A method for improving the three-axis stability of a satellite

A stability and satellite technology, applied in the direction of artificial satellites, space navigation equipment, space navigation vehicles, etc., can solve the problems that cannot be completely eliminated, high risk, and time delay has a great influence, so as to optimize the performance of attitude control and facilitate Engineering realization, the effect of reducing the response range

Active Publication Date: 2020-03-17
SHANGHAI ENG CENT FOR MICROSATELLITES
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AI Technical Summary

Problems solved by technology

[0009] (1) Reduce the interference of dynamic and static unbalance as far as possible through structural design and dynamic balance trimming from the source, but it cannot be completely eliminated, and for irregular rotating parts, it is impossible to perform effective trimming
[0010] (2) The attitude control system adopts the open-loop feedforward method to further suppress the interference, but the open-loop control has high requirements for the modeling accuracy of the amplitude and phase of the interference, and is greatly affected by the time delay; in addition, the feedforward control will Add a new zero point in the system closed-loop transfer function, this new zero point may seriously affect the dynamic performance of the closed-loop system
Therefore, the method of applying open-loop feedforward has high risk

Method used

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Embodiment 1

[0124] A fixed-frequency interference active closed-loop suppression PID wheel control method with a digital structure enhancer provided by an embodiment of the present invention includes:

[0125] Step 1. The rotation speed of the rotating parts on the satellite is unknown, and the angular velocity fluctuation frequency f (Hz) of the satellite is obtained through on-orbit measurement. Then the fixed frequency ωrad / s of the disturbance torque introduced by the rotating parts is:

[0126] ω=2πf.

[0127] Step 2. Design a digital structure enhancer for this frequency, and its transmission schematic diagram is as follows figure 1 As shown, the corresponding expression is:

[0128]

[0129]

[0130]

[0131] The fixed-frequency disturbance torque has components in the X, Y, and Z axes of the satellite, so the expressions of the parameters of the digital structure enhancer are:

[0132]

[0133]

[0134]

[0135]

[0136]

[0137] In the above formula, T i...

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Abstract

The invention relates to a method for improving the three-axis stability of a satellite, comprising the following steps: determining the fixed frequency of the disturbance moment of the rotating part; determining the transfer function of the digital structure enhancer according to the fixed frequency and the control period of the control system; Determine the PID wheel control method of the digital structure enhancer according to the inertia of the satellite; and provide the digital structure enhancer to improve the three-axis stability of the satellite. Through this method, the influence of the disturbance moment of the rotating parts on the satellite on the satellite's three-axis stability can be significantly reduced, and at the same time at least partially avoid the shortcomings of the existing technology, such as the inability to trim irregularly rotating parts, or affect the system dynamics performance etc.

Description

technical field [0001] The present invention generally relates to the technical field of spacecraft attitude control, in particular to a method for improving the three-axis stability of a satellite. Background technique [0002] With the continuous expansion of the application field of modern satellites, the load on the star has an increasing demand for the rotating mechanism, so there are more and more rotating parts on the star, the inertia of the rotating parts is getting larger, and the speed is getting faster and faster. [0003] The center of mass deviation and uneven mass distribution of the rotating parts on the star will cause dynamic and static unbalanced disturbance moments in the rotating plane (static unbalanced disturbance moments T s and dynamic unbalance disturbance torque T d ). Both dynamic and static unbalanced disturbance torques are sinusoidal disturbance torques with fixed frequency. Since the rotation plane of the rotating part has no necessary rela...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/10
CPCB64G1/10B64G1/24B64G1/245
Inventor 谢祥华张锐赵璟刘剑严玲玲本立言于晓至董祯胡志强祁海铭黄志伟何夏维
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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