Zero momentum magnetic control sun capture device and method of satellite

A technology of sun capture and zero momentum, which is applied to the guidance device of space navigation vehicle, the power supply system of space navigation vehicle, etc., can solve the problems of increasing the complexity of the control system, low maturity, and high power consumption of the flywheel. The effect of data processing, simplifying stand-alone configuration, and saving onboard resources

Active Publication Date: 2014-10-15
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology

[0003] The disadvantage of the existing technology is: using thrusters in the rate damping stage, although the purpose of fast derotation can be achieved, but the thrusters used on satellites are expensive and not mature, which not only increases the complexity of the control system , and there are

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  • Zero momentum magnetic control sun capture device and method of satellite
  • Zero momentum magnetic control sun capture device and method of satellite
  • Zero momentum magnetic control sun capture device and method of satellite

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Embodiment Construction

[0012] The specific implementation of a satellite zero-momentum magnetron sun capture device and method provided by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0013] see figure 1 , a structure diagram of the satellite zero-momentum magnetron sun capture device described in the present invention. The device includes: a 0-1 solar sensor 12 , a magnetometer 14 and a magnetic torquer 16 .

[0014] The 0-1 sun sensor 12 cooperates with the magnetometer 14 for satellite attitude measurement. Wherein, when the sun sensor 12 of the 0-1 formula judges that the sun appears in its field of view, a two-vector attitude determination FORM algorithm is adopted to determine the three-dimensional position of the satellite through the sun sensor 12 of the 0-1 formula and the magnetometer 14. Axis attitude array; when the 0-1 type sun sensor 12 judges that the satellite enters the shadow area, the satellite pitch angle is determined...

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Abstract

The invention discloses a zero momentum magnetic control sun capture device and method of a satellite. The device comprises a 0-1 type sun sensor, a magnetometer and a magnetic torquer, wherein the 0-1 type sun sensor and the magnetometer are matched, and are used for performing satellite attitude measurement; the output of the magnetic torquer acts on the satellite body after delay, and is used for providing control moment for the satellite in the satellite rate damping process and controlling the attitude angle deviation to be less than a preset threshold value, so as to realize zero momentum magnetic control sun capture; when the 0-1 type sun sensor judges that the sun appears in the field of view, the double-vector attitude determination FORM algorithm is adopted, and a three-axis attitude matrix of the satellite is determined through the 0-1 type sun sensor and the magnetometer; when the 0-1 type sun sensor judges that the satellite enters the shadow zone, the satellite elevation angle is determined through the magnetometer. According to the zero momentum magnetic control sun capture device and method, the single machine configuration of the control system is simplified, the reliability of an attitude control subsystem is improved, and the resources on the satellite are saved.

Description

technical field [0001] The invention relates to the technical field of aerospace measurement and control, in particular to a zero-momentum magnetically controlled sun capture device and method suitable for microsatellites. Background technique [0002] At present, in order to achieve the purpose of rapid derotation during the orbiting stage and safety mode, the satellites mostly use thrusters or magnetic torque control methods to achieve three-axis large angular velocity rate damping. When the three-axis angular velocity of the satellite decreases to the preset threshold, the star sensor is introduced as the attitude sensor, and the reaction flywheel group is used as the actuator, and the three-axis wheel control is used to make the normal line of the satellite sail point to the sun, so as to realize the sun capture and ensure the safety of the satellite. energy supply. [0003] The disadvantage of the existing technology is: using thrusters in the rate damping stage, altho...

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Application Information

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IPC IPC(8): B64G1/44B64G1/24B64G1/36
Inventor 刘爽李东万松吴子轶李晓红阳应权
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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