CN110160516A - It is a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision - Google Patents
It is a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision Download PDFInfo
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- CN110160516A CN110160516A CN201910372583.3A CN201910372583A CN110160516A CN 110160516 A CN110160516 A CN 110160516A CN 201910372583 A CN201910372583 A CN 201910372583A CN 110160516 A CN110160516 A CN 110160516A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C1/00—Measuring angles
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
- G01S13/06—Systems determining position data of a target
- G01S13/08—Systems for measuring distance only
- G01S13/10—Systems for measuring distance only using transmission of interrupted, pulse modulated waves
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Abstract
It is a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, the image of space junk is shot by Visible Light Camera, the range information of space junk is obtained by tellurometer survey load simultaneously, the range information of space junk relative satellite is obtained in the angle information for extracting space junk relative satellite by optical recognition algorithm, and by radar pulse ranging model.The angle information and range information of known spatial fragment relative satellite pass through the high-precision positioning result of the available space junk of data fusion model.The segmental arc of the in-orbit tracking space junk of satellite can be reduced, the angle information and range information obtained within the shorter tracking time by measurement combines the calculation method convenient for software implementation, realize the high accuracy positioning to space junk, the present invention can realize the high accuracy positioning of extraterrestrial target in observation time of the space-based tens of seconds to several minutes.
Description
Technical field
The present invention relates to a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, belongs to space
In-orbit field of locating technology.
Background technique
After the harmfulness for recognizing large number of space junk, people, which have been working hard, verifies space junk
Quantity and distribution situation.This requires knowing space junk position in orbit and variation, the operation rail of space junk is determined
Road, distribution of the space junk in space are extremely non-uniform, and are difficult how accurately to obtain the rail of space junk by all-the-way tracking
Road parameter is always a problem.Can by ground-based radar or the observation space fragment of optical telescope, and to observation data
The location information for obtaining space junk is resolved, but more space junks are difficult to be tracked by ground installation.
Space-based space junk monitoring multi-pass crosses satellite loading visible optical camera and is monitored and tracks, and is passing through processing light
It learns observation data and obtains the location information of space junk.Different from ground based observa tion, space-base monitoring is flat by optics camera properties, satellite
Platform orbital period and system operating mode restrict, and may only obtain tens of seconds to several points to space junk in single measurement task
The observation time of clock, opposite fragment orbital period belong to short arc measurement.The short arc of single observation time measures the sky that can reflect
Between fragment kinetic characteristic or track characteristic it is limited, it is difficult to extract measurement second order and lead or the order of information such as segmental arc curvature, can not be effective
Handle out the location information of space junk.Meanwhile except will also be by addition to by earth center graviational interaction in the in-orbit movement of space junk
To the influence of a variety of perturbative force factors, need as needed to accept or reject perturbative force in high accuracy positioning.
Summary of the invention
Present invention solves the technical problem that are as follows: overcome space junk to be difficult to be determined by groundwork detection system discovery and in-orbit short arc
The not high problem of rail precision, provide it is a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, can
The image of space junk is shot by Visible Light Camera, while the range information of space junk is obtained by tellurometer survey load,
It is obtained in the angle information for extracting space junk relative satellite by optical recognition algorithm, and by radar pulse ranging model
The range information of space junk relative satellite passes through routine according to the angle information and range information of space junk relative satellite
The high-precision positioning result of the available space junk of data fusion model.
The technical solution that the present invention solves are as follows: a kind of based on the in-orbit positioning of the extraterrestrial target of angle measurement and ranging information high-precision
Method, steps are as follows:
1) the Visible Light Camera continuous multiple frames that satellite carries shoot space；
2) information extraction is carried out to the space of step 1) shooting and space Spatial Object phase is obtained according to the information of extraction
To the angle information of observation satellite；
3) asteroid, micrometeor and artificial satellite are rejected from extraterrestrial target, obtained space junk is with respect to observation satellite
Angle information；
4) space junk obtained according to step 3) guides spaceborne microwave radar to emit with respect to the angle information of observation satellite
Pulse pointing space fragment obtains range information (ranging information) of the space junk with respect to observation satellite；
5) range information of the opposite observation satellite of the space junk obtained according to step 4), the space in conjunction with step (3) are broken
Piece obtains the location information under target debris inertial system with respect to the angle information of observation satellite；
6) step 1) -5 is repeated), obtain the multiple location information under target debris inertial system；
7) the multiple location information under the target debris inertial system obtained according to step 6), it is accurately fixed to carry out to space junk
Position, obtains positioning result；
8) by the storage of positioning result that step 7) obtains and under pass.
