CN104570319A - Photoelectric observing system for space debris with array structures - Google Patents
Photoelectric observing system for space debris with array structures Download PDFInfo
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- CN104570319A CN104570319A CN201410707539.0A CN201410707539A CN104570319A CN 104570319 A CN104570319 A CN 104570319A CN 201410707539 A CN201410707539 A CN 201410707539A CN 104570319 A CN104570319 A CN 104570319A
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
- G02B23/16—Housings; Caps; Mountings; Supports, e.g. with counterweight
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
- H04N7/181—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a plurality of remote sources
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Abstract
The invention discloses a photoelectric observing system for space debris with array structures, belongs to the technical field of astronomical observation, and aims to solve the problem of the low observation efficiency of a photoelectric telescope. The system adopts the structure that a main control subsystem is connected with a servo subsystem, so as to control a frame subsystem; the frame subsystem supports a telescope tube subsystem; the telescope tube subsystem is connected with an image collection subsystem; the image collection subsystem is bilaterally connected with the main control subsystem and an object identification and positioning subsystem; the object identification and positioning subsystem is bilaterally connected with the main control subsystem; the output end of a time subsystem is connected with the main control subsystem and the image collection subsystem; the frame subsystem adopts a simplified horizontal structure and is provided with only one azimuth axis; the observing system rotates around the azimuth axis, and the observing system points to a center azimuth angle with the most space debris forecasted; the telescope tube subsystem comprises N telescope partial systems which are mounted on one frame subsystem and are arranged and combined according to a certain array structure, have the same elevation angles, and are positioned on the same horizontal plane; surveillance spaces are connected with one another.
Description
Technical field
The present invention relates to a kind of array junctions configuration space junk photoelectric observation system, it has, and visual field is large, unit is numerous, covering spatial domain is wide, high reliability, hi-Fix can be carried out to batch space junk, be a kind ofly be convenient to the very high space junk observation system of Project Realization, cost performance, belong to astronomical observation technical field.
Background technology
Space junk refers to all cultures in cosmic space except the aircraft of normal work, greatly to the satellite of finishing the work and rocket entirety, and the little powder produced to engine ignition.The main integrated distribution of space junk is at the near-earth orbit highly lower than 2000km, geostationary orbit and the earth half geo-stationary orbit.In recent years, mankind's space operation is frequent all the more, and space environment goes from bad to worse.If space junk and in-orbit spacecraft collide, its average stroke speed, in 10km/s magnitude, damages directly causing spacecraft device or disintegrates, will cause the loss of several hundred million unit.In addition, China launches spacecraft and carries out space test and also can produce space junk, and these space junks threaten to the spacecraft in-orbit of other countries, once collide not only can cause economic dispute, also can produce political fallout simultaneously.
In order to ensure spacecraft safety in-orbit, guaranteeing normally carrying out of mankind's solar-system operation, must observe space junk, determine space junk each moment on high in position and change, for spacecraft transmitting with provide safety assurance in orbit.
Space junk ground based observa tion technological means mainly contains Radar Technology and photoelectric observation technology.The detectivity of Radar Technology and the biquadratic of space junk oblique distance are inversely proportional to, still come with some shortcomings part: operating cost is high, detection range is near, detection accuracy is low, initiatively transmit and add that equipment volume is huge, disguised difference etc., Radar Technology is mainly used in detection low earth orbital fragment.Square being inversely proportional to of the detectivity of photoelectric observation technology and space junk oblique distance, photoelectric observation technology has plurality of advantages: operating cost is low, detection range is far away and the detectable satellite to radar stealth, certainty of measurement are high, the observation of environmentally safe, passive type, little and the good concealment etc. of equipment volume, photoelectric observation technology occupies an important position in space junk observation.
In addition, the photo-electric telescope in existing photoelectric observation technology, can only observe single space junk within the unit interval, not yet realizes multiple space junk and observes simultaneously.The observed efficiency of this working method is lower, can not meet the requirement of modern space fragment cataloguing.
Summary of the invention
The present invention can only observe single space junk in order to solve photo-electric telescope of the prior art within the unit interval, the problem that observed efficiency is low, array junctions configuration space junk photoelectric observation system is proposed, it can be observed batch space junk, can the automatic identification of implementation space fragment and hi-Fix.
