CN109633510B - Satellite magnetometer magnetic environment analysis method based on ground backup single machine - Google Patents
Satellite magnetometer magnetic environment analysis method based on ground backup single machine Download PDFInfo
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- CN109633510B CN109633510B CN201910044500.8A CN201910044500A CN109633510B CN 109633510 B CN109633510 B CN 109633510B CN 201910044500 A CN201910044500 A CN 201910044500A CN 109633510 B CN109633510 B CN 109633510B
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Abstract
The invention discloses a satellite magnetometer magnetic environment analysis method based on a ground backup single machine, which comprises the steps of rotating the ground backup magnetometer on a nonmagnetic turntable at intervals of a certain angle for a circle, measuring three-direction data of the magnetometer at each interval angle, and calculating the magnitude of a magnetic field vector; placing the satellite on a non-magnetic rotary table to rotate for a circle at the same angle interval, measuring three-direction data of a magnetometer in the satellite at each interval angle, and calculating the magnitude of a magnetic field vector; and subtracting the magnetic field vector measured by the ground backup magnetometer from the magnetic field vector measured by the in-satellite magnetometer to obtain the magnetic field influence of the satellite residual magnetism at the in-satellite magnetometer at each angle interval, and calculating the arithmetic mean value of the calculation results of each angle, namely the influence of the satellite residual magnetic field on the magnetometer. When the measured magnetic field intensity is less than 1/10 of the magnetic field intensity of the satellite orbit environment, the whole satellite remanence environment is considered to have no influence on the magnetometer, otherwise, the layout needs to be changed or the magnetic optimization design needs to be carried out. The invention can provide support for layout and design optimization of the magnetometer.
Description
Technical Field
The invention relates to the technical field of satellite tests, in particular to a method for measuring and analyzing the influence of satellite residual magnetism on an in-satellite magnetometer, which can be used for reference of other spacecrafts.
Background
The magnetometer is a sensor which measures the satellite attitude by taking the earth magnetic field as a reference. The magnetometer has been widely used due to its small mass, reliable performance, low power consumption, wide working temperature range and no moving parts. The magnetometer itself is used to measure the magnetic field strength in a spatial environment. Because the magnetic field intensity of each point around the earth can be determined in advance by the earth magnetic field model, the attitude of the satellite relative to the earth magnetic field can be determined by comparing the information measured by the satellite in-orbit magnetometer with the earth magnetic field model.
Because the earth magnetic field model is only an approximate description of the earth magnetic field, the measurement accuracy of the model as a reference for measuring the star attitude by using the magnetometer is not high. In addition, the intensity of the earth magnetic field at a certain point is inversely proportional to the 3 rd power of the distance from the earth center of the point, so that the intensity of the earth magnetic field at the height of a satellite orbit is very weak, and the influence of the earth magnetic field is exceeded when the residual magnetism inside the spacecraft is too large, thereby influencing the measurement of a magnetometer.
Therefore, when the satellite is designed, on one hand, the residual magnetism of the whole satellite and a single satellite on the satellite needs to be strictly controlled, and low-magnetism or even non-magnetism materials are selected; on the other hand, during the layout, the magnetometer is far away from a single machine with larger residual magnetism, such as a driving mechanism, a storage battery and the like.
In order to provide a cleaner magnetic field environment for the magnetometer, the influence of satellite residual magnetism on the magnetometer is accurately evaluated in the ground development stage, and the normal use of the magnetometer in orbit is ensured. At present, no similar explanation or report is found, and no similar data at home and abroad is collected.
Disclosure of Invention
The invention aims to provide a geomagnetic field characteristic-based satellite magnetometer magnetic environment analysis method, which solves the problem of analyzing the influence of satellite remanence on an in-satellite magnetometer under a geomagnetic field environment condition by utilizing the characteristics of invariable influence and direction of the satellite remanence on the in-satellite magnetometer and can provide support for layout and design optimization of the magnetometer.
