390 results about "Space environment" patented technology

The invention belongs to the field of flight path prediction, and discloses a flight path stability optimization method and system, a storage medium and equipment, and the method comprises the steps: responding to aircraft kinetic parameters, pilot physiological state parameters and three-dimensional space environment parameters which are synchronously collected from multiple sources, and constructing a dynamic fusion data set through timestamp alignment; based on a pre-constructed dual-channel feature extraction architecture, dual-channel features of the dynamic fusion data set are extracted, a first channel analyzes a dynamic coupling relationship in a time dimension through a sparse attention mechanism, and a second channel models a spatial correlation topology of environmental parameters through a graph neural network; a deep reinforcement learning decision engine is constructed by fusing dual-channel features, an environment state-control action-flight path stability mapping strategy is established, and control strategy optimization is driven through a reward mechanism; and generating a multi-parameter collaborative optimization instruction of the flight control plane based on the real-time decision engine. According to the method, the efficiency and precision during flight path prediction can be improved, and then the flight path is optimized.

The invention discloses a navigation satellite high-precision orbit forecasting method based on a bidirectional long short-term memory network, and relates to the technical field of satellite orbit forecasting, and the method comprises the following steps: (1) obtaining a reference orbit; (2) extrapolating a dynamic orbit; (3) constructing an orbit forecast error sequence; (4) training a network model; (5) predicting orbit forecast errors at future moments; and (6) compensating a forecast result. According to the method, the orbit prediction error sequence is constructed to describe the difference between the dynamic model and the real space environment, and the change rule of the orbit prediction error is captured and learned by adopting the bidirectional long-short-term memory network, so that the orbit error at the future moment is predicted, and the orbit prediction result based on the dynamic model is corrected; therefore, the defects of dynamic modeling in comparison with a real space environment are compensated, the trend that orbit errors are rapidly diverged along with the increase of forecasting time is inhibited, and a high-precision orbit forecasting task of a navigation satellite is effectively realized.

The invention discloses a power transmission line intelligent inspection method and system based on an unmanned aerial vehicle, and relates to the technical field of power transmission line robots, and the method comprises the steps: collecting three-dimensional space environment data of laser point cloud, visible light, infrared and meteorological data through an airborne multi-mode sensing module; constructing a dynamically updated environment digital twinborn model based on the environment digital twinborn model; online path re-planning is carried out by using an improved fast extended random tree algorithm, and static obstacles and dynamic meteorological risks are synchronously avoided; in a multi-machine cooperation scene, distributing inspection subtasks by adopting a greedy partitioning algorithm based on load balancing; performing real-time defect detection and positioning on the tower image by using a multi-scale feature pyramid convolutional neural network through an edge calculation unit; the whole-process automatic closed loop of power transmission line inspection from environment perception, intelligent planning, collaborative operation to defect identification is realized, and the safety, efficiency and accuracy of inspection operation are improved.

The invention discloses an ultra-low orbit guarantee method, system and equipment for a near-earth satellite. Comprising the following steps: determining a satellite orbit element at the current moment based on an atmospheric resistance perturbation item, a conventional perturbation item and a small thrust perturbation item, and inputting the satellite orbit element at the current moment into an orbit mechanical model; based on the orbit mechanical model and the satellite orbit elements, determining a first velocity position parameter of the satellite at the prediction moment under the ICRS coordinate system, and converting the first velocity position parameter into an ECEF coordinate system to obtain a second velocity position parameter at the prediction moment; inputting the time characteristic, the satellite state characteristic, the space environment characteristic and the second speed position parameter of the current moment into an orbit correction model to obtain a target error prediction value; adjusting the second speed position parameter based on the target error prediction value to obtain a target speed position parameter of the satellite at the prediction moment; and performing orbit attenuation risk early warning based on the target speed and position parameters of the satellite at the prediction moment.

The invention discloses a spacecraft space environment safety guarantee system and method based on three-step calculation, and the system comprises two subsystems: a space environment data service subsystem and a three-step calculation and analysis subsystem, and the three-step calculation and analysis subsystem calls data and an algorithm model from the space environment data service subsystem. The space environment safety guarantee analysis based on the three-step calculation is executed; the space environment data service subsystem comprises a metadatabase and a comprehensive database; the metadatabase comprises space environment space-based monitoring data, space environment foundation monitoring data and data from a specified space environment mechanism; the comprehensive database comprises a space environment numerical calculation model library and a spacecraft business application rule algorithm model library; the three-step calculation and analysis subsystem comprises a sun-earth space environment analysis and calculation module, a spacecraft orbit ring layer environment analysis and calculation module and a spacecraft task influence risk assessment and calculation module, and three-step calculation is executed through the three modules.