Visible Light Camera, specific requirement are as follows: Visible Light Camera uses the face battle array imaging sensor of high dynamic range.
The space junk obtained according to step 3) guides spaceborne microwave radar transmitting arteries and veins with respect to the angle information of observation satellite
Pointing space fragment is rushed, range information of the space junk with respect to observation satellite is obtained, specific as follows:
Satellite-borne microwave radar, receiving step 3) angle information, by the wave beam of the phased array antenna of itself quickly be directed toward should
The space junk band of position, the phased array antenna on radar are received from the reflected echo-signal of fractal surfaces, are realized to sky
Between fragment range measurement.
The extraterrestrial target of step (1), comprising: space junk, asteroid, micrometeor and artificial satellite.
The Visible Light Camera continuous multiple frames that step 1) observation satellite carries shoot extraterrestrial target, specific as follows: optical camera
Short exposure continuous multiple frames shoot extraterrestrial target.
Fixed star asterism in the multiple image of step 1) shooting remains stationary
The space junk that step 3) obtains is Angle Information with respect to the angle information of observation satellite.
The space junk of step 4) is ranging information with respect to the range information of observation satellite.
Step 2) carries out information extraction to the extraterrestrial target that step 1) is shot and obtains cosmic space according to the information of extraction
Spatial Object is with respect to the angle information of observation satellite, and specific as follows: the fixed star asterism in the multiple image of step 1) shooting is protected
Hold motionless, extraterrestrial target is in discrete continuous short arc in multiple image, by target position characteristic by fixed star and extraterrestrial target
It distinguishes and identifies, then the motion profile of extraterrestrial target is obtained by fitting algorithm, defended in conjunction with the monitoring observation of track initial point
The orbit information of star itself calculates angle information of the extraterrestrial target with respect to observation satellite.
Step 6) repeats step 1) -5), the multiple location information under space junk inertial system is obtained, it is specific as follows: repeatedly
Repeat step 1) -5), multiple observation space fragment, and the position under space junk inertial system is obtained by angle measurement and distance measuring method
Information.
The advantages of the present invention over the prior art are that:
(1) present invention can realize the high-precision fixed of extraterrestrial target in observation time of the space-based tens of seconds to several minutes
Position.
(2) in the present invention, space debris detection is identified using multiframe mode, extracts angle information；Using microwave radar
Ranging localization technology orients active radiated electromagnetic wave by radar antenna, and receives the reflected electromagnetic wave of target and extract
Effective information can measure the geometric distance between satellite and extraterrestrial target using the time difference between them；Fundamentally keep away
The defect for having opened short arc segments positioning in space junk monitoring reaches 500m to all space junk positioning accuracies that can stablize cataloguing
~200m, precision of 3km grades much higher than conventional mapping methods.
(3) the in-orbit localization method of space junk of the invention high-precision can reduce the in-orbit tracking space junk of satellite
Segmental arc, the angle information and range information obtained within the shorter tracking time by measurement combine the calculating side convenient for software implementation
Method realizes the high accuracy positioning to space junk, is a kind of method that can be widely applied in in-orbit space junk monitoring.
(4) each step according to the present invention can be executed and be completed by software on Satellite；The software can be existing
Have and increase what step of the present invention was constituted on the basis of software of technology, is also possible to newly grind software.
Detailed description of the invention
Fig. 1 is the schematic diagram of optics angle measurement and each block combiner of tellurometer survey at present system.
Specific embodiment
The invention will be described in further detail in the following with reference to the drawings and specific embodiments.
