13 results about "Flexible spacecraft" patented technology

The invention belongs to the technical field of spacecraft control, and discloses a flexible spacecraft attitude control method and related equipment based on an all-drive system theory, and the method comprises the steps: building an attitude tracking error model containing flexible vibration, external interference and rotational inertia uncertainty, the model is converted into a second-order all-wheel-drive system model with a lumped disturbance term; converting the second-order all-drive system model into a linear steady-state closed-loop system containing a lumped disturbance term, and constructing a preset time sliding mode control law capable of enabling the state of the linear steady-state closed-loop system to converge within a preset time; constructing an RBF disturbance observer for performing approximation estimation on the lumped disturbance item; according to the second-order all-drive system model, the preset time sliding mode control law and the RBF disturbance observer, an RBF preset time pseudo-linear sliding mode controller is constructed; the flexible spacecraft is controlled by the pseudo-linear sliding mode controller according to the RBF preset time; therefore, the method has the advantages of realizing preset time convergence and improving attitude control precision and stability.

This invention relates to a test device and verification method for the space-ground consistency of a flexible spacecraft control system based on uncertainty quantification, belonging to the fields of intelligent manufacturing equipment industry and space-ground consistency verification technology. To address the problem of space-ground consistency verification and evaluation for flexible spacecraft, this invention includes an air-floating robot and a flexible component. The air-floating robot simulates the central rigid body of the flexible spacecraft, and the flexible component simulates the deployed solar panels. One end of the flexible component is connected to the upper support column of the air-floating robot, while the other end is free and equipped with a weight. Fiber optic grating sensors are distributed on the flexible component to measure flexible vibrations. A piezoelectric ceramic plate is installed at the end of the flexible component connected to the air-floating robot for driving and controlling the vibration of the flexible component. This invention evaluates the space-ground consistency of the designed flexible spacecraft control test system and, based on uncertainty quantification analysis, provides the impact level of uncertainty sources on space-ground consistency.

The application discloses an anti-unwinding flexible spacecraft attitude tracking composite control method, first, based on the quaternion method, a flexible spacecraft attitude tracking error kinematics and dynamics model is established; then, the flexible accessory vibration mode, external environmental disturbance and model uncertainty are regarded as a lumped disturbance, a generalized proportional integral observer is designed, and the lumped disturbance is observed and estimated; finally, a non-singular terminal sliding mode surface is constructed, the lumped disturbance observation and estimation compensation of the generalized proportional integral observer is taken as a feedforward signal, and a feedforward-feedback anti-unwinding attitude tracking composite controller is designed. Through determining appropriate control gain, the closed-loop attitude tracking error system is globally finite time stable, and the anti-unwinding effect can be realized. The application can realize finite time attitude tracking of the flexible spacecraft, has high attitude tracking precision and strong robustness.

The application belongs to the technical field of satellite attitude control, and relates to a large flexible spacecraft distributed fault-tolerant attitude and vibration control method, a large flexible spacecraft rigid-flexible coupling dynamics model with distributed actuators is established by using the Lagrange method, a hierarchical Stackelberg game control framework is established by taking an attitude control subsystem as a leader layer and a vibration suppression subsystem and a fault-tolerant control subsystem as follower layers, performance functions of the three subsystems are defined, and through game of spacecraft distributed fault-tolerant attitude and vibration control, strategy cooperation and dynamic balance between at least two control targets are realized; the application realizes three-axis attitude stabilization and low-frequency vibration suppression of a target spacecraft, and shows stronger fault-tolerant capability under node failure.

The application discloses a flexible spacecraft attitude control method and system, and the method comprises the following steps: establishing a flexible spacecraft attitude control model and a flexible accessory model; according to the homogeneous system theory, the flexible spacecraft attitude control model and the flexible accessory model are simplified for multiple times to obtain a simplified flexible spacecraft attitude control model and a simplified flexible accessory model; according to the coupling relationship between the simplified flexible spacecraft attitude control model and the simplified flexible accessory model, a full drive model is obtained; the output equation in the flexible accessory model is combined to design an observer, the modal variable in the flexible accessory model is estimated through the observer, the full drive model is combined, and a controller is designed based on a high-order full drive system method; the controller is substituted into the full drive model to obtain a linear closed-loop system; according to a parameterized design method, a parameterized controller is obtained, and a stable linear closed-loop system is obtained. The application can stabilize the flexible spacecraft attitude control system.

The multi-node distributed flexible spacecraft configuration and intelligent attachment trajectory planning method disclosed by the application belong to the field of spacecraft guidance and control. The spacecraft configuration has the advantages of light weight, high energy absorption efficiency, avoidance of contact collision between rigid structure and spacecraft surface, facilitation of multi-point distributed detection, and modularization and rapid assembly, and can avoid rebound escape during spacecraft attachment. The multi-node distributed flexible spacecraft intelligent attachment trajectory planning method adopts a linear spring model to describe the flexible connection constraint force generated by the deformation of the flexible air bag; a multi-node distributed flexible spacecraft cooperative attachment trajectory planning model under multiple constraint conditions is constructed, and is converted into a standard quadratic programming form to reduce the complexity of the planning problem; an original dual neural network algorithm is adopted to construct a trajectory planning solution framework with state coupling at each control node, and the attachment trajectory of each control node is solved, and the safety and stability of the overall spacecraft attachment are improved through distributed cooperation.

