43 results about "Single star" patented technology

The invention discloses a single-satellite target sight atmospheric refraction correction method and system based on multi-spectral range finding, and relates to the field of atmospheric refraction processing, and the method comprises the steps: determining a target radiation intensity ratio based on two radiation intensities on different wavebands at the same moment; obtaining observation sight lines of the satellite on the measured target on different wave bands at the same moment, and carrying out light trace tracking to obtain a light ray tracking trajectory; determining a target grid through which each ray tracing trajectory passes from the atmosphere gridding model, determining an extinction coefficient of each target grid, and constructing a target function of a radiation intensity ratio with respect to the height of the target from the ground in combination with a radiation intensity calculation formula; determining a target height from the measured target to the ground based on a target function and a target radiation intensity ratio, determining the position of the measured target according to a track point matched with the target height in each light ray tracing track, and determining a sight line vector after atmospheric refraction correction by combining the position of a satellite, therefore, high-precision atmospheric refraction correction under a single-star observation condition is realized.

The invention discloses a multi-type satellite collaborative observation task planning method based on deep reinforcement learning, and belongs to the technical field of satellite task planning. The method comprises the following steps: firstly, acquiring attributes of multiple types of satellites and attribute information of observation tasks such as single-satellite, double-satellite cooperation and three-satellite cooperation; then, constructing a multi-dimensional constraint model; a deep reinforcement learning decision model based on the Seq2Seq architecture is built, a coding layer extracts position information for relative position coding, and a decoding layer outputs a task-satellite allocation scheme and an execution sequence; an Actor-Critic algorithm is adopted to train the model, and minimization of loss of an uncompleted task is taken as a target optimization strategy. The problems that a traditional satellite task planning method is difficult in multi-constraint balance, low in calculation efficiency and weak in generalization ability are solved, and the method has the advantages of being high in multi-constraint fusion ability, high in calculation efficiency, excellent in generalization performance and remarkable in income optimization and can be effectively applied to the fields of agricultural monitoring, disaster emergency, environmental governance and the like.

The invention provides a laser terminal calibration method and system based on inter-satellite orbit mutual transmission, and the method comprises the steps: carrying out the static calibration of a laser terminal through employing a star sensor or ground assistance before the establishment of an inter-satellite communication link, and enabling the pointing error of an optical axis to be smaller than 0.1 degree; after a communication link is established, orbit parameters of two satellites are exchanged in real time, a relative orbit normal vector is calculated through coordinate transformation, and a fusion reference is dynamically generated in combination with a static calibration result. According to the method, the real-time track mutual transmission data is used as dynamic correction input, the initial static calibration result is not only relied on any more, and fusion benchmark optimization of calibration and track mutual transmission is achieved. Compared with a traditional static calibration method depending on a ground station or a single-star inertial reference, the method breaks through the precision bottleneck of static calibration through the fusion of the orbit dynamic data and the static calibration result, effectively eliminates the orbit dynamic error, improves the laser calibration precision to a micro-radian level, and improves the calibration precision. And the establishment efficiency and reliability of the inter-satellite laser link are greatly improved.

The invention discloses a radar imaging detection satellite constellation design method, which comprises the following steps of: decomposing a constellation into a plurality of orbit surfaces, uniformly describing each orbit surface through four parameters, constructing an asymmetric constellation structure, and establishing a multi-target optimization model for solving by taking the total cost of the constellation, the maximum revisit time and the detection performance as targets. Non-dominated quantizer sorting is introduced in the sorting process, and satellite constellation design is completed. According to the method, single-satellite-based optimization of the salted fish is converted into orbital plane-based optimization, the optimization variable dimension is remarkably reduced, the method is particularly suitable for large-scale constellation design comprising hundreds of satellites, meanwhile, the Pareto frontier is obtained through non-dominated sorting, various constellation configuration schemes emphasizing different performances are provided, and the method is suitable for large-scale constellation design. Compared with an existing constellation design method, the problems that the to-be-optimized parameters are increased along with the number of satellites, and efficiency is low are solved, the scheme output by the algorithm is more reasonable through the improved sorting mode, and the method can be used for constellation design.