The present invention is a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, passes through visible light phase
Machine shoots the image of space junk, while the range information of space junk is obtained by tellurometer survey load, knows by optics
Other algorithm extracts the angle information of space junk relative satellite, and it is opposite by radar pulse ranging model to obtain space junk
The range information of satellite.The angle information and range information of known spatial fragment relative satellite, can be with by data fusion model
Obtain the high-precision positioning result of space junk.The segmental arc that the in-orbit tracking space junk of satellite can be reduced, in shorter tracking
The angle information and range information obtained in time by measurement combines the calculation method convenient for software implementation, realizes to space junk
High accuracy positioning, the present invention can realize the high-precision of extraterrestrial target in observation time of the space-based tens of seconds to several minutes
Positioning.
The present invention provides a kind of based on the in-orbit localization method of the space junk of angle measurement and ranging information high-precision, can obtain
In the case where obtaining angle information and range information of the space junk with respect to observation satellite, realize that space junk is in-orbit high-precision fixed
Position, is a kind of in-orbit localization method of the space junk conducive to engineering.This method can make the in-orbit observation space of observation satellite broken
In short tens of seconds to several minutes of observation time of piece, realizes to the high accuracy positioning of space junk, breach original observation
It is difficult in satellite single observation mission effectively to resolve the problem of space junk location information, is using the observation satellite of this method
System scale will be substantially reduced, and more utilize popularization in engineering and use.
The present invention is a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, and steps are as follows:
1) the Visible Light Camera continuous multiple frames that satellite carries shoot space；
2) information extraction is carried out to the space of step 1) shooting and space Spatial Object phase is obtained according to the information of extraction
To the angle information of observation satellite；
3) asteroid, micrometeor and artificial satellite are rejected from extraterrestrial target, obtained space junk is with respect to observation satellite
Angle information；
4) space junk obtained according to step 3) guides spaceborne microwave radar to emit with respect to the angle information of observation satellite
Pulse pointing space fragment obtains range information (ranging information) of the space junk with respect to observation satellite；
5) range information of the opposite observation satellite of the space junk obtained according to step 4), the space in conjunction with step (3) are broken
Piece obtains the location information under target debris inertial system with respect to the angle information of observation satellite；
6) step 1) -5 is repeated), obtain the multiple location information under target debris inertial system；
7) the multiple location information under the target debris inertial system obtained according to step 6), it is accurately fixed to carry out to space junk
Position, obtains positioning result；
8) by the storage of positioning result that step 7) obtains and under pass.
Visible Light Camera, preferred embodiment are as follows: Visible Light Camera using high dynamic range face battle array imaging sensor, camera at
Short exposure continuous multiple frames (more than 2 frame of 1s) shoot extraterrestrial target when picture, and fixed star and detected extraterrestrial target are in point source figure
Picture, asterism of the fixed star in multiple image is relatively motionless, and asterism of the extraterrestrial target in multiple image is mobile.
Satellite-borne microwave radar, preferred embodiment are as follows: the angle information of satellite-borne microwave radar receiving step three, by the phased of itself
The wave beam (electricity is swept) of array antenna is quickly directed toward the space junk band of position, and phased array antenna reception is reflected from fractal surfaces
Echo-signal realize range measurement to space junk.
The extraterrestrial target of step (1) preferably includes: space junk, asteroid, micrometeor and artificial satellite.
The Visible Light Camera continuous multiple frames that step 1) observation satellite carries shoot extraterrestrial target, and preferred embodiment is as follows: optics
Camera short exposure, fixed star and detection fragment target are in point source image, and asterism of the fixed star in multiple image is relatively motionless, space
Asterism of the fragment in multiple image is mobile, and multiple image is all stored in observation satellite memory.
Step 2) carries out information extraction to the extraterrestrial target that step 1) is shot and obtains cosmic space according to the information of extraction
For Spatial Object with respect to the angle information of observation satellite, preferred embodiment is as follows: the fixed star star in the multiple image of step 1) shooting
Point remains stationary, and extraterrestrial target is in discrete continuous short arc in multiple image, by target position characteristic by fixed star and space
Target is distinguished and is identified, then obtains the motion profile of extraterrestrial target by fitting algorithm, is monitored and is seen in conjunction with track initial point
The orbit information for surveying satellite itself, calculates angle information of the extraterrestrial target with respect to observation satellite.