The invention discloses an orbit-driven atmospheric density estimation method. The method comprises the following steps: acquiring historical orbit element data and screening satellite numbers in a required time range; based on the obtained historical orbit element data and the screened satellite number, calculating a propagation orbit of the satellite in a future time period through an orbit propagation model; defining historical orbit element data as a real orbit, and calculating a propagation error at the same time point according to the real orbit and the propagation orbit; dividing the propagation errors into a regular class and an irregular class, and selecting satellite orbit parameters of the regular class; constructing an atmospheric density prediction model, and inputting the selected rule-class satellite orbit parameters into the atmospheric density prediction model for training and evaluation to obtain an optimized atmospheric density prediction model; and inputting the orbit parameter, the state vector, the space environment index and the error of the front and back orbit propagation in the previous time period into the optimized atmospheric density prediction model to obtain the atmospheric density at the future moment.

The invention relates to the technical field of satellite load thermal balance tests, in particular to a thermal control device for a satellite load vacuum thermal balance test. The heat isolation cabin is mounted above the supporting assembly; the heat dissipation assembly comprises a heat dissipation plate arranged on one side plate of the heat isolation cabin, a first heat rapid transfer assembly connected with the heat dissipation plate and the heat isolation cabin, and a first heater arranged on the heat dissipation plate; the heat compensation assembly comprises a second heat rapid transfer assembly and a second heater arranged on the side plate, away from the heat dissipation plate, of the heat isolation cabin; and a program-controlled temperature acquisition system. The device provided by the invention can simulate all working conditions of a satellite load in an in-orbit space environment, can realize conversion of different working conditions without opening the tank, reduces air pumping and deflation of the vacuum tank, saves the satellite load heat balance test time, does not need frequent disassembly and assembly in the test process, and improves the test efficiency. And the risk caused by frequent disassembly and assembly to the satellite load is reduced.

The invention discloses a forecasting method and device for an atmospheric resistance coefficient of a low-orbit satellite in the technical field of satellite navigation. The forecasting method comprises the following steps: acquiring satellite orbit determination data and a space environment index in a preset time period before forecasting; according to the satellite orbit determination data, performing simplified dynamic precise orbit determination on a low-orbit satellite, and fitting an atmospheric resistance coefficient in the simplified dynamic precise orbit determination process; performing data preprocessing on the space environment index and the atmospheric resistance coefficient and generating a sample set; constructing an LSTM prediction model, and training, adjusting and evaluating the LSTM prediction model through the sample set; predicting an atmospheric resistance coefficient in a future preset time period according to the finally obtained LSTM prediction model; and applying the atmospheric resistance coefficient in the future preset time period to the atmospheric resistance perturbation model of the low-orbit satellite for orbit forecasting. According to the method, the atmospheric resistance coefficient in the LEO satellite orbit prediction process is predicted in a high-precision manner through the LSTM prediction model, so that the orbit prediction precision is effectively improved.

The invention discloses a permanent magnet synchronous motor failure monitoring method, system and equipment for a space environment, and relates to the technical field of motor fault monitoring, and the method comprises the steps: constructing a simulation space environment experiment module, carrying out the accelerated aging experiment of a permanent magnet synchronous motor, and obtaining multi-dimensional degradation data; performing material performance evaluation on the permanent magnet synchronous motor, determining a material performance degradation result, performing failure analysis, and constructing a space environment failure feature library; and monitoring a motor operation parameter set of the permanent magnet synchronous motor in real time, determining an abnormal mode, and making a failure maintenance suggestion. The technical problems that in the prior art, the failure condition of the permanent magnet synchronous motor in the space environment cannot be accurately monitored, the reliability of the motor in the space environment is poor, and the operation stability is insufficient are solved, the failure condition of the permanent magnet synchronous motor is accurately monitored, and the reliability of the motor is improved. And the reliability and the operation stability of the permanent magnet synchronous motor in a space environment are improved.