Technical scheme of the present invention is:
Array junctions configuration space junk photoelectric observation system, this system comprises lens barrel subsystem, frame subsystem, time subsystem, servo subsystem, IMAQ subsystem, target identification and location subsystem and master control subsystem; Adopt serial port to connect between master control subsystem and servo subsystem, control frame subsystem; Frame subsystem supports lens barrel subsystem, lens barrel subsystem connects IMAQ subsystem, IMAQ subsystem is bi-directionally connected master control subsystem and target identification and locates subsystem, target identification is bi-directionally connected master control subsystem with location subsystem, and the output of time subsystem connects master control subsystem and IMAQ subsystem; It is characterized in that, described frame subsystem adopts a kind of altitude azimuth form structure of simplification, is only equipped with an azimuth axis; Rotate around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles; Described lens barrel subsystem is made up of N number of lens barrel subsystem, is arranged in a frame subsystem; N number of lens barrel subsystem carries out permutation and combination according to certain array structure, and each lens barrel subsystem elevation angle is identical, is on a horizontal plane, monitors that spatial domain interconnects.
Described lens barrel subsystem adopts refractive optical structure that is small-bore, Large visual angle, and is all equipped with a large target surface scientific grade CCD camera, and the photon of collection space fragment reflected sunlight and the photon of background fixed star, realize the maximization in system monitoring sky district.
Described time subsystem provides CCD camera to expose the temporal information of beginning and finish time for IMAQ subsystem and master control subsystem, comprises the year, month, day, hour, min in Coordinated Universal Time(UTC) time system, second, millisecond, is accurate to 0.1ms.
Described master control subsystem is system backbone, be responsible for observation mission scheduling, issue image capture instruction, positioning result display and store, generate observation mission plan and observe performance report etc., computer memory fragment forecasts maximum azimuths at set intervals, drive chassis subsystem rotates around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles, realizes the maximization of observation space number of tiles.
The invention has the beneficial effects as follows:
The present invention can realize automatic identification and the hi-Fix of batch space junk, thus realizes batch space junk cataloguing.This system has that visual field is large, unit is numerous, cover that spatial domain is wide, high reliability, can carry out hi-Fix to batch space junk, is a kind ofly to be convenient to the very high space junk observation system of Project Realization, cost performance.
Accompanying drawing explanation
Fig. 1 is array junctions configuration space junk photoelectric observation system schematic of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further details.
As shown in Figure 1, array junctions configuration space junk photoelectric observation system, is made up of following seven subsystems: lens barrel subsystem, frame subsystem, time subsystem, servo subsystem, IMAQ subsystem, target identification and location subsystem and master control subsystem.Wherein, between master control subsystem and servo subsystem, adopt serial port to connect, control frame subsystem; Frame subsystem supports lens barrel subsystem, lens barrel subsystem connects IMAQ subsystem, IMAQ subsystem is bi-directionally connected master control subsystem and target identification and locates subsystem, target identification is bi-directionally connected master control subsystem with location subsystem, and the output of time subsystem connects master control subsystem and IMAQ subsystem.
Lens barrel subsystem is made up of N number of lens barrel subsystem, is arranged in a frame subsystem; N number of lens barrel subsystem carries out permutation and combination according to certain array structure, and each lens barrel subsystem elevation angle is identical, is on a horizontal plane, monitors that spatial domain interconnects.
Lens barrel subsystem adopts refractive optical structure that is small-bore, Large visual angle, and be all equipped with a large target surface scientific grade CCD (Charge Coupled Device, charge coupled device) camera, the photon of collection space fragment reflected sunlight and the photon of background fixed star, realize the maximization in system monitoring sky district.
Frame subsystem adopts a kind of altitude azimuth form structure of simplification, is only equipped with an azimuth axis; Rotate around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles.Its azimuth, center is obtained by the analytical calculation of master control subsystem.
Time subsystem provides CCD camera to expose the temporal information of beginning and finish time for IMAQ subsystem and master control subsystem, comprises the year, month, day, hour, min in Coordinated Universal Time(UTC) time system, second, millisecond, is accurate to 0.1ms.
Servo subsystem rotates according to the order-driven azimuth axis of master control subsystem, and according to certain frequency by information feed back such as azimuth axis position, speed, acceleration to master control subsystem.