The space junk that step 3) obtains is Angle Information with respect to the angle information of observation satellite.The space of step 4) is broken
Piece is ranging information with respect to the range information of observation satellite.
Step 3) rejects asteroid, micrometeor and artificial satellite from extraterrestrial target, obtained space junk relative satellite
Angle information, preferred embodiment is as follows: the angle information calculated in step 2) can in conjunction with the orbit information of observation satellite itself
To calculate that the orbit information for being observed extraterrestrial target, orbit information are not obviously met around earth movements spacecraft orbit feature
For asteroid and micrometeor, the observation data can be rejected；And the orbit information of artificial satellite, moment are observed, and can pass through phase
Shutting mechanism or query site, it is similar therewith to be observed extraterrestrial target and first close data and reject.By to extraterrestrial target
The natural celestial body and artificial satellite etc. such as fixed star, asteroid, micrometeor are rejected in Celestial Background imaging, micro- in next step convenient for improving
The efficiency and preferably space junk is positioned that wave detects.
The space junk that step 4) is obtained according to step 3) guides spaceborne microwave radar with respect to the angle information of observation satellite
Emit pulse pointing space fragment, obtains range information of the space junk with respect to observation satellite, preferred embodiment is as follows: by step
(3) space junk determined is transmitted to microwave radar with respect to the angle information of observation satellite, oneself phased array day of microwave radar
The wave beam (electricity is swept) of line is quickly directed toward the crumb position region, receives from the reflected echo-signal of fractal surfaces, microwave thunder
Up to the measurement realized based on doppler principle to space junk with respect to observation satellite distance.
The range information for the space junk observation satellite relatively that step 5) is obtained according to step 4), in conjunction with the sky of step (3)
Between fragment with respect to the angle information of observation satellite, obtain the location information under target debris inertial system, preferred embodiment is as follows:
Range information of the space junk with respect to observation satellite is obtained by step (4), obtains space junk in conjunction with step (3)
Angle information, in the posture and orbit information using observation satellite, location information under available space junk inertial system,
The information is calculated into the absolute location information it can be concluded that space junk by filtering equations again, and processing result is stored in star
On.
Step 6) repeats step 1) -5), the multiple location information under space junk inertial system is obtained, preferred embodiment is as follows:
Step 1) -5 is repeated several times), multiple observation space fragment, and obtained under space junk inertial system by angle measurement and distance measuring method
Location information.
Multiple location information under the space junk inertial system that step 7) is obtained according to step 6) carries out essence to space junk
Determine position, preferred embodiment is as follows: multiple location information under the space junk inertial system obtained to step 6) first removes deviation center
The maximum and minimum of value are obtaining space junk location information the most accurate by qualitative modeling to remaining data.
Step 8) by the storage of positioning result that step 7) obtains and under pass, preferred embodiment is as follows: the position that step 7) is obtained
Confidence breath is stored on the star of observation satellite in memory, is transferred to ground for location information when satellite to be observed transmits data over the ground
Face.
A kind of preferred embodiment based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision of the invention,
As shown in Figure 1, successively carrying out according to the following steps:
1) the Visible Light Camera continuous multiple frames that satellite carries shoot extraterrestrial target；Wherein, it is seen that light camera uses high dynamic
The face battle array imaging sensor of range, short exposure continuous multiple frames (preferably greater than 1s2 frame) shoot extraterrestrial target, fixed star when camera imaging
It is in point source image with detected extraterrestrial target, asterism of the fixed star in multiple image is relatively motionless, and extraterrestrial target is in multiframe
Asterism in image is mobile.