The invention discloses a fault-tolerant reconstruction method for sensing faults of a spatial dexterous hand, and relates to the field of robot control. In order to solve the defects that in the prior art, a dexterous hand on-orbit sensor is weak in fault-tolerant capability, insufficient in model generalization capability and incapable of being adaptive to complex space environment changes, the technical scheme provided by the invention comprises the following steps: constructing a conditional variation auto-encoder model, inputting a joint position and a rope length sequence, and constructing a model; time sequence features are extracted, and a reconstructed joint position mean value and a prediction variance are output; the reconstructed joint position mean value is compared with actual joint data, a dynamic confidence interval is generated, and whether the data breaks down or not is judged; for the data judged to be normal, information entropy is calculated based on the prediction variance, and data samples with the information entropy exceeding a set threshold value are screened and written into a dynamic buffer area; and when the buffer data is fully loaded, incremental learning is triggered, and model parameters are updated by utilizing the buffer data. The method is suitable for real-time detection and fault-tolerant reconstruction of sensor faults in the long-term on-orbit operation process of the space dexterous hand.

The invention relates to a space far-field time-sensitive target optical data set generation method, in particular to a high-fidelity space far-field time-sensitive target optical data set generation method, and solves the technical problem of lack of a far-field time-sensitive target optical data set rapid generation method with complete label information in a space complex environment at present. The method comprises the following steps: firstly, establishing a space camera imaging model for converting a fixed star from a celestial coordinate system to a space camera imaging coordinate system, then respectively carrying out coordinate conversion and star magnitude-to-gray scale conversion on the fixed star in a view field of the space camera according to a navigation star catalogue, and displaying on a display to obtain an ideal background star map. Meanwhile, a simulation image of the time-sensitive target is obtained according to the same method, light path tracking is carried out on the simulation image, and an initial simulation image including the position and brightness characteristics of the time-sensitive target is obtained. And then simulating the noise in imaging, and fusing the ideal background star map, the noise and the initial simulation image to realize the generation of the high-fidelity space far-field time-sensitive target optical image.

The invention relates to a system digital three-dimensional situation display and rendering system comprising an environment visualization module used for collecting environment information data from various data sources and integrating the collected scene information data into the system; the scene visualization module is used for displaying the satellite space environment, the operation effect, the search action and the sensor load by using the scene information data; the spacecraft visualization module is used for checking detailed parameters and detailed information of the spacecraft; and the three-dimensional earth scene rendering module is used for digital earth rendering, and scheduling visual area data based on a terrain scheduling algorithm by acquiring image data and elevation data of a map. According to the method, the understanding and sensing ability of a user to the remote sensing satellite situation is improved through the three-dimensional display technology, the accuracy and scientificity of space situation analysis are enhanced, the limitation of a traditional simulation system in the aspect of space situation display is solved, and situation display is more visual.

The present invention relates to a ring-synchronized separation adapter for separating a payload in a space environment, and more specifically, to a ring-synchronized separation adapter for separating a payload in space environment, in which the ring-synchronized separation adapter has a configuration in which a plurality of segmented clamp portions are simultaneously fastened or unfastened by rotating a drive member making contact with all of the plurality of segmented clamp portions, so that accuracy in separation of the payload is improved, explosion is not utilized, and stability of the ring-synchronized separation adapter is improved as a whole.

The invention discloses an on-orbit control method based on butt joint of a mechanical arm and an electromagnet, which comprises the following steps: acquiring an initial pose of a target spacecraft through a sensor, and planning a motion track of the mechanical arm; when the tail end of the mechanical arm is close to a target by a preset distance, an electromagnetic docking module is activated to apply non-contact adsorption force to the surface of the target; a cascade force / position hybrid control algorithm is adopted to adjust the pose of the tail end of the mechanical arm, so that the electromagnetic butt joint surface is aligned with the target contact point; when the butt joint face error is smaller than a threshold value, the electromagnetic module is switched to a rigid locking mode, and rigid connection between the mechanical arm and the target is completed; and executing a task through the mechanical arm, and releasing electromagnetic locking and separating after the task is completed. The active electromagnetic module is integrated at the tail end of the mechanical arm, flexible adsorption and high-precision rigid docking of a non-cooperative target are achieved in combination with a multi-mode sensing and cascade predictive control algorithm, and the robot has the advantages of being high in docking efficiency, low in energy consumption and high in adaptability and is suitable for on-orbit service tasks in a complex space environment.

