CN102353343A - Synchronous detecting system and method for planet-surface geometrical-characteristic and substance component thereof - Google Patents
Synchronous detecting system and method for planet-surface geometrical-characteristic and substance component thereof Download PDFInfo
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- CN102353343A CN102353343A CN2011101875505A CN201110187550A CN102353343A CN 102353343 A CN102353343 A CN 102353343A CN 2011101875505 A CN2011101875505 A CN 2011101875505A CN 201110187550 A CN201110187550 A CN 201110187550A CN 102353343 A CN102353343 A CN 102353343A
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Abstract
The invention discloses a synchronous detecting system and method for planet-surface geometrical-characteristics and substance components thereof. A main analyzing and control system is adopted to send out control signals to start a control-signal distributor, and the control signals are respectively transmitted to an X-axis stepping motor, a Y-axis stepping motor and a laser-pulse controller by the control-signal distributor to start different characteristic points of an infrared-pulse laser device focused to a planet-surface scanning area. A 1064nm laser-reflecting signal in an echoed signal is received by a PIN (Personal Identification Number) photoelectric detector to obtain a focus-point distance, an enhanced-type imaging device ICCD is controlled for exposure after a certain time delay to obtain a plasma spectral image after the light splitting of a spectrometer, and the substance components of planet-surface focus points are analyzed according to different spectral-line distribution. After the scanning for all the points at the planet-surface scanning area is finished, the three-dimensional surface topography of the area is reconstructed, and meanwhile, the substance components of each characteristic point on the surface are calibrated.
Description
Technical field
This patent relates to the measuring technology of geometric properties and material composition thereof; Specifically refer to a kind of laser test system and method for obtaining celestial body three-dimensional surface shape and material composition simultaneously, it is used for the Synchronization Analysis of survey of deep space China and foreign countries celestial body surface target area geometric properties and material chemical analysis.
Background technology
In survey of deep space, externally celestial body surface topography and material analysis of components are important tasks.Traditional test is surface topography test and the different system of material chemistry analysis of components employing often; Separately carry out; Its shortcoming is can't geometric properties point is corresponding one by one with its material composition; And, increased the cost of survey of deep space because of having adopted two cover systems to increase the load of star landing device.Therefore how geometric properties point surface topography and the detection of its material composition are combined, design new detection system and method, reduce lander load and have great importance.
This patent is to some problems that exist in celestial body surface topography and the material analysis of components system; The synchronism detection system and method for a kind of celestial body surface geometry characteristic and material composition thereof is proposed; This system and method can be in same set of system; Celestial body surface target area geometric properties point surface topography and material composition thereof are detected simultaneously; Can reduce the load of lander, improve the economy of survey of deep space.
Summary of the invention
The purpose of this patent provides in a kind of survey of deep space, the synchronism detection system and method for celestial body surface geometry characteristic and material composition thereof.This method adopts main analysis and control system to send control signal start-up control signal distributor; By the control signal divider control signal is sent to X-axis respectively and goes on foot dynamo-electric machine; Y-axis goes on foot dynamo-electric machine and laser pulse controller, to start the different characteristic point that the pulsed infrared laser device focuses to celestial body surface scan zone.1064nm laser reflection signal in the echoed signal is received by the PIN photodetector; Obtain focus point distance and after certain delay; Control enhancement mode image device ICCD makes public; Obtain the plasma spectrometry image after the spectrometer beam split; Distribute according to spectral lines with different, analyze the material composition of this celestial body surface focus point.After accomplishing the scanning of being had a few in celestial body surface scan zone, the 3 d surface topography that reconstructs the zone also calibrates the material composition of each unique point of surface simultaneously.
