CN1049982C - Two-dimensional deflection plane mirror scanner - Google Patents
Two-dimensional deflection plane mirror scanner Download PDFInfo
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- CN1049982C CN1049982C CN 97106253 CN97106253A CN1049982C CN 1049982 C CN1049982 C CN 1049982C CN 97106253 CN97106253 CN 97106253 CN 97106253 A CN97106253 A CN 97106253A CN 1049982 C CN1049982 C CN 1049982C
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- plane mirror
- dimensional deflection
- cam
- deflection plane
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Abstract
A two-dimensional deflection plane mirror scanner is mainly used for aerial remote sensing measurement. Such as airborne laser radar, three-dimensional imaging scanner, laser scanning range finder, airborne laser sweep the fields such as sea sounding. The device comprises a laser forming a remote sensor emission source, a two-dimensional deflection plane mirror component arranged at an alpha angle with an optical axis of a laser output beam, a receiving telescope system forming a remote sensor receiving system, a diaphragm, an optical filter, a photoelectric receiver and a signal processing system. The method has the characteristics of uniform scanning point, large accommodation area, high efficiency, intuition, good linearity, convenient post-processing and capability of accurately measuring the position of the target in real time.
Description
The present invention is a kind of with the two-dimensional deflection plane mirror scanister of laser instrument as the remote sensor emissive source.Being mainly used in airborne remote sensing measures.For example airborne laser radar, airborne laser scanning range finding, three-dimensional imaging scanning, airborne laser are swept fields such as extra large depth measurement.
Prior art:
1) rotation linear scanner: it is an one side and the catoptron at the optical axis angle at 45 system that finishes object space scanning (see that the Shen Ming of Shanghai technology physics institute of the Chinese Academy of Sciences is bright, the thermal infrared multispectral scanner of Yang Cunwu invention, the airborne remote sensing utility system that energy publishing house published in 1989 with use the 102nd page) of pivoting.This Scan Architecture utilization factor is very low, has only in minute surface limited angle over the ground (60 ° or 90 °) to measure, and most time minute surface is swept to engine room inside or top, at this moment just can't measure.When initiatively measuring, power source must be compressed in work in the limited scanning angle, and the duration of work repetition frequency requires 4～6 times raising, and this obviously is disadvantageous.
2) circular scan system: catoptron normal and rotating shaft form an angle (for example 7.5 ° of angles) in this scanning system, catoptron forms ± 7.5 ° beat when rotating, if emissive source and receiver all are horizontal positioned, and rotating shaft and level angle at 45 is provided with, then the rotation sweep result is one ± 15 ° a cone, it on ground a circle away from aircraft, when aircraft advances, form a go-ahead helix and [see Stephen P.Haimbach, HillaryC.Mesick, OPTICAL VATHYMETRY FOR THE U.SNAVY:A FIELD MEASUREMENTPROGRAM 214/SPIE VOL 925 Ocean Optics IX (1988)].The measurement dot matrix of this spiral distribution is very inhomogeneous, and the aftertreatment trouble is not directly perceived, not ideal enough yet.
3) vibration mirror scanning structure: this Scan Architecture is common in penlight scanning, is difficult to contain simultaneously emission, receives two bundle clear apertures.Because the positive and negative alternate of direction of movable body can produce impact shock, little good solution of size, the big just difficulty of size.Particularly deflection amplitude requires when big, just more difficult realization when rate request is fast.Galvanometer swing has realized the rectilinearity shuttle-scanning, along with the motion of carrier forms scanning in a zigzag, along zigzag line do measurements, measurement point is still uneven dot matrix distribution.
4) documents, specially number of the edition is RV 2010280-C1, and (940330) GO2B26/10 has introduced the two coordinate scanners that a kind of piezoelectric crystal drives, and this scanner only is applicable to the oscillating scanning state that frequency is very high, and its complex structure, scanning angle also can not be done greatly.
5) the documents patent No. is that to have introduced a kind of luminous scanner-recorder among EP 0,354 028 A1 (900207) G11B7/00 be to be used for a scanning optical mechanical hook-up that the light emitting source luminescence process is write down, and this device is that of prior art 1 operating position reverses application records mechanism in other words.
6) the documents patent No.: US 5150250 (920922) GO2B26/10 adopt the visual output scanning optical system of dynamo-electric photomodulator, are used for document copying and copying equipment.Its invention focuses on manufacturing of dynamo-electric photomodulator, and what innovation scanning mechanism there is no.
