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Dual-satellite formation only-ranging relative navigation method

A relative navigation and dual-star technology, which is applied to combined navigators, navigation calculation tools, etc., and can solve the problems of complex operation, low observability, and low security.

Active Publication Date: 2018-11-30
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Therefore, in the existing technology, the dual-star formation only needs relative navigation by distance measurement, and requires satellite platform orbital maneuvering or multiple receivers to coordinate measurement to complete relative navigation. Low sex

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  • Dual-satellite formation only-ranging relative navigation method
  • Dual-satellite formation only-ranging relative navigation method
  • Dual-satellite formation only-ranging relative navigation method

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Embodiment Construction

[0043] The present invention will be further described in detail below in conjunction with specific embodiments, which are explanations of the present invention rather than limitations.

[0044] The present invention is a dual-star formation-only ranging-only relative navigation method, aiming at the current implementation of the dual-star formation-only distance-angle relative navigation method, it is necessary to use multiple data link antennas to coordinate measurement methods or satellite platforms to maneuver through special orbits to solve the problem of only ranging The problem of state ambiguity in relative navigation; the proposed method is assisted by attitude maneuvering, and the communication antenna is installed eccentrically through the spaceborne data link to achieve relative navigation only from distance measurement, which can be applied to short-range relative navigation of double-satellite formations.

[0045] The present invention takes the double-star format...

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Abstract

The invention relates to a dual-satellite formation only-ranging relative navigation method. The dual-satellite formation only-ranging relative navigation method can only rely on off-mass-center installation and attitude maneuvering assistance of an antenna receiver to realize dual-satellite formation autonomous relative navigation without special orbit maneuvering of satellites or increase of on-board data link receiving antennas. Relative orbital evolution is performed by use of a relative orbital motion equation of dual satellites in the dual-satellite formation as a navigational state equation, and dual-satellite formation only-ranging relative navigation can be completed by use of an iterative algorithm to solve relative position and relative velocity according to relative distance information measured by the on-board data link receiving antenna receiver installed in the manner of deviated from centers of mass of the satellites. By introducing of the eccentricity effect of the antenna receiver installed in the manner deviated from the centers of mass of the satellites, the observable ability of the only-ranging relative navigation solution is obtained. The attitude maneuveringassistance is used to improve the observability, and the relative position and the velocity are obtained by the iterative solution method.

Description

technical field [0001] The invention belongs to the field of space autonomous relative navigation, and relates to a relative navigation method for a double-star formation only for distance measurement. Background technique [0002] With the development of space technology and the deteriorating space environment, the complexity of space missions is increasing. A large part of the tasks that can be completed by a single expensive and precise satellite in the past will be gradually replaced by distributed satellite systems due to problems such as high cost, long development cycle, poor maintainability, and limited working life. [0003] One of the important links in the work of the distributed satellite system is satellite formation flight, and high-precision relative navigation is the key premise of formation flight. The commonly used microwave radar can only be installed and used on large spacecraft such as spacecraft because of its complex system, high cost, and huge energy...

Claims

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Application Information

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IPC IPC(8): G01C21/20G01C21/24
CPCG01C21/20G01C21/24
Inventor 龚柏春李爽赵吉松施俊杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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