The invention relates to a low-orbit constellation satellite collection database building and space target orbit forecasting method, and belongs to the field of satellite communication. The method comprises the following steps: firstly, implementing low-orbit constellation satellite collection database construction, including satellite target resource analysis, resource description and resource mining, describing satellite resource individuals to be stored, acquiring multi-dimensional key information, and constructing a comprehensive and accurate low-orbit satellite target resource database; and in combination with a subsequent orbit forecasting algorithm and the parameters of the geographic position, the antenna pitch angle and the beam width of the communication receiving and transmitting end, the quantity and distribution of satellites in the beam intersection area of the receiving and transmitting end are obtained by using the forecasting model, and satellite resources are mined in a resource library. And predicting a satellite orbit by using the SGP4 orbit prediction model, obtaining the instantaneous position and speed of the satellite in-orbit operation, comparing the result of the orbit prediction model with the STK software simulation result, and verifying the prediction model. Technical guarantee is provided for efficient management and utilization of cooperative and non-cooperative giant low-orbit constellations in a complex space environment.

The invention relates to the technical field of aerospace, in particular to a multi-objective optimization method for a pod-shaped composite space thin-wall deployable structure. The method comprises the following steps: selecting an optimal sample point for uniformizing the space deployable structure in an interval range of structure parameters; constructing a finite element analysis model of the pod-shaped composite material space thin-wall deployable structure; the method comprises the following steps: by taking a damage failure criterion as a failure mode judgment basis of fibers and a matrix of a pod-shaped composite material, describing an evolution path of material rigidity in a damage development process by utilizing a bilinear rigidity degradation model after failure occurs, and constructing a random forest model based on adaptive particle swarm optimization as an agent model; and a Pareto leading edge optimal solution is obtained by calling the proxy model and is used as an optimal pod rod structure. In this way, the axial bearing capacity and folding performance of the unfolded structure are comprehensively improved, and the optimized structure can show more excellent mechanical performance and adaptability to different scenes in a complex space environment.

The invention provides a total electron amount calculation and correction method for space-based detection ionosphere data. The method comprises the following steps: converting an earth-fixed coordinate system; calculating collision parameters; sorting collision parameters and phase arrays; performing phase calibration; and obscuration correction of the total electron amount. The method has the beneficial effects that according to the forward relation between the total electron content of the ionosphere and the additional time delay of radio wave propagation caused by the ionosphere, the accurate total electron content is obtained from the satellite-ground radio detection ionosphere data by using a calculation and correction method; the method is of great significance in the aspects of satellite positioning navigation radio wave correction, space environment monitoring and the like.

The invention relates to the technical field of space operation equipment, in particular to an electric tool applied to on-orbit operation of a space mechanical arm. The high-precision control and the autonomous operation capability of the tail end of the space manipulator on the tool state in a complex space environment are realized, and the reliability, the flexibility and the automation degree of on-orbit operation are greatly improved. Compared with the prior art, the electric tool has the advantages that the structural integration degree, the function expandability and the intelligent feedback control are remarkably improved, and the electric tool is innovatively designed in the aspects of automatic storage of the bit, operation continuity and space environment adaptability; and the execution efficiency and the safety level of on-orbit maintenance and construction tasks of space stations, satellites and other spacecrafts can be effectively improved.

The invention discloses a satellite orbit space environment disturbance coping method and device and a computer program product, and the method comprises the steps: obtaining the current position data and current space environment data of a target orbit, the current space environment data comprises a first high-energy particle integral flux at a high-energy particle flux target position and a first upper atmosphere daily average atmospheric density; according to the current position data, querying a second high-energy particle integral flux and a second upper atmosphere daily average atmospheric density at the high-energy particle flux target position when the target orbit environment is quiet; calculating the relative disturbance quantity of the high-energy particle radiation environment of the target orbit and the maximum relative disturbance quantity of the atmospheric density of the upper layer; determining the current high-energy particle radiation environment disturbance degree and the current atmospheric environment disturbance degree in combination with the disturbance degree judgment range; and generating risk coping suggestions. According to the invention, the operation environment disturbance condition of the spacecraft can be accurately known, and the in-orbit operation safety of the spacecraft is improved.

The invention discloses a low-orbit satellite orbit state prediction method, device and equipment. The method comprises the following steps: defining a pseudo resistance coefficient according to an atmospheric resistance perturbation formula; decomposition operation based on pseudo resistance coefficient correlation analysis is carried out on the space environment parameters according to a VMD algorithm, space environment characteristic parameters are obtained, and the space environment parameters comprise a solar radiation flow index and a geomagnetic index; performing pseudo resistance coefficient prediction training on the initial SVM model by adopting the space environment characteristic parameters and a preset equivalent resistance coefficient to obtain an optimized SVM model; predicting a pseudo resistance coefficient at a future moment by optimizing the SVM model to obtain a pseudo resistance predicted value; and performing prediction calculation on the orbit state of the low-orbit satellite according to the pseudo resistance prediction value to obtain a state prediction result. The technical problem that in the prior art, it is difficult to ensure the influence degree of space environment changes, and consequently low-orbit satellite orbit state forecasting accuracy is poor can be solved.

