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Inertial system spacecraft attitude control/angular momentum management method

A technology for angular momentum management and attitude control, which is applied in the field of attitude control of aerospace satellites and can solve problems such as high dimension of state space equations and workload of controller design.

Active Publication Date: 2015-12-16
BEIHANG UNIV
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Problems solved by technology

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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  • Inertial system spacecraft attitude control/angular momentum management method
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Embodiment Construction

[0132] see figure 1 —— Figure 7 In this paper, the simulation verification of the space station with "T" configuration is carried out. In the simulation, the dynamic model adopts the central rigid body model with flexible attachment, and the actuator only adopts CMG. Since the balance attitude does not coincide with 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 interference moment is shown in Table 1. The moment of inertia in this system is:

[0133] I b = 5.1 - 0.2 0.1 - 0.2 8.3 - 0.08 0.1 - 0.08 4.8 X 10 6 k g · m 2

[0134] Table 1 Other disturbance moments

[0135]

[0136] The orbit of the space station is a near-circular orbit of 400km, so the orbital angular velocity is approximately taken as ω 0 =0.0011rad / s. From the state equations (15) and (17), it can be seen that the cons...

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Abstract

The invention provides an inertial system spacecraft attitude control / angular momentum management method including four steps. The invention aims to solve the problems of control moment gyro angular momentum accumulation caused by gravitation gradient moment and other interference moments in an inertial system, the gravitation gradient moment is adopted to balance the gestures, and a space station angular momentum management controller based on pole assignment is designed. A space station linear model is established under the inertial system, the infeasibility of the inertial system angular momentum management in the pitch axis direction is analyzed, the pitch axis is decoupled from a rolling / yaw axis, and the CMG angular momentum in the pitch axis direction is not restrained, constant disturbance, disturbance being one-time of the track frequency, and disturbance being twice of the track frequency are brought into a state equation to suppress the influence to the pitch axis gestures, and a linear quadratic algorithm based on pole assignment is adopted to solve a feedback gain matrix. The algorithm prevents the selection of cost matrix Q, and based on the requirement of the system performance, the closed-loop poles can be configured to a specified area at the left side of a complex plane imaginary axis, and at the end, the feasibility of the algorithm is verified by the simulation results.

Description

Technical field [0001] The invention relates to the field of aerospace satellite attitude control, in particular to an inertial system spacecraft attitude control / angular momentum management method. It is an attitude control / angular momentum management (ACMM) algorithm used on a space station, which uses the gravity gradient moment to maintain The spacecraft has a certain attitude accuracy while trying to avoid the saturation of the angular momentum of the control moment gyroscope (CMG). Background technique [0002] With the rapid development of the aerospace industry and the diversification of space missions, a variety of spacecraft have emerged from a few kilograms of pico-satellites to hundreds of tons of space stations. This has also given birth to a wide variety of attitude control algorithms, including jet control, attitude control through angular momentum exchange devices, and attitude control by applying space environmental moments. Attitude control is also a prerequisi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 党庆庆金磊李海燕
Owner BEIHANG UNIV
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