The invention discloses a multi-satellite cooperative task planning method based on a behavior tree. S101, the ground planning layer carries out modeling description of satellite tasks by combing satellite task requirements and sends a behavior tree task template to the high-orbit satellite layer; s102, after receiving the task, the high-orbit satellite layer plans the task according to the behavior tree task template; task decomposition is carried out to obtain meta-task sub-trees (tasks capable of being executed by a single satellite), specific satellite planning is carried out, satellites conforming to task constraints are planned to bear task execution, and the task sub-behavior trees are issued to a low-orbit execution layer; and S103, after receiving the task sub-behavior tree, the low-orbit execution layer binds a function according to a mechanism of the behavior tree and constructs code execution so as to realize execution of a specific task. According to the method, high flexibility, expandability and execution efficiency of task planning are remarkably improved, and the defects of a traditional method in the aspects of complex task decomposition, multi-satellite coordination and real-time response capability are effectively overcome.

The application discloses a kind of online calibration methods of multi-antenna navigation darkroom link delay, belong to satellite navigation user equipment test field.The application includes: by metrology / testing, the receiving zero value of calibration receiver at each frequency point is obtained;Navigation signal link delay calibration environment is constructed in multi-antenna navigation darkroom;Single star multi-output navigation signal simulator transmits single star single frequency point test signal;The current channel link delay is obtained by calibration receiver;Change single star multi-output navigation signal simulator output signal frequency point and obtain other frequency point link delay;Change signal output channel and obtain the link delay of each frequency point of other channel.The application can realize the automation online calibration of multi-antenna navigation darkroom link delay, can effectively shorten system calibration time, reduce the advantages of link delay calibration complexity.

The invention discloses an inertial navigation method based on single-star vector assistance, and belongs to the technical field of satellite navigation and inertial navigation combination. In particular to a method and a system for realizing high-precision positioning of a dynamic target by fusing observed quantities of a pseudo range, a pitch angle and an azimuth angle under the condition that only a single satellite is available, and the method and the system are suitable for complex environments where satellite signals of unmanned aerial vehicles, vehicle navigation and the like are limited in urban canyons, indoor environments and the like. According to the method, high-precision positioning can be realized under the condition that a single satellite is available, the method is suitable for complex environments with limited satellite signals, such as urban canyons or indoor environments, and the robustness and stability of a navigation system in a dynamic environment are enhanced. Compared with a method only using single-star pseudo-range or single-star angle observed quantity, the method provided by the invention has the advantages that through multi-dimensional observed quantity fusion, the accumulation speed of errors of the inertial navigation system is effectively slowed down, the risk of system divergence is reduced, and the effective working time of the system is prolonged.

This invention discloses a single-satellite orbit design method, system, and electronic equipment. Based on the orbital parameter description method using correlation coefficient k, this design method proposes orbit configuration optimization methods for both plane angle optimization and vector angle optimization. Considering avoidance constraints and imaging constraints, an objective function for correlation coefficient k is obtained. Further simulations yield single-satellite orbits for observation of key points on the space station. This invention significantly simplifies the traditional optimization process, providing a rapid design optimization algorithm for single-satellite orbit configurations in specific regions or random locations on the space station.

The application discloses a kind of low orbit single-satellite Doppler static positioning method, equipment and storage medium of integration, the method includes using ephemeris information to calculate the position, velocity and clock drift of satellite at each observation epoch;According to time window, Doppler frequency shift observation value is integrated, and observation data set is obtained;Based on the position, velocity and clock drift of satellite at each observation epoch, a plurality of candidate initial positions are screened from observation data set, and the plurality of candidate initial positions are sorted;With the first candidate initial position as iteration initial position, positioning solution is carried out, and position solution is obtained;Based on position solution, velocity solution is calculated, and velocity solution is obtained;Judge whether velocity solution satisfies velocity constraint, if yes, then output corresponding position solution;If not, then take the next candidate initial position as iteration initial position, and repositioning solution is carried out.The application directly uses Doppler frequency shift observation value to quickly screen out candidate initial position, without prior position in advance.

The application discloses a milling cutter with star-shaped line cutting edges and an optimization method thereof, and relates to the technical field of milling cutter design, which comprises the following steps: determining the initial value of a scale factor based on production target parameters, adjusting the initial value in combination with the hardness value of a machining target material and cutting process parameters to obtain the accurate scale factor of a single star-shaped line cutting edge, constructing a milling cutter model, establishing a plane coordinate system at the center of a cutter head, determining the curvature of the star-shaped line according to a single star-shaped line cutting edge parameter equation containing the accurate scale factor and an angle change parameter, rotating the cutter head center by different angles to form a plurality of star-shaped line cutting edges with different positions, and respectively adopting a circular arc, a spline curve and a helical transition surface to optimize the transition connection between the sharp corners in the star-shaped line cutting edge, adjacent star-shaped line cutting edges and the star-shaped line cutting edge and the cylindrical surface of the cutter head, so as to help optimize the load distribution during cutting, reduce vibration and wear.

