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Satellite composite formation method

A satellite and center satellite technology, applied in the field of satellite composite formation, can solve the problem of low control precision, achieve high control precision, and improve the effect of formation precision

Active Publication Date: 2020-02-14
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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Problems solved by technology

[0005] In order to overcome the deficiency of low control accuracy of the existing satellite autonomous formation flight control method, the present invention provides a satellite composite formation method

Method used

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Embodiment Construction

[0032] refer to Figure 1-6 . The composite satellite formation method of the present invention takes the formation flight of two satellites relative to the center satellite as an example, and a separate active vibration isolation and control system 7 is designed between the satellite body and the load, through the first separate electromagnetic force actuator 10-eighth Separate electromagnetic force actuator 17 is connected. Specific steps are as follows:

[0033] Step 1. Design the separate active vibration isolation and control system between the satellite body and the payload. The system is composed of 8 separate electromagnetic force actuators. The payload is driven by the cooperation of the actuators to realize the fine formation of the payload. control.

[0034] The satellite body and the payload are connected by 8 separate electromagnetic force actuators. Taking the first formation satellite as an example, the first separated electromagnetic force actuator 10-the f...

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Abstract

The invention discloses a satellite composite formation method which is used for solving the technical problem that an existing satellite autonomous formation flight control method is low in control precision. According to the technical scheme, a separating-type active vibration isolation and controlling system is designed between each satellite body and a corresponding load, the satellite body and the load are regarded as fixed connection, the conventional formation method is adopted to conduct rough formation on satellite groups, aiming at the problem of control of master-slave formation satellite postures and orbits, a satellite six-degree-of-freedom relative motion model is established, and a micro-thruster is used for adjusting the postures and the orbits to maintain relative motion between formation satellites by measuring the relative postures and relative positions between the formation satellites. A dynamic model of a single load is established, three-axis control force and three-axis control torque are generated through cooperated using of eight separated type electromagnetic force actuators, and six-degree-of-freedom precise control is conducted on the loads to realize the high-precision composite formation between the satellite loads.

Description

technical field [0001] The invention relates to a satellite autonomous formation flight control method, in particular to a satellite compound formation method. Background technique [0002] In recent years, with the increasing complexity of satellite functions and the increase of antenna and optical load apertures, the cost and difficulty of development have increased sharply, and the risk of development has also increased, and the functions and performance indicators of a single satellite are limited. Therefore, the use of small satellites Formation flight cooperative work has become an important research direction, and its applications in electronic reconnaissance, positioning imaging, and meteorological observation are becoming more and more extensive. On the other hand, the formation flying satellite super-large-aperture observation tasks and high-resolution execution tasks have higher and higher requirements for formation accuracy and stability. [0003] The traditiona...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10B64G1/24G05D1/10
Inventor 刘磊李青唐硕
Owner NORTHWESTERN POLYTECHNICAL UNIV
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