The purpose of the invention is realized by the following technical scheme:
a satellite magnetometer magnetic environment analysis method based on a ground backup single machine comprises the following steps:
step 1: arranging a non-magnetic rotary table in the center of a magnetic field measuring chamber, then placing a single ground backup magnetometer in the center of the non-magnetic rotary table, and connecting and conducting the magnetometer and ground testing equipment; rotating the non-magnetic turntable for one circle at intervals of 10 degrees (or 20 degrees and 30 degrees), and reading the measurement data (B) of the magnetometer in three directions at each interval angleiX，BiY，BiZ) (i ═ 1, 2, 3,. n), then the vector of field strength at that angle is
Step 2: taking the ground backup magnetometer down from the non-magnetic turntable, placing the satellite in the center of the non-magnetic turntable, connecting the satellite with ground power supply and test equipment, and powering up the satellite according to an on-orbit steady-state mode; rotate at intervals of 10 degrees (or 20 degrees and 30 degrees) without magnetic rotationOne turn of the stage was taken, and measurement data (B ') of the on-board magnetometer in three directions was read at every interval angle'iX，B′iY，B′iZ) (i 1, 2, 3.) the vector of the magnetic field strength at that location is
And step 3: because the magnetic field intensity data measured by the satellite magnetometer is the superposition of the geomagnetic field and the satellite residual magnetic field, the magnetic field intensity measured by the satellite magnetometer is subtracted from the magnetic field intensity measured by the ground backup magnetometer, so that the magnetic field intensity generated by the satellite residual magnetic field can be obtained, and the satellite residual magnetic field intensity vector at the position is B ″i＝B′i-Bi. Since the remanent field strength vector of the satellite is determined relative to the in-satellite magnetometer, the magnitude of the remanent field strength vector of the satellite is
Wherein n is the angular interval number of one rotation of the satellite, B ″iThe satellite remanent field intensity vectors at all interval angles are obtained;
and 4, step 4: obtaining the magnetic field intensity B of the environment of the satellite in orbit by referring to GJB/Z19-1991' near-earth space magnetic field0If magnitude of residual magnetic field intensity vector of satellite
The influence of the satellite residual magnetism on the in-satellite magnetometer can be ignored, otherwise, the satellite layout needs to be adjusted or the whole-satellite magnetism optimization design needs to be carried out, so that the influence of the satellite on the magnetic field of the magnetometer meets the requirement.
Wherein, the magnetic field strength of the near-earth orbit space which is generally lower than 1000km is about 20000-40000 nT, so the measured magnetic field strength B of the satellite residual magnetism needs to be less than 2000 nT.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention solves the problem of analyzing the influence of the residual magnetism of the satellite on the magnetic intensity meter in the satellite under the ground environment condition;
2. the invention provides support for the ground layout and design optimization of the magnetometer.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a flowchart of a method for analyzing a magnetic environment of a satellite magnetometer based on a ground backup single machine according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, in the method for analyzing the magnetic environment of a satellite magnetometer based on a ground backup single machine according to the embodiment of the present invention, by using the characteristic that the residual magnetism of a satellite has no change in the magnitude and direction of the influence on the satellite magnetometer in the satellite, the ground backup magnetometer is rotated on a non-magnetic turntable at intervals of a certain angle for one circle, three-direction data of the magnetometer at each interval angle are measured, and the magnitude of a magnetic field vector is calculated; placing the satellite on a non-magnetic turntable, rotating for a circle at the same angle interval, measuring three-direction data of a magnetometer in the satellite at each interval angle, and calculating the magnitude of a magnetic field vector; and subtracting the magnetic field vector measured by the ground backup magnetometer from the magnetic field vector measured by the in-satellite magnetometer to obtain the magnetic field influence of the satellite residual magnetism at the in-satellite magnetometer at each angle interval, and calculating the arithmetic mean value of the calculation results of each angle to obtain the influence of the satellite residual magnetic field on the magnetometer. When the measured magnetic field intensity is less than 1/10 of the magnetic field intensity of the satellite orbit environment, the whole-satellite residual magnetism environment is considered to have no influence on the magnetometer, otherwise, the layout needs to be changed or the magnetism optimization design needs to be carried out; the method specifically comprises the following steps:
step 1: and arranging a non-magnetic turntable and a ground backup magnetometer and debugging.