The objective of the invention is to propose a kind of new two-dimensional deflection plane mirror scanister, the emission, receiving beam that makes remote sensor by this scanner and with the aircraft pace synthetic after, obtain the measurement band that certain width is arranged that good, an even dot matrix of rectilinearity distributes on the ground.It can overcome the low problem of scan efficiency of prior art 1, remote sensor is in all the time measures state over the ground.Simultaneously it can overcome inhomogeneous, the shortcoming intuitively not of the measuring point of prior art 2 circular scans again, for Data Post brings convenience.It can solve prior art 3 vibration mirror scanning sizes again and the amplitude of oscillation can not be done big limitation and the uneven problem of sweep trace density, for airborne remote sensing increases the wide comparatively ideal scanner of a kind of purposes.
Scanner of the present invention contains the laser instrument 1 as the transmitting illuminant of remote sensor 8, on the position that becomes angle α with the optical axis (also being the optical axis of remote sensor 8) of laser instrument 1 output beam, be equipped with the plane mirror 711 on deflecting plate 71 1 side surfaces of being attached at that constitutes two-dimensional deflection level crossing member 7, the receiving telescope system 2 of remote sensor 8 receiving systems is housed on the light path of advancing along plane mirror 711 folded light beams successively, light hurdle 3, optical filter 4, photelectric receiver 5 and signal processing system 6, as shown in Figure 1.
Above said two-dimensional deflection level crossing member 7 contains deflecting plate 71, on a side surface of deflecting plate 71, be pasted with plane mirror 711, on the center on the opposite side surface of deflecting plate 71, be fixed with spherical hinge 72, on the axle that becomes XY two vertical direction on the same side surface of the deflecting plate 71 that is fixed with spherical hinge 72, be fixed with two extension springs, first extension spring 77 respectively, second extension spring 78, two extension springs 77,78 and the other end of ball hinge 72 be fixed on the fixed support 714, by first cam 73 and second cam 75, two groups of cam ejection pin mechanisms that first push rod 74 and second push rod 76 constitute act on the deflecting plate 71 along X-axis and Y direction respectively, two cams 73 and 75 rotating shaft are linked on the same drive motor 79, that is to say two cams 73,75 rotation unification is driven by drive motor 79, and the instantaneous angle value of drive motor 79 is measured by angle measurement code-disc 710.As shown in Figure 2.
Above said angle α be chosen as α=30 °～60 ° usually.
Above the said plane mirror 711 that is attached on deflecting plate 71 1 side surfaces, because its minute surface becomes the α angle to put with the optical axis of remote sensor 8, and it will contain the whole light beams that transmit and receive, so its size is wanted enough greatly, might be greatly to about 350 millimeters (laterally) * 500 millimeter (vertically).
The curved surface that first rolling bearing, 712, the first cams 73 are equipped with on the top of first push rod 74 is pressed on first push rod 74 by first rolling bearing 712, and the amount of exercise of first push rod 74 should satisfy first cam, 73 variable θ
1Requirement.
The curved surface that second rolling bearing, 713, the second cams 75 are equipped with on the top of second push rod 76 is pressed on second push rod 76 by second rolling bearing 713, and the amount of exercise of second push rod 76 should satisfy second cam, 75 variable θ
2Requirement.
Second cam 75 is made of two identical involute surfaces, its major diameter b
2With minor axis a
2Difference θ
2(θ
2=b
2-a
2) controlled the amount of deflection of plane mirror 711 vertical (Y directions), shown in Fig. 3-2.If when the sweep trace vertical line-spacing of airborne sensor 8 on ground, 500 meters distant places requires 10 meters intervals,
Wherein B is that second push rod 76 acts on the application point on the deflecting plate 71Y axle, and OB is that second push rod 76 acts on the arm of force length on the deflecting plate Y-axis, θ when the OB=200 millimeter
2=2 millimeters.The length of OA and OB can be selected according to structure situation by the deviser.
Two extension springs 77 and 78 are that the deflecting plate 71X axle, the Y-axis that have plane mirror 711 are attached to respectively on two masthead cam mechanisms tightly.
The rotating speed of drive motor 79 is relevant with the speed of system requirements scanning, is determined by the work repetition frequency of flying height, scan angle, emissive source, the space requirement of measurement point.For example when 500 meters of flying height, scan angle ± 15 °, laser repetition rate per second 189 times, during 10 meters of measurement point space requirements, the rotating speed of drive motor 79 should be 3.5 revolutions per seconds.First cam 73 makes deflecting plate 71 transversely round totally 7 beats in X-axis, second cam 75 make deflecting plate 71 Y-axis vertically on 7 elder generations of per second gradually analyzing spot is done the back to straight correction (influence that the low aircraft that disappears advances), do a forward direction saltus step at last at transversal scanning limit place.
