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Sub-orbit satellite fully passive stable attitude control system and method

A passively stabilized, sub-orbital technology, applied in the aerospace field, can solve the problems of adding aerodynamic rudders, disadvantageous satellite low cost, etc.

Inactive Publication Date: 2020-06-19
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Description
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Problems solved by technology

[0004] The problem solved by the present invention is that the attitude control of existing suborbital satellites needs to increase the pneumatic rudder, which is not conducive to the miniaturization and low cost of satellites; the above problems are not solved, and the present invention provides a fully passive stable attitude control system and method for suborbital satellites

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  • Sub-orbit satellite fully passive stable attitude control system and method
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  • Sub-orbit satellite fully passive stable attitude control system and method

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Embodiment Construction

[0024] Hereinafter, the spirit and essence of the present invention will be further described in conjunction with the drawings and embodiments.

[0025] It can be seen from the background technology that in order to overcome aerodynamic moments to achieve attitude control and stability, it is necessary to use actuators on suborbital satellites. The actuators include aerodynamic rudders, which is not conducive to the miniaturization and low cost of satellites; the inventors have studied the above problems and abandoned the past The aerodynamic moment is used as a disturbance moment for active attitude control. A brand-new way is used to model the satellite aerodynamic moment, and the suborbital satellite attitude motion description model in the body coordinate system is calculated. The study found that under the action of aerodynamic moment, the satellite pitch The law of motion of attitude and yaw attitude is simple harmonic motion without damping; the law of free motion of rollin...

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Abstract

The invention provides a suborbital satellite fully-passive stable attitude control system and method. The suborbital satellite fully-passive stable attitude control system provided in the invention comprises a three-axis magnetometer, a three-axis magnetic torquer and a bias momentum wheel. The three-axis magnetometer measures magnetic field intensity in a satellite body coordinate system, a magnetically controlled damping magnetic moment value is calculated via P<ci>=P<0i>sign(B<.><bi>), i=x, y, z, P<0i> is a maximum i-direction magnetic moment which can be provided by the three-axis magnetic torquer, B<bi> is an i component of the magnetic field intensity in the satellite body coordinate system, the magnetically controlled damping magnetic moment value obtained through calculation is input into the three-axis magnetic torque, the three-axis magnetic torque generates a magnetically controlled damping magnetic moment, the magnetically controlled damping magnetic moment interacts with a geomagnetic field to generate an electromagnetic moment, and the bias momentum wheel is used to couple rolling and yaw attitudes.

Description

Technical field [0001] The invention relates to the field of aerospace technology, in particular to a suborbital satellite fully passive stable attitude control system and method. Background technique [0002] In the prior art, the design of satellite attitude control systems mostly uses aerodynamic torque as interference torque for active attitude control. Due to the extreme suborbital aerodynamic force, a large amount of active control resources are required to achieve attitude control and stability, which is bound to cause resources Waste is extremely unfavorable to satellites in terms of cost reduction, miniaturization and low cost, and the consumption of active control resources also makes the life of the satellite limited. [0003] Suborbital satellites are satellites with a lower orbit than the ultra-low orbit satellites studied in the past, and their orbits are about 120km. At present, there are very few researches on the design of satellite attitude control systems at this...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 刘善伍陈宏宇容建刚夏喜旺刘洋王俊王尊赵永佳孙国文
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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