127 results about "Satellite attitude control system" patented technology

The invention discloses a cross-platform extendible satellite dynamic simulation test system, which comprises a satellite attitude control system simulator, a flight environment and motion simulator, a satellite basic subsystem simulator and an operation monitoring and management system simulator. The satellite attitude control system simulator comprises a sensor simulator, a controller simulatorand an actuating mechanism simulator; the flight environment and motion simulator comprises an orbit and attitude dynamics resolver, a celestial body simulator, a kinematics and dynamics turntable, akinematics and dynamics translation platform, a hot vacuum and electromagnetic environment simulator and the like; and the satellite basic subsystem simulator comprises a power supply subsystem simulator and a remote measuring and remote control subsystem simulator. The operation monitoring and management system simulates functions of a satellite ground measurement and control center, such as remote measuring data decoding, remote control command generating, data archiving and analyzing and operation managing. The cross-platform extendible satellite dynamic simulation test system has strong extendibility, can be conveniently transplanted on a development and debugging platform, a distributed real-time simulation platform and an embedded semi-physical real-time simulation platform.

Various embodiments of the present invention include an attitude control system for use with small satellites. According to various embodiments, the system allows rapid retargeting (e.g., high slew rates) and full three-axis attitude control of small satellites using a compact actuation system. In certain embodiments, the compact actuation system includes a plurality of single-gimbaled control moment gyroscopes (SGCMG) arranged in a pyramidal configuration that are disposed within a small satellite.

A ground simulation-test system of satellite attitude based on satellite network comprises simulation test unit of parts grade, digital simulation test unit of system grade and semiphysical simulation test unit of system grade. It is featured as using simulation test unit of parts grade and digital simulation test unit of system grade to provide physical data basis for semiphysical simulation test unit of system grade. The ground simulation testing-method of satellite attitude based on satellite network is also disclosed.

The invention provides a single frame control moment gyro control method based on moment output capability optimization, relating to the prompt satellite attitude control field and solving the problems that the existing single frame control moment gyro control rule can not effectively avoid strange and big moment error can be caused when escaping strange. The method includes the concrete steps that: a satellite attitude control system obtains the current expected moment Tc output by CMG system according to the current attitude information; capability optimized frame angular velocity for the CMG system to output the expected moment Tc is calculated; and a frame rotating speed instruction of CMG system is obtained according to the expected moment Tc and the optimal frame angular velocity, so as to realize satellite attitude control. The method of the invention can effectively avoid strange problem, and meanwhile output moment error can be reduced, thus improving satellite attitude control accuracy.

The invention relates to a satellite active fault-tolerant control method based on an observer and online control allocation. The active fault-tolerant control method based on the iterative learning observer is provided for the problems of actuator faults, limited input saturation and external disturbance in the satellite attitude control process. The method comprises the following steps that a satellite attitude control system model is established by considering the actuator faults and the external disturbance subjected by a satellite; the iterative learning observer is designed, and invalidation factors of an actuator are estimated; a virtual feedback controller is constructed based on fault estimation information, online control allocation is conducted simultaneously, and therefore precise estimation of the actuator faults and controller reconstruction can be conducted through the satellite. According to the method, the stability of the attitude control system is guaranteed when an on-orbit working satellite is subjected to actuator faults, and the method has the advantages that the control accuracy is high, and the fault-tolerant capability and robustness to the external disturbance are high.

The invention discloses a satellite attitude control system failure diagnosis device based on a state observer and an equivalent space and a satellite attitude control system failure diagnosis method based on the state observer and the equivalent space, which belong to the field of aerospace and aim to solve the problems of high hardware complexity, low control accuracy and low failure diagnosis algorithm effectiveness of the conventional failure diagnosis method. The method provided by the invention comprises the following steps that: 1, a failure diagnosis observer outputs a satellite triaxial angular rate residual according to output signals of an actuator and a gyro sensor; 2, an equivalent vector space description module constructs equivalent space descriptions of the gyro sensor according to the output signal of the gyro sensor, wherein an output equivalent vector p is used for judging whether the gyro sensor fails or not; and 3, a failure diagnosis and isolation module outputs a failure separation result indicating that the actuator or the gyro sensor fails according to the satellite triaxial angular rate residual obtained by the step 1 and the equivalent vector p obtained by the step 2, and further judges which axis of the failing part fails.

