CN103075971A - Length measuring method of space target main body - Google Patents

Abstract

The invention belongs to the intersecting field of the space technology and the computer vision and particularly relates to a length measuring method of a space target main body. The method is particularly applied to the length measurement of space satellites. According to the method, the rail number of a space target is utilized for carrying out simulation in an STK (satellite tool kit), and a coordinate of the space target is obtained; then, the side projection length of the space target is obtained according to the coordinate of the space target and the coordinate of an observation station; and finally, the relative positions of the observation station, the space target and the geocenter are used as the bases, and the practical length of the satellite main body is obtained. The method has the advantages that the STK simulation software is combined, and the length (the error is smaller than 8 percent) of the space target main body can be accurately calculated, so the performance and the efficiency of a foundation observing system on the space target observation are improved.

Description

A kind of extraterrestrial target modal length measuring method

Technical field

The invention belongs to spationautics and computer vision crossing domain, be specifically related to the method that a kind of extraterrestrial target modal length is measured, the method is particularly useful for the linear measure longimetry of Aerospace Satellite main body.

Background technology

The spacefaring nations such as the U.S., Russia, European Union have been launched a large amount of reconnaissance satellites, telstar, HA Global Positioning Satellite etc., and China's national security is consisted of great threat.Non-collaborative space satellite is carried out ground photoelectricity observe, analyze and study its structure and function, have important military value.The function of extraterrestrial target can be estimated by its Structure Deduction, and therefore obtaining good spatial target images and rebuild its three-dimensional structure is the only way that achieves the above object.Because the spatial resolution limitations of ground telescopic system, atmospheric environment are on also existing the impact of atmospheric turbulence in the random disturbance of long-reach optics imaging and the imaging process, so that the ground based sensor obtains the image quality degradation, cause the quality of image can not satisfy the basic demand that structure detailed survey, function are differentiated.Therefore, must carry out the research that is intended to improve image quality, SUPERRESOLUTION PROCESSING FOR ACOUSTIC and three-dimensional rebuilding method, implicit information in the sequence image that extraction feature, the telescopic system that undermines obtain improves the ground based observa tion system to performance and the usefulness of Space-objects Observation.

Summary of the invention

The object of the present invention is to provide a kind of extraterrestrial target modal length measuring method, the method is utilized the size of the image information measurement space target subject of extraterrestrial target to be measured.

A kind of extraterrestrial target modal length measuring method provided by the invention comprises the steps:

(1) image by the extraterrestrial target to be measured of inputting is to obtain constantly t of target imaging in the testing image;

(2) obtain the orbital tracking of this extraterrestrial target according to the types index of extraterrestrial target;

(3) testing image is carried out pre-service, comprise image denoising and image rectification;

(4) obtain the constantly locus coordinate (x of t of extraterrestrial target _t, y _t, z _t);

(5) the size L of computer memory target subject lateral projection in the space, unit are rice;

(6) the physical length l of computer memory target, unit are rice:

$l=\frac{L}{\cos \mathrm{\α}}$

Wherein, $\cos \mathrm{\α}=\frac{h_1^2+h_2^2-h_3^2}{2h_1{h}_2}$

$h_1=\sqrt{{(x_t-x_m)}^2+{(y_t-y_m)}^2+{(z_t-z_m)}^2}$

$h_2=\sqrt{x_t^2+y_t^2+z_t^2}$

$h_3=\sqrt{x_m^2+y_m^2+z_m^2}.$

The inventive method mainly is to carry out the length analysis for the main body of extraterrestrial target, utilizes orbital tracking emulation in STK of extraterrestrial target to obtain the coordinate of extraterrestrial target; Then obtain lateral projection's length of extraterrestrial target according to the coordinate of the coordinate of extraterrestrial target and research station; With the research station, extraterrestrial target and the earth's core three's relative position is the basis at last, obtains the physical length of satellite main body.The inventive method can calculate the length (its error is less than 8%) of extraterrestrial target main body more accurately in conjunction with the STK simulation software, thereby improves the ground based observa tion system to performance and the usefulness of Space-objects Observation.

