48 results about "Spacecraft formation" patented technology

For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method further iteratively calculates an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. In response to determining the inner polytope boundary will be breached, the method maneuvers the given spacecraft to within the inner polytope boundary based on a switching condition, a guidance law, and model predictive control to minimize fuel consumption.

The invention relates to a spacecraft collaborative formation safety control method and system based on an adjustable self-adaptive control barrier function. The method comprises the following steps: establishing a six-degree-of-freedom model for describing relative motion of a spacecraft formation; multiple safety key constraints which need to be met by the spacecraft formation are established, and the constraints are formalized into a zero-hyperlevel set function of a state variable; a disturbance observer is designed, and unknown lumped disturbance existing in the six-degree-of-freedom model is estimated and compensated online; a safety controller is constructed, the safety controller comprises an adjustable self-adaptive control barrier function used for generating a safety constraint boundary changing along with time, and parameters of the adjustable self-adaptive control barrier function are adjusted online through the auxiliary dynamic system; and constructing a quadratic programming problem, and solving to obtain an optimal safety control instruction which minimizes the deviation between the actual control input and the nominal control input. Compared with the prior art, the method has the advantages of improving the task success rate and safety of the spacecraft formation in a complex, dynamic and uncertain environment and the like.

The invention discloses an earth-moon translation point orbit spacecraft formation relative motion configuration design and control method, and belongs to the technical field of spacecraft orbit dynamics and control. The method comprises the following steps: firstly, constructing a double-layer dynamic model consisting of a circular restrictive three-body problem model and a high-precision ephemeris model, and defining an orbit amplitude difference and a phase difference as configuration parameters; then, according to different track amplitude difference and phase difference combinations, three types of natural relative motion configurations are set, a periodic track is rapidly generated under a circular restrictive three-body problem model, and multi-circle correction is conducted through a high-precision ephemeris model and two-stage multiple targeting; a hierarchical constraint model is established for a controlled task surrounding a fixed position, a plane and a space, and a control pulse is solved by adopting a two-stage optimization strategy. According to the method, efficient design and stable control of formation configuration in a complex dynamic environment are realized, and the method is suitable for various translation point orbit tasks.

The application relates to the technical field of multi-spacecraft cooperative control, and discloses a multi-spacecraft grouping consistency restraint control method and device under optimized FLS, which comprises the following steps: acquiring the network topology of a heterogeneous multi-spacecraft system and constructing a multi-subgroup directed communication topology network, constructing a spacecraft attitude control system model based on modified Rodrigues parameters; approximating unknown nonlinear terms in the model through a fuzzy logic system, constructing a fuzzy logic system based on a gradient descent algorithm and Armijo line search criterion; constructing a restraint control term and using a backstepping method to construct a virtual control law, combining the output of the fuzzy logic system based on the gradient descent algorithm and the Armijo line search criterion to construct an actual control input law, so that grouping consistency restraint control of the heterogeneous multi-spacecraft system is realized. The application can improve real-time approximation precision and adaptive step length adjustment capability while guaranteeing grouping consistency, and can enhance topology applicability and task cooperation flexibility.

The invention provides a multi-spacecraft leader following formation control method based on neural adaptation. The method comprises the following steps: firstly, establishing a multi-space aircraft system model with a leader-follower structure; then, designing a robust formation control scheme based on neural self-adaption; firstly, designing a self-adaptive distributed state observer based on local discontinuous interaction for a follower spacecraft; secondly, a distributed robust formation controller based on neural network fitting is designed for the follower spacecraft; and finally, designing an inter-aircraft communication mechanism based on a static event triggering mechanism for the follower spacecraft. According to the method, the problems of local knowing of leader information, limited communication, adverse influence of external disturbance on control performance and the like in the multi-spacecraft formation with a leader-following structure are considered, an effective formation control scheme is designed, and the robustness and reliability of a multi-spacecraft system are remarkably improved.

