A Method for Determining Installation Parameters of Relative Navigation On-orbit Demonstration of Space Non-cooperative Targets

A non-cooperative target and relative navigation technology, which is applied in the field of determination of on-orbit demonstration installation parameters of non-cooperative target relative navigation, can solve the problem that there is no method for determining key parameters of on-orbit tests, and achieve clear constraints and simple determination of initial values , to ensure the effect of observability

Active Publication Date: 2020-04-10
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

Regarding relative navigation of non-cooperative targets, there is no method for determining key parameters for on-orbit testing

Method used

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  • A Method for Determining Installation Parameters of Relative Navigation On-orbit Demonstration of Space Non-cooperative Targets
  • A Method for Determining Installation Parameters of Relative Navigation On-orbit Demonstration of Space Non-cooperative Targets
  • A Method for Determining Installation Parameters of Relative Navigation On-orbit Demonstration of Space Non-cooperative Targets

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Embodiment Construction

[0043] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0044] Such as figure 1 As shown, the present invention provides a method for determining the installation parameters of a space non-cooperative target relative to navigation on-orbit demonstration. The installation separation parameter determination method includes the installation direction offset Δα of the spaceborne target T , the separation initial velocity Δv of the spaceborne target, and the installation deflection angle Δβ of the observation camera, the method includes the following steps:

[0045] (1) Take the center of mass of the observation satellite as the coordinate origin O, the direction of the earth center pointing to the center of mass of the observation satellite is the positive direction of the X-axis, and the normal direction of the flight orbit of the observation satellite is the positive direction of the Z-axis, accordi...

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Abstract

The invention discloses an installation parameter determination method for on-orbit demonstration of relative navigation of a spatial non-cooperative target, which is used for designing installation location and separated pulse of a satellite-borne target and the installation location of an observation camera with the satellite-borne target as an observation object according to the parameters of the observation camera, sensing measurement on the non-cooperative target and observation demand of the relative navigation, thus forming a relative movement orbit of the satellite-borne target relative to an observation satellite, which can satisfy the task demands of the on-orbit demonstration and verification. The method not only can obtain an optimal solution of observation time, but also guarantees observability of the relative navigation task and security of the observation satellite and the satellite-borne target.

Description

technical field [0001] The invention relates to a method for determining installation parameters of a non-cooperative space target relative to navigation on-orbit demonstration, and belongs to the field of satellite orbit design. Background technique [0002] Space non-cooperative targets are characterized by no specific identification, no response device, inability to perform action coordination, and are often in a state of invalid roll. Therefore, determining the location and status of such non-cooperative targets is a prerequisite for on-orbit service. In the on-orbit demonstration and verification test of non-cooperative target perception, measurement and identification, the on-orbit perception and identification system is mainly composed of subsystems such as a stereo vision system, an intelligent perception and identification processing unit, a spaceborne target and a target release mechanism. After the observation satellite releases the spaceborne target, it perceive...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 刘德成邹元杰赵峭王大轶黄美丽史文华史纪鑫周静张磊
Owner BEIJING INST OF SPACECRAFT SYST ENG
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