2) information extraction is carried out to the extraterrestrial target of step 1) shooting and space mesh in space is obtained according to the information of extraction
Mark the angle information of opposite observation satellite；(extraterrestrial target, comprising: space junk, asteroid, micrometeor and artificial satellite), tool
Body are as follows: information extraction is carried out to the extraterrestrial target of step 1) shooting, cosmic space Spatial Object is obtained according to the information of extraction
The angle information of opposite observation satellite, the fixed star asterism in multiple image that step 1) is shot remain stationary, and extraterrestrial target is more
It is in discrete continuous short arc in frame image, fixed star is distinguished and identified with extraterrestrial target by target position characteristic, then is led to
Over-fitting algorithm obtains the motion profile of extraterrestrial target, in conjunction with the orbit information of track initial point monitoring observation satellite itself, meter
Calculate angle information of the extraterrestrial target with respect to observation satellite.
3) asteroid, micrometeor and artificial satellite are rejected from extraterrestrial target, obtained space junk is with respect to observation satellite
Angle information (Angle Information), specifically:
The angle information calculated in step 2) can calculate in conjunction with the orbit information of observation satellite itself and be observed space
The orbit information of target, it is asteroid and miniflow that orbit information, which is not obviously met around earth movements spacecraft orbit feature,
Star can reject the observation data；And the orbit information of artificial satellite, moment are observed, and can be looked by associated mechanisms or website
It askes, it is similar therewith to be observed extraterrestrial target and first close data and reject.It, will by the Celestial Background imaging to extraterrestrial target
The natural celestial body and artificial satellite etc. such as fixed star, asteroid, micrometeor are rejected, convenient for improving the efficiency and more of next step microwave sounding
Good positions space junk.
4) space junk obtained according to step 3) guides spaceborne microwave radar to emit with respect to the angle information of observation satellite
Pulse pointing space fragment obtains range information (ranging information) of the space junk with respect to observation satellite；Specifically: by step
(3) space junk determined is transmitted to microwave radar with respect to the angle information of observation satellite, and satellite-borne microwave radar is phased with oneself
The wave beam (electricity is swept) of array antenna is quickly directed toward the space junk crumb position region, and phased array antenna is received to reflect from fractal surfaces
Echo-signal back, microwave radar realize the measurement to space junk with respect to observation satellite distance based on doppler principle.
5) range information of the opposite observation satellite of the space junk obtained according to step 4), the space in conjunction with step (3) are broken
Piece obtains the location information under target debris inertial system with respect to the angle information of observation satellite；Specifically: it is obtained by step (4)
Range information to space junk with respect to observation satellite, obtains the angle information of space junk in conjunction with step (3), is utilizing observation
The posture and orbit information of satellite, the location information under available space junk inertial system, then the information is passed through into filtering side
Journey calculates the absolute location information it can be concluded that space junk, and processing result is stored on star.
6) step 1) -5 is repeated), the multiple location information under target debris inertial system is obtained, specifically:
Step 1) -5 is repeated several times), multiple observation space fragment, and space junk is obtained by angle measurement and distance measuring method and is used to
Location information under property system.
7) the multiple location information under the target debris inertial system obtained according to step 6), it is accurately fixed to carry out to space junk
Position, specifically: multiple location information under the space junk inertial system obtained to step 6), first removal deviates the maximum of central value
And minimum, space junk location information the most accurate is being obtained by qualitative modeling to remaining data.
8) by the storage of positioning result that step 7) obtains and under pass, specifically: the location information for obtaining step 7) stores
On the star of observation satellite in memory, location information is transferred to ground when satellite to be observed transmits data over the ground.
It is not high by groundwork detection system discovery and in-orbit short arc orbit determination accuracy that the present invention overcomes the problems, such as that space junk is difficult to,
It provides a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, can be shot by Visible Light Camera
The image of space junk, while by the range information of tellurometer survey load acquisition space junk, it is extracted passing through recognizer
The angle information of space junk relative satellite out obtains the distance of space junk relative satellite in conjunction with angle information and range information
Information passes through the available sky of routine data Fusion Model according to the angle information and range information of space junk relative satellite
Between the high-precision positioning result of fragment.The present invention can realize space mesh in observation time of the space-based tens of seconds to several minutes
Target high accuracy positioning；The in-orbit localization method of space junk high-precision of the invention, it is broken can to reduce the in-orbit tracking space of satellite
The segmental arc of piece, the angle information and range information obtained within the shorter tracking time by measurement combine the meter convenient for software implementation
Calculation method realizes the high accuracy positioning to space junk, is a kind of side that can be widely applied in in-orbit space junk monitoring
Method.