The invention discloses a satellite attitude control semiphysical simulation system based on a multi-target machine. The satellite attitude control semiphysical simulation system comprises a real-time positioning sub system, an attitude measurement sub system, an attitude control comprehensive processing system, an execution mechanism, a signal conditioning box, a target machine, a working computer and a display system, wherein the real-time positioning sub system acquires real-time position information of a satellite; aiming at different working modes of the satellite during orbit flying, the attitude measurement sub system acquires real-time attitude information of the satellite; the attitude control comprehensive processing system manages all attitude measurement components and the execution mechanism; the target machine performs attitude calculation and torque calculation according to acquired real-time position information and the acquired attitude information and sends control information to the execution mechanism; and the execution mechanism sends actual execution information back to the target machine through the signal conditioning box, acquires the real-time attitude information of the satellite through dynamics and sends the attitude information to the attitude measurement components. The satellite attitude control semiphysical simulation system has high simulation instantaneity, high fault-tolerant capability and high integration degree and has great instructional significance for design and development of satellite attitude control systems.

The invention relates to a satellite fault diagnosis and fault-tolerant control method based on a T-S fuzzy model and a learning observer. The satellite fault diagnosis and fault-tolerant control method based on the T-S fuzzy model and the learning observer is used for solving the problems that a conventional fault diagnosis method cannot be used for effectively treating the influence caused by space disturbance torque and ensuring the robustness of a fault diagnosis method, and a conventional fault-tolerant control method has a poor fault-tolerant property. The satellite fault diagnosis and fault-tolerant control method based on the T-S fuzzy model and the learning observer comprises the following steps: step 1. establishing a mathematical model of a non-linear satellite attitude control system; step 2. establishing the T-S fuzzy model of the satellite attitude control system by using results obtained in the step 1; step 3. designing a T-S fuzzy learning observer by using the results obtained in the step 2 so as to realize the robust fault detection, isolation and fault reconstruction of a satellite attitude angular velocity estimation and executing mechanism; 4. designing a state feedback fault-tolerant controller by using the results obtained in the step 3 so as to ensure that a closed loop of a satellite attitude control T-S fuzzy system is stable. The satellite fault diagnosis and fault-tolerant control method based on the T-S fuzzy model and learning observer can be applied to an aerospace field.

The invention provides an electromagnetic formation satellite attitude and track relative control method. The method comprises the following steps: 1, attitude dynamics equations are built; 2, according to the attitude dynamics equation in a linear form with quaternion representation built in the first step, an attitude dynamics equation in a body coordinate system and a rigid satellite dynamics equation, a satellite attitude control system feedback control law is designed and obtained; and 3, according to the feedback control law obtained in the second step, relative control is carried out on the electromagnetic formation satellite attitude and the track. The method of the invention has the advantages that the attitude dynamics equations, a relative motion dynamics equation and electromagnetic force and electromagnetic torque models are built, the designed satellite attitude control system feedback control law, a flywheel angular momentum magnetic unloading algorithm, a large angle attitude maneuver method, an electromagnetic formation flying satellite motion controller and a magnetic dipole control distribution method can have good working performance, and high-efficiency relative control on the electromagnetic formation satellite attitude and the track can be realized.

The invention provides a method for performance evaluation of a spacecraft attitude control ground simulation system. According to the method, the credibility of a dynamic system, a kinematics system, a measurement system and a control system is studied based on the simulation system credibility theory, the overall credibility of the spacecraft attitude control ground simulation system is obtained through comprehensive calculation, and then the performance of the spacecraft attitude control ground simulation system is evaluated. According to the evaluation method, the credibility of the ground simulation system and an actual satellite attitude control system is considered from all aspects, simulation data are fully utilized, and the credibility of the ground simulation system is described objectively and quantitatively; the theoretical basis is reliable, the calculation process is simple, the application range is wide, and a new idea and reference are provided for performance evaluation study of other simulation systems.

