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An ultra-agile vibration-free space observation system and its method

An observation system and space technology, which is applied in the direction of motor vehicles, space navigation equipment, space navigation aircraft, etc., to avoid micro-vibration and quickly switch.

Active Publication Date: 2017-01-11
BEIJING INST OF SPACECRAFT SYST ENG
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  • Description
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Problems solved by technology

[0003] The technical problem to be solved by the present invention is: to overcome the shortcomings and deficiencies of the existing systems, to propose an ultra-agile and vibration-free space observation system, which solves the problems encountered by high-precision remote sensing satellites in micro-vibration, and the technical solution of the present invention The problem can provide high-precision ground pointing without control parts, effectively avoiding micro-vibrations caused by control parts, and meeting the needs of flexible mobile observation applications and high-precision imaging satellites for pointing accuracy and micro-vibration suppression

Method used

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  • An ultra-agile vibration-free space observation system and its method
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  • An ultra-agile vibration-free space observation system and its method

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Embodiment Construction

[0033] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0034] In one embodiment of the present invention, as figure 1 As shown, an ultra-agile vibration-free space observation system includes a spherical support structure unit, an optically adjustable unit based on a flexible substrate, an omnidirectional photosensitive unit, and an attitude stabilization unit.

[0035]The spherical support structure unit is a V60 fullerene polyhedron structure, which can shrink and expand. The fullerene polyhedron structure includes 60 vertices, 32 faces and 90 edges. The 32 faces include 20 hexagons and 12 pentagons.

[0036] The fullerene polyhedron structure also includes four rigid struts, each rigid strut has the same structure and is a sleeve tubular extension rod, which is formed by nesting coaxial circular tubes of different diameters ,Such as figure 2 As shown, 1 is a sleeve tubular extension rod, a...

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Abstract

The invention relates to a super-agility no-vibration space observation system and method. According to the system and the method, by virtue of an isotropic satellite system overall design, accurate orientation switch and the fast response of multiple scattered targets can be completed through adjusting states of system surface units, so that the flexibility and the observation efficiency are extremely high, and the insufficiency of maneuvering capability and observation efficiency of the current space observation systems can be made up; the thought of the integration of heaven and earth is adopted, and the traditional attitude control is replaced with attitude measurement and determination by virtue of a proposed satellite overall framework, so that micro vibration and the like resulting from control on an execution component are avoided. The super-agility no-vibration space observation system can be applied to the overall design of ultrahigh-precision optical satellites in the future.

Description

technical field [0001] The invention relates to an ultra-agile and vibration-free space observation system, in particular to an ultra-agility, control-free, and vibration-free space observation system, which belongs to the field of overall design of remote sensing satellites. Background technique [0002] With the rapid development of space observation technology, the performance and accuracy of detection instruments carried on satellites are getting higher and higher. In order to achieve high-resolution earth observation, the payload focal length of remote sensing satellites is getting longer and larger, and the aperture is getting larger and larger, which makes the satellites more and more sensitive to micro-vibration, which also restricts the performance improvement of remote sensing satellites. one of the important factors. Due to the various moving parts carried by the satellite (such as high-speed rotating parts such as momentum wheels, stepping parts such as solar wi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/66
Inventor 王倩莹高冀刘勇赵志伟王兴泽
Owner BEIJING INST OF SPACECRAFT SYST ENG
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