The present invention can realize the high accuracy positioning of extraterrestrial target in observation time of the space-based tens of seconds to several minutes,
The present invention identifies space debris detection using multiframe mode, extracts angle information；Using microwave radar range location technology, lead to
Radar antenna orientation active radiated electromagnetic wave is crossed, and receives the reflected electromagnetic wave of target and extracts effective information, utilizes it
Between time difference, the geometric distance between satellite and extraterrestrial target can be measured；Fundamentally avoid space junk prison
The defect that short arc segments position in survey reaches 500m~200m to all space junk positioning accuracies that can stablize cataloguing, is much higher than
The precision that 3km grades of conventional mapping methods.
The in-orbit localization method of space junk high-precision of the invention, can reduce the arc of the in-orbit tracking space junk of satellite
Section, the angle information and range information obtained within the shorter tracking time by measurement combine the calculating side convenient for software implementation
Method realizes the high accuracy positioning to space junk, is a kind of method that can be widely applied in in-orbit space junk monitoring.This
Each step involved in inventing can be executed and be completed by logic on Satellite；The logic can be the logic in the prior art
On the basis of increase step of the present invention composition, be also possible to newly grind logic.
Present invention obviates the defects of short arc segments positioning in space junk monitoring, to all space junks that can stablize cataloguing
Positioning accuracy reaches 500m~200m, precision of 3km grades much higher than conventional mapping methods.
Claims (10)
1. a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision, it is characterised in that steps are as follows:
1) the Visible Light Camera continuous multiple frames that satellite carries shoot space；
2) information extraction is carried out to the space of step 1) shooting, according to the information of extraction, obtains the opposite sight of space Spatial Object
Survey the angle information of satellite；
3) asteroid, micrometeor and artificial satellite, angle of the obtained space junk with respect to observation satellite are rejected from extraterrestrial target
Spend information；
4) space junk obtained according to step 3) guides spaceborne microwave radar transmitting pulse with respect to the angle information of observation satellite
Pointing space fragment obtains range information of the space junk with respect to observation satellite；
5) range information of the opposite observation satellite of the space junk obtained according to step 4), in conjunction with the space junk phase of step (3)
To the angle information of observation satellite, the location information under target debris inertial system is obtained；
6) step 1) -5 is repeated), obtain the multiple location information under target debris inertial system；
7) the multiple location information under the target debris inertial system obtained according to step 6), is accurately positioned space junk,
Obtain positioning result；
8) by the storage of positioning result that step 7) obtains and under pass.
2. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: Visible Light Camera, specific requirement are as follows: Visible Light Camera uses the face battle array imaging sensor of high dynamic range.
3. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: the space junk obtained according to step 3) guides spaceborne microwave radar to send out with respect to the angle information of observation satellite
Pulse pointing space fragment is penetrated, range information of the space junk with respect to observation satellite is obtained, specific as follows:
Satellite-borne microwave radar, receiving step 3) angle information, the wave beam of the phased array antenna of itself is quickly directed toward the space
Crumb position region, the phased array antenna on radar are received from the reflected echo-signal of fractal surfaces, are realized broken to space
The range measurement of piece.
4. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: the extraterrestrial target of step (1), comprising: space junk, asteroid, micrometeor and artificial satellite.
5. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: the Visible Light Camera continuous multiple frames that step 1) observation satellite carries shoot extraterrestrial target, it is specific as follows: optics phase
Machine short exposure continuous multiple frames shoot extraterrestrial target.
6. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: the fixed star asterism in the multiple image of step 1) shooting remains stationary.
7. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: the space junk that step 3) obtains is with respect to the angle information of observation satellite, it is Angle Information.
8. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: range information of the space junk of step 4) with respect to observation satellite, is ranging information.
9. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: step 2) carries out information extraction to the extraterrestrial target that step 1) is shot, according to the information of extraction, universe sky is obtained
Between Spatial Object with respect to observation satellite angle information, it is specific as follows: step 1) shooting multiple image in fixed star asterism
It remains stationary, extraterrestrial target is in discrete continuous short arc in multiple image, by target position characteristic by fixed star and space mesh
Mark is distinguished and is identified, then obtains the motion profile of extraterrestrial target by fitting algorithm, is monitored and is observed in conjunction with track initial point
The orbit information of satellite itself calculates angle information of the extraterrestrial target with respect to observation satellite.
10. it is according to claim 1 a kind of based on the in-orbit localization method of the extraterrestrial target of angle measurement and ranging information high-precision,
It is characterized by: step 6) repeats step 1) -5), the multiple location information under space junk inertial system is obtained, it is specific as follows: more
It is secondary to repeat step 1) -5), multiple observation space fragment, and the position under space junk inertial system is obtained by angle measurement and distance measuring method
Confidence breath.
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| CN110940310A (en) * | 2019-11-15 | 2020-03-31 | 北京遥测技术研究所 | Calculation method for phased array antenna beam pointing angle of missile-borne relay measurement and control terminal |
| CN111581309A (en) * | 2020-03-27 | 2020-08-25 | 中国科学院西安光学精密机械研究所 | Observation method for space debris in geosynchronous orbit zone |
| CN111609857A (en) * | 2020-06-01 | 2020-09-01 | 中国科学院微小卫星创新研究院 | Space debris orbit determination traversal observation method and system |
| CN111751789A (en) * | 2020-06-30 | 2020-10-09 | 北京无线电测量研究所 | Method, system, medium, and apparatus for forecasting passing of artificial satellite through radar detection range |
| CN112363167A (en) * | 2020-11-02 | 2021-02-12 | 重庆邮电大学 | Extended target tracking method based on fusion of millimeter wave radar and monocular camera |
| CN112630775A (en) * | 2020-12-01 | 2021-04-09 | 北京航天驭星科技有限公司 | Method and system for measuring distance of target flying object |
| CN112945182A (en) * | 2021-01-26 | 2021-06-11 | 深圳市微视星辰数据网络科技有限公司 | Observation data-catalogue target association matching method |
| CN113063440A (en) * | 2021-02-26 | 2021-07-02 | 上海卫星工程研究所 | Full-physical simulation test method and system for image positioning and registration of stationary orbit microwave detection satellite |
| CN113532372A (en) * | 2021-06-28 | 2021-10-22 | 长春理工大学 | Space-based double-star intersection angle measurement and distance measurement device and use method thereof |
| CN113624242A (en) * | 2021-07-28 | 2021-11-09 | 中国测绘科学研究院 | Space debris orbit determination method and system, electronic equipment and storage medium |
| CN113671483A (en) * | 2021-08-19 | 2021-11-19 | 上海无线电设备研究所 | Satellite-borne composite data fusion method based on pulse per second |
| CN113805169A (en) * | 2021-08-11 | 2021-12-17 | 航天恒星科技有限公司 | Space target low-power-consumption small satellite radar searching and tracking method |
| CN115096319A (en) * | 2022-08-24 | 2022-09-23 | 航天宏图信息技术股份有限公司 | Method and device for determining initial orbit of satellite in star chain based on optical angle measurement data |
| CN115285381A (en) * | 2022-10-09 | 2022-11-04 | 北京开运联合信息技术集团股份有限公司 | Collision early warning method and device for space debris |
| CN115790607A (en) * | 2023-01-31 | 2023-03-14 | 南京航空航天大学 | Short arc historical data-based non-cooperative target maneuvering characteristic detection method |
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| CN110940310B (en) * | 2019-11-15 | 2021-12-07 | 北京遥测技术研究所 | Calculation method for phased array antenna beam pointing angle of missile-borne relay measurement and control terminal |