The invention discloses a system of satellite attitude control integrated simulation and an implement method. The system comprises a simulation computer and an interface expansion board; simulation application under five working modes of complete mathematical simulation, component-level semi-physical simulation, component-level semi-physical simulation, whole-spacecraft semi-physical simulation, satellite-ground united simulation and in orbit attitude visualization can be realized through the combining connection of the simulation system and tested hardware; the system integrates a number of functions in one set to reduce the repeated simulation software development work to achieve the universality and generalization of the simulation system; the visualization and operability of a simulation process is enhanced; the whole flow comparison simulation analysis from scheme design to in orbit test of the satellite attitude control system is supported.

The invention provides a sensor fault tolerance observing method for a satellite attitude control system. Firstly, the control system carries out the sensor fault detecting isolation; if a first sensor is judged to have faults according to an isolation result, a second KX observer is selected to observe; and if a second sensor is judged to have faults, a first KX observer is selected to observe. The first or second KX observer has the ensuring method that if the second or first sensor has faults, the control system is analyzed into a normal subsystem and a fault subsystem by using system feedback stable control as a target, and a low-dimension KX function observer is designed by respectively aiming at the two subsystems to combine and obtain a system KX observer with fault tolerance performance. The two parallel KX observers are designed and are fused into a controlling and switching flow; and when the partial sensor output is unreliable, the satellite attitude control system still can ensure the fault tolerance observation of system rest part observed quantity to ensure the closed loop control integrality of a failure system.

The invention discloses a UKF based combined attitude determining method and satellite attitude control system, and belongs to the technical field of satellite attitude determining. A nonlinear stateequation in the differential form is constructed based on a star sensor of UKF and a gyro combined pose determining algorithm, a four-order Runge-Kutta integration method is used to solve time updateof a state variable, and discretization of the nonlinear differential state equation is avoided; and the UKF algorithm is used to filter and correct a quaternion of the star sensor and the gyro angular speed. The four-order Runge-Kutta integration method is used to update the time, a quaternion multiplication error is used to calculate the weighted mean value and covariance, the UKF algorithm is used, an observed value of the star sensor is introduced to implement filtering and updating, and the estimated error quaternion is used to correct attitude data. The attitude determining performance when a measurement error of an attitude sensor is relatively large is high, and compared with an attitude determining algorithm based on expanded Kalman filtering, the estimation precision is higher.

A satellite attitude and orbit control system based on satellite network is prepared for sending transfer order for obtaining information to certain assigned intelligent sensor with microprocessor through satellite network for making satellite affairs dispatch unit obtain relevant information, sending control command to certain assigned intelligent execution element by dispatch unit through satellite network after calculation, executing said control command by intelligent execution element with microprocessor in order to make satellite be moved for realizing control purpose after control command is received by said execution element.

The invention relates to a satellite multiple attitude control mode test system based on a double gimbal control moment gyroscope (DGCMG) structure. Performance of three satellite attitude control systems which are based on a DGCMG, a single gimbal control moment gyroscope (CMG) and a flywheel is tested and verified through a DGCMG actuating mechanism. The satellite multiple attitude control mode test system based on the DGCMG structure comprises a platform system, the satellite attitude control system, a space environment simulation system and a ground station system. The platform system is composed of a tri-axial air bearing table, a satellite service comprehensive management system, a power source and a wireless bridge and used for simulating satellite dynamic characteristics and information management. The satellite attitude control system is composed of a jet propulsion system, the DGCMG, a fiber-optic gyroscope, a star sensor, a sun sensor and a global position system (GPS) receiver and used for determination of an attitude and an orbit and control of a satellite platform. The space environment simulation system is composed of a GPS simulator, a sliding block which is of a pyramidal structure, a sun simulator and a star simulator and used for simulating space interference torque, and part performance of a GPS satellite and a celestial body. The satellite multiple attitude control mode test system based on the DGCMG structure can provide ground testing and verification for multiple attitudes of a satellite.

The invention provides a data transmission antenna whole-satellite testing method based on a minisatellite information system. At first, orbital data are input to a satellite attitude control system and a GPS dynamic simulator, by regulating orbit parameters of the satellite attitude control system, controlling start-up time of the GPS dynamic simulator and satellite-arrow separating time, and combining a program control command and a program control data block sequence, time information, orbit information and attitude information of the satellite attitude control system, a GPS receiver and a satellite task distribution system are completely synchronized, testing data are obtained by controlling a data transmission antenna to carry out ground station tracking, and finally, by comparing theoretical data and the testing data of antenna tracking, actual antennal tracking angle errors under different orbit conditions and different satellite attitudes are obtained. According to the data transmission antenna whole-satellite testing method, the orbit and time information state of a minisatellite are accurately simulated, testing of the data transmission antenna under the whole-satellite state of the minisatellite is achieved, and the method is applied to other types of minisatellites at present.

The invention relates to an embedded VxWorks based satellite attitude and orbit control system fault simulation system and method, which adopts a host computer and a target machine technology to realize a single machine model and a failure mode. The method comprises the following steps. A fault simulation host computer runs the Matlab modeling software, establishes a fault model based on Simulink, and generates a target application under the VxWorks real-time operating system under. A fault simulation target machine, connected with the fault simulation host computer through a network, runs the VxWorks real-time operating system and the target application for fault simulation. A fault injection and instruction control machine, connected with the fault simulation target machine and a satellite mounted single-mode machine respectively for transmitting the failure mode instruction of the single-mode machine to realize the switching between the single-mode simulation serial port of the fault simulation target machine and the real single-mode serial port of the satellite mounted single-mode machine. The system and the method of the invention can carry out fault diagnosis and system reconfiguration tests to improve the fault-tolerant ability of the single-machine hardware and the attitude track working in the failure mode of the satellite attitude control system so as to ensure the safety of the satellite.

The invention discloses a low-orbit constellation GEO frequency interference avoidance method based on multiple coverage. In view of the problem that in a current low-orbit communication constellationGEO interference avoidance method, the attitude of a low-orbit satellite is periodically biased, other loads of the low-orbit satellite cannot work easily, and low-orbit satellite attitude control engineering cannot be achieved easily, GEO frequency interference avoidance is achieved through opening and closing of different low-orbit satellite beams in a low-orbit constellation, and continuity oflow-orbit constellation services is guaranteed. And meanwhile, in the whole working process of the low-orbit satellite, the satellite attitude can always keep a normal three-axis stable attitude to the ground, so that the work of other loads of the low-orbit satellite is facilitated, and the engineering realization of a satellite attitude control system is also facilitated.

The invention discloses a disturbance torque identification method suitable for satellite attitude control, and belongs to the technical field of spacecraft attitude control. The invention aims at solving the problem that a conventional filter algorithm cannot achieve the separated measurement of noise and disturbance torque in a high-precision attitude control task. The method comprises the following steps: 1, building a small quantized satellite attitude control mode with an unknown disturbance torque according to a to-be-identified satellite attitude control system; 2, employing an obtained disturbance torque, comprising noise, estimated by an unknown input observer according to the unknown input observer obtained according to the satellite attitude control system built at step 1; 3, employing the DFT (Discrete Fourier Transformation) and the IDFT (Inverse Discrete Fourier Transformation) to process the obtained disturbance torque, comprising noise, estimated at step 2 in an off-line manner, and obtaining the estimation results of the disturbance torque after noise removal; 4, carrying out the Fourier series fitting of estimation results, obtained at step 3 to obtain a mathematical expression of the disturbance torque. The method is used for the attitude control of satellites in orbit.

The invention discloses an optical imaging minisatellite attitude control system and an in-orbit working mode switching method, belongs to the field of satellite attitude control and aims at solving the problem that existing optical imaging satellites cannot be simply and effectively switched in the orbit. The optical imaging minisatellite attitude control system comprises an attitude measurement sensor, an actuating mechanism and an attitude controller, wherein the attitude measurement sensor comprises a sun sensor, a star sensor and a gyroscope; the actuating mechanism comprises a counteraction flywheel and a magnetorquer. According to an in-orbit working mode switching method of the optical imaging minisatellite attitude control system, the optical imaging minisatellite attitude control system has six working modes, namely a rate damping mode, a sun capture mode, a sun-orientated three-axis stabilization mode, an earth-orientated three-axis stabilization mode, a data transmission mode and a safety mode. The optical imaging minisatellite attitude control system and the in-orbit working mode switching method are suitable for all the optical imaging minisatellites.

The invention relates to a method for estimating additive fault size of an executing agency of a satellite attitude control system through a second order Kalman filtering algorithm. The method for estimating the additive fault size of the executing agency of the satellite attitude control system through the second order Kalman filtering algorithm is achieved through the flowing steps of firstly, establishing a discrete control system model according to a kinetic equation and a kinematical equation; secondly, performing calibration on noise vectors wk and vk of the discrete control system model in an actual operational process; thirdly, establishing a discrete control system mathematical model which contains executing agency additive faults; fourthly, measuring a white noise vector wk<f> in the output torque of the executing agency; and fifth, estimating the additive fault sizes of the executing agency through the second order Kalman filtering algorithm. The method for estimating the additive fault size of the executing agency of the satellite attitude control system through the second order Kalman filtering algorithm can be applied to a spacecraft attitude control field and aims at solving the problem that the size of a flywheel generated fault cannot be really reflected in modeling through a Kalman filtering algorithm in the existing satellite attitude control system.

The invention discloses a system of an attitude and orbit control actuator for an all-electric propulsion satellite platform. The system of the attitude and orbit control actuator for the all-electric propulsion satellite platform comprises a satellite orbit control system, a satellite attitude control system, an electric propulsion system, a control torque gyroscope system, a reaction flywheel system and a satellite measurement and feedback system. In view of the working characteristics of a GEO satellite, the system of the attitude and orbit control actuator for the all-electric propulsion satellite platform provides an actuator system which adopts the control torque gyroscope, the reaction flywheel and the electric propulsion system, and aims at providing technical assurance for orbit transfer, orbit keeping and agile maneuvering of the GEO satellite; and through cooperation of the system, the following objectives on GEO satellite that the launch and orbit quality are reduced, the launch cost is reduced, the satellite position maintains accurate, the maneuverability and agility of the satellite attitude are improved, and the service life of the satellite is prolonged are achieved.

The invention provides a magnetic-control bias momentum satellite attitude control method based on the periodic Lyapunov equation, and relates to a magnetic-control bias momentum satellite attitude control system. The magnetic-control bias momentum satellite attitude control method based on periodic Lyapunov equation solves the problems that magnetic-control moment magnitude is limited, and a quantitative relation between selection of a weighting matrix and a performance index of an actual system is difficult to build in a traditional optimum control design method. The magnetic-control bias momentum satellite attitude control method based on the periodic Lyapunov equation comprises the steps that (1) a linear kinetic model of the magnetic-control bias momentum satellite attitude control system is built, (2) a symmetrical positive definite solution W(t) of the periodic Lyapunov equation is obtained, (3) a symmetrical positive definite solution P(t) of the periodic Riccati differential equation is obtained, (4) a state feedback controller is obtained, and (5) the control effect and the magnitude of control moment are tested. The magnetic-control bias momentum satellite attitude control method based on periodic Lyapunov equation is applied to the field of magnetic-control bias momentum satellite attitude control.

A satellite attitude control system includes a programmed processor system which includes a gyroscopic actuator first control stage for changing the attitude of the satellite and a reaction wheel second control stage for assuring that pointing of the satellite is accurate and stable. The method is intended to be used for a satellite including the two control stages indicated above, which it uses selectively for the operations indicated above.

The invention belongs to the automatic control technology field and relates to an adaptive fault tolerance control method for flexible liquid-filled satellite attitude based on a fault characteristic model. According to the method, when a system in under the condition of liquid shaking, flexible vibration and external interference, a fault tolerance controller based on the fault characteristic model is designed for performer faults. The method comprises steps that (1), the fault characteristic model is established according to a flexible liquid-filled satellite attitude kinetic equation; (2), a parameter estimation algorithm is utilized to identify a coefficient of the fault characteristic model, and a coefficient estimation value of the fault characteristic model is acquired; (3), the adaptive fault tolerance controller is designed according to the coefficient estimation value of the fault characteristic model; and (4), a control torque is acquired through the adaptive fault tolerance controller, and the control torque is applied to the satellite attitude control system to control a satellite attitude angle. Through the method, control precision before and after fault generation is guaranteed to be quite high, and the time for realizing the stable state is short.

