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A double-hysteresis-loop method for synthesizing angular momentum of a satellite by using a magnetic torquer to unload satellites

A magnetic torque device and synthetic angle technology, applied in the field of double hysteresis, can solve problems such as satellite attitude angle and angular velocity fluctuations, frequent switching of magnetic control voltage, and adverse effects of satellite high-stability control, so as to reduce the impact and solve the problems of spacecraft The effect of attitude angular velocity fluctuation

Active Publication Date: 2020-11-20
BEIJING INST OF CONTROL ENG
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Problems solved by technology

The traditional magnetic unloading generally calculates the magnetron voltage according to the angular momentum accumulation of the satellite, but when the unloading condition is just met, the magnetron voltage will switch frequently. At this time, the magnetron torque will cause the satellite attitude angle and angular velocity to fluctuate. Harmful effect on the high stability control of the satellite

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  • A double-hysteresis-loop method for synthesizing angular momentum of a satellite by using a magnetic torquer to unload satellites
  • A double-hysteresis-loop method for synthesizing angular momentum of a satellite by using a magnetic torquer to unload satellites
  • A double-hysteresis-loop method for synthesizing angular momentum of a satellite by using a magnetic torquer to unload satellites

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Embodiment

[0062] The present invention is described in detail below:

[0063] It is assumed to be running in a sun-synchronous orbit with an orbital altitude of about 500km and an inclination of 97°. The satellite is equipped with three sets with a maximum magnetic moment of Mmlf=200Am 2 The magnetic torque device, such as Figure 1-5 shown;

[0064] (1) According to the geographical location of the satellite, calculate the magnetic field B of the space environment where the satellite is located b ;

[0065] Assuming that the current geographic location of the satellite is 94° east longitude, 0.03° north latitude, and a height of 492km, the three-axis components of the environmental magnetic field strength in the body coordinate system are

[0066] Time t1:

[0067] B b =[-3.0084979825743828e-005,5.9109881461567932e-006,-8.4364482182156017e-006]nT.

[0068] Time t2:

[0069] B b =[-6.8490665271550280e-007,1.0552072686590731e-005,-4.2079269982111809e-005]nT.

[0070] (2) Calcul...

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Abstract

The invention relates to a double hysteresis method for unloading resultant angular momentum of a satellite through a magnetic torquer, and belongs to the technical field of satellite attitude control. According to the double hysteresis method, aiming at solving the problem of frequent switching of magnetic control voltage near a track arc segment exactly meeting the unloading condition in the geomagnetic field direction of magnetic unloading and aiming at the angular momentum error, the geomagnetic field vector and the angular momentum error vector included angle, a double hysteresis unloading strategy is introduced, finally, the unloading voltage is subjected to filter smoothing and then is output, the influence of magnetic control torque on the satellite attitude stability is effectively lowered, and high-stability attitude control over the satellite is achieved. Compared with a traditional magnetic unloading method, by adopting the double hysteresis method, fluctuation of the satellite attitude angle and the angular velocity caused by the magnetic control torque can be reduced, and the adverse effect of magnetic unloading on the satellite attitude stability is effectively overcome.

Description

technical field [0001] The invention relates to a double hysteresis loop method for synthesizing angular momentum of a satellite by using a magnetic torque device to unload satellites, and belongs to the technical field of satellite attitude control. Background technique [0002] During the flight of the satellite in orbit, it will be affected by various environmental disturbances, which will cause deviations in the attitude angle and angular velocity of the satellite. In order to maintain the stability of the satellite's three-axis attitude, contemporary satellites generally use a momentum wheel equiangular momentum exchange device to convert the interference of the external environment on the satellite attitude into angular momentum and store it in the momentum wheel. When the angular momentum reaches a certain level, the magnetic force will be activated. The torquer generates the magnetic unloading torque to unload the angular momentum of the momentum wheel, which is the ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/36
CPCB64G1/366
Inventor 陆栋宁王淑一雷拥军顾斌刘洁田科丰傅秀涛
Owner BEIJING INST OF CONTROL ENG
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