Feature Recognition Method for Space High Orbit Small Size Target Based on Photometric Curve

A technology of target features and photometric curves, applied in the direction of optical device exploration, etc., can solve the problems affecting target feature recognition, effective estimation of light pressure terms, and difficulty in effectively estimating target position and speed, so as to ensure effective identification capabilities and avoid difficult convergence. , to ensure the effect of convergence ability

Active Publication Date: 2019-10-11
XI AN JIAOTONG UNIV
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0005] The original method for high-orbit target feature recognition is based on the kinematics model, and the light pressure term is very important to the performance of the algorithm, but the light pressure term has a weak influence on the target orbit and attitude in the dynamic characteristics of the target, and in the It is difficult to reflect its impact on the target trajectory and attitude in a short period of time. For this real-time recursive algorithm, it is difficult to effectively estimate this light pressure item, which makes it difficult to effectively estimate the position and velocity of the target, which in turn affects the accuracy of the target. identification of features

Method used

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  • Feature Recognition Method for Space High Orbit Small Size Target Based on Photometric Curve
  • Feature Recognition Method for Space High Orbit Small Size Target Based on Photometric Curve
  • Feature Recognition Method for Space High Orbit Small Size Target Based on Photometric Curve

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Embodiment 1

[0093] The present invention is further described in conjunction with a specific example of the shape recognition of a quadrangular prism satellite, and the fast convergence of the feature recognition algorithm for space high-orbit small-size targets based on photometric curves is realized. The basic simulation environment is set as follows: the target is a satellite in geosynchronous orbit, the orbital inclination is 30°, and the satellite is at 120° longitude; Ease of availability data, other data are given by STK. In addition to the need to change the corresponding parameters related to the design of the model set, the area of ​​each surface is generally 60m 2 ; diff = 0.4, R spec = 0.5. The start time of the simulation is 05:00:00UT on May 22, 2015, and the end time of the simulation is 07:00:00UT on May 22, 2015.

[0094] According to the algorithm of the present invention, the steps of feature recognition are as follows:

[0095] The first step is to calculate the p...

Embodiment 2

[0119] Size estimate:

[0120] The estimation of different sizes under the same shape model is realized by the multi-model adaptive estimation method, so the design of the model set is about the design of the size parameters, and other parameters are consistent with the single model. The shape is selected as a quadrangular prism, and each model set is composed of 5 possible sizes. The size parameter is represented by the area of ​​the six faces in the shape. The real model is A=[6060 60 60 60 60], which will consider the real model contained in Model focus.

[0121] The real model contained in the model set is designed as:

[0122] Model 1: A=[60 60 60 60 60 60]

[0123] Model 2: A=[60 60 120 60 120 60]

[0124] Model 3: A=[60 60 60 120 60 120]

[0125] Model 4: A=[30 30 30 30 30 30]

[0126] Model 5: A=[120 120 120 120 120 120]

[0127] In the simulation, the photometric data comes from model 1, that is, model 1 is the real model; Image 6 are the angular velocity esti...

Embodiment 3

[0129] Material parameter estimation:

[0130] The estimation of the material parameters under the same shape model is realized by the multi-model adaptive estimation method, so the design of the model set is about the design of the material parameters, and other parameters are consistent with the single model. The shape model is selected as a quadrangular prism shape, and 5 size models are designed for the model set. Because the A-S model is selected for measurement and modeling in this paper, the material parameters are selected from the parameters in the A-S model. Here, n is selected. v and n u Perform model set design.

[0131] Model 1: n u =[10 10 10 10 10 10], n v =[10 10 10 10 10 10]

[0132] Model two: n u =[10 10 10 10 10 10], n v =[5 5 5 5 5 5]

[0133] Model three: n u = [5 5 5 5 5 5], n v =[10 10 10 10 10 10]

[0134] Model four: n u = [5 5 5 5 5 5], n v =[5 5 5 5 5 5]

[0135] Model five: n u = [20 20 20 20 20 20], n v =[5 5 5 5 5 5]

[0136] In t...

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Abstract

The invention discloses a luminosity-curve-based real-time online characteristic recognition method for a spatial high-orbit small-sized target so that problems of spatial high-orbit target characteristic recognition and motion estimation can be solved and a defect that the existing method can not be converged under luminosity observation can be overcome. On the basis of analyses of the dynamic characteristics and luminosity observation data characteristics of a high-orbit target, a novel idea for characteristic recognition is realized by combining the attitude estimation of the target. The method is a parallel fusion algorithm established based on a target attitude kinematics model, so that the convergence and convergence speed of the algorithm are ensured; and characteristics of the target shape, the dimension, and the material parameter and the like can be identified effectively. The method is established based on a multi-model hybrid estimation framework; and the target attitude estimation and characteristic recognition are realized synchronously in an optimized manner.

Description

technical field [0001] The invention belongs to the field of optical observation target feature recognition, relates to a method for space high-orbit spacecraft feature recognition, in particular to a real-time and optimal convergence method for space high-orbit small-size target feature recognition and motion estimation based on photometric curves. Background technique [0002] Space high-orbit small-size targets refer to high-orbit spacecraft, and their feature recognition is one of the difficulties and key points of space situational awareness, such as the feature recognition of space non-cooperative targets, the feature acquisition of space failure or abnormal cooperative targets and diagnosis. The difficulty is that the target is small in size and tens of thousands of kilometers away from the ground. Commonly used radars are limited by detection capabilities and noise, and cannot detect high-orbit targets; optical sensors cannot obtain target images due to the limitatio...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01V8/10
Inventor 梁勇奇单斌
Owner XI AN JIAOTONG UNIV
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