Spacecraft attitude control system based on momentum wheel and reflectivity control device

A control device and attitude control technology, which is applied in the direction of aerospace vehicles, aerospace vehicle guidance devices, motor vehicles, etc., can solve the problems of unable to meet the unloading requirements of momentum wheels, unable to continue to provide unloading torque, high earth magnetic field strength, etc. Achieve high reliability, prolong life, and fast response speed

Active Publication Date: 2021-03-30
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, the unloading of geomagnetic moment requires a high strength of the earth's magnetic field, so it is only suitable for medium and low orbit satellites
Thruster torque unloading needs to consume working fluid, when the working fluid is exhausted, it cannot continue to provide unloading torque
With the improvement of the mission boundary of future spacecraft and the increase of mission time, the traditional unloading method will not be able to meet the unloading requirements of the momentum wheel and become one of the bottlenecks in the development of the aerospace industry.

Method used

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  • Spacecraft attitude control system based on momentum wheel and reflectivity control device
  • Spacecraft attitude control system based on momentum wheel and reflectivity control device
  • Spacecraft attitude control system based on momentum wheel and reflectivity control device

Examples

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no. 1 example

[0043] This embodiment is aimed at a solar sail spacecraft, applying the spacecraft attitude control system based on the momentum wheel and reflectivity control device proposed by the present invention.

[0044] see figure 1 , figure 2 , figure 1 It is a schematic diagram of the composition of the spacecraft attitude control system based on the momentum wheel and the reflectivity control device in the first embodiment. In this embodiment, the spacecraft body cabin 50 specifically refers to the central cabin body of the solar sail spacecraft, and the outer accessories 60 of the spacecraft specifically refer to the sail surface and its supporting structure of the solar sail spacecraft, both of which are used to demonstrate the solar sail spacecraft in this embodiment. , the installation position of each component of the attitude control system. figure 2 It is a schematic diagram of the working principle of the attitude control system in this embodiment. The spacecraft atti...

no. 2 example

[0065] This embodiment is aimed at a conventional spacecraft, applying the spacecraft attitude control system based on the momentum wheel and reflectivity control device proposed by the present invention. The structure of the conventional spacecraft adopts the structural form of a central body + solar battery arrays on both sides.

[0066] see Figure 9 , that is, in the second embodiment, a schematic diagram of the composition of the spacecraft attitude control system based on the momentum wheel and the reflectivity control device. In this embodiment, the spacecraft body cabin 50 specifically refers to the central cabin body of the spacecraft, and the spacecraft outboard accessories 60 specifically refer to the solar cell array of the spacecraft, both of which are used to demonstrate the components of the attitude control system in this embodiment. installation location.

[0067] refer to Figure 9 As with the first embodiment, those skilled in the art can obtain the speci...

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Abstract

The invention discloses a spacecraft attitude control system based on a momentum wheel and a reflectivity control device, and belongs to the technical field of spacecraft attitude control. The spacecraft attitude control system comprises an actuation subsystem, an unloading subsystem, an attitude determination subsystem and a drive control subsystem. According to the attitude control system, a momentum wheel is adopted as an actuating mechanism for spacecraft attitude control, an emissivity control device capable of autonomously adjusting reflectivity is adopted to generate an unloading torque, and the momentum wheel tending to be saturated is selectively unloaded. According to the spacecraft attitude control system based on the system scheme assembly, an attitude control capability can beguaranteed, dependence on traditional unloading methods such as geomagnetic moment unloading and thruster unloading can be avoided, and a spacecraft is made to have an ultra-long-term service condition in the space environment far away from a medium-high orbit.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, in particular to a spacecraft attitude control system based on a momentum wheel and a reflectivity control device. Background technique [0002] The spacecraft attitude control system is an important part of the spacecraft, and it is very important for the spacecraft to perform various tasks smoothly. Momentum wheel is a kind of mechanical angular momentum exchange device, which can generate attitude control torque with high precision, so it is widely used as actuator in spacecraft attitude control system. However, limited by the physical limit of the rotational speed, when the rotational speed of the momentum wheel exceeds a certain threshold, it will no longer have complete control capability, which will bring hidden dangers to the attitude control system. Therefore, when the momentum wheel is about to reach saturation, its angular momentum must be unloaded. Common unloadi...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/28
CPCB64G1/244B64G1/285
Inventor 季浩然李东旭刘望张斌斌吴军
Owner NAT UNIV OF DEFENSE TECH
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