This application belongs to the field of spacecraft control technology and discloses a flexible spacecraft attitude control method and related equipment based on the theory of all-drive systems. The method includes: establishing an attitude tracking error model that includes the uncertainty of flexible vibration, external disturbances, and rotational inertia, and transforming it into a second-order all-drive system model with lumped disturbance terms; converting the second-order all-drive system model into a linear time-invariant closed-loop system with lumped disturbance terms, and constructing a preset-time sliding mode control law that enables the state of the linear time-invariant closed-loop system to converge within a preset time; constructing an RBF disturbance observer to approximate the estimation of the lumped disturbance terms; constructing an RBF preset-time pseudo-linear sliding mode controller based on the second-order all-drive system model, the preset-time sliding mode control law, and the RBF disturbance observer; and controlling the flexible spacecraft according to the RBF preset-time pseudo-linear sliding mode controller. This method has the advantages of achieving preset-time convergence and improving attitude control accuracy and stability.

A flexible spacecraft attitude active fault-tolerant control method without angular velocity measurement is proposed to solve the problems of actuator faults, flexible appendage vibrations and external disturbances in the process of spacecraft on-orbit attitude maneuver. The method considers the actuator faults, space environment external disturbances and flexible appendage vibrations, establishes the spacecraft attitude kinematics and dynamics model, designs the fixed-time sliding mode observer based on cosine sliding mode function and the flexible vibration observer, uses the estimation results of the two types of observers to rewrite the dynamics model equivalently, and designs the adaptive learning observer to estimate the comprehensive uncertainty caused by actuator faults, angular velocity estimation error, flexible vibration estimation error and external disturbances. Finally, the specified time fault-tolerant controller is designed according to the estimated value of the comprehensive uncertainty. The method has strong fault-tolerant ability, good flexible vibration suppression performance and robustness to external disturbances.

The invention discloses a quantitative stability attitude tracking control method, device and equipment of a flexible spacecraft, belongs to the technical field of flexible spacecrafts, and particularly relates to quantitative stability attitude tracking control of the flexible spacecraft. The problem that an existing flexible spacecraft attitude control method cannot give consideration to the convergence speed and the quantitative stability of precision is solved. The method comprises the following steps: representing the attitude of the spacecraft by using a modified Rodrigues parameter, and obtaining an attitude dynamic model of the flexible spacecraft. The quantitative stability attitude tracking control method, device and equipment of the flexible spacecraft are suitable for quantitative stability attitude tracking control of the flexible spacecraft.

This invention relates to the field of on-orbit satellite structural condition monitoring technology, specifically disclosing an intelligent assessment method for satellite structural condition based on fiber optic sensors. The method includes: Step S1, conducting ablation simulations of the rubber material on the surface of a flexible spacecraft to obtain different damage states and corresponding strain data; Step S2, training a time recurrent neural network (LSTM) using the different damage states and corresponding strain data to obtain a classification prediction model; Step S3, inputting the data to be predicted into the classification prediction model to obtain the predicted damage state output by the model. This invention achieves intelligent assessment of laser ablation damage modes of flexible satellite surface materials through fiber Bragg grating sensing networks and long short-term memory (LSTM) network technology.

The invention relates to a hierarchical reinforcement learning cooperative control method for a large flexible spacecraft, and belongs to the field of spacecraft attitude control. The method comprises the following steps: 1) converting a large flexible spacecraft attitude control system into an interconnection system composed of a decentralized multi-rigid-body attitude control subsystem and an overall structure vibration control subsystem; the hierarchical reinforcement learning cooperative control method for the large-scale flexible spacecraft has the advantages that high-precision pointing control of the large-scale flexible spacecraft can be realized, and the robustness of the system is enhanced. The hierarchical reinforcement learning cooperative control method for the large-scale flexible spacecraft has the advantages that the hierarchical reinforcement learning cooperative control method for the large-scale flexible spacecraft can be implemented by the aid of the hierarchical reinforcement learning cooperative control method for the large-scale flexible spacecraft, and the hierarchical reinforcement learning cooperative control method for the large-scale flexible spacecraft can be implemented by the hierarchical reinforcement learning cooperative control method;

The application provides a method and system suitable for full-physical simulation of attitude dynamics of a flexible spacecraft, and relates to the field of spacecraft dynamics and control technology, and the method comprises the following steps: a static pressure gas lubrication three-axis air bearing table is used to simulate the dynamic environment of the spacecraft in on-orbit flight; the balance of the table body is coarsely adjusted by adding or reducing the weight blocks of the table body, and the slider on the guide rail on the table is finely adjusted to adjust the center of mass of the table body to the origin; inertia identification is performed on the table body to obtain the three-axis rotational inertia of the air bearing table, and a required scale reduction coefficient of the test is determined; a disturbance simulator is used to simulate the flexible disturbance torque generated in the jet process; and the attitude angle of the table body is measured according to different measurement ranges, the influence of the disturbance torque generated by the flexible accessory on the spacecraft is analyzed, and the flexible disturbance torque generator is used to simulate the disturbance torque generated by the vibration of the flexible accessory on the spacecraft, so that the center of mass can be kept unchanged, and the table overturning phenomenon can be avoided; and the application can also provide a reference basis for the design and demonstration of the attitude control scheme of the spacecraft.

The application relates to a flexible spacecraft attitude inner mode control method under external interference, in particular to a flexible spacecraft attitude tracking method, and particularly relates to a flexible spacecraft attitude maneuver control method in space operation under unknown frequency disturbance, and belongs to the technical field of spacecraft attitude control. In the case that unknown external disturbance exists and uncertain parameters exist in inertial information, a compound attitude controller based on the combination of an inner mode principle and an adaptive control method is provided, on the basis of realizing high-precision attitude control, asymptotic modal vibration suppression and unknown external disturbance suppression can be realized, the size of a control moment can be adjusted through corresponding parameters, and the compound attitude controller has actual engineering application value and theoretical research value.