The invention discloses a satellite-borne microwave general positioning method, which is used for single-satellite multi-orbit positioning when a ground radiation source searches and traverses an airspace in the air, and comprises the following steps of: determining a sub-satellite point visual circle radius according to a satellite orbit height; determining the possible position of the ground radiation source according to the M sub-satellite point positions and the visible circle radius, wherein the visible circle intersection corresponding to all the sub-satellite point positions is the possible position of the ground radiation source; aiming at the possible position of each ground radiation source, calculating an azimuth angle and a pitch angle of each sub-satellite point corresponding to the possible position of each ground radiation source, and extracting a corresponding gain array from an antenna pattern; comparing a signal energy array acquired by a sub-satellite point with the gain array, and calculating a variance of an energy gain difference array as a matching criterion; and traversing all the possible positions of the ground radiation source, and averaging the positions with the minimum variance of 0.5% to obtain a general positioning result. According to the invention, a method of averaging possible positions with the minimum variance of 0.5% is adopted, so that the approximate positioning precision is greatly improved.

The invention relates to a micro-nano satellite group distributed cooperative multi-target tracking method, and belongs to the technical field of space target tracking. Through inter-satellite cooperative networking construction, single-satellite weak and small target detection, single-satellite multi-target tracking, cross-view-field track association, multi-satellite distributed information fusion and the like, the target tracking number of satellite group cooperation can be greater than or equal to 12, and support is provided for the micro-nano satellite group in the fields of space situation awareness, on-orbit target monitoring and the like. According to the method, the problems of poor robustness of a centralized architecture, insufficient cross-view-field tracking precision and the like in micro-nano satellite group multi-target tracking are solved, the real-time performance and reliability of space target tracking are improved, and the requirement for accurate and stable tracking of multiple targets in a complex space environment is met.

The invention discloses a navigation mode transition method, an electronic device and a medium, in a working process of a first navigation mode, geometric angles among a mother satellite, a service spacecraft and space debris are monitored, and when the geometric angles meet a mode switching requirement, the position of a target orbit under a J2000 coordinate system is obtained through double-satellite geometric estimation; and taking the position as an initial position calculated in the second navigation mode, and switching to the second navigation mode. Before the navigation mode is switched, the target orbit position is determined through double-satellite geometric estimation, the single-satellite navigation positioning precision can be rapidly improved, a good initial value is provided for double-satellite angle measurement filtering, and the convergence process is accelerated.

The invention discloses a wide-spectrum interference type star sensor based on an eight-optical-wedge light splitting assembly and a centroid positioning method of the wide-spectrum interference type star sensor, and belongs to the technical field of spacecraft attitude measurement. In order to solve the problem that the single-star measurement precision of an interference type star sensor is reduced, the interference type star sensor comprises an interference assembly, an eight-optical-wedge light splitting assembly, a focusing assembly and a detector which are arranged in sequence, the interference assembly comprises two gratings G1 and G2 which are spaced by a certain distance and is used for modulating the starlight phase and further generating interference fringes; the eight-optical-wedge light splitting assembly is an optical wedge array composed of eight optical wedges and is used for dividing interference fringes into eight parts of fringe light. The focusing assembly is used for focusing and imaging the stripe light at different positions of the detector; the detector is located on the focal plane of the focusing assembly and used for receiving the starlight image. By adopting an eight-optical-wedge light splitting structure, the single-satellite measurement precision of the system in a wide-spectrum working environment is remarkably improved.

This invention discloses a large field-of-view automatic calibration device and method for pre-calibrating star arrays, solving the problem that existing star array pre-calibration methods cannot directly measure the relative spatial angle relationship between simulators of distant single stars. The calibration device includes a turntable, a calibration unit disposed at the working end of the turntable, and a host computer disposed outside the turntable. The calibration unit includes a mounting base and a starlight detection module, a data fusion module, and a relative spatial angle calculation module disposed within the mounting base. The mounting base is detachably connected to the working end of the turntable, and its side wall has a mounting through hole. The incident end of the starlight detection module is opposite to the mounting through hole, and its signal output end is electrically connected to the first signal input end of the data fusion module. The second signal input end of the data fusion module is connected to the signal output end of the turntable, and its output end is connected to the input end of the relative spatial angle calculation module. The relative spatial angle calculation module is electrically connected to the host computer.

