement sensor. The device is simple in principle and construction mode, has a relatively ideal controlled unloading mode, has the test advantage of controllable fine adjustment, is mainly used for simulating a space micro-vibration / microgravity environment to carry out a ground test, reproduces a space environment on the ground to the greatest extent so as to verify the functions and performance of a spacecraft and components thereof, and has a wide application prospect. For example, whether the vibration isolator can work reliably on orbit is verified, so that the on-orbit risk is remarkably reduced, the research and development cycle is shortened, and huge cost is saved.

The invention discloses an asteroid exploration robot oriented to a microgravity environment. The asteroid exploration robot comprises a robot base body, a six-foot moving mechanism, an anchoring mechanism and a hub mechanism. The device has the beneficial effects that the anchoring mechanism adopts a spatial six-connecting-rod mechanism, a grabbing and attaching mechanism of insect claw thorns and a climbing and attaching mechanism of woodpeckers are combined, a brand new method is provided for microgravity surface exploration of asteroids, the technical limitation in the field at home and abroad at present is broken through, and the anchoring mechanism is different from a traditional rope-driven anchoring technology; each crawling unit has three degrees of freedom, and an anchoring mechanism and a hub mechanism are integrated at the tail end of the moving device; by means of the design, the robot can alternately work in a three-foot attaching mode or a three-foot crawling mode, meanwhile, a three-wheel rapid moving mode is supported, horizontal moving and flexible steering of the robot are achieved, and the technology can support the robot to complete multi-site and multi-target moving surveying tasks.

The invention discloses an induction type high-precision urine flow or coronary flow measuring device, which belongs to the technical field of medical instruments, and comprises a measuring box, a cantilever beam extending to the outer side of the measuring box is fixed on the inner side of the measuring box through a fixing assembly, and micro-weight sensing elements attached to the upper side and the lower side of the cantilever beam are arranged in the measuring box. The micro-weight sensing element and the variable resistor form a measuring bridge circuit and are connected with an electric signal recording device located on the outer side of the measuring box through a signal line. A liquid collecting assembly is arranged at the outer end part of the cantilever beam, a flow guide pipe fixing rod is arranged on one side of the liquid collecting assembly and is used for vertically fixing an external flow guide pipe, and the inner side of the flow guide pipe fixing rod is fixed on the side wall of the measuring box. The induction type high-precision urine flow or coronary flow measuring device is simple in structure and convenient to use, changes of liquid flow at different flow speeds can be accurately displayed, and the accuracy and scientificity of measurement and analysis of experimental results are effectively improved.

The invention discloses a gear service life evaluation method, and belongs to the technical field of aerospace mechanism service life evaluation. According to the technical scheme, firstly, a five-stress wear rate data set containing the rotating speed, the torque, the temperature alternating, the vacuum degree and the microgravity is established; then constructing a tooth surface solid lubricating film thickness evolution model based on a Hertz-Archard coupling model, and taking the film thickness approaching to zero as a failure criterion; acceleration factors under each acceleration working condition are calculated through model iteration, and a gear acceleration life test is carried out under an optimized working condition; after the test, the film thickness is measured and compared with model prediction, the rated working condition life of the gear is reversely deduced, the long-time on-orbit life of the gear is equivalently predicted through the short-time ground test, and high acceleration efficiency and reliability are achieved. The technical problems of environmental simulation distortion and low acceleration efficiency in aerospace lubrication gear service life evaluation are solved.

