332 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 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 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 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 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 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 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.

The invention relates to the technical field of thermal control of commercial spaceflight unfolding mechanisms, in particular to a deformable liquid metal thermal control commercial spaceflight flexible unfolding mechanism which comprises a flexible unfolding mechanism body and a flexible fluid circulation pipeline integrated inside or on the surface of the flexible unfolding mechanism body and synchronously folded and unfolded along with the flexible unfolding mechanism body. The fluid driving and heat exchange unit is arranged in the non-flexible area of the spacecraft platform or the body and is connected with the flexible fluid circulation pipeline to form a closed circulation loop; wherein the flexible fluid circulation pipeline is filled with a liquid metal working medium. The liquid metal working medium has high thermal conductivity and flow characteristics, and is matched with the vein-shaped / grid-shaped microtube array, so that the temperature of each region of the flexible unfolding mechanism can be quickly balanced, and structural stress deformation caused by temperature gradient is effectively eliminated; and the adaptive capacity of the mechanism in extreme space environments such as high and low temperature alternation and intense radiation is greatly improved.

The invention provides a deep space exploration simulation test system and method.The deep space exploration simulation test system comprises a thermal interface structure, a cryogenic subsystem and a heating structure, the cryogenic subsystem can refrigerate and cool the thermal interface structure, and the heating structure can heat the thermal interface structure; the deep cooling subsystem comprises a low-temperature refrigeration assembly and a gas cooling assembly, the low-temperature refrigeration assembly transmits cold energy to the thermal interface structure in a one-way mode, and the gas cooling assembly cools the thermal interface structure through cooling gas. The continuous temperature regulation in the range of 300K to 423K is realized through the combination of air cooling and electric heating, and the continuous temperature regulation in the range of 38K to 300K is realized through the combination of a G-M low-temperature refrigerator and electric heating; compared with the existing space environment simulation equipment, the temperature zone can be expanded to 38K to 423K, and the extreme temperature zone environment required by deep space exploration including the lunar surface polar zone and the Mars can be completed; meanwhile, the integrated heat exchange cryogenic subsystem based on heat conduction and convection is compact in structure, liquid nitrogen and liquid helium do not need to be used, and energy conservation and environmental protection are achieved.

The invention discloses an LEO track single event effect inversion method and device, a medium and a product, and relates to the field of space environment monitoring and evaluation, and the method comprises the steps: carrying out the training and optimization of a first LSTM neural network and a second LSTM neural network at the same time through a training data set, and obtaining a classification model and a regression model; the current position and the current time are pushed forwards for a set number of hours, the average value of the space weather parameters of each hour is input into a classification model and a regression model at the same time, and a numerical value output by the classification model and a particle flux predicted value at the current position output by the regression model are multiplied; obtaining a final particle flux prediction value at the current position; obtaining the particle flux of the LEO orbital plane according to the final predicted value of the particle flux at each position to be predicted on the LEO orbital plane; and obtaining the single event upset rate of the LEO orbital plane according to the particle flux of the LEO orbital plane. The method can accurately predict the particle flux of the LEO orbital plane and the single event upset rate of the LEO orbital plane.

The invention discloses a spacecraft form control method and system based on an evolutionary algorithm and reinforcement learning, and the method specifically comprises the steps: S1, building an initial population, and enabling individuals in the population to be spacecrafts of different forms, which are different functional modules and different module number combinations; s2, performing inner ring initialization learning training on all individuals in the population, and calculating a fitness value of each individual; s3, selecting individuals with relatively high fitness values to form an elite population; s4, performing uniform crossover and single-point mutation on the elite population by using genetic and mutation operations in a genetic algorithm to generate elite offspring; s5, inner ring reinforcement learning: performing learning training on the elite offspring obtained in the step S4; s6, performing form evaluation; and S7, forming an optimal individual. According to the method, the characteristics of a space environment and task requirements are fully combined, an inner and outer ring algorithm architecture based on deep evolution reinforcement learning is adopted, and through continuous alternation of outer ring form evolution and inner ring learning training, form autonomous generation of the modular spacecraft is realized.