This invention discloses a dynamic clustering method for space-based distributed collaborative detection. First, based on dynamically changing mission requirements and target status, a dynamic clustering algorithm optimized for collaborative detection performance is designed to cluster satellites within the constellation. Then, using the comprehensive capabilities of nodes as a crucial basis for node star election and cluster structure maintenance, a multi-factor weighted dynamic edge node star selection algorithm is designed, ultimately achieving a hierarchical, ordered, distributed collaborative architecture of "constellation-cluster-single star". This invention can reduce the information propagation cost within the constellation and improve information collaboration and mission execution efficiency.

The application provides a distributed star cluster task cooperative planning method based on a contract network, which comprises the following steps: a task receiving star receives a guide task; the task receiving star calculates the task attributes of each star according to a task management star selection rule; a task management star determines the content of a published task contract; after receiving the task, a task execution star feeds back the task information according to the task executability; the task management star collects all the task feedback information, selects the task information with the highest cooperative benefit, and publishes a task execution command to the selected execution star to complete the task contract signing; after receiving the execution command, the selected task execution star executes the task according to the requirements of the prepared contract and feeds back the execution result to the task management star in real time; the task management star receives the execution states of all the execution stars, fuses the target single-star observation information fed back by the execution stars, generates target comprehensive situation information, and sends the target comprehensive situation information to a situation information user.

A distribution method for improving remote sensing constellation target capacity through three-dimensional coordinate different-satellite fusion comprises the steps that two-dimensional coordinates of the same observation target group are generated on two task satellites executing an observation task, and three-dimensional coordinate fusion and numbering sorting are carried out based on the two-dimensional coordinates; distributing the two-dimensional coordinates which are not fused to the satellites which do not execute the observation task according to the upper limit of the capability of calculating the three-dimensional coordinates by the satellites, and performing three-dimensional coordinate fusion by the satellites which do not execute the observation task by receiving the two-dimensional coordinates which are sent by the two satellites and have the same serial number. After the two-dimensional coordinates are successfully fused in the upper limit range of the capability of calculating the three-dimensional coordinates, the two-dimensional coordinates are sent back to the task satellite, the part exceeding the upper limit range of the capability of calculating the three-dimensional coordinates is sent to another satellite which does not execute the observation task, and so on until all the two-dimensional coordinates are fused, and the target tracking capacity of the satellite is increased. The method overcomes the limitation of the calculation capability of the existing single satellite, and provides a mode that the satellites networked in the stationary orbit do not need to interact through a fixed rule.

A spacecraft relative position correction method based on single star angle measurement information, the steps are as follows: (1) based on the initial orbit determination information, recursively calculate the target position of the space target in J2000 system; (2) calculate the estimated value of the relative position of the two stars in the VVLH coordinate system; (3) judge whether the relative position full component error correction condition is satisfied; if the correction condition is satisfied, execute step (4); otherwise, execute step (5); (4) based on the relative position estimate value and the spacecraft line-of-sight angle measurement value, calculate the Moore-Penrose inverse matrix of the first Jacobian matrix of the observation with respect to the relative position, and calculate the spacecraft and space target relative position correction value, complete the spacecraft relative position correction; (5) based on the relative position estimate value and the spacecraft line-of-sight angle measurement value, calculate the inverse matrix of the second Jacobian matrix of the observation with respect to the relative position, and calculate the spacecraft and space target relative position X-axis and Z-axis correction value, complete the spacecraft relative position correction.

The application discloses a kind of large-scale MIMO multi-star positioning and direction estimation method and system based on angle information.The application first obtains the channel matrix estimation between each satellite and user by sending pilot signal;Then the estimated value of channel parameter is obtained using tensor-ESPRIT algorithm, including angle of departure and angle of arrival;According to the estimated angle of departure, the direction vector between user and each satellite is obtained, the optimization problem on spherical surface is established, considering the altitude constraint, the user position estimation value is obtained by using Riemann conjugate gradient method;Finally, according to the estimated user position and angle of arrival, the optimization problem on SO (3) manifold is established, and the estimated value of user array rotation matrix is obtained by using Riemann gradient descent method.The application combines the channel information between multiple satellites and users for positioning and direction estimation, and considers the altitude constraint during positioning, compared with single satellite and unconstrained case, can significantly improve the positioning performance, while having good direction estimation performance.