A communication quantization distributed spacecraft formation control method comprises the following steps: establishing a spacecraft dynamic model near an asteroid, modeling a gravitational field near the asteroid by adopting a polyhedron method, constructing a spacecraft formation near a balance point in the gravitational field, and establishing a relative kinematic model of the spacecraft formation; a logarithm quantizer is constructed to quantify state variables transmitted between spacecrafts, a distributed spacecraft formation controller based on communication quantization is constructed, and finally, the quantized state variables are input into the controller to obtain a spacecraft formation deployment strategy. According to the method, the formation control strategy of the spacecrafts near the asteroid is improved by quantifying the communication information, and the distributed spacecraft formation controller based on communication quantification is constructed, so that the problem that the formation communication frequency and the data transmission rate of the existing formation control method near the asteroid are too harsh is solved.

An integrated control method for a multi-spacecraft formation system based on predictive behavior control, comprising the following steps: Step S1: Define the global tasks to be executed by the multi-spacecraft formation: formation keeping, movement; local tasks: obstacle avoidance, and then establish a composite task through the way of behavior control projection in the null space; Step S2: Design a trajectory tracker based on decentralized model predictive control to track the reference trajectory; Step S3: Feed the predicted trajectory back to the planning layer for predicting the future task priorities, and extend the single-step planning in the traditional null space to multi-step prediction. Applying this technical solution can obtain a trajectory tracking control problem without task constraints, greatly reducing the online calculation cost. In addition, the predicted information on the future state of the spacecraft is considered in the process of determining the task priorities, making its switching effect more ideal compared with the traditional logic switching method.

The present application relates to the field of aerospace technology, specifically to a kind of multi-pulse parallel construction method of gravitational wave detection formation considering timing optimization, each spacecraft of formation simultaneously departs from virtual center, each spacecraft is moved to the preset specified position by applying multiple pulses, so as to form a kind of spacecraft formation that can be used for space gravitational wave detection, by giving the steps of calculating the initial position and velocity of each spacecraft and applying initial control to reach the initial position and velocity, the state quantity of each spacecraft at each time in the formation construction process is calculated, so as to provide reference for the design of satellite formation task in actual engineering application, and the accuracy of the linearized relative motion dynamics model established by the multi-pulse parallel space gravitational wave detection formation is improved by differential correction, the error in the relative motion dynamics model is reduced, the initial state set in advance can be effectively reached, and the working efficiency of formation component is improved.

The application provides a spacecraft formation trajectory tracking distributed control method and related equipment, comprising: constructing a relative motion PH equation of each spacecraft in a target spacecraft formation; converting the relative motion PH equation of each spacecraft respectively to obtain a relative motion trajectory tracking error PH equation of the target spacecraft as a tracking error system of the target spacecraft formation; based on the tracking error system, constructing an expected Hamilton function that couples the relative position error of each spacecraft in the target spacecraft formation to the tracking error system; designing a control law of the target spacecraft formation according to the expected Hamilton function and calculating a value of the distributed cooperative control law of the target spacecraft formation; performing trajectory tracking distributed control on the target spacecraft formation according to the value of the distributed cooperative control law; the spacecraft formation can accurately and quickly reach the expected motion trajectory and maintain the configuration, and the distributed cooperative control of the spacecraft cluster network is realized.

The present invention discloses a distributed fault-tolerant control system for a multi-spacecraft formation attitude system based on a fractional-order sliding mode, belonging to the field of automatic control. The method comprises: first, constructing a multi-spacecraft formation attitude system model, including a spacecraft mixed fault model and a multi-spacecraft formation flight attitude error system. Based on the constructed multi-spacecraft formation attitude system model, a distributed finite state observer is designed based on finite time theory, so that each observer can timely observe its own concentrated interference value and perform effective compensation. Finally, a new distributed collaborative fault-tolerant controller for the multi-spacecraft formation attitude system is designed based on fractional-order sliding mode theory, which can realize fault-tolerant control of the spacecraft formation attitude system, thereby ensuring the stability and reliability of the multi-spacecraft formation attitude system during mission execution.

