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Atmospheric drag torque compensation method and system for controlling attitude of ultra-low orbit satellite

A technology for orbiting satellites and atmospheric drag, which is applied to space navigation equipment, space navigation vehicles, space navigation equipment, etc., and can solve the problems of satellite orbit attenuation, satellite attitude, disturbance, etc., to reduce atmospheric resistance and drag moment, and low cost , good control effect

Active Publication Date: 2021-04-02
成都天巡微小卫星科技有限责任公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is the attenuation of ultra-low orbit satellite orbit and the disturbance of satellite attitude caused by atmospheric resistance and atmospheric resistance moment. The purpose is to provide a compensation method and system for controlling the attitude of ultra-low orbit satellites. Satellite attitude guidance rate, so that the longitudinal axis of the satellite is always parallel to the direction of incoming flow velocity, minimizing aerodynamic resistance and drag moment

Method used

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  • Atmospheric drag torque compensation method and system for controlling attitude of ultra-low orbit satellite
  • Atmospheric drag torque compensation method and system for controlling attitude of ultra-low orbit satellite
  • Atmospheric drag torque compensation method and system for controlling attitude of ultra-low orbit satellite

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Embodiment

[0035] 1) if figure 1 Shown, a kind of atmospheric drag moment compensation method and system of the present invention controls the attitude of ultra-low orbit satellites, according to the orbit parameters (semi-major axis a, eccentricity e, true anomaly f and earth center distance r), calculate and obtain Tangential linear velocity of satellite orbit

[0036]

[0037] and radial speed

[0038]

[0039] The linear velocity of the orbital motion under the satellite's own system

[0040]

[0041] where C BO is the satellite attitude matrix, μ=398600.5.

[0042] 2) Calculate the linear velocity of atmospheric rotation

[0043]

[0044]

[0045] in is the satellite geocentric distance vector, C BI is the inertial attitude matrix of the satellite, m is the correction coefficient, generally 1.0~1.5; ω e =7.2722051e -5 .

[0046] 3) Calculation of atmospheric relative satellite velocity

[0047] Consists of two parts: one part is the orbital velocity of the sa...

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Abstract

The invention discloses an atmospheric drag torque compensation method and system for controlling the attitude of an ultra-low orbit satellite. The attitude is guided to adapt to the atmospheric incoming flow of the satellite at different orbit positions under the condition that the hardware configuration of a satellite system is not additionally increased, thereby reducing the atmospheric drag and drag torque to the maximum degree, and improving the reliability; extra hardware cost of the satellite is not increased; atmospheric resistance is resisted without increasing propellant consumption,a large angular momentum flywheel system does not need to be adopted to absorb resisting moment, the method and system are completely achieved based on existing hardware configuration of a satellite,and the method and system are good in economical efficiency and particularly suitable for small satellites with low cost. Secondly, the control effect is good, test simulation shows that the aerodynamic resistance and the resistance torque can be reduced to one third of those before compensation, and good realizability is achieved.

Description

technical field [0001] The invention relates to the technical field of overcoming atmospheric resistance and resistance moment for ultra-low orbit satellites, in particular to an atmospheric resistance moment compensation method and system for controlling the attitude of ultra-low orbit satellites. Background technique [0002] At present, ultra-low orbit means that the orbit height is about 200km, and satellites operating at this orbit height are called ultra-low orbit satellites. Compared with traditional low-orbit satellites operating at an orbital altitude of 500km to 600km, ultra-low-orbit satellites have incomparable advantages, such as: enabling higher spatial resolution of optical cameras; less power consumption for signal transmission; lower launch costs ; and rapid deployment, etc. [0003] However, satellites flying in ultra-low orbits also face severe challenges, making long-term stable ultra-low orbit flights full of risks. The main difficulty lies in the signi...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/244B64G1/245Y02T90/00
Inventor 黎康祁飞刘伟邹晶晶郑覃黄一
Owner 成都天巡微小卫星科技有限责任公司
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