Multi-stage attitude control method for remote sensing micro-nano satellite

A technology for attitude control and micro-nano satellites, which is applied in the direction of space navigation vehicle guidance devices, etc., and can solve the problems of not considering satellites, not considering the cooperative work of multiple attitude control execution components, etc.

Active Publication Date: 2019-05-31
TSINGHUA UNIV
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Problems solved by technology

[0004] In the above-mentioned existing attitude control methods of micro-satellites, the different control methods of the satellite in different stages and the control methods of the maneuvering process between stages are not considered, and only one control strategy of the attitude control execution unit is adopted, and the multiple control methods are not considered. Collaborative work between individual attitude control executive components

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Embodiment Construction

[0070] The present invention proposes a multi-stage attitude control method for remote sensing micro-nano satellites, which will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0071] In one embodiment of the method of the present invention, the whole star mass of the micro-nano satellite is set to be 38.5kg, and the three-axis moment of inertia is 1.43kg·m on the X axis 2 ; Y-axis 1.76kg m 2 ; Z-axis 2.43kg m 2 . Set the lens of the remote sensing imaging camera to point in the same direction as the Z-axis of the satellite. In the attitude execution part, the momentum wheel set consists of three formally mounted three-axis integrated momentum wheels and one obliquely mounted momentum wheel, and the moment of inertia of each axis is 1.1318×10-4kg·m 2 , the maximum speed is greater than 7000rpm, the speed control error is less than 3rpm (3σ), the maximum output torque is greater than 2mNm; the three-axis magnetic...

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Abstract

The invention relates to a multi-stage attitude control method for a remote sensing micro-nano satellite, and belongs to the technical field of spacecraft attitude control. A three-axis magnetic moment device and a momentum wheel set are adopted as an attitude control execution component, and the attitude control method for the four main stages of recemization after satellite-rocket separation, counterglow capture, counterglow orientation and counter-earth remote sensing is designed, and an attitude mobile control method for the two stages of counterglow orientation and counter-earth remote sensing is designed. According to the recemization stage, the large angular rate of the satellite obtained after satellite-rocket separation is eliminated, and the basic controlled attitude is built; inthe counterglow capture and counterglow orientation stages, it is ensured that a sun sailboard is in the charging state for a long time; in the counter-earth remote sensing stage, it is ensured thatthe remote sensing photographing task is completed. According to the method, traditional PD control is adopted as the foundation, on the basis of feedforward control, quaternion is used for representing attitude errors, the method has the advantages of being rapid in satellite maneuvering response, high in steady state robustness and high in control precision, and the task requirement for a remotesensing micro-nano satellite is met.

Description

technical field [0001] The invention relates to a multi-stage attitude control method for remote sensing micro-nano satellites, belonging to the technical field of spacecraft attitude control. Background technique [0002] For satellites used as remote sensing payload platforms, during non-remote sensing imaging missions, it is necessary to keep the solar panels facing the sun stably to ensure energy supply on the planet; during remote sensing imaging missions, in order to obtain high-resolution remote sensing images, it is necessary to maintain High-precision and stable satellite attitude; at the same time, due to the relatively short time of the remote sensing imaging task, the satellite needs to have the ability to quickly maneuver the attitude to perform attitude conversion during different mission periods. Therefore, it is very necessary to accurately control the attitude of the satellite. [0003] In 2005, Yu Yong and other researchers proposed a micro-satellite attit...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/28B64G1/36
Inventor 孟子阳廖茂有袁斌文尤政
Owner TSINGHUA UNIV
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