The application discloses a multi-level low-orbit constellation configuration design method suitable for diversified services and belongs to the field of wireless communication; specifically comprising the following steps: firstly, a single-satellite coverage and multi-satellite global coverage geometric model is established, including a constellation configuration of P orbits and M satellites respectively arranged on each orbit; then, an aggregated QoS utility characterization model is established, the aggregated utility function of a single user is calculated, when different types of users access different levels of low-orbit satellites, the overall system optimal aggregated utility function is calculated by adjusting the constellation configuration; finally, combined with the deployment cost, a multi-objective optimization function and constraint conditions of large-scale multi-level constellation configuration design are constructed; and the adaptive particle swarm algorithm is used to solve the large-scale low-orbit satellite constellation deployment parameters, and finally, the multi-level low-orbit constellation configuration is designed according to the parameters. The application fully considers the orbit parameter design to meet the differentiated service requirements and considers the constellation deployment cost.

The invention belongs to the technical field of communication signal processing, and more particularly relates to a same-frequency interference cancellation method and system based on a multi-start satellite operation neural network, and the method can accurately and quickly obtain a target linear interference component of a target receiving signal through calculating an equivalent linear channel response between the target receiving signal and a target transmitting signal. According to the method, by introducing the target nonlinear reconstruction model of the multiple target single-star models, the target nonlinear interference component of the target receiving signal can be quickly and accurately obtained from multiple dimensions by utilizing linear transformation and star operation of two characteristic branches under the condition of not increasing deep convolutional layer stacking or a large number of cyclic structures; therefore, on the basis of the target linear interference component, the target nonlinear interference component and the target receiving signal, effective cancellation of the same-frequency interference signal in a high-speed dynamic change channel environment can be realized.

The invention relates to the technical field of ground task management and control of aerospace earth observation satellites, and discloses an electronic satellite parallel resource scheduling method based on a greedy algorithm. According to the method, a reconnaissance task set obtained through reconnaissance requirements is divided into a real transmission task set and a playback task set, the real transmission task directly allocates resources according to task time, the playback task uses constraints according to various types of satellites, and playback task data transmission resource allocation based on a greedy algorithm is carried out in parallel; according to the method, a multi-satellite data transmission resource scheduling initial solution of an electronic satellite is formed, data transmission resource conflict resolution of each station is carried out, a multi-satellite resource conflict resolution problem of the electronic satellite is modeled as a classic dynamic planning algorithm revenue maximization problem, a resource scheduling allocation scheme with the maximum benefit is obtained, and the feasibility of the scheme is verified by calling a single-satellite plug-in. According to the method, the electronic star resource scheduling is relatively completely described, and the method has the characteristics of advancement, practicability and the like.

The application discloses an in-orbit reference frequency stability estimation method of an inter-satellite link system, which comprises the following steps: calculating a combined phase measurement value Θ p (t) according to a two-way phase measurement value Θ(t) without time scale correction; calculating a relative frequency error δf i ‑δf j ; calculating a relative frequency error sampling value, repeating the sampling according to a nominal sampling frequency, and calculating a relative Allan variance. The application is improved based on the calculation formula of the Allan variance, can accurately estimate the relative frequency stability between two stars of the inter-satellite link, and further estimate the frequency stability of a single star.

The invention relates to a real-time area coverage method and device for medium-orbit area observation constellations, and the method comprises the steps: carrying out the subarea division of a target area, and uniformly generating sampling points and area mask vectors corresponding to the sampling points in the target area; according to the pointing information of the satellites to the target area at the current moment, obtaining a single-satellite instantaneous coverage mask vector of each satellite to the sampling point; counting the coverage multiple number of each sampling point to obtain an instantaneous multiple coverage vector; obtaining an instantaneous region coverage vector according to the instantaneous multiple coverage vector and the region mask vector; according to the instantaneous region coverage vector, calculating an instantaneous i-fold coverage proportion of the sub-region at the current moment; taking a pointing vector formed by all satellites as a decision variable, and constructing a target function according to an instantaneous i-fold coverage proportion; and solving the objective function by adopting a particle swarm algorithm to obtain an optimal pointing vector so as to realize area coverage. According to the invention, a real-time area coverage area observation task can be realized.