The technical scheme of this patent realizes like this;, the arrival of star landing device hovers when leaving top, target area, celestial body surface certain altitude; Send first target area unique point X and Y-axis rotational angle value signal by main analysis and control system, driven rotary polyhedron scanning mirror rotates to the precalculated position and starts the 1064nm pulsed laser.Pulse laser is divided into two-way: the one tunnel directly received by the laser sampling receiver through main beam splitter after immediately the enabling counting device begin counting; After another road is reflected by main beam splitter, after focusing on, the line focus optical system gets to celestial body surface focus point.After celestial body surface focus point was hit by pulse laser, the laser reflection signal of existing 1064nm comprised the plasma resonance spectral signal that laser pulse is induced generation again in the echoed signal.The reverse two-way that is divided into equivalent optical path through quilt time beam splitter behind the Focused Optical system of echoed signal: the one tunnel directly passes through beam splitter; Go into to inject optical fiber through fiber coupler, the plasma light spectrum signal that induced with laser produces is carried out beam split by the diffraction grating in the spectrometer; One the road is passed through the 1064nm narrow band pass filter after the beam splitter reflection; 1064nm laser reflection signal in the echoed signal is received by the PIN photodetector; After amplifier amplifies; Control counter stops counting and starts digital delay pulse producer DG535 simultaneously; After certain delay; Control enhancement mode image device ICCD makes public, and obtains the plasma spectrometry image after the spectrometer beam split.The laser induced plasma signal calculation circuit distributes according to spectral lines with different, analyzes the material composition of this celestial body surface focus point; The laser radar computing circuit can calculate the distance of this focus point from the PIN photodetector according to the numeral and the light velocity in the vacuum of counter simultaneously; And obtain the corresponding target area planimetric coordinates of this focus point through coordinate transform, with reconstructed object zone 3 d surface topography; After laser induced plasma signal calculation circuit and the computing of laser radar computing circuit finish, the result is delivered to main the analysis and control system, comprehensively both information can draw this focus point geometric properties and material composition information synchronously.Send next target area unique point control signal by main analysis and control system then, driven rotary polyhedron scanning mirror rotates to next precalculated position; Repeat above signals collecting and analytic process, can get the geometric properties and the material composition information of next target area unique point.After accomplishing the scanning of whole target area, the 3 d surface topography that can reconstruct the zone also calibrates the material composition of surperficial each point simultaneously.
Description of drawings
Fig. 1 is the schematic diagram of this patent, among the figure: 1---and the celestial body surface; 2---surperficial focus point; 3---total reflective mirror; 4---rotating multisurface swept-volume mirror; The 5X axle goes on foot dynamo-electric machine; 6---telescopic system; 7---the 1064nm pulsed laser; 8---beam expanding lens; 9---convex lens; 10---main beam splitter; 11---inferior beam splitter; 12---fiber coupler; 13---optical fiber; 14---the 1064nm narrow band pass filter; 15---the PIN photodetector; 16---the laser sampling receiver; 17---amplifier; 18---counter; 19---digital delay pulse producer DG535; 20---the laser radar computing circuit; 21---spectrometer; 22---enhancement mode image device ICCD; 23---the laser induced plasma signal calculation circuit; 24---the main analysis and control system; 25---the control signal divider; 26---laser pulse controller; 27---Y-axis goes on foot dynamo-electric machine.
Embodiment
The principle of this patent as shown in Figure 1;, the arrival of star landing device hovers when leaving top, 1 target area, celestial body surface certain altitude; Analyze and control system 24 is sent first target area unique point X and Y-axis rotational angle value signal to control signal divider 25 by main; By control signal divider 25 control signal is sent to X-axis respectively and goes on foot dynamo-electric machine 5, Y-axis goes on foot dynamo-electric machine 27 and laser pulse controller 26.X-axis goes on foot dynamo-electric machine 5 and Y-axis goes on foot dynamo-electric machine 27 according to the control signal that receives, and driven rotary polyhedron scanning mirror 4 rotates to the precalculated position; After laser pulse controller 26 receives control signal, start 1064nm pulsed laser 7.Pulse laser is through being divided into two-way behind beam expanding lens 8, convex lens 9 to the main beam splitter 10: the one tunnel directly received by laser sampling receiver 16 through main beam splitter 10 after immediately enabling counting device 18 begin counting; Celestial body surface focus point 2 is got to after being reflected by main beam splitter 10 in another road after the Focused Optical system that telescopic system 6, total reflective mirror 3, rotating multisurface swept-volume mirror 4 are formed