A method for detecting relative orbital maneuvers of spacecraft based on cluster analysis includes: reading the TLE historical data of the master star of the spacecraft formation and calculating the instantaneous orbital elements, using the SGP4 model for recursion to obtain the orbital state at the moment when the latitude angle is 0; reading the TLE historical data of the slave star of the spacecraft formation and calculating the instantaneous orbital elements, using the SGP4 model to recursively calculate the orbital state at the same time as the master star data, and realizing the time synchronization of the dual-star data; calculating the relative distance of the spacecraft formation, and performing data denoising and normalization to obtain a data set; using the silhouette coefficient to determine the number of clusters, that is, the number of orbital maneuver types; using the fuzzy C-means algorithm for cluster analysis, obtaining a clustering result based on the relative distance of the spacecraft orbit, and realizing orbital maneuver detection. The method of the present invention can effectively avoid the influence of human subjective cognition and experience on the judgment of orbital maneuvers, meet the timeliness requirements of orbital maneuver detection, and significantly improve the accuracy of orbital control maneuver detection.

A fully distributed control method for heterogeneous spacecraft formations considering time-varying topology and time-varying time delays is proposed. The method includes establishing an orbital dynamics model of the accompanying satellite formation with distinct input time delays and obtaining its state-space equations; establishing a signal model of the master spacecraft to be tracked and obtaining its state-space equations; constructing explicit fully distributed observers for each accompanying satellite to obtain the master spacecraft's state information constrained by time-varying communication time delays; designing explicit linear state feedback gains and feedforward gains respectively; and using the state feedback gains, feedforward gains, and fully distributed observers, establishing a corresponding fully distributed control protocol for the accompanying satellite formation system affected by time-varying topology and time-varying time delays to ensure that each accompanying satellite completes its tracking mission of the master spacecraft. This invention exhibits good control performance, ensuring stable operation of the heterogeneous spacecraft formation system and achieving the task of accompanying satellites tracking the master spacecraft.

The application provides a simplified attitude distribution cooperative control method for a directed communication leader-follower spacecraft formation, which comprises the following steps: firstly, describing the simplified attitude motion of the spacecraft in a unit celestial coordinate system, and converting the simplified attitude motion into a translation of the terminal point of a pointing vector on a unit celestial sphere; secondly, designing a distributed cooperative virtual control quantity under a directed communication topology according to the consistency theory, so as to ensure that the pointing vector of the follower spacecraft converges to a fixed pointing direction in the inertial space determined by the pointing vector of the leader spacecraft, and then calculating an ideal angular velocity vector of the follower spacecraft according to the virtual control quantity; thirdly, taking the difference between the angular velocity vector of the follower spacecraft and the ideal angular velocity vector as a sliding mode variable, and designing a sliding mode surface; and finally, designing a distributed cooperative control law for the follower spacecraft based on a super-twisting second-order sliding mode control method. The application can ensure that the pointing vector of the follower spacecraft in the directed communication formation converges to the pointing vector of the leader spacecraft fixed in the inertial space under a disturbance environment, and reduces the communication amount of the formation.

This application provides an electromagnetic spacecraft control method, device, product, and electronic device, relating to the field of spacecraft control technology. This method can obtain the directed connected topology network of an electromagnetic spacecraft formation system and the dynamic equations of each electromagnetic spacecraft. Based on the dynamic equations and the directed connected topology network, a distributed control protocol is constructed. When the state update error of the distributed control protocol meets preset conditions, position control is performed on each electromagnetic spacecraft based on the distributed control protocol. This method can save communication resources while precisely controlling the electromagnetic spacecraft and can solve the actuator saturation problem involved in maintaining the formation configuration of a multi-electromagnetic spacecraft formation system. Compared with related technologies, this method considers the inherent characteristics of electromagnetic spacecraft, eliminating the need to trigger communication at every moment; communication only needs to be triggered when the state update error of the distributed control protocol meets preset conditions.

This invention discloses a method for modeling and simulating the attitude-orbit coupling of spacecraft formations, comprising: establishing coupling models of the desired attitude and orbital parameters of the lead satellite, the actual attitude and orbital parameters of the lead satellite, the desired attitude and orbital parameters of the follower satellite, and the actual attitude and orbital parameters of the follower satellite; calculating the desired attitude and orbital parameters of the lead / follower satellites and the actual attitude and orbital parameters of the lead / follower satellites respectively based on the models; and performing flight formation control based on the calculated parameters to achieve formation flight of the follower satellites relative to the lead satellite. This invention can be used in satellite controller design. On the one hand, by modeling the attitude and orbital parameter information using dual quaternions, this method can more accurately establish a satellite dynamics model; on the other hand, by using the parameters of the lead satellite to determine the parameters of the follower satellites, the follower satellites can more accurately maintain their relative positional relationship with the lead satellite.