Description of drawings

Fig. 1 is that the modal length of extraterrestrial target of the present invention is measured basic flow sheet;

Fig. 2 is STK secondary development process flow diagram;

Fig. 3 is STK scene track simulation software synoptic diagram;

Fig. 4 is the survey projection size measuring principle figure of extraterrestrial target main body;

Fig. 5 is the physical length instrumentation plan of extraterrestrial target main body;

Fig. 6, Fig. 9, Figure 12 are figure degraded images of Heavenly Palace of real scene shooting;

Fig. 7, Figure 10, Figure 13 are the images of Heavenly Palace after proofreading and correct;

Fig. 8, Figure 11, Figure 14 are a modal length measurement result of Heavenly Palace figure;

Figure 15, Figure 18, Figure 21 are long bent No. 3 degraded images of real scene shooting;

Figure 16, Figure 19, Figure 22 are long bent No. 3 images after proofreading and correct;

Figure 17, Figure 20, Figure 23 are long bent No. 3 modal length measurement result figure.

Embodiment

Below in conjunction with accompanying drawing the specific embodiment of the present invention is described further.Need to prove at this, understand the present invention for the explanation of these embodiments for helping, but do not consist of limitation of the invention.In addition, below in each embodiment of described the present invention involved technical characterictic just can mutually not make up as long as consist of each other conflict.

The present invention mainly tells about the linear measure longimetry of extraterrestrial target main body, and the below illustrates the specific implementation step of the inventive method take Aerospace Satellite as example in conjunction with Fig. 1:

(1) obtains constantly t of target imaging in the testing image by input.

Testing image is the image of extraterrestrial target to be measured, in the photographed data form according to testing image, directly reads constantly t of target imaging.

(2) obtain the orbital tracking of additional space target according to type index from track database of extraterrestrial target;

Track database is the database of setting up as index take the type of extraterrestrial target, and this database mainly comprises two attributes, and major key is the type of extraterrestrial target, and another attribute is orbital tracking.The query function of employing database can obtain the orbital tracking of this extraterrestrial target.

Orbital tracking can be passed through STK simulation software (the satellite kit software of U.S. Analytical Graphics company exploitation, its secondary development flow process is as shown in Figure 2) carry out simulating, verifying, and simulation track imaging results and actual photographed result compared, with the validity of Orbit track data.

Simulate it in the rail scene such as lacrosse 3 (25017) in the orbital tracking on January 24th, 2010, orbital tracking is as follows:

125017U 10024.00000000 .00000088 00000-0 50662-5 0 000002 25017 57.0107 253.9158 0003558 93.2642 181.9245 14.7160839100000

The position of land station is: 100.1 ° of longitudes, 26.6 ° in latitude, 3000 meters of height.Scene track simulation result as shown in Figure 3.

(3) testing image of input carried out pre-service;

Extraterrestrial target imaging measurement data noise is very large, signal to noise ratio (S/N ratio) is low, and fuzzy serious.Therefore before imaging data is carried out subsequent treatment, must at first carry out pre-service to imaging data, namely at first imaging data is carried out denoising, subsequently for the characteristics of imaging data, utilize effective correcting algorithm that spatial target images is carried out the image Recovery processing.Algorithm kind for the preconditioning technique of measuring image has a lot, mainly comprises denoise algorithm and correcting algorithm.Wherein, denoise algorithm remove picture noise, thereby noise decrease is on the impact of correcting algorithm by setting up the spatial target images noise model.

Locus coordinate (x when (4) obtaining extraterrestrial target moment t _t, y _t, z _t);

According to the orbital tracking that (2) obtain, utilize STK simulation software simulation space aim in the rail scene, each position coordinates constantly of derived space target therefrom obtains t locus coordinate (x constantly _t, y _t, z _t).

(5) the size L of computer memory target subject lateral projection in the space;

Obtain the pixel length n of target subject from testing image, utilize the constantly volume coordinate (x of extraterrestrial target of t that step (4) obtains _t, y _t, z _t) and known research station position coordinates (x _m, y _m, z _m) calculate extraterrestrial target t size L of lateral projection constantly in the space.

Among Fig. 4, R represents that t moment extraterrestrial target to the distance of research station, is $R=\sqrt{{(x_t-x_m)}^2+{(y_t-y_m)}^2+{(z_t-z_m)}^2},$ Unit is rice, and β represents the pixel angle of testing image, and the value of β is determined by taking the camera attribute.

As required, we will obtain the pixel length n of target subject from testing image, in conjunction with the distance R of t moment extraterrestrial target to the research station, measure according to following size computing formula again.

The size L of estimation extraterrestrial target main body lateral projection in the space, unit are rice:

$L=\frac{n\×\mathrm{\β}\×\mathrm{\π}\×R\×1000}{3600\×180}$

(6) according to extraterrestrial target, the space geometry in research station and the earth's core relation, the length l of calculating real space target.

Because the main body place axis of extraterrestrial target is always vertical with the earth's core, can provide the synoptic diagram of instrumented satellite modal length by such priori, as shown in Figure 5.