710 are the angle measurement code-disc, angle measurement code-disc 710 can provide the accurate position of two cams 73,75, that is to say that angle measurement code-disc 710 can measure the instantaneous position that plane of scanning motion catoptron 711 is swung, emission with this signal controlling laser instrument of measuring 1, also just can draw the accurate measurement point of remote sensor 8, this point is in Data Post and do measurement and positioning and very useful during the oblique distance correction.
Advantage of the present invention:
1) sweeps a little even, directly perceived, good linearity, convenient post-treatment.
2) efficient height is not interrupted and stops the survey problem.
3) the logical area of the scan light that can contain is big.
4) distribution of measuring point can reach better measuring point distribution strip by the suitable correction to two cam surface types.
5) drive motor is all corresponding with the measured value of angle measurement code-disc with the operating angle of two cams, the x time of laser instrument can be set and control with the angle value signal of angle measurement code-disc, no matter how selected the repetition frequency of Laser emission is, can determine the coordinate position of laser acquisition point by angle measurement code-disc angle signal value, this brings convenience for data processing and oblique distance correction.
6) scanner of the present invention also can be used for other occasions of ground, reflects leaded light in the time need carrying out the pointwise quick detection to a remote large scale target, scans the dot matrix that needs.
Description of drawings:
Fig. 1 is a scanner structure synoptic diagram of the present invention.
Fig. 2 is the structural representation of two-dimensional deflection level crossing member 7 in the scanner of the present invention.
Fig. 3 is cam structure and scanning result synoptic diagram.Wherein
Fig. 3-1 is the structural representation of first cam 73;
Fig. 3-2 is the structural representation of second cam 75;
Fig. 3-3 is a scanning result synoptic diagram among the embodiment
Most preferred embodiment:
Sweep in the extra large sounding system at airborne laser that to use be a most concrete example.Be used for a kind of like this remote sensing actual needs: 500 meters of aircraft flying height, the speed of a ship or plane 70 meter per seconds, remote measurement ocean from the aircraft (geodetic face also can).The frequency of measuring is 189 times/second, the moment visual field of remote sensor 8 is about the lonely degree of 10 millis (5 meters of the measuring point diameter phi on ground or sea), owing to survey the needs of weak signal, effective clear aperture of receiving telescope needs φ more than 200 millimeters, remote sensor 8 emissions, receive total clear aperture φ more than 300 millimeters, in the measurement airborne sensor 8 need under ± 15 ° underground scope (wide approximately 270 meters) carries out dot matrix and measures, the aerial survey result is 10 meters of spaces preferably, evenly the ground band that distributes of dot matrix.For reaching above every requirement, scanner is just very important, because remote sensor 8 volume weights are big, can not directly do the shaking of fast whole ± 15 ° of angles of per second 7 times, essential horizontal setting is appropriate, allow light path by plane mirror 711 aiming ground, plane mirror 711 be designed to scanner reach desired measurement result.
Select angle [alpha]=45 ° of the minute surface of the plane mirror 711 on the deflecting plate 71 and laser instrument 1 optical axis (being the optical axis of remote sensor 8)
The major axis b of first cam 73
1With minor axis a
1Difference θ
1=b
1-a
1=26.8 millimeters shown in Fig. 3-1, the major axis b of second cam 75
2With minor axis a
2Difference θ
2=b
2-a
2=2 millimeters, shown in Fig. 3-2.Plane mirror 711 is of a size of 350 millimeters (directions X) * 500 millimeter (Y direction), and the rotating speed of drive motor 79 is 3.5 revolutions per seconds.
With the radially sudden change of second cam 75, be improved to the inclined-plane shown in c, d, the e line, just can eliminate the impact shock of mechanism, see Fig. 3-2.Calculate the shared scope of the impact zone that disappears below and to the influence of scanning result.
Deflecting plate 71 drives plane mirror 711 round sweeping away 7 times/second, whenever sweep laser instrument 1 work 27 measuring points (laser instrument repetition frequency 189 times/second) one time, the cam angle degree that every measuring point accounts for is 180 °/27=6.7 °, wherein 24 points are effective linear zone, (about 160 ° of cam angles), 3 points are edge transition district (about 20 ° of cam angles, c, d, e oblique line part), see shown in Fig. 3-2.
Corresponding to the scanning result of distant place measurement point shown in Fig. 3-3.Aircraft flying height H=500 rice scans ± 15 °, accounts for wide 268 meters.Sweep away a Laser emission and measure 27 points, lucky 10 meters quite at interval, middle 240 meters is linear, and measurement is effective, and two edges are zone of transition for each 15 meters, measure for reference.Push rod 76 has been eliminated impact in 20 ° of scopes of zone of transition, and sweep trace is finished 10 meters translation forward smoothly.