The invention particularly relates to a spacecraft formation flight mission planning method based on cooperation of a large language model and a professional tool set. The method comprises the following steps: constructing a three-layer mission planning architecture of the professional tool set, an LLM and a high-level dynamic execution engine; constructing the professional tool set for spacecraft formation flight; disassembling the user instruction into a meta-task sequence through a complex task decomposition model; and calling the tool set in sequence to execute the meta-task through the task sequence execution model. The invention provides a more efficient and flexible intelligent solution with scene generalization ability for the spacecraft formation flight task planning problem.

The application particularly relates to a spacecraft formation flight task planning method based on cooperation of a large language model and a professional tool set, and comprises the following steps: constructing a three-layer task planning architecture of the professional tool set, the LLM and a high-level dynamic execution engine; constructing the professional tool set for the spacecraft formation flight; decomposing a user instruction into a meta-task sequence through a complex task decomposition model; and calling the tool set to execute the meta-task in sequence through a task sequence execution model. The application provides a more efficient, flexible and intelligent solution with scene generalization capability for the spacecraft formation flight task planning problem.

The invention provides an electromagnetic spacecraft control method and device, a product and electronic equipment, and relates to the technical field of spacecraft control, and the method can obtain a directed connected topology network of an electromagnetic spacecraft formation system and a kinetic equation of each electromagnetic spacecraft, and further obtains a control result based on the kinetic equations and the directed connected topology network. According to the method, the distributed control protocol is constructed, and when the state updating error of the distributed control protocol meets the preset condition, the position of each electromagnetic spacecraft is controlled based on the distributed control protocol, so that communication resources can be saved while the electromagnetic spacecrafts are accurately controlled; and the problem of actuator saturation involved in the formation configuration keeping process of the multi-electromagnetic spacecraft formation system can be solved, compared with the related technology, the inherent characteristics of the electromagnetic spacecrafts are considered, communication does not need to be triggered at each moment, and the communication efficiency is improved. And the communication only needs to be triggered when the state updating error of the distributed control protocol meets the preset condition.

For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method iteratively calculates a desired trajectory relative to the virtual point for a given spacecraft of the plurality of spacecraft using a relative orbital elements (ROE) state x of the virtual point and the given spacecraft. Model predictive control maintains the given spacecraft within an ROE constraint for a given time interval subject to a fuel consumption. In response to determining a drift trajectory of the given spacecraft is outside of a trajectory tolerance of the desired trajectory, maneuvering the given spacecraft to within the trajectory tolerance using a maneuver trajectory determined using the model predictive control.

A method for collision avoidance control of complex-shaped spacecraft based on algebraic conditions belongs to the field of spacecraft formation control. The invention solves the problem of collision when spacecraft perform close-range posture maneuvers in space. The method of the invention comprises the following steps: S1, establishing kinematic and dynamic equations of a tracking satellite relative to a space tumbling target spacecraft based on Lie group SE (3); S2, introducing a configuration error potential function to obtain a configuration error vector; S3, designing a collision avoidance mechanism, including collision avoidance between a tracking satellite and a target spacecraft and collision avoidance between tracking satellites, wherein the tracking satellite and the target spacecraft both construct a minimum envelope ellipsoid; S4, designing a continuously differentiable artificial potential function for the collision avoidance constraint; S5, designing a collision avoidance feedback control law in combination with S1-S4.