Specifically, step 1.1: arranging a non-magnetic rotary table in the center of a magnetic field measuring chamber;
step 1.2: a ground backup magnetometer stand-alone is placed in the center of the non-magnetic turntable and is connected and conducted with ground test equipment;
step 1.3: rotating the non-magnetic turntable for one circle at intervals of 10 degrees (or 20 degrees and 30 degrees), and reading the measurement data (B) of the magnetometer in three directions at each interval angleiX，BiY，BiZ) (i ═ 1, 2, 3.., n), then the vector of field strength at that angle is
Step 2: arranging a satellite, connecting and testing; specifically, the method comprises the following steps:
step 2.1: taking down the ground backup magnetometer from the non-magnetic turntable;
step 2.2: placing the satellite in the center of the non-magnetic turntable, and connecting ground power supply and test equipment;
step 2.3: powering up the satellite, and setting the satellite single machine according to an on-orbit steady-state mode;
step 2.4: the non-magnetic turntable was rotated at intervals of 10 ° (or 20 °, 30 °) for one revolution, and measurement data (B 'in three directions of the on-satellite magnetometer was read at each interval angle'iX，B′iY，B′iZ) (i 1, 2, 3.), the vector of the magnetic field strength at this angle is
And step 3: calculating the satellite residual magnetic field intensity at the magnetometer on the satellite and the satellite residual magnetic field intensity vector size B' at each interval angleiComprises the following steps:
B″i＝B′i-Bi (2)
then, the magnitude of the satellite remanent field strength vector B' at the on-satellite magnetometer is:
and 4, step 4: evaluating the influence of the satellite residual magnetic field on the on-satellite magnetometer; specifically, the method comprises the following steps:
step 4.1: obtaining the magnetic field intensity B of the environment of the satellite in orbit by referring to GJB/Z19-1991' near-earth space magnetic field0Generally, the magnetic field intensity of the near-earth orbit space less than 1000km is about 20000-40000 nT;
step 4.2: if the magnetic field intensity B' generated by the satellite residual magnetism at the position of the magnetic intensity meter in the satellite meets the following conditions:
the influence of the satellite residual magnetism on the in-satellite magnetometer can be ignored, otherwise, the satellite layout needs to be adjusted or the whole-satellite magnetism optimization design needs to be carried out, so that the magnetic field influence of the satellite on the magnetometer meets the requirement of the formula (1), and generally needs to be less than 2000 nT.
The foregoing describes a specific embodiment of the present invention. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (2)
1. A satellite magnetometer magnetic environment analysis method based on a ground backup single machine is characterized by comprising the following steps:
step 1: arranging a non-magnetic rotary table in the center of a magnetic field measuring chamber, then placing a ground backup magnetometer stand-alone in the center of the non-magnetic rotary table, and connecting and conducting a magnetometer and ground testing equipment; rotating the nonmagnetic turntable for one circle at intervals of 10 degrees, 20 degrees or 30 degrees, and reading the measurement data of the magnetometer in three directions at each interval angle (B)iX，BiY，BiZ) 1, 2, 3, n, the magnetic field strength vector at that angle is
Step 2: taking off the ground backup magnetometer from the non-magnetic turntable, and placing the satellite on the non-magnetic turntableThe center of the platform is connected with satellite ground power supply and test equipment, and the satellite is powered up according to an on-orbit steady-state mode; rotating the non-magnetic turntable for one circle at intervals of 10 degrees, or 20 degrees or 30 degrees, and reading the measurement data (B ') of the on-satellite magnetometer in three directions at each interval angle'iX，B′iY，B′iZ) The vector of the magnetic field intensity at that position is
And step 3: calculating the magnetic field intensity generated by the satellite residual magnetic field, wherein the satellite residual magnetic field intensity vector at each interval angle is B ″i＝B′i-BiThe magnitude of the remanent field strength vector of the satellite at the in-satellite magnetometer is then
And 4, step 4: obtaining the magnetic field intensity B of the environment of the satellite in orbit by referring to GJB/Z19-1991' near-earth space magnetic field0If, if
The influence of the satellite residual magnetism on the in-satellite magnetometer can be ignored, otherwise, the satellite layout needs to be adjusted or the whole-satellite magnetism optimization design needs to be carried out, so that the influence of the satellite on the magnetic field of the magnetometer meets the requirement;
wherein B is the magnetic field intensity of the satellite residual magnetism.
2. The method as claimed in claim 1, wherein the measured remanent magnetic field strength B of the satellite is generally less than 2000 nT.
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