The invention relates to an annular antenna microgravity simulation experiment device based on a magnetic suspension technology. The annular antenna microgravity simulation experiment device comprises a rack, a linear guide rail group, a magnetic suspension driving module, a suspension rope, an annular deployable antenna, a driving rope and an antenna driving module, the linear guide rail group is horizontally arranged above the rack, and the tail end of the linear guide rail group is fixedly connected with the top end of the rack; the magnetic suspension driving modules are respectively arranged at the lower parts of the linear guide rail groups; the bottom of the magnetic suspension driving module is connected with nodes of the annular deployable antenna through suspension ropes. And the antenna driving module is arranged at one end of the bottom of the rack. The device has the characteristics of high-precision microgravity environment simulation, a large-aperture annular deployable antenna structure, excellent synchronous following performance and no friction, and solves the problems that the friction force is large, the antenna node and the gravity compensation device cannot be synchronized in real time and the like when the conventional large-aperture annular antenna performs a gravity compensation experiment by using a suspension method.

The microgravity anti-oscillation energy conversion device comprises a retainer, a first rack and a second rack which are parallel to each other and are arranged in opposite directions are fixedly mounted on the retainer; the inertia floating block is fixedly provided with a first joint gear and a second joint gear, and the inertia floating block can linearly move relative to the retainer, so that when the inertia floating block and the retainer move relatively, the first joint gear and the first rack are kept meshed, and a rotary motion is generated; the second joint gear is meshed with the second rack, so that a reverse rotation motion is generated; the flywheel is fixedly arranged on the inertia floating block; the first gear transmission system and the second gear transmission system are fixedly arranged on the inertia floating block, and the flywheel is in one-way connection with the first joint gear through the first gear transmission system and in one-way connection with the second joint gear through the second gear transmission system; and the generator is fixedly arranged on the inertia floating block and is always driven by the flywheel in one direction to generate power. According to the device, the wave energy recycling efficiency can be remarkably improved.

The invention discloses a space variable-gravity on-orbit fluid experiment system and method in the technical field of space fluid management, and the system comprises a variable-gravity centrifugal platform which is used for manufacturing a variable microgravity environment required by an experiment; the experiment box is mounted on the variable-gravity centrifugal platform, and an experiment storage box and a liquid storage box are arranged in the experiment box; the electric control box is arranged on the variable-gravity centrifugal platform and is connected with an electronic device in the experiment box; a box body of the experiment storage box is made of a transparent material, a gas-liquid interface in the experiment storage box can be observed, and the liquid storage box is used for storing a liquid working medium; the experiment storage box is provided with observation scales, and the observation scales are arranged in the centrifugal acceleration direction of the variable-gravity centrifugal platform so that the filling ratio of liquid in the experiment storage box can be observed through centrifugal force.

The invention discloses a press-in hardness measuring device and method in a microgravity environment, and relates to the technical field of space science experimental equipment. The invention discloses a press-in hardness measuring device in a microgravity environment. The press-in hardness measuring device comprises an airtight module, an air filtering module and a hardness measuring module, the airtight module comprises an airtight cabin body and a negative pressure device; the air filtering module is directly mounted in the airtight cabin body or is communicated with the interior of the airtight cabin body through a pipeline, and is used for circularly filtering dust in air in the airtight cabin body; the hardness measuring module is used for being coupled with or separated from a to-be-tested sample, and the air tightness of the airtight cabin body is not damaged in the coupling and separating processes. The invention discloses a press-in hardness measurement method in a microgravity environment. The method comprises the following steps: 1, carrying out sealing operation; 2, negative pressure operation; 3, hardness measurement and dust filtration; and 4, taking out the sample. The device has the advantages that by actively establishing a negative pressure environment, the airflow direction is inward even if extremely small leakage exists in the sealed cabin, so that chippings are efficiently restrained in the sealed space, and the safety is high.