The invention discloses a lossless convexity method for gravitational wave spacecraft formation attitude alignment random optimal control, and the method comprises the steps: setting related parameters in a task scene, including the rotational inertia of a spacecraft, the maximum thrust moment, the initial state and target state of the spacecraft, the pointing constraint, and a disturbance coefficient matrix; establishing a random spacecraft attitude dynamic model; utilizing opportunity constraints to describe a plurality of constraints with uncertainty, including moment constraints, taboo constraints and forced constraints; converting a non-convex part in the constraint condition into a linear matrix inequality (LMIs) by adopting the Schel complement theorem, and adding a virtual control variable and a penalty term to obtain a convex problem which can be directly solved by using the CVX; the invention aims to realize random optimal control of gravitational wave spacecraft formation attitude alignment through a convex optimization method.

The application discloses a kind of under DoS attack based on dynamic event triggering's spacecraft formation system's self-adapting consistency control method.The method is first based on multi-agent consistency model theory, establishes the multi-agent system model of multi-agent spacecraft formation system, then consider based on time series DoS attack, by the frequency and duration of DoS attack are analyzed and researched, to solve the consistency problem of multi-agent spacecraft formation under DoS attack, then design a dynamic event triggering mechanism to reduce communication transmission frequency, and it is proved that there is no Zeno behavior existence, finally based on Lyapunov stability theory analysis, design a kind of event triggered distributed adaptive controller, solve the consistency problem of multi-spacecraft formation.The method is applied to multi-spacecraft formation system, guarantee the normal operation of system under DoS attack.

The present application relates to the field of spacecraft control technology and provides a method for coordinated attitude control of a spacecraft formation coupled with flywheel dynamics. The method comprises: obtaining a Hamiltonian energy function based on the angular kinetic energy of the spacecraft and the angular kinetic energy of the flywheel, and calculating the navigator's estimated state based on the attitude dynamics and kinematic equations; constructing the PH equation of the target spacecraft formation based on all Hamiltonian energy functions and the attitude dynamics and kinematic equations; constructing the expected Hamiltonian function of the target spacecraft formation based on the attitude dynamics and kinematic equations of all spacecraft and the navigator's estimated state of all spacecraft; calculating the system controller equation of the target spacecraft formation using the IDA-PBC algorithm based on the PH equation and the expected Hamiltonian function, and obtaining the control law equation of the spacecraft based on the system controller equation; and controlling the spacecraft using the control law equation of the spacecraft. The method of the present application can improve the rationality of spacecraft formation control.

The invention relates to a detection task planning method and device, equipment, a medium and a product, and the method comprises the steps: screening a first observation target of which the absolute value of the yellow latitude is greater than a solar avoidance angle from to-be-observed targets, and obtaining a target observation set; determining a first observation parameter of each first observation target in the target observation set, and determining first observation time consumption of the spacecraft formation for each first observation target based on the first observation parameter; determining a first observation sequence on the sun-earth translation point task orbit based on the first observation time consumption; wherein the first observation sequence is a sequence in which the beam combiner observes the first observation target according to a yellow channel nearest principle; processing the first observation sequence through a convex optimization algorithm to obtain a target sequence serial plan; wherein the target sequence serial planning is used for indicating the light collector to be matched with the beam combiner to observe the first observation target under the optimal fuel track. According to the invention, distributed detection of a plurality of targets by the spacecraft formation can be realized.

The application discloses a spacecraft attitude preset time cooperative control method based on reinforcement learning, carries out mathematical description of a multi-spacecraft attitude cooperative control problem, constructs a preset time distributed observer, guarantees that a follower obtains observation information of a state of a leader within preset time, determines a preset time performance function, quantitatively characterizes convergence time, transient performance and steady-state performance constraints of a cooperative tracking error, carries out error transformation based on an obstacle function, converts the cooperative tracking error system subjected to preset performance constraints into an unconstrained system, determines a performance index function and a corresponding Hamilton-Jacobi-Bellman equation, solves partial derivatives about optimal control to obtain an expression form of optimal control input about an optimal function, and designs an approximate optimal controller under an evaluation network framework by using a reinforcement learning method. The application can guarantee that a spacecraft formation system meets preset convergence time, transient and steady-state performance, and considers energy consumption problems.