focuses on.After celestial body surface focus point 2 was hit by pulse laser, the laser reflection signal of existing 1064nm comprised the plasma resonance spectral signal that laser pulse is induced generation again in the echoed signal.The reverse two-way that is divided into equivalent optical path through quilt time beam splitter 11 behind the Focused Optical system of echoed signal: the one tunnel directly through beam splitter 11; Go into to inject optical fiber 13 through fiber coupler 12, the plasma light spectrum signal that induced with laser produces is carried out beam split by the diffraction grating in the spectrometer 21; One the road is passed through 1064nm narrow band pass filter 14 after beam splitter 11 reflections; 1064nm laser reflection signal in the echoed signal is received by PIN photodetector 15; After amplifier 17 amplifies; Control counter 18 stops counting and starts digital delay pulse producer DG53519 simultaneously; After certain delay; Control enhancement mode image device ICCD 22 makes public, and obtains the plasma spectrometry image after spectrometer 21 beam split.Laser induced plasma signal calculation circuit 23 distributes according to spectral lines with different, analyzes the material composition of this celestial body surface focus point; Laser radar computing circuit 20 can calculate the distance of this focus point from PIN photodetector 15 according to the numeral and the light velocity in the vacuum of counter 18 simultaneously; And obtain the corresponding target area planimetric coordinates of this focus point through coordinate transform, with reconstructed object zone 3 d surface topography; After laser induced plasma signal calculation circuit 23 and 20 computings of laser radar computing circuit finish, the result is delivered to main the analysis and control system 24, comprehensively both information can draw this focus point geometric properties and material composition information synchronously.Analyze and control system 24 is sent next target area unique point X and Y-axis rotational angle value signal to control signal divider 25 by main then; By control signal divider 25 control signal is sent to X-axis respectively and goes on foot dynamo-electric machine 5, Y-axis goes on foot dynamo-electric machine 27 and laser pulse controller 26.X-axis goes on foot dynamo-electric machine 5 and Y-axis goes on foot dynamo-electric machine 27 according to the control signal that receives, and driven rotary polyhedron scanning mirror 4 rotates to next precalculated position; Repeat above signals collecting and analytic process, can get the geometric properties and the material composition information of next target area unique point.After accomplishing the scanning of whole target area, the 3 d surface topography that can reconstruct the zone also calibrates the material composition of surperficial each point simultaneously.
Claims (2)
1. the synchronism detection system of celestial body surface geometry characteristic and material composition thereof; It comprises: total reflective mirror (3); Rotating multisurface swept-volume mirror (4); X-axis goes on foot dynamo-electric machine (5); Y-axis goes on foot dynamo-electric machine (27); Telescopic system (6); 1064nm pulsed laser (7); Beam expanding lens (8); Convex lens (9); Main beam splitter (10); Inferior beam splitter (11); Fiber coupler (12); Optical fiber (13); 1064nm narrow band pass filter (14); PIN photodetector (15); Laser sampling receiver (16); Amplifier (17); Counter (18); Digital delay pulse producer DG535 (19); Laser radar computing circuit (20); Spectrometer (21); Enhancement mode image device ICCD (22); Laser induced plasma signal calculation circuit (23); The main analysis and control system (24); Control signal divider (25) and laser pulse controller (26) is characterized in that:
, the arrival of star landing device hovers when leaving top, (1) target area, celestial body surface certain altitude; Analyze and control system (24) is sent first target area unique point X and Y-axis rotational angle value signal to control signal divider (25) by main, control signal is sent to respectively that X-axis goes on foot dynamo-electric machine (5), Y-axis goes on foot dynamo-electric machine (27) and laser pulse controller (26) by control signal divider (25); X-axis goes on foot dynamo-electric machine (5) and Y-axis goes on foot dynamo-electric machine (27) according to the control signal that receives, and driven rotary polyhedron scanning mirror (4) rotates to the precalculated position; After laser pulse controller (26) receives control signal; Start 1064nm pulsed laser (7), pulse laser is through being divided into two-way behind beam expanding lens (8), convex lens (9) to the main beam splitter (10): the one tunnel directly received by laser sampling receiver (16) through main beam splitter (10) after immediately enabling counting device (18) begin to count; After another road is reflected by main beam splitter (10),, gets to the Focused Optical system that telescopic system (6), total reflective mirror (3), rotating multisurface swept-volume mirror (4) are formed celestial body surface focus point (2) after focusing on; After celestial body surface focus point (2) is hit by pulse laser; The laser reflection signal of existing 1064nm comprises the plasma resonance spectral signal that laser pulse is induced generation again in the echoed signal; The reverse two-way that is divided into equivalent optical path through quilt