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Determining method for compensating factor of magnetometer for magnetic control moonlet

A technology for compensating factors and determining methods, which is applied to the simulation device of space navigation conditions, space navigation equipment, transportation and packaging, etc., can solve the problems of the whole satellite residual magnetic moment, magnetic noise interference, etc., and achieve high reliability and easy implementation Effect

Inactive Publication Date: 2014-12-17
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

Therefore, in the magnetic test of this type of satellite, it is necessary to solve the problem of magnetic noise interference of the whole satellite residual magnetic moment and dynamic magnetic moment on the measurement data of the magnetometer during orbit operation; and the measurement accuracy of the magnetic induction device

Method used

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  • Determining method for compensating factor of magnetometer for magnetic control moonlet
  • Determining method for compensating factor of magnetometer for magnetic control moonlet
  • Determining method for compensating factor of magnetometer for magnetic control moonlet

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Embodiment Construction

[0026] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0027] like figure 1 Shown, a kind of method for determining the magnetometer compensation factor of the present invention is used for magnetron small satellite, comprises steps as follows:

[0028] (1) The whole satellite is placed in the zero magnetic laboratory, and the coordinate system of the satellite body is adjusted to be consistent with the three axes of the magnetic field coordinate system of the laboratory, and the residual magnetic field value B of the whole satellite in the residual magnetic field environment is obtained by measuring with a magnetometer x0 , B y0 , B z0 ;

[0029] Measured to get the whole star residual magnetic field value B x0 , B y0 , B z0 The specific method is as follows:

[0030] (1a) Place the entire star in a zero magnetic field environment;

[0031] (1b) Corresponding the three coordinate ...

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Abstract

The invention provides a determining method for a compensating factor of a magnetometer for a magnetic control moonlet. The method comprises the following steps that the whole moonlet is placed in a zero-magnetism laboratory, a moonlet body coordinate system is regulated to be consistent with a laboratory magnetic field coordinate system in the pointing direction, and the magnetometer is used for measurement to obtain the whole moonlet residual magnetic field value in a residue magnetic field environment; a real ground magnetic field is simulated in the zero-magnetism laboratory, a controllable magnetic field is generated through adopting a coil galvanization method, simulated ground magnetic intensity values are respectively loaded in the three-axis directions of the moonlet, and in addition, the magnetometer is use for measurement to obtain the whole moonlet magnetic induction intensity in the simulated ground magnetic field environment; the compensating factor of the magnetometer is determined. The determining method has the greatest innovation point that the problem of magnetic field measuring precision of the magnetic control moonlet is solved, the solution to the problem is a necessary premise for successfully completing a space mission by the moonlet of which the posture is determined by the measuring value of the magnetometer, and the method has a very crucial engineering practical significance.

Description

technical field [0001] The invention relates to a method for determining a magnetometer compensation factor for a magnetron small satellite, and belongs to the technical field of space environment testing. Background technique [0002] The technology of using the space magnetic field environment to control the attitude of the satellite is favored by the micro-satellite platform because it saves energy and fuel, reduces the mass of the satellite, and reduces the launch cost. The geomagnetic field is described by the International Reference Geomagnetic Field Model (IGRF). The strength and vector of the geomagnetic field are functions of the position. When the orbit of the satellite is determined, the component of the geomagnetic field vector in the orbital coordinate system can be obtained (which can be recorded as B O ). The measured value of the magnetometer is the component of the geomagnetic field vector in the coordinate system of the satellite body (which can be denoted ...

Claims

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Application Information

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IPC IPC(8): B64G7/00
Inventor 刘佳徐森仇越邓卫华
Owner AEROSPACE DONGFANGHONG SATELLITE
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