CN103293332A - Speed measurement photoelectric component for socket sled test - Google Patents
Speed measurement photoelectric component for socket sled test Download PDFInfo
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- CN103293332A CN103293332A CN2013102102170A CN201310210217A CN103293332A CN 103293332 A CN103293332 A CN 103293332A CN 2013102102170 A CN2013102102170 A CN 2013102102170A CN 201310210217 A CN201310210217 A CN 201310210217A CN 103293332 A CN103293332 A CN 103293332A
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Abstract
The invention discloses a speed measurement photoelectric component for socket sled test. The speed measurement photoelectric component for socket sled test has the advantages that a photoelectric transmitting terminal of the speed measurement photoelectric component for socket sled test is flexible in design, variable resistors are used, and laser emitting frequency and laser emitting strength can be adjusted for the transmitting terminal so as to adapt to different operating environments; a receiving terminal processing circuit can also be selectively matched according to the different environments, and the component is more widely applicable; the component is not limited by limitations of a zero time synchronization and time unification system, only the time for a light shade providing blocking signals for the component needs to be known, a calculating method is simple and reliable, and the reliability problem caused by the large quantity of devices is solved; compared with the expensive equipment such as radar which costs hundreds of billions, the component has the advantages of low production cost, reliability in performance and the like; while the test conditions are unchanged, test preparation time is saved, test expenditure is saved, manpower and material resources are saved, and test reliability and continuity are guaranteed.
Description
Technical field
The present invention relates to a kind of rocket sledge and test the photoelectric subassembly that tests the speed, particularly the photoelectric subassembly of testing based on the inertial measuring unit rocket sledge of 9km track that tests the speed belongs to the space experiment technical field.
Background technology
The rocket sledge is to adopt rocket engine as power, along the research technique of a kind of recoverable of the orbital motion of special construction.Measurement sledge running body speed is surveyed and two kinds of methods of remote measurement outside having in the test of rocket sledge, and typical outer survey method is disconnected target test, and typically the method for telemetering is radar velocity measurement.
Disconnected target test rocket sledge key point speed is the principle when adopting spacing to survey, each speed trial ground is formed by starting target and stopping target, requires to lay in orbit according to trajectory measurement during test and start target and stop target, and equipment links to each other when surveying, between two targets apart from S by measuring acquisition.When the rocket sledge moves, equipment when cutting off signal that disconnected target target line produces and starting respectively and stop to survey, the time T of equipment records is the rocket sledge through the time of S section operation during survey, namely gets the rocket sledge through the speed V of this interval mid point by S/T.As can be seen, this kind method is to draw speed by position and time indirect, and in operational process, obtain measured value by ways of contact such as physics cuttings, if obtain the high-accuracy speed value, just need make the try one's best precision of little and Measuring Time of distance between two targets enough high, therefore, the method is used for early stage rocket sledge test.
Another outer survey means is radar velocity measurement systems, and radar is to find target and measure them in the position in space with radio method, so radar also is a kind of radiolocation technology.Along with the development of Radar Technology, the task of radar is not only the distance of measurement target, orientation and the elevation angle, but also comprises the speed of measurement target, and can obtain more information about targets the ripple from target.Radar Doppler is exactly the radar that utilizes work such as Doppler effect positions, tests the speed, range finding.Some radar also need be measured the relative velocity of moving target except the position of determining target.When having relative velocity between target and the radar station, the carrier frequency that receives echoed signal produces a frequency displacement with respect to the carrier frequency that transmits, and this frequency displacement is called Doppler shift in physics, and its numerical value is
In the formula, f
dBe Doppler shift, unit is Hz; v
rBe the radial velocity between radar and the target, unit is m/s; λ is carrier wavelength, and unit is m.When target is moved towards radar station, v
r0, the echo carrier frequency improves; Otherwise, v
r＜0, the echo carrier frequency reduces.As long as radar can be measured the Doppler shift f of echoed signal
d, just can determine the relative velocity between target and the radar station.
The velocity survey radar is a kind of speed measuring equipment of designing according to Doppler's principle.During work, launch the electromagnetic wave of continuous constant amplitude by radar antenna to the rocket sledge, the electromagnetic wave signal that reflects of receiving target simultaneously, utilize record Doppler frequency, treated acquisition target velocity data.Radar velocity measurement is that no physics contact, velocity measurement are uniformly-spaced exported with respect to the advantage of disconnected target test, therefore, generally adopts the radar velocity measurement mode in the rocket sledge test at home.But adopt iterative algorithm in the present rocket sledge radar velocity measurement data processing method, calculated amount is big and the error of calculation is relatively large, rate accuracy has only ppt relatively, and in low speed segment and the nearer place of radar, the phenomenon that precision is degenerated can occur, be difficult to satisfy the requirement that inertial measurement system rocket sledge test error is separated, and radar equipment precision, expensive price, startup and setup time are long, safeguard deficiencies such as inconvenience.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, propose a kind of rocket sledge and test the photoelectric subassembly that tests the speed, equipment is simple, cost is low, rate accuracy is high.
Technical solution of the present invention: a kind of rocket sledge is tested the photoelectric subassembly that tests the speed, and comprises photoemission end and signal receiving end; The photoemission end is by first resistance R 1, second resistance R 2, the 3rd resistance R 3, the 4th resistance R 4, the 5th resistance R 5, the 6th resistance R 6, the 7th resistance R 7, light emitting diode D1, LASER Discharge Tube D2, first capacitor C 1, the first triode Q1 and multivibrator U1 form, wherein, one end ground connection of first capacitor C 1, low triggering end mouth and the high-triggering end mouth of another termination multivibrator U1, first resistance R 1 one terminates to the power port of multivibrator U1, the other end is connected in series the discharge port that connects multivibrator after second resistance R 2, the 3rd resistance R 3 is with in parallel with the first light emitting diode D1 again after the 4th resistance R 4 is connected, circuit one after the parallel connection terminates to the discharge port of multivibrator U1, the other end is received low triggering end mouth and the high-triggering end mouth of multivibrator U1, the grounding ports ground connection of multivibrator U1, one termination power of the 5th resistance R 5, the other end connects the positive pole of LASER Discharge Tube D2 by the 6th resistance R 6, the negative pole of LASER Discharge Tube D2 connects the drain electrode of the first triode Q1, the source ground of the first triode Q1, grid connects the output port of multivibrator U1 by the 7th resistance R 7, the control port of multivibrator U1 is unsettled or by capacity earth, the replacement port of multivibrator U1 connects power supply by direct current; Signal receiving end is made up of second capacitor C 2, receiver U2, signal conditioning circuit U2A, an end ground connection of second capacitor C 2 wherein, another termination power, the grounding ports ground connