A Method for Attitude Control/Angular Momentum Management of Inertial System Spacecraft
A technology of angular momentum management and attitude control, applied in the field of aerospace satellite attitude control, can solve the problems of controller design workload and high dimension of state space equations
Active Publication Date: 2017-08-08
BEIHANG UNIV
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However, the dimension of the state space equation of the algorithm is relatively high, reaching 24 dimensions. It is not an easy task to obtain a satisfactory control effect by selecting the weight matrix Q, which will bring great difficulties to the initial design work of the controller. burden, and so far there is no ACMM control algorithm that is more practical in the inertial system
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[0132] See figure 1 —— Figure 7 In this paper, the simulation verification is carried out for the space station with "T" configuration. The dynamic model in the simulation adopts the central rigid body model with flexible accessories, and the actuator only uses CMG. Since the balance attitude is not the coincidence of the body and the inertial system, without loss of generality, the initial attitude angle and attitude angular velocity are taken as zero, and the system disturbance torque is shown in Table 1. The moment of inertia of this system is:
[0133]
[0134] Table 1 Other disturbance moments
[0135]
[0136] The orbit of the space station is a nearly circular orbit of 400 km, so the orbital angular velocity is approximated by ω 0 =0.0011rad / s, from the state equations (15) and (17), it can be seen that the constant disturbance in the roll / yaw direction of the equation after dimension expansion is absorbed by the attitude bias, which avoids the accumulation o...
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A method for attitude control / angular momentum management of an inertial system spacecraft has four steps. The invention aims at the problem of accumulating angular momentum of the control moment gyro caused by the gravitational gradient moment and other disturbance moments in the inertial system, uses the gravitational gradient moment to balance the posture, and designs a space station angular momentum management controller based on pole configuration. Establish a linearized model of the space station in the inertial system, and analyze the infeasibility of angular momentum management in the direction of the pitch axis, decouple the pitch axis from the roll / yaw axis, and not constrain the CMG angular momentum in the direction of the pitch axis, A constant value and a disturbance of one or two times the orbital frequency are included in the state equation to suppress its influence on the attitude of the pitch axis, and then the feedback gain matrix is solved by using the linear quadratic algorithm with pole configuration. The algorithm avoids selecting the cost matrix Q, and according to the system performance requirements, the closed-loop poles can be allocated to the designated area on the left side of the imaginary axis of the complex plane. Finally, the simulation results verify the feasibility of the algorithm.
Description
technical field [0001] The present invention relates to the field of attitude control of aerospace satellites, in particular to a method for attitude control / angular momentum management of an inertial system spacecraft, which is an attitude control / angular momentum management (ACMM) algorithm used on a space station, which utilizes the gravity gradient moment to maintain The technique of avoiding angular momentum saturation of the Control Moment Gyroscope (CMG) while maintaining a certain attitude accuracy of the spacecraft. Background technique [0002] With the rapid development of the aerospace industry and the diversification of space missions, various spacecraft have emerged as the times require, ranging from pico-satellites of a few kilograms to space stations of hundreds of tons. This has also led to a wide variety of attitude control algorithms, mainly including jet control, attitude control through angular momentum exchange devices, and attitude control using space ...
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IPC IPC(8): G05D1/08
Inventor 党庆庆金磊李海燕
Owner BEIHANG UNIV