In the satellite main body, the research station, in the triangle that ground is formed centrally, can calculate:

$\cos \mathrm{\α}=\frac{h_1^2+h_2^2-h_3^2}{{2h}_1{h}_2}$

Wherein: $h_1=\sqrt{{(x_t-x_m)}^2+{(y_t-y_m)}^2+{(z_t-z_m)}^2}$

$h_2=\sqrt{x_t^2+y_t^2+z_t^2}$

$h_3=\sqrt{x_m^2+y_m^2+z_m^2}$

In satellite main body imaging surface, have:

lcosα＝L

Namely get the size l estimation of satellite main body orthogonal projection:

$l=\frac{L}{\cos \mathrm{\α}}$

In the imaging surface of satellite, L can obtain according to above-mentioned formula, finally tries to achieve the length l of satellite main body.

Example:

In order to verify the validity of the inventive method, use sky No. one in the example and long bent No. 3 satellites.

In this example, denoise algorithm is selected Wavelet Algorithm, and correcting algorithm is selected maximal possibility estimation algorithm (MAP), and the pixel angle β of testing image is 0.029.

Annotate: a represents satellite main body physical length, i.e. l in the preamble in Figure of description.The main body physical length that No. one, Heavenly Palace is 10.4 meters; Long bent No. 3 modal length is about 6 meters.

In Fig. 8, modal length a of Heavenly Palace is 10.0, and its relative error is 3.84%.

In Figure 11, modal length a of Heavenly Palace is 9.81, and its relative error is 5.67%.

In Figure 14, modal length a of Heavenly Palace is 11.02, and its relative error is 5.96%.

In Figure 17, long bent No. 3 modal length a is 5.54 meters, and relative error is 7.66%.

In Figure 20, long bent No. 3 modal length a is 6.31 meters, and relative error is 5.16%.

In Figure 23, long bent No. 3 modal length a is 5.76 meters, and relative error is 4.0%.

Know that by analysis error causes mainly due to extracting the length of image picture elements in the image and finding the solution hypothesis (satellite main body and the earth's core, observation station three is at same plane) three.

The present invention not only is confined to above-mentioned embodiment; persons skilled in the art are according to content disclosed by the invention; can adopt other multiple embodiment to implement the present invention; therefore; every employing project organization of the present invention and thinking; do some simple designs that change or change, all fall into the scope of protection of the invention.

Claims (3)

1. an extraterrestrial target modal length measuring method comprises the steps:

(1) image by the extraterrestrial target to be measured of inputting is to obtain constantly t of target imaging in the testing image;

(2) obtain the orbital tracking of this extraterrestrial target according to the types index of extraterrestrial target;

(3) testing image is carried out pre-service, comprise image denoising and image rectification;

(4) obtain the constantly locus coordinate (x of t of extraterrestrial target _t, y _t, z _t);

(5) the size L of computer memory target subject lateral projection in the space, unit are rice;

(6) the physical length l of computer memory target, unit are rice:

$l=\frac{L}{\cos \mathrm{\α}}$

Wherein, $\cos \mathrm{\α}=\frac{h_1^2+h_2^2-h_3^2}{{2h}_1{h}_2}$

$h_1=\sqrt{{(x_t-x_m)}^2+{(y_t-y_m)}^2+{(z_t-z_m)}^2}$

$h_2=\sqrt{x_t^2+y_t^2+z_t^2}$

$h_3=\sqrt{x_m^2+y_m^2+z_m^2}.$

2. extraterrestrial target modal length measuring method according to claim 1 is characterized in that,

Step (4) is specially: according to the orbital tracking that step (2) obtains, utilize STK simulation software simulation space aim in the rail scene, each position coordinates constantly of derived space target therefrom obtains t locus coordinate (x constantly _t, y _t, z _t).

3. extraterrestrial target modal length measuring method according to claim 1 and 2, it is characterized in that, step (5) is specially: obtain the pixel length n of target subject from testing image, utilize the constantly volume coordinate (x of extraterrestrial target of t that step (4) obtains _t, y _t, z _t) and known research station position coordinates (x _m, y _m, z _m) calculate extraterrestrial target t lateral projection's size constantly in the space:

$L=\frac{n\×\mathrm{\β}\×\mathrm{\π}\×R\×1000}{3600\×180}$

R represents moment t extraterrestrial target to the distance of research station, $R=\sqrt{{(x_t-x_m)}^2+{(y_t-y_m)}^2+{(z_t-z_m)}^2},$ Unit is rice, and β represents the pixel angle of testing image.

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