| CN110940310A (en) * | 2019-11-15 | 2020-03-31 | 北京遥测技术研究所 | Calculation method for phased array antenna beam pointing angle of missile-borne relay measurement and control terminal |
| CN111581309A (en) * | 2020-03-27 | 2020-08-25 | 中国科学院西安光学精密机械研究所 | Observation method for space debris in geosynchronous orbit zone |
| CN111581309B (en) * | 2020-03-27 | 2023-02-14 | 中国科学院西安光学精密机械研究所 | Observation method for space debris of geosynchronous orbit zone |
| CN111609857A (en) * | 2020-06-01 | 2020-09-01 | 中国科学院微小卫星创新研究院 | Space debris orbit determination traversal observation method and system |
| CN111751789A (en) * | 2020-06-30 | 2020-10-09 | 北京无线电测量研究所 | Method, system, medium, and apparatus for forecasting passing of artificial satellite through radar detection range |
| CN111751789B (en) * | 2020-06-30 | 2023-07-11 | 北京无线电测量研究所 | Method, system, medium and equipment for forecasting radar detection range of artificial satellite |
| CN112363167A (en) * | 2020-11-02 | 2021-02-12 | 重庆邮电大学 | Extended target tracking method based on fusion of millimeter wave radar and monocular camera |
| CN112630775A (en) * | 2020-12-01 | 2021-04-09 | 北京航天驭星科技有限公司 | Method and system for measuring distance of target flying object |
| CN112945182A (en) * | 2021-01-26 | 2021-06-11 | 深圳市微视星辰数据网络科技有限公司 | Observation data-catalogue target association matching method |
| CN112945182B (en) * | 2021-01-26 | 2022-05-17 | 深圳市微视星辰科技有限公司 | Observation data-catalogue target association matching method |
| CN113063440B (en) * | 2021-02-26 | 2022-12-27 | 上海卫星工程研究所 | Full-physical simulation test method and system for image positioning and registration of stationary orbit microwave detection satellite |
| CN113063440A (en) * | 2021-02-26 | 2021-07-02 | 上海卫星工程研究所 | Full-physical simulation test method and system for image positioning and registration of stationary orbit microwave detection satellite |
| CN113532372B (en) * | 2021-06-28 | 2022-08-09 | 长春理工大学 | Using method of space-based double-satellite intersection angle and distance measuring device |
| CN113532372A (en) * | 2021-06-28 | 2021-10-22 | 长春理工大学 | Space-based double-star intersection angle measurement and distance measurement device and use method thereof |
| CN113624242B (en) * | 2021-07-28 | 2024-04-09 | 中国测绘科学研究院 | Space debris orbit determination method, system, electronic equipment and storage medium |
| CN113624242A (en) * | 2021-07-28 | 2021-11-09 | 中国测绘科学研究院 | Space debris orbit determination method and system, electronic equipment and storage medium |
| CN113805169A (en) * | 2021-08-11 | 2021-12-17 | 航天恒星科技有限公司 | Space target low-power-consumption small satellite radar searching and tracking method |
| CN113805169B (en) * | 2021-08-11 | 2024-05-03 | 航天恒星科技有限公司 | Space target low-power consumption small satellite radar searching and tracking method |
| CN113671483A (en) * | 2021-08-19 | 2021-11-19 | 上海无线电设备研究所 | Satellite-borne composite data fusion method based on pulse per second |
| CN113671483B (en) * | 2021-08-19 | 2024-02-20 | 上海无线电设备研究所 | Satellite-borne composite data fusion method based on second pulse |
| CN115096319A (en) * | 2022-08-24 | 2022-09-23 | 航天宏图信息技术股份有限公司 | Method and device for determining initial orbit of satellite in star chain based on optical angle measurement data |
| CN115096319B (en) * | 2022-08-24 | 2022-11-18 | 航天宏图信息技术股份有限公司 | Method and device for determining initial orbit of satellite in star chain based on optical angle measurement data |
| CN115285381A (en) * | 2022-10-09 | 2022-11-04 | 北京开运联合信息技术集团股份有限公司 | Collision early warning method and device for space debris |
| CN115790607B (en) * | 2023-01-31 | 2023-05-12 | 南京航空航天大学 | Non-cooperative target maneuvering characteristic detection method based on short arc historical data |
| CN115790607A (en) * | 2023-01-31 | 2023-03-14 | 南京航空航天大学 | Short arc historical data-based non-cooperative target maneuvering characteristic detection method |
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