The invention relates to an adjustable load space test support method. The load cold table and the telescopic device fix the load, the pressure is regulated and controlled through the pressure control assembly, the temperature is regulated and controlled through the heat support assembly and the load cold table, and the environment with the adjustable short-time space exposure radiation quantity is provided for the test load by combining stretching and retracting of the telescopic device and opening and closing of the load cabin door. Comprising the step of providing a load test support method for pressure control and temperature regulation in the microgravity cabin. A vacuum exposure test method which is long in time consumption and high in risk and is transferred by grabbing a load adapter through a mechanical arm is improved, and a load space test supporting method with exposure ionizing radiation and adjustable temperature in a microgravity cabin is provided. According to the load space test supporting method, the telescopic device carrying the load directly extends out of the cabin to carry out an exposure test, and the telescopic device can retract into the spacecraft at any time to achieve urgent danger avoiding. According to the invention, diversification of load space test support methods is expanded, complexity and cost of test support are reduced, and test safety and efficiency are improved.

The invention discloses a force-position coupling control method and system for a magnetic-pneumatic suspension servo device, and relates to the technical field of ground microgravity experiments of space mechanisms. After the sling inclination angle detection device is used for detecting the angle of the sling deviating from the numerical direction, the position following controller drives the omni-directional wheel to conduct position correction based on deflection angle feedback, meanwhile, the constant force compensation controller drives the constant force compensation motor to conduct tension adjustment through the deflection angle feedback and tension feedback, and therefore higher-precision gravity unloading is achieved.

The invention discloses a repeated unfolding and folding mechanism in a space microgravity environment, the repeated unfolding and folding mechanism comprises a transmission assembly, a winding assembly, a tensioning wheel assembly, a steel wire rope, an unfolding and folding spring and a load mounting interface, and the load mounting interface is mounted on a star; the unfolding and folding spring is fixedly connected between the transmission assembly and the load mounting interface; one end of the steel wire rope is fixedly mounted on the winding assembly, the other end is fixedly connected with the load mounting interface, and the middle part bypasses the tensioning wheel assembly; the tensioning wheel assembly is used for tensioning the steel wire rope; when the transmission assembly drives the winding assembly to rotate forwards, the steel wire rope is wound around the winding assembly, the unfolding and folding spring is compressed by winding the steel wire rope, and the unfolding and folding spring is folded; when the transmission assembly drives the winding assembly to rotate reversely, the steel wire rope is released from the winding assembly, and the unfolding and folding spring stretches under the action of spring force. The mechanism is suitable for unfolding and folding actions of load equipment in a space microgravity environment, and has the characteristics of repeated unfolding and folding and adjustable speed.

The invention relates to a gas-liquid separation device available for microgravity and lunar surface. The gas-liquid separation device comprises a gas-liquid separation cavity, a spiral flow guide structure, a metal net and two layers of porous media. The gas-liquid separation device is applied to a manned spacecraft environment control and life support system and is used for separating urine of astronauts from mixed gas-liquid fluid. A plurality of gas-liquid mixture inlets, an exhaust port and a liquid discharge port are formed outside the gas-liquid separation cavity, a spiral flow guide structure is arranged inside the gas-liquid separation cavity, and a layer of metal net is clamped between two layers of porous media below a flow guide plate. Gas-liquid mixed fluid enters the gas-liquid separation cavity through a plurality of inlet pipelines above and sequentially passes through the spiral flow guide structure, the metal net and the porous medium, finally liquid is discharged through a liquid outlet below the porous medium, gas in the gas-liquid mixed fluid is discharged through an exhaust port above the device, and gas-liquid separation in the urine mixed gas-liquid fluid is achieved.

The invention relates to the technical field of space robot ground testing, in particular to a space crawling robot surface and microgravity simulation system. Comprising a surface simulation assembly, an inclined plane adjusting assembly and a gravity balancing assembly, the surface simulation assembly is arranged on the inclined plane adjusting assembly, and the inclined plane adjusting assembly is used for adjusting the inclination angle of the surface simulation assembly; the gravity balancing assembly is arranged above the surface layer simulation assembly and used for being connected with the space crawling robot to be tested, and when the space crawling robot moves on the surface layer simulation assembly according to a set trajectory plan, the gravity balancing assembly can passively adapt to the motion trajectory of the space crawling robot; and the climbing motion of the simulated satellite surface in the space microgravity environment is completed. The space crawling robot simulates crawling on the surfaces of satellites and spacecrafts in the microgravity state, verification of the motion performance of the crawling robot under the space microgravity in a ground test is completed, and the problem that the ground test of the space crawling robot is difficult is solved.