Its experiment situation is as shown in table 1.
The action of table 1. scanning motion parts and light beam be the scanning result relation a long way off
Claims (7)
1. two-dimensional deflection plane mirror scanister, contain with the remote sensor (8) of laser instrument (1) as emissive source, on the light path of the receiving system in remote sensor (8), on the direction of advancing from the light signal that receives, the order that successively arrives by light is receiving telescope system (2) successively, light hurdle (3), optical filter (4), photelectric receiver (5) and signal processing system (6), it is characterized in that it contains two-dimensional deflection level crossing member (7), the minute surface that is attached at the plane mirror (711) on deflecting plate (71) one side surfaces in two-dimensional deflection level crossing member (7) becomes angle α to put with the optical axis of remote sensor (8).
2. two-dimensional deflection plane mirror scanister according to claim 1 is characterized in that said angle α=30 °～60 °.
3. two-dimensional deflection plane mirror scanister according to claim 1 is characterized in that said two-dimensional deflection level crossing member (7) contains deflecting plate (71), is pasted with plane mirror (711) on a side surface of deflecting plate (71); On the center on the opposite side surface of deflecting plate (71), be fixed with spherical hinge (72), the other end of spherical hinge (72) is fixed on the fixed support (714), on the surface, the same side of the fixing inclined to one side biography plate (71) of spherical hinge (72), become to be fixed with two extension spring first extension springs (77) and second extension spring (78) on XY two vertical direction respectively, two extension springs (77), (78) the other end is fixed on the fixed support (714), and is fixed with first cam (73) that constitutes two groups of cam ejection pin mechanisms on XY two vertical direction respectively, second cam (75) and first push rod (74), second push rod (76); The rotating shaft of two cams (73), (75) is linked on the same drive motor (79); The instantaneous angle value that angle measurement code-disc (710) The real time measure drive motor (79) is arranged.
4. two-dimensional deflection plane mirror scanister according to claim 3 is characterized in that first cam (73) is to place first push rod (74) top to have on the position of first rolling bearing (712).
5. two-dimensional deflection plane mirror scanister according to claim 3 is characterized in that second cam (75) is to place second push rod (76) top to have on the position of second rolling bearing (713).
6. two-dimensional deflection plane mirror scanister according to claim 3, the positive camber that it is characterized in that first cam (73) are made of the involute urve of symmetry and gradually closing line.
7. two-dimensional deflection plane mirror scanister according to claim 3, the positive camber that it is characterized in that second cam (75) are made of two identical involute surfaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97106253 CN1049982C (en) | 1997-01-30 | 1997-01-30 | Two-dimensional deflection plane mirror scanner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97106253 CN1049982C (en) | 1997-01-30 | 1997-01-30 | Two-dimensional deflection plane mirror scanner |
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| Publication Number | Publication Date |
|---|---|
| CN1189626A CN1189626A (en) | 1998-08-05 |
| CN1049982C true CN1049982C (en) | 2000-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97106253 Expired - Fee Related CN1049982C (en) | 1997-01-30 | 1997-01-30 | Two-dimensional deflection plane mirror scanner |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101153795B (en) * | 2006-09-26 | 2012-07-04 | 株式会社拓普康 | Laser scanner |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AUPS022002A0 (en) * | 2002-02-01 | 2002-02-21 | Tenix Lads Corporation Pty Ltd | An apparatus and method for the measurement of water depth using a controlled receiver |
| CN1310494C (en) * | 2004-10-26 | 2007-04-11 | 中国科学院上海技术物理研究所 | Speed variable scanner of space infrared opto-mechanical scanning remote sensing instrument |
| CN101589316B (en) * | 2006-10-30 | 2012-08-29 | 奥拓诺塞斯有限公司 | Scanning system for lidar |
| CN101493526B (en) * | 2008-11-28 | 2011-05-11 | 北京工业大学 | Lunar vehicle high speed three-dimensional laser imaging radar system and imaging method |
| CN103673979A (en) * | 2013-12-10 | 2014-03-26 | 苏州市峰之火数码科技有限公司 | Aerial photographing device used for continuous plotting |
| CN105204158B (en) * | 2015-11-03 | 2018-06-05 | 深圳市斯尔顿科技有限公司 | A kind of light path apparatus for fast switching |
-
1997
- 1997-01-30 CN CN 97106253 patent/CN1049982C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101153795B (en) * | 2006-09-26 | 2012-07-04 | 株式会社拓普康 | Laser scanner |
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| CN1189626A (en) | 1998-08-05 |
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