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Formation method of satellite distributed load

A distributed and satellite technology, applied in the field of satellite distributed load formation, can solve the problem of low control accuracy

Active Publication Date: 2017-09-22
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to overcome the deficiency of low control precision of existing satellite autonomous formation flight control methods, the present invention provides a formation method of satellite distributed load

Method used

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Embodiment Construction

[0065] refer to Figure 1-5 . The specific steps of the formation method of satellite distributed load of the present invention are as follows:

[0066] Step 1. Determine the position and connection method of each component on the satellite.

[0067]Design the split Stewart drive platform4. The separated Stewart driving platform 4 uses the two oblique interfaces of the cube as the upper and lower platforms, and the six edges of the cube serve as the six legs of the separated Stewart driving platform 4 . Six separate electromagnetic voice coil actuators 2 are used instead of telescopic actuators to control the six-degree-of-freedom motion of distributed loads. Assuming that there are three distributed loads on the satellite, namely the distributed main load 1, the first distributed slave load 3 and the second distributed slave load 6, determine the position of each distributed load on the satellite, separate Stewart drive The platform 4 connects the satellite body 5 with th...

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Abstract

The invention discloses a formation method of satellite distributed loads, and is used to solve the technical problem that an existing satellite autonomous formation flight control method is low in control accuracy. The technical scheme adopted by the invention lies in that based on different task requirements, distributed loads are arranged in different positions of the same satellite; a load formation comprises a master load and a plurality of slave loads; all the loads in the formation cooperatively work together to complete the given task; a separate Stewart drive platform is adopted to connect a satellite body with the loads; separate electromagnetic voice coil actuators instead of retractable legs are used as an actuating mechanism; and the formation of the distributed loads is controlled by the proportional differential (PD) control law. This method can meet the requirements for high accuracy, high stability, ultra-static environment and the like, proposed by a large-aperture optical application system such as distributed optical imaging, and can complete a variety of space tasks; and besides, an actuating mechanism does not consume working mediums, does not cause micro vibration, does not need unloading, and effectively improves the control accuracy of the satellite loads.

Description

technical field [0001] The invention relates to a satellite autonomous formation flight control method, in particular to a satellite distributed load formation method. Background technique [0002] The satellite load formation technology is an emerging technology different from the traditional satellite formation. It refers to arranging distributed loads at different positions on the same satellite, and forming these loads to maintain high-precision relative to a certain main load. position and relative posture to jointly accomplish certain tasks. Distributed optical imaging and other large-aperture optical application systems have put forward requirements for satellite payload formation technology such as high precision, high stability, and hyperstatic environment. [0003] The traditional satellite formation technology, that is, formation of different satellites, generally uses the linearized C-W equation to describe the relative motion between two satellites; when perfor...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/24
CPCB64G1/22B64G1/24B64G1/245
Inventor 刘磊熊敏魏震唐硕
Owner NORTHWESTERN POLYTECHNICAL UNIV
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