The invention relates to the technical field of space on-orbit robots, in particular to a reconfigurable rigid-flexible coupling space on-orbit assembly robot which comprises a spacecraft cluster, a lifting type parallel robot, a flexible cable system, a flexible cable driving platform, a mechanical arm module and a bistable self-adaptive clamping jaw module. A spacecraft cluster is used as a base, and the modular reconfigurable characteristic is achieved; the lifting type parallel robot located at the bottom of the spacecraft cluster executes position and posture fine adjustment of the spacecrafts by dynamically adjusting the position and posture of a movable platform of the lifting type parallel robot, when an assembly task is executed, the spacecraft cluster reaches a designated position, the relative position and posture between the spacecrafts in the spacecraft cluster are adjusted according to the requirement of the assembly task, and reconstruction of the robot is achieved; the multi-stage and multi-task on-orbit operation adaptive capacity is achieved, on-orbit operation of a variable-size and unstructured space target can be effectively executed, and the operation stability and robustness in the unstable space environment are remarkably enhanced.

The invention discloses a high-reliability satellite service software solidification, verification and loading method and system, and belongs to the technical field of satellite service software, bootloader guide software and on-orbit single particle protection. The problems that satellite service software in an on-orbit program storage area is overturned, the ground does not perceive, and autonomous recovery cannot be achieved after overturning are solved. The method comprises a processing and checking strategy of a satellite service software program, a starting strategy of guiding software and a processing strategy after a program storage area is overturned. The method specifically comprises the following steps of: after a satellite service source program is processed, reading program files of three storage areas in sequence, judging the program of each area through a calculation checksum mode, and if all the programs cannot run, taking out a complete program in a bitwise two-out-of-three mode to run; after the satellite service software is reset, the overturned condition is repaired through verification and moving operation; and when the satellite service program runs, repairing is completed through an overturning detection mechanism. The method is suitable for curing, checking and loading the satellite service software of the high-orbit satellite in a more complex space environment.

The invention relates to a satellite energy system intelligent control method and a storage medium, and the method comprises the steps: obtaining the real-time operation data of a satellite energy system; inputting the real-time operation data into a satellite energy system environment model, performing semantic understanding and feature correlation analysis on the real-time operation data by using a large language sub-model in the environment model, and extracting key features; using an intelligent decision framework in the environment model to generate state data corresponding to the state space based on the key features; generating action data corresponding to the action space based on the key features and the state data, and generating a reward prediction value based on the key features, the state data and a reward function; generating an optimization strategy based on the action data and the reward prediction value; and performing real-time control operation on the satellite energy system based on the optimization strategy. Through the method and the device, the problems that the dynamic space environment is difficult to adapt and the multi-task requirement cannot be efficiently balanced are solved, and efficient management and optimization of the satellite energy system are realized.

The invention discloses a target detection network radiation hardening method for a space spacecraft AI chip, and belongs to the technical field of neural network radiation resistance. The method comprises the following steps: acquiring a target detection network model; a Dropout enhancement model and an exponential bit quantization optimization model are adopted respectively; and carrying out target detection in a space environment by adopting the optimized model. According to the method, the robustness of the neural network in the space radiation environment can be remarkably improved, the reasoning precision and speed of the model can be kept, the problem of reliable operation of the deep learning model in the space environment is solved, and the stability and task success rate of a spacecraft intelligent system are optimized. Aiming at the problem of single event upset caused by high-energy particle radiation in a space environment, the invention provides a training-reasoning collaborative optimization strategy, and provides reliable guarantee for AI application on a spacecraft.

The invention discloses a space false target system based on an inflatable structure and a deployment method thereof. Relates to the technical field of spacecraft protection, and the system comprises a load cabin and a storage cabin, the storage cabin is internally provided with a camouflage module, and the load cabin is internally provided with an inflation module used for inflating the camouflage module, a power supply module used for supplying power and a posture regulation and control module used for controlling the posture; the storage cabin is composed of a plurality of folding plates and can be automatically unfolded so as to release the camouflage modules in the storage cabin. According to the deployment method, satellite release is carried out along with the following steps of attitude adjustment, inflation and the like. Rapid unfolding is achieved through the folding type storage cabin and the torsional spring hinge, rapid deployment and stable control are achieved in combination with the inflation module and the posture regulation and control module, and the problems that a traditional system is complex in deployment, low in unfolding efficiency and insufficient in posture adjustment are solved; the system has the advantages of rapid deployment, compact structure, stable and reliable attitude and suitability for a dynamic space environment.