The invention discloses a dual-path non-cooperative spacecraft pose estimation method based on uncertainty perception, and belongs to the technical field of spacecraft pose estimation. According to the method, a dual-path prediction framework based on a shared backbone network is constructed and comprises a geometric reasoning path and a global context sensing path. In the training stage, prediction results of the two paths are aligned through a geometric consistency loss function, and joint optimization is carried out by combining multi-task losses such as key point regression, classification, rotation and translation regression and the like. In the inference stage, the pose estimation result is adaptively fused according to the predicted variance output by each path, when the variance is low, the output of the global context sensing path is directly adopted, otherwise, the key point projections of the two paths are combined, and the final pose is recovered. The method has higher estimation precision, robustness and interpretability in complex space environments such as shielding, illumination variation and large-scale variation, and provides reliable visual navigation support for on-orbit autonomous tasks.

The invention relates to a satellite-borne electronic hardware design guarantee method and system. The method comprises the following steps: determining a satellite-borne hardware guarantee level (SHL) of satellite-borne electronic hardware; integrating a fault mode injection FM I into a design process of satellite-borne electronic hardware, and adjusting the execution depth of the FM I based on the SHL level; and providing a process cutting engine, and realizing adaptive process cutting based on a DO-254 standard according to the SHL level and in combination with the execution depth of the FM I. The system comprises an SHL evaluation module; an FM I management module; a space environment effect knowledge base; and a process cutting engine. According to the method, the problem that the DO-254 standard is insufficient in adaptability in the aerospace field is solved, the reliability design and verification efficiency of satellite-borne electronic hardware is remarkably improved, and the method is suitable for aerospace tasks such as various satellites and deep space probes.

The invention discloses simulated lunar soil for engineering and a preparation process thereof, the simulated lunar soil has a multilayer structure design, and comprises a basic mineral structure layer, a surface activity control layer and a simulated space environment effect layer. The basic mineral structure layer is prepared from modified olivine, titanium-rich basalt, rare earth doped plagioclase, calcium phosphate minerals, nano iron particles and vitreous minerals according to a specific proportion; the surface activity control layer adopts an atomic layer deposition technology to form a nano oxide layer on the surface of the mineral particles; the simulated space environment effect layer is formed through low-pressure helium ion bombardment and ultraviolet irradiation. The preparation process comprises the steps of intelligent graded crushing, mineral phase change control, surface modification and activation treatment, multi-parameter synchronous regulation and control and the like. The simulated lunar soil can be produced in a customized mode according to different lunar area characteristics, the matching degree with real lunar soil physical characteristics exceeds 90%, the ground testing precision of lunar exploration equipment is remarkably improved, and technical support is provided for lunar on-site resource utilization and lunar base construction.

The invention discloses an anomaly detection method and device based on the receiving power of a low-orbit satellite-borne GNSS receiver, and the method comprises the steps: obtaining a source receiving power sequence of the low-orbit satellite-borne GNSS receiver, and carrying out the enhancement processing based on Doppler frequency shift compensation and ionospheric noise filtering, and then generating a to-be-detected receiving power sequence; performing feature extraction on the to-be-detected receiving power sequence and then generating a receiving power feature vector based on a multi-scale entropy feature and a chaotic feature; and comparing the received power feature vector with a pre-constructed dynamic anomaly threshold to generate an anomaly detection result. According to the method, time sequence mismatching caused by frequency shift is overcome, energy distortion caused by ionosphere disturbance is also remarkably weakened, so that the accuracy and sensitivity of a subsequent nonlinear feature extraction process are guaranteed, and particularly, the robustness and effectiveness of GNSS receiving power anomaly detection can be remarkably improved in a complex dynamic space environment.

