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Method for determining initial orbit of spatial target under constraint of virtual coplanar condition

A technique for determining spatial objects and methods, which is applied in the interpretation of photos, etc., and can solve problems such as joint adjustment of multi-frame images that cannot realize the calculation of spatial object positions

Active Publication Date: 2019-04-12
SUZHOU ZHONGKE IMAGE SKY REMOTE SENSING TECH CO LTD
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Problems solved by technology

[0003] In the process of space target detection, the observation platform and the space target move at the same time, so the joint adjustment of multi-frame images based on the traditional photogrammetry method cannot realize the position calculation of the space target

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  • Method for determining initial orbit of spatial target under constraint of virtual coplanar condition
  • Method for determining initial orbit of spatial target under constraint of virtual coplanar condition
  • Method for determining initial orbit of spatial target under constraint of virtual coplanar condition

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Embodiment Construction

[0064] The present invention will be further clarified below in conjunction with the drawings and specific embodiments. The described embodiments of the present invention are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

[0065] The invention establishes an observation platform motion compensation algorithm based on affine transformation, and constructs a static virtual coplanar condition observation model and a space-time domain joint initial orbit algorithm supported by geometric and dynamic theories.

[0066] The method for determining the initial orbit of a space target under the constraint of virtual coplanarity according to the present invention includes the following steps:

[0067] Step A: Use the six-parameter affine transformatio...

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Abstract

The invention discloses a method for determining an initial orbit of a spatial target under the constraint of a virtual coplanar condition, and belongs to the field of surveying and mapping science and technology. The method comprises the steps of extracting a fixed star trail equation based on a star map, and carrying out motion compensation on an observation platform by utilizing a six-parameteraffine transformation model to acquire image plane coordinates of a target star under a virtual static observation condition; by utilizing an imaging geometrical relationship between the observationplatform and the target star which are coplanar under the virtual static observation condition, building a virtual static coplanar condition observation model, and calculating a spatial position of the target star; and establishing a time-space domain combined initial orbit determination algorithm, and calculating the number of target orbits. The virtual static coplanar condition observation modelconverts the "dynamic-to-dynamic" orbit estimation problem into the "static-to-dynamic" satellite dynamic photography measurement problem, and solves the difficult problem of no distance measuring data in detection of a space-based visible light camera (SBV).

Description

Technical field [0001] The invention belongs to the technical field of photogrammetry, and particularly relates to a method for determining the initial orbit of a space target under virtual coplanar conditions. Background technique [0002] After years of development, space target in-orbit measurement has formed a complete and effective theoretical system. The in-orbit measurement of space targets using angle observation information is divided into initial orbit determination and orbit improvement. The initial orbit determination of two-body dynamics constraints mainly includes Gaussian method, Laplace method and double-r iteration method, based on perturbation theory The main improvements of the track include least square method and filtering method. Orbit calculation is regarded as a deterministic problem, but the initial epoch orbit element number is required to obtain the relative distance between the observation platform and the space target, and then the orbit element numb...

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Application Information

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IPC IPC(8): G01C11/04
CPCG01C11/04
Inventor 盛庆红杨锐王博肖晖洪然
Owner SUZHOU ZHONGKE IMAGE SKY REMOTE SENSING TECH CO LTD
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