The application discloses a completely distributed state observation method with a time convergence, and belongs to the technical field of multi-agent system cooperative control and state estimation. The application solves the problems that the existing method needs to depend on global network topology information and cannot realize controllable real convergence time and poor robustness. The application can make each follower independently and efficiently reconstruct the state and derivative of a leader which cannot be directly obtained without any global network information, and ensure that the estimation error accurately converges to zero within the real time set by a user. Moreover, the state observation method of the application is suitable for dynamic systems with external disturbance and model uncertainty, has good robustness and engineering application prospect, and is suitable for application scenes, such as spacecraft formation, unmanned aerial vehicle cluster and robot cooperation, which need high-precision synchronization and robustness. The method of the application can be applied to multi-agent system cooperative control and state estimation.

The invention provides a data-driven spacecraft formation configuration reconstruction method and device, and belongs to the technical field of spaceflight. According to the method, the current relative motion state of each slave spacecraft in a plurality of slave spacecrafts in the spacecraft formation, the target relative motion state after configuration reconstruction and the state auto-encoder are combined to construct the control law of each slave spacecraft for realizing spacecraft formation configuration reconstruction, and the process improves the calculation efficiency of solving the control law and improves the calculation efficiency of the spacecraft formation configuration reconstruction. The method is low in computing power requirement, is easy to achieve on-satellite deployment, achieves autonomous planning, can improve the reconstruction efficiency of the spacecraft formation configuration, and facilitates the spacecraft formation to complete tasks.

The application discloses an inter-satellite baseline high-precision measurement and estimation method, and is characterized in that the method comprises the following steps: S1. Estimating and calibrating GNSS measurement information through a star sensor and laser ranging information; S2. Determining a measurement noise variance matrix R, and estimating in combination with satellite motion characteristics and noise characteristics; and S3. Adopting an interactive multiple model unscented Kalman filtering method to perform information processing. In the application, the problems that a measurement scale of an existing method does not meet long-interference baseline measurement requirements, measurement information is single, measurement precision is unknown, and an information processing method is not suitable are overcome, and a method for realizing fusion of GNSS, laser link and star sensor measurement information by using an interactive multiple model unscented Kalman filtering is provided, so that inter-satellite high-precision real-time baseline measurement information is obtained, the demand of future multi-spacecraft formation cooperation for high-precision inter-satellite measurement information is met, and mm-level inter-satellite baseline measurement precision is achieved.

The application discloses a spacecraft formation configuration decoupling control method and belongs to the technical field of satellite formation control. The application aims at solving the problems of serious approximation error accumulation and high fuel consumption of a spacecraft formation control method based on a CW equation. The method comprises the following steps: calculating relative orbit elements of a sub-satellite and a main satellite, obtaining a radial relative motion equation, a trace relative motion equation and a normal relative motion equation of the sub-satellite and the main satellite, and obtaining a modified equation; determining a velocity pulse according to a dynamic equation between the relative orbit elements and the velocity pulse; determining a required change amount of the relative orbit elements, and then determining a required change amount of a relative orbit inclination vector, a required change amount of a relative semi-major axis, a required change amount of a relative eccentricity vector and a required change amount of a relative angular distance; controlling the relative orbit inclination vector by adopting a single-pulse normal control strategy; controlling the relative semi-major axis and the relative eccentricity vector by adopting a double-pulse trace pulse strategy; and controlling the relative angular distance by adopting a multi-period trace control strategy. The application is used for formation control.

The invention relates to the technical field of space on-orbit robot control, in particular to a reconfigurable rigid-flexible coupling space on-orbit assembly robot hierarchical control method and system, and the control system comprises a spacecraft formation control system and a rigid-flexible coupling robot control system. According to the rigid-flexible coupling robot control system, the working stroke of a robot can be changed through reconfiguration of spacecraft formation re-planning, and on the basis of an upper-layer task planner, a controller fuses multi-perception information of vision, force sense and position to achieve hierarchical control over a flexible cable driving robot and a mechanical arm. The control method is oriented to space large-size component assembly tasks, the robot hierarchical controller fused with multi-source information is designed by decoupling robot kinematics and dynamics and combining operation scene requirements, the overall operation efficiency and precision of the robot are improved, and the adaptability of the robot to different on-orbit tasks is enhanced.