The invention relates to the technical field of spacecraft structure micro stress detection, in particular to a spacecraft structure micro stress detection device and a use method thereof, and the spacecraft structure micro stress detection device comprises a displacement amplification structure, a single mode fiber, a reflector, a broadband light source and a spectrum analyzer. An optical resonant cavity formed by an optical fiber end face and a lens is combined with a displacement amplification structure, when stress acts on a spacecraft structure, the cavity length of the Fabry-Perot resonant cavity changes, so that phase movement of light is caused, and accurate measurement of the stress can be achieved by detecting the phase movement. The antenna has extremely high anti-electromagnetic interference capability, and can work stably in a complex space environment. Even under the condition of violent temperature change, high measurement accuracy can be kept, and detection of tiny stress can be achieved through the amplification effect of the displacement amplification structure. And the stress characteristic signal and the background noise can be effectively separated, so that the detection reliability is remarkably improved.

The invention relates to a transformer substation unmanned aerial vehicle mounting automatic load changing cooperative control method and system, and the method comprises the steps: building a transformer substation three-dimensional space environment model, and fusing the electromagnetic interference field intensity distribution characteristics and the meteorological disturbance characteristics through the three-dimensional space environment model; constructing a mounting device dynamic behavior model of the unmanned aerial vehicle, wherein the mounting device dynamic behavior model comprises a mounting device constraint parameter set of mechanical arm joint motion constraints and mounting object deformation compensation coefficients; calling the three-dimensional space environment model and the mounting device dynamic behavior model to implement co-simulation verification based on a load switching path planning instruction of the unmanned aerial vehicle; and when a path conflict feature or a load instability feature is detected in the co-simulation verification process, it is determined that co-simulation verification is not passed, and the mounting device constraint parameter set is reconfigured and updated, so that co-simulation verification is passed. The method can adapt to the complex environment of the transformer substation, guarantees smooth mounting and changing operation of the unmanned aerial vehicle, and is suitable for the operation and maintenance scene of the transformer substation.

The invention discloses an on-orbit automatic focusing method for a spaceborne space target observation camera, relates to the technical field of space application of spaceborne cameras, and solves the problems of poor real-time performance and insufficient unattended operation adaptability of a manual focusing technology in the existing focusing technology. And meanwhile, in the automatic focusing technology, the hardware structure is complex, the space environment adaptability is weak, satellite-borne platform resources are limited and difficult to deploy, and focusing is difficult in a severe out-of-focus scene. According to the invention, the realization of automatic focusing is divided into a coarse adjustment stage and a fine adjustment stage. A large step pitch is adopted in the coarse tuning stage, rapid crossing is achieved, and an area adjacent to a positive focus position is rapidly positioned; in the fine adjustment stage, small step pitch is adopted, fine adjustment is achieved, and the peak position is accurately locked. The contradiction between the search speed and the positioning precision is balanced. When far away from the positive focus, a large-step-pitch fast approximation peak region is used, so that the number of iterations and the number of image acquisition frames are greatly reduced; when the focus is approached, small step pitch is switched for fine tuning, and the final precision is ensured.

The invention provides an orbit game system and method combining reinforcement learning and optimal control, and the system comprises an initialization problem setting module, an optimization solving module, a reinforcement learning module, a virtual environment module and a loop execution module. And solving a spacecraft orbit control quantity based on a CW equation by using an optimization solving module, and generating a final control strategy in combination with a TD3 algorithm in the reinforcement learning module. The system provided by the invention considers J2 perturbation influence in a virtual environment, continuously iterates and optimizes a control strategy, realizes an efficient and reliable orbit pursuit game under incomplete information and nonlinear disturbance, and is suitable for a multi-spacecraft autonomous decision-making task in a complex space environment.

The invention discloses a dynamic thermal protection device of space exploration optoelectronic equipment based on a flexible heat pipe, which comprises a heat dissipation support arranged on the outer side of the space exploration optoelectronic equipment, a bending driving device and the flexible heat pipe, the heat dissipation support is used for heat dissipation of the space exploration optoelectronic equipment, and the flexible heat pipe comprises a hot end, a cold end and a flexible connecting part. The flexible connecting part is communicated with the hot end and the cold end, the hot end of the flexible heat pipe is fixedly connected with the heat dissipation support, the cold end of the flexible heat pipe is connected to the output end of the bending driving device, the bending driving device drives the cold end of the flexible heat pipe to move, deformation of the flexible connecting part is achieved, and the heat conduction capacity of the flexible heat pipe is changed. According to the dynamic thermal protection device for the space environment detection satellite photoelectric equipment cabin by using the flexible variable heat pipe, the change of the heat conductivity coefficient of the heat pipe is realized by adjusting the bending angle of the flexible variable heat pipe, so that the self-adaptive adjustment of the temperature of the space environment detection satellite photoelectric equipment is realized.

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.