IMAQ subsystem is made up of N number of image acquisition subsystem, and each image acquisition subsystem carries out IMAQ according to the instruction of master control subsystem to the sky district specified.
Target identification is made up of N number of target identification and positioning subsystem with location subsystem, each target identification and positioning subsystem receive the ccd image and corresponding temporal information that corresponding image acquisition subsystem exports, space junk is identified automatically and locates, and the positioning result of output region fragment.
Master control subsystem is system backbone, be responsible for observation mission scheduling, issue image capture instruction, positioning result display and store, generate observation mission plan and observe performance report etc., calculate and monitor that space junk forecasts maximum azimuths, realize the maximization of observation space number of tiles.
Embodiment 1:
Array junctions configuration space junk photoelectric observation system is made up of following seven subsystems: lens barrel subsystem, frame subsystem, time subsystem, servo subsystem, IMAQ subsystem, target identification and location subsystem and master control subsystem.
Lens barrel subsystem is made up of 8 lens barrel subsystems, is arranged in a frame subsystem; 8 lens barrel subsystems carry out permutation and combination according to certain array structure, and each lens barrel subsystem elevation angle is identical, and the elevation angle, center is 25 °, are on a horizontal plane, monitor that spatial domain interconnects.
Lens barrel subsystem is all equipped with a pixel number and is 3056 × 3056, is of a size of the scientific grade CCD camera of 12 μm × μm, adopt the refractive optical structure of bore 150mm, focal length 150mm, monitor that sky district is more than or equal to 14 ° × 14 °, the photon of collection space fragment reflected sunlight and the photon of background fixed star.
Frame subsystem adopts a kind of altitude azimuth form structure of simplification, is only equipped with an azimuth axis; Rotate around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles.Its azimuth, center is obtained by the analytical calculation of master control subsystem.
Time subsystem is made up of GPS timing equipment and time service card, for IMAQ subsystem and master control subsystem provide CCD camera to expose the temporal information of beginning and finish time, comprise the year, month, day, hour, min in Coordinated Universal Time(UTC) time system, second, millisecond, be accurate to 0.1ms.
Servo subsystem is made up of grating encoder, torque motor, motor driving and motion controller etc., order-driven azimuth axis according to master control subsystem rotates, and according to certain frequency by information feed back such as azimuth axis position, speed, acceleration to master control subsystem.
IMAQ subsystem is made up of 8 image acquisition subsystems, and each image acquisition subsystem carries out IMAQ according to the instruction of master control subsystem to being more than or equal to 14 ° × 14 °Tian districts.
Target identification is made up of 8 target identifications and positioning subsystem with location subsystem, each target identification and positioning subsystem receive the ccd image and corresponding temporal information that corresponding image acquisition subsystem exports, space junk is identified and high accuracy astrofix automatically, and the positioning result of output region fragment.
Master control subsystem is system backbone, be responsible for observation mission scheduling, issue image capture instruction, positioning result display and store, generate observation mission plan and observe performance report etc., within every 30 minutes, calculate and monitor that space junk forecasts maximum azimuths, drive chassis subsystem rotates around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles, realizes the maximization of observation space number of tiles.
Above-mentioned array junctions configuration space junk photoelectric observation system can realize following technical indicator:
Detectivity:
Under the background daylight such as 19 and the condition of 200ms time for exposure, can detect 500km diameter is at a distance the space junk of 0.5m, and also can detect 2000km diameter is at a distance the space junk of 1m;
Monitor sky district: >=1500 square degree square grades;
Observation sky district: elevation angle 18-32 °;
Accuracy of observation :≤9 ".
Claims (4)
1. array junctions configuration space junk photoelectric observation system, this system comprises lens barrel subsystem, frame subsystem, time subsystem, servo subsystem, IMAQ subsystem, target identification and location subsystem and master control subsystem; Adopt serial port to connect between master control subsystem and servo subsystem, control frame subsystem; Frame subsystem supports lens barrel subsystem, lens barrel subsystem connects IMAQ subsystem, IMAQ subsystem is bi-directionally connected master control subsystem and target identification and locates subsystem, target identification is bi-directionally connected master control subsystem with location subsystem, and the output of time subsystem connects master control subsystem and IMAQ subsystem; It is characterized in that, described frame subsystem adopts a kind of altitude azimuth form structure of simplification, is only equipped with an azimuth axis; Rotate around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles; Described lens barrel subsystem is made up of N number of lens barrel subsystem, is arranged in a frame subsystem; N number of lens barrel subsystem carries out permutation and combination according to certain array structure, and each lens barrel subsystem elevation angle is identical, is on a horizontal plane, monitors that spatial domain interconnects.
