A Method for Rapid Attitude Maneuvering Control of Agile Small Satellites
A satellite attitude and control method technology, applied in the aerospace field, can solve problems such as high control difficulty, low stability, and poor agility, and achieve the effects of low control difficulty, reduced difficulty, and improved agility and stability
Active Publication Date: 2019-05-24
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology
[0005] In order to solve the problems of high control difficulty, poor agility and low stability existing in the existing actuators, the present invention provides a rapid maneuvering control method for the attitude of an agile small satellite
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specific Embodiment approach 1
[0042] Taking a certain satellite as an example, in the task of using four high-torque flywheels and four reaction flywheels at the same time, during maneuvering, the high-torque flywheels on the X-axis and Y-axis and the reaction flywheels on the corresponding axes provide control torque at the same time. After the end, use the reaction flywheel on the corresponding shaft to absorb the angular momentum of the high-torque flywheel, and give the high-torque flywheel a zero-speed command to keep the high-torque flywheel at zero speed, but it will not be powered off.
[0043] In the three-axis stable push-broom mission over the ground, the angular momentum absorbed by the reaction flywheel after the maneuver is completed is simulated and analyzed.
[0044] After the maneuver is over, at the designed time, the reaction flywheel on the corresponding axis begins to absorb the angular momentum of the high-moment flywheel, and the high-moment flywheel outputs a reverse torque of a cert...
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The invention discloses an agile small satellite attitude quick maneuvering control method, and relates to the aerospace field. The method includes that: the moment output directional included anglesof a first counteractive flywheel, a second counteractive flywheel, and a third counteractive fly wheel are 90 degrees; the included angle of a fourth counteractive flywheel is identical to that of the first counteractive flywheel, the second counteractive flywheel, and the third counteractive flywheel; the moment output directional included angles of a first large moment flywheel, a second largemoment flywheel and a third large moment flywheel are 90 degrees; the included angle of a fourth large moment flywheel is identical to the first large moment flywheel, the second large moment flywheeland the third large moment flywheel; moment output directions of the first counteractive flywheel and the first large moment flywheel are parallel and opposite to each other, and so on; the flywheelsare started to output moment in the same direction; the large moment flywheels output moment in the opposite direction after it is determined that a designated attitude is achieved; the counteractiveflywheels output despun moment and control moment; it is determined if an absolute value of the rotation speed of the large moment flywheels decreases within 10 rpm or not; the large moment flywheelsstop outputting moment, the counteractive flywheels output attitude control moment. The agile small satellite attitude quick maneuvering control method is low in control difficulty and is high in agility and stability.
Description
technical field [0001] The invention relates to the field of aerospace technology, in particular to a rapid maneuvering control method for the attitude of an agile small satellite. Background technique [0002] With the development of satellite technology and the continuous enhancement of video and imaging functions, higher requirements are put forward for the attitude control of satellites, and improving the agility of satellites has become the focus of research in this field. [0003] The configuration and use strategy of satellite attitude control actuators are the basic links of control design. The existing attitude control actuators for small satellites are composed of a flywheel and a magnetic torquer. The advantage of this configuration is that the output torque of the flywheel is fine, the control stability is good, and the precision is high. At the same time, the magnetic torquer is used to smoothly unload the accumulated angular momentum of the flywheel; the disadv...
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IPC IPC(8): B64G1/28B64G1/24
Inventor 徐开刘萌萌张晓磊钟兴张雷戴路陈志刚李峰范林东
Owner CHANGGUANG SATELLITE TECH CO LTD