The invention discloses a self-compensating method for a dynamic and still unbalancing disturbance moment of a satellite rotating part. The dynamic and still unbalancing disturbance moment produced by quick rotating of the rotating part on a satellite can influence the stability of the satellite and reduce the control precision of the satellite. A traditional method for eliminating a dynamic and still unbalancing disturbance moment of a rotating part comprises the steps that the rotating part is subjected to dynamic balancing, and then, active control over dynamic and still unbalancing disturbance is conducted through a satellite attitude control system. The traditional method has limitation to application of rotating parts which are large in inertia, high in rotating speed and irregular in shape. According to the self-compensating method for the dynamic and still unbalancing disturbance moment of the satellite rotating part, two small bias momentum wheels are arranged on the rotating part of the satellite, and the rotating speed of the two bias momentum wheels is set according to the on-orbit calibration result of dynamic and still unbalancing disturbance so that the dynamic and still unbalancing disturbance moment produced during rotating of the rotating part can be eliminated. The self-compensating method is simple, obvious in effect and low in cost, and engineer achieving can be facilitated.

The invention discloses a satellite attitude control system health state assessment and prediction method based on a cloud model. The method is close to the structure and function of a satellite attitude control system. The method comprises the steps of establishing a satellite attitude control system health assessment index set, then using the historical data and the current data to introduce thecloud model theory to establish a satellite attitude control system health state determination method; obtaining an objective and reasonable comprehensive health state assessment result by combiningthe importance degree weight of each index in the established index set, at the same time, knowing the possible change conditions of the health state of the satellite attitude control system, and carrying out the health state trend prediction research analysis on the basis. According to the present invention, the satellite attitude control system simulation platform is subjected to the short-termand long-term health trend prediction analysis, and an efficient method is provided for the autonomous health management of the satellites.

The invention discloses a self-adaption compensation method for uncertainty of drive signs of an actuator of a satellite attitude control system and belongs to the field of aerospace. The self-adaption compensation method comprises steps as follows: (1), modeling is performed on the uncertainty of the drive signs of the actuator, and an actuator drive sign mode set is formed; (2), different self-adaption estimators are designed respectively for different drive sign modes in the established actuator drive sign mode set, and a self-adaption estimator set is formed; (3), a self-adaption controller set is designed by means of output of the self-adaption estimator set; (4), a control switching mechanism among self-adaption controllers is designed by means of output of the self-adaption estimator set, and an appropriate self-adaption controller is selected from the self-adaption controller set to generate a control signal to drive the actuator. The self-adaption compensation method can effectively guarantee the control accuracy when the drive signs of the actuator of the satellite attitude control system are uncertain, and the system can have satisfying work quality.

The invention provides a reaction flywheel output torque measuring circuit and a measuring method thereof and relates to the field of measurement on output torque of a reaction flywheel, and solve the circuit and method provided by the invention can be used for solving the problems in measuring the output torque of the reaction flywheel in the calculation process of a dynamical model. The microprocessor of the circuit is connected to a communication interface, a counter and an integral module, and acquires a flywheel rotating speed direction signal and a 50ms pulse signal; the integral moduleacquires a flywheel rotating speed pulse signal; the counter is further connected to a crystal oscillator; and the communication interface outputs the signals of a dynamical calculation module. The method comprises the following steps of: initializing the microprocessor and the counter, wherein 50ms pulse interruption is superior to flywheel rotating speed pulse interruption; performing the 50ms pulse interruption: recording T50, setting flag to be equal to 1 and quitting the interruption; and performing the flywheel rotating speed pulse interruption: 1, adding 1 to the count value, performing a step 2 if the flag is equal to 1, otherwise, quitting the interruption; 2, reading Tflag, and calculating the rotating speed of the reaction flywheel within a current calculation cycle; 3, calculating moment; and 4, sending the moment to the dynamical model and quitting the interruption. The circuit and method disclosed by the invention are applied to dynamically testing a satellite attitude control system.