Attitude control method for solar sail spacecraft

Abstract

The invention discloses an attitude control method for a solar sail spacecraft, which can realize attitude control over the spacecraft. According to the method, a variable-reflectivity flexible thin-film device is pasted to the outer edge area of the upper surface of the solar sail of the spacecraft, and the reflectivity of the variable-reflectivity flexible thin-film device is changed by controlling the voltage of the variable-reflectivity flexible thin-film device so as to change the light pressure on the surface of the solar sail of the spacecraft to generate a differential moment, and further realize attitude control over the spacecraft. An attitude controller is the thin-film device and can be integrated with the solar sail spacecraft more easily to improve the integration level and the reliability of the solar sail. In addition, the attitude controller has a light weight, can greatly reduce the weight of the spacecraft, increases the load ratio and greatly improves the solar sail attitude control performance. With no mechanical structure, the attitude controller has high reliability.

Description

technical field [0001] The invention relates to a method for controlling the attitude of a spacecraft, in particular to a method for controlling the attitude of a solar sail spacecraft. Background technique [0002] The light pressure propulsion solar sail spacecraft relies on the reflection of sunlight by the huge but light solar sail to obtain a steady stream of thrust. It is the only aircraft that does not rely on reaction propulsion to achieve flight control. It does not need to consume fuel, and its life in space is not limited by limited fuel. Using the continuous acceleration provided by the sun's light pressure, after a long period of acceleration, the speed of the solar sail spacecraft can be 4 to 6 times faster than the fastest spacecraft propelled by rockets today. Due to the huge advantages of solar sail spacecraft, it will play a more important role in future space mission applications. [0003] However, the solar sail is a flexible body spacecraft with 6 degr...

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Problems solved by technology

[0003] However, the solar sail is a flexible body spacecraft with 6 degrees of freedom, and its moment of inertia, natural frequency, damping and modal constants are all uncertain. Moreover, the flight time of the mission is long, and there are many disturbance moments. Using the traditional attitude control method will greatly reduce the flight performance of the solar sail spacecraft, which is no longer suitable for the attitude control of the solar sail spacecraft. Scholars at home and abroad have proposed in this field A variety of new attitude control technologies have been proposed, which can be divided into two categories through induction. One is to change the center of mass through the slider on the guide rail to form a moment for attitude control, and the other is to use the angle adjustment of the small sail to obtain the attitude control moment. These two types have mechanical moving parts, their reliability cannot be fully guaranteed, and the implementation process is more complicated

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