time beam splitter (11) behind the Focused Optical system of echoed signal: the one tunnel directly through beam splitter (11); Go into to inject optical fiber (13) through fiber coupler (12), the plasma light spectrum signal that induced with laser produces is carried out beam split by the diffraction grating in the spectrometer (21); One the road is passed through 1064nm narrow band pass filter (14) after beam splitter (11) reflection; 1064nm laser reflection signal in the echoed signal is received by PIN photodetector (15); After amplifier (17) amplifies; Control counter (18) stops counting and starts digital delay pulse producer DG535 (19) simultaneously; After certain delay; Control enhancement mode image device ICCD (22) makes public, and obtains the plasma spectrometry image after spectrometer (21) beam split; Laser induced plasma signal calculation circuit (23) distributes according to spectral lines with different, analyzes the material composition of this celestial body surface focus point; Laser radar computing circuit (20) can calculate the distance of this focus point from PIN photodetector (15) according to the numeral and the light velocity in the vacuum of counter (18) simultaneously; And obtain the corresponding target area planimetric coordinates of this focus point through coordinate transform, with reconstructed object zone 3 d surface topography; After laser induced plasma signal calculation circuit (23) and laser radar computing circuit (20) computing finish, the result is delivered to main the analysis and control system (24), comprehensively both information can draw this focus point geometric properties and material composition information synchronously; Analyze and control system (24) is sent next target area unique point X and Y-axis rotational angle value signal to control signal divider (25) by main then; By control signal divider (25) control signal is sent to X-axis respectively and goes on foot dynamo-electric machine (5); Y-axis goes on foot dynamo-electric machine (27) and laser pulse controller (26); X-axis goes on foot dynamo-electric machine (5) and Y-axis goes on foot dynamo-electric machine (27) according to the control signal that receives, and driven rotary polyhedron scanning mirror (4) rotates to next precalculated position; Repeat above signals collecting and analytic process, can get the geometric properties and the material composition information of next target area unique point; After accomplishing the scanning of whole target area, the 3 d surface topography that can reconstruct the zone also calibrates the material composition of surperficial each point simultaneously.
2. one kind based on the celestial body surface geometry characteristic of the said test macro of claim 1 and the synchronous detecting method of material composition thereof, it is characterized in that may further comprise the steps:
1) echoed signal is divided into two-way, and wherein the 1064nm laser reflection signal is used to measure the distance of celestial body surface focus point; The plasma light spectrum signal of induced with laser is received by spectrometer and ICCD, distributes according to spectral lines with different, analyzes the material composition of this celestial body surface focus point;
2) main analysis and control system are sent X and Y-axis rotary angle signal, and the control X-axis goes on foot dynamo-electric machine, Y-axis goes on foot dynamo-electric machine rotation, makes pulse laser focusing to scanning area different character point;
3) repeating step 1) the make new advances material composition of focus point of the distance and the analysis that obtain new focus point;
4) after the scanning that completion celestial body surface scan zone is had a few, the 3 d surface topography that reconstructs the zone also calibrates the material composition of surperficial each point simultaneously.
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| CN102608079A (en) * | 2012-03-03 | 2012-07-25 | 南昌航空大学 | Detection method of long-distance laser induced plasma spectrum |
| CN103217145A (en) * | 2013-03-27 | 2013-07-24 | 南京航空航天大学 | Mars DEM (Digital Elevation Model) making and strip aerial triangulation method |
| RU2618608C2 (en) * | 2015-07-29 | 2017-05-04 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королёва" | Method and device for sampling material from astronomical object surface |
| CN107748011A (en) * | 2017-09-20 | 2018-03-02 | 南京航空航天大学 | The test system and method for testing of medium-wave infrared detector image-forming time delay |
| CN110954527A (en) * | 2019-12-11 | 2020-04-03 | 南京信息工程大学 | Novel automatic detection system for floating atmospheric particulates |
| CN114877869A (en) * | 2022-05-25 | 2022-08-09 | 中国航空工业集团公司沈阳空气动力研究所 | Motion blur suppression test system and working method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102608079A (en) * | 2012-03-03 | 2012-07-25 | 南昌航空大学 | Detection method of long-distance laser induced plasma spectrum |
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| CN107748011B (en) * | 2017-09-20 | 2019-08-16 | 南京航空航天大学 | The test macro and test method of medium-wave infrared detector image-forming delay time |
| CN110954527A (en) * | 2019-12-11 | 2020-04-03 | 南京信息工程大学 | Novel automatic detection system for floating atmospheric particulates |
| CN114877869A (en) * | 2022-05-25 | 2022-08-09 | 中国航空工业集团公司沈阳空气动力研究所 | Motion blur suppression test system and working method thereof |
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