The invention belongs to the technical field of high-temperature heat pipe heat transfer performance testing, and particularly relates to a high-temperature heat pipe performance testing device and method under the microgravity condition. The device comprises a heat pipe performance test body, a test cabin, a protection recovery system and a high-altitude carrying platform, the heat pipe performance test body is arranged in the test cabin, and the high-altitude carrying platform comprises a lift-off mechanism and a release mechanism and is used for sending the test cabin to an airspace at a specified height and releasing the test cabin to realize free falling of the test cabin. The protection recovery system adopts two-stage deceleration buffering to protect the test cabin. The device has the advantages of being controllable in cost, long in microgravity time and capable of being repeatedly used, performance testing of the large-length-diameter-ratio heat pipe under the simulated space microgravity environment can be carried out, and the performance of the high-temperature heat pipe under the real working condition can be accurately and comprehensively evaluated; the device is especially suitable for testing the starting characteristic, transient and steady-state characteristics and temperature uniformity of the high-temperature heat pipe under the microgravity condition.

A space-based repeatable tolerance-tolerant docking ground simulation test device is disclosed. This invention addresses the limitations of existing ground simulation technologies in accurately simulating docking errors, faithfully reproducing microgravity environments, and simulating tunnel conditions. The invention includes a ball-joint servo-oscillating frame. A six-degree-of-freedom attitude adjustment component is located at the bottom of the ball-joint servo-oscillating frame. A standardized interface prototype is mounted on the six-degree-of-freedom attitude adjustment component, and a servo component is mounted on the standardized interface prototype. One end of a steel wire rope is connected to the servo component, and the other end of the steel wire rope passes through a pulley system fixed to the ball-joint servo-oscillating frame and is connected to a counterweight. This invention belongs to the field of aerospace engineering ground simulation test technology.

The present invention provides a space intelligent flying robot in a microgravity-normal air environment, belonging to the field of flying robots. To achieve the goal of enabling the space intelligent flying robot in a microgravity environment to have independent control over position, posture, output force, and torque. The robot comprises a carrier main frame, an outer shell, a computing system disposed within the carrier main frame, a visual navigation system disposed in front of and behind the carrier main frame, a laser ranging module embedded in the outer shell, a power supply system disposed on the left and right sides of the carrier main frame, a power system embedded in the outer shell and within the carrier main frame, a gripping system disposed below the carrier main frame, and an interactive system disposed in front of and above the main frame. While realizing basic functions, the present invention also makes innovative designs in the robot architecture, optimizing the robot's performance in manipulation, control, perception, and real-time performance, and has high engineering application value and good engineering application prospects.

The application discloses a microgravity simulation simulation dynamic anchor point seat rope-driven parallel robot, relates to the field of rope-driven parallel robots, and comprises an outer frame, at least two layers of track modules are arranged in the outer frame, a plurality of dynamic anchor point seats are slidably connected on the track modules, at least four groups of dynamic anchor point seats are arranged on the track modules in the same layer, and the plurality of dynamic anchor point seats are connected with long-arm spread mechanical arms through ropes. Through the structure arranged in the application, the dynamic anchor point seat rope-driven parallel robot has super-redundant degrees of freedom and sufficient working space, can be applied to ground microgravity simulation simulation of the long-arm spread mechanical arm, a plurality of dynamic anchor point seats are installed on the track, the dynamic anchor point seats are connected with upper lifting points of the mechanical arms through the ropes, and each section of the rope can be used to drive the mechanical arm.