2. the space junk photoelectric observation system of array junctions configuration according to claim 1, it is characterized in that, described lens barrel subsystem adopts refractive optical structure that is small-bore, Large visual angle, and be all equipped with a large target surface scientific grade CCD camera, the photon of collection space fragment reflected sunlight and the photon of background fixed star, realize the maximization in system monitoring sky district.
3. the space junk photoelectric observation system of array junctions configuration according to claim 1, it is characterized in that, described time subsystem starts and the temporal information of finish time for IMAQ subsystem and master control subsystem provide CCD camera to expose, comprise the year, month, day, hour, min in Coordinated Universal Time(UTC) time system, second, millisecond, be accurate to 0.1ms.
4. the space junk photoelectric observation system of array junctions configuration according to claim 1, it is characterized in that, described master control subsystem is system backbone, be responsible for observation mission scheduling, issue image capture instruction, positioning result display and storage, generate observation mission plan and observation performance report etc., computer memory fragment forecasts maximum azimuths at set intervals, drive chassis subsystem rotates around azimuth axis, array junctions configuration space junk photoelectric observation system pointing space fragment is forecast maximum central party parallactic angles, realize the maximization of observation space number of tiles.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106850051A (en) * | 2017-04-12 | 2017-06-13 | 上海航天控制技术研究所 | A kind of space junk cleaning system and method based on microsatellite |
| CN109901232A (en) * | 2018-12-30 | 2019-06-18 | 中国科学院软件研究所 | Generation method, storage medium and the system of space junk space-based optic observation task |
| CN113596332A (en) * | 2021-07-29 | 2021-11-02 | 中国科学院国家天文台长春人造卫星观测站 | Photoelectric monitoring system for spark events |
| CN113791454A (en) * | 2021-09-16 | 2021-12-14 | 中国科学院国家天文台长春人造卫星观测站 | Method, system, terminal and medium for detecting gravitational wave by using Mossbauer effect |
| CN113900245A (en) * | 2021-10-11 | 2022-01-07 | 中国科学院国家天文台长春人造卫星观测站 | Telescope observation device, control method and control system for transient source |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106850051A (en) * | 2017-04-12 | 2017-06-13 | 上海航天控制技术研究所 | A kind of space junk cleaning system and method based on microsatellite |
| CN106850051B (en) * | 2017-04-12 | 2020-04-03 | 上海航天控制技术研究所 | Space debris cleaning system and method based on microsatellite |
| CN109901232A (en) * | 2018-12-30 | 2019-06-18 | 中国科学院软件研究所 | Generation method, storage medium and the system of space junk space-based optic observation task |
| CN109901232B (en) * | 2018-12-30 | 2020-05-19 | 中国科学院软件研究所 | Space debris space-based optical observation task generation method, storage medium and system |
| CN113596332A (en) * | 2021-07-29 | 2021-11-02 | 中国科学院国家天文台长春人造卫星观测站 | Photoelectric monitoring system for spark events |
| CN113596332B (en) * | 2021-07-29 | 2023-05-30 | 中国科学院国家天文台长春人造卫星观测站 | Photoelectric monitoring system for firestain event |
| CN113791454A (en) * | 2021-09-16 | 2021-12-14 | 中国科学院国家天文台长春人造卫星观测站 | Method, system, terminal and medium for detecting gravitational wave by using Mossbauer effect |
| CN113791454B (en) * | 2021-09-16 | 2024-01-16 | 中国科学院国家天文台长春人造卫星观测站 | Method, system, terminal and medium for detecting gravitational wave by using Mossburg effect |
| CN113900245A (en) * | 2021-10-11 | 2022-01-07 | 中国科学院国家天文台长春人造卫星观测站 | Telescope observation device, control method and control system for transient source |
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