The invention relates to an optical positioning method, in particular to a multi-target multi-mode fusion positioning method based on a motion platform, and solves the problem that an existing optical positioning mode cannot meet target positioning requirements for complex application scenes with complex observation backgrounds, long observation distances, multiple and dense target image points and long observation arc segments. When intersection positioning is carried out on multiple targets, laser ranging positioning is carried out on a key main tracking target, intersection measurement positioning is carried out on targets observed by two measurement stations at the same time, single-satellite pure-angle positioning is carried out on a target observed by only a single measurement station, and target positioning can be realized by using single-station and double-station observation data; therefore, the target measurement arc length is increased, and long arc section positioning of more targets can be realized under limited measurement station resources.

The present application relates to the technical field of space target detection, and discloses a star cluster cooperative space target search and orbit determination method, which comprises the following steps: a ground computing center generates prior guidance data of a space target and injects the star cluster; a wide field satellite node performs sky domain search according to the prior guidance data, extracts a two-dimensional observation error covariance through dimension reduction and shift superposition processing, and sends an inter-satellite data frame containing the covariance and instantaneous pose to a narrow field satellite node; the narrow field satellite node receives the inter-satellite data frame, performs reference alignment and state extrapolation in combination with a prior distance error variance and an earth-centered inertial coordinate system, and generates an extrapolated three-dimensional error ellipsoid; the narrow field satellite node generates a boresight maneuver trajectory according to the error ellipsoid to realize physical locking of the target; and the star cluster performs state convergence based on a cross-line-of-sight network to complete cooperative orbit determination. The present application overcomes the problem of limited single-satellite field of view and lack of depth data, and realizes effective capture and orbit determination of a multi-satellite cooperative space target.

The invention relates to the technical field of space target simulation, in particular to a high-star magnitude simulation system of a single-star simulator and a calibration method. The high star magnitude simulation system comprises an LED light source and a photoelectric detector which are embedded in an integrating sphere, a light outlet of the integrating sphere is connected to a mechanical optical fiber attenuator through a conduction optical fiber, and the mechanical optical fiber attenuator is connected to a transmission-type collimator through a conduction optical fiber. And establishing a star magnitude energy model of the high star magnitude simulation system according to the reading of the photoelectric detector, the attenuation coefficient of the mechanical optical fiber attenuator and the change relation of the emergent illumination of the transmission-type collimator. The calibration star simulator achieves dynamic, large-range and high-precision simulation on high magnitude, and the calibration requirement for a weak target is met.

The invention discloses a communication and conduction integrated low-orbit single-satellite Doppler static positioning method and device and a storage medium. The method comprises the following steps: calculating the position, speed and clock drift of a satellite under each observation epoch by using ephemeris information; integrating Doppler frequency shift observation values according to time panes to obtain an observation data set; based on the position, the speed and the clock drift of the satellite under each observation epoch, screening out a plurality of candidate initial positions from the observation data set, and sorting the plurality of candidate initial positions; carrying out positioning calculation by taking the first candidate initial position as an iteration initial position to obtain a position solution; performing speed calculation based on the position solution to obtain a speed solution; judging whether the speed solution meets a speed constraint or not, and if yes, outputting a corresponding position solution; and if not, taking the next candidate initial position as the iteration initial position, and carrying out positioning calculation again. According to the method, the candidate initial position is quickly screened out by directly utilizing the Doppler frequency shift observation value, and the prior position does not need to be known in advance.

The application provides a large-scale constellation earth observation task planning method and device, and belongs to the technical field of satellite task planning. The large-scale constellation earth observation task problem is divided into a multi-star cluster cluster allocation problem and a single-star cluster cluster autonomous task planning problem by the application, an improved adaptive large neighborhood search algorithm combined with tabu search is used to allocate the large-scale constellation earth observation task to different star clusters, and then a star cluster autonomous task planning algorithm based on an extended contract net mechanism is used to realize multi-star task planning in the star cluster. In this way, the problem scale can be reduced, the search space can be greatly reduced, the solving efficiency can be improved, the cooperation between satellites in the star cluster can be increased, especially in the face of satellite damage and interference, the anti-interference ability and cooperative completion efficiency of the task can be improved, and the robustness and reliability of the task planning can be ensured.