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 the effects of wide applicability, high reliability and fast response speed

Active Publication Date: 2022-07-29
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

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no. 1 example

[0043] This embodiment is directed to a solar sail spacecraft, and the spacecraft attitude control system based on the momentum wheel and the reflectivity control device proposed in the present invention is applied.

[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 compartment 50 refers specifically to the central compartment of the solar sail spacecraft, and the spacecraft extravehicular attachment 60 refers specifically to the sail surface and its supporting structure of the solar sail spacecraft, all of which are used to illustrate the present embodiment. , the installation position of each component of the attitude control system. figure 2 In this embodiment, a schematic diagram of the working principle of the attitude control system is shown. The spacecraft at...

no. 2 example

[0065] This embodiment is aimed at a conventional spacecraft, and applies the spacecraft attitude control system based on the momentum wheel and the reflectivity control device proposed in the present invention. The structure of the conventional spacecraft adopts the structure of a central body + a solar cell array carried on both sides.

[0066] see Figure 9 , that 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 second embodiment. In this embodiment, the spacecraft body compartment 50 refers specifically to the central compartment of the spacecraft, and the spacecraft extravehicular accessories 60 refers specifically to the solar cell array of the spacecraft. installation location.

[0067] refer to Figure 9 As with the first embodiment, those of ordinary skill in the art can obtain the specific implementation of the attitude control system described in the second ...

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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 includes an actuation subsystem, an unloading subsystem, an attitude determination subsystem, and a drive control subsystem; the attitude control system adopts a momentum wheel as the actuation mechanism for spacecraft attitude control, and adopts an autonomously adjustable The emissivity control device of the reflectivity generates an unloading torque, and selectively unloads the momentum wheel that tends to saturate. The spacecraft attitude control system based on the system solution components can not only ensure the attitude control ability, but also get rid of the dependence on traditional unloading methods such as geomagnetic moment unloading and thruster unloading, so that the spacecraft can operate in the space environment beyond the medium and high orbit. With super long-term service conditions.

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, which 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 brings hidden dangers to the attitude control system. Therefore, when the momentum wheel is about to reach saturation, its angular momentum must be unloaded. Common unloading me...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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