The invention provides a management device for small plate type storage PMD, and particularly belongs to the technical field of gas-liquid separation. A large blade assembly and a small blade assembly both adopt vertical blades, the blades adopt a plug-in type mounting structure, the principle that surface tension drives liquid under microgravity is utilized, a plate type liquid management technology is adopted, and the surface tension of the liquid is utilized to complete transmission and storage of the liquid, and the blades are designed into middle hollow structures and small blades. The structure weight is reduced, the liquid storage function under microgravity is achieved through the combination of the two parts, and therefore liquid drainage without gas filling is achieved, shaking of liquid can be restrained, the overall structure is optimized, the weight is reduced, the structure is simple, and reliability is high. The device comprises a large blade assembly and a small blade assembly, and further comprises a blade positioning shaft and a liquid collector assembly, the large blade assembly is composed of a first large blade and a second large blade, and the small blade assembly is composed of a first small blade, a second small blade, a third small blade and a fourth small blade.

The invention discloses a long-distance large-capacity SF6 gas pipeline bus total immersion liquid cooling microgravity supporting structure and method, and the structure comprises a total immersion environment system which comprises a total immersion environment system housing, an SF6 pipeline bus, a water body, and a plurality of radial limiting supporting structures. The SF6 pipeline bus and the radial limiting support structure are arranged in a closed cavity formed by the shell of the total immersion environment system, the radial limiting support structure is sleeved outside the SF6 pipeline bus, and the radial limiting support structure can move back and forth in the total immersion environment system; the space between the outer wall of the SF6 pipeline bus and the inner wall of the full-immersion environment system shell is filled with water, and the full-immersion water charging and discharging device is mounted on the full-immersion environment system shell; the shell of the pipeline bus is liquid-cooled, so that the cooling capacity of the pipeline bus is greatly improved; the radial limiting and supporting structure can freely slide in a full-immersion environment system, accumulative stretching and deformation of a long-distance and long vertical pipeline bus are achieved, and the problems of high-fall supporting and stretching of the pipeline bus are solved.

The invention discloses a high-precision gravity unloading device capable of achieving three-dimensional motion, and belongs to the field of gravity unloading. The device comprises an unloading truss assembly, a first longitudinal guide rail assembly, a second longitudinal guide rail assembly and two independent moving units, wherein the first longitudinal guide rail assembly and the second longitudinal guide rail assembly are different in installation height. Each set of motion unit comprises a longitudinal tackle assembly slidably connected to the longitudinal guide rail assembly, a transverse guide rail assembly bridged between the longitudinal guide rail assemblies, a transverse tackle assembly slidably mounted on the transverse guide rail assembly, a fixed pulley assembly fixedly connected to the transverse tackle assembly, and a lifting rope crossing the fixed pulley assembly to connect the tested rotating mechanism and the counterweight. Two sets of independent movement units are arranged, and the structural interference of a plurality of unloading points in the longitudinal opposite staggered movement process is avoided through the arrangement of longitudinal guide rails which are arranged in a high-low staggered mode. By optimizing the layout of the fixed pulley and the counterweight, three-dimensional high-precision dynamic follow-up unloading of a complex double-shaft rotating mechanism in a large rotating angle range is realized, and reliable microgravity environment simulation is provided for ground testing of aerospace equipment.

The utility model discloses a microgravity test bench, which relates to the field of microgravity technology. The utility model comprises an operating panel, wherein two inclined grooves are provided on the upper side of the operating panel, one end of the two inclined grooves are connected, and the bottom of the inclined grooves is connected to a collecting tube; two fixed plates are installed on the operating panel, one side of the fixed plate is rotatably matched with a threaded rod, and a U-shaped plate is threadedly matched between the two threaded rods. The utility model uses a suction cup to adsorb the sample through the inner side wall of the suction cup and move it for microgravity testing, thereby reducing the large friction generated during the sample falling process, reducing the problem of large errors in the experimental data obtained due to the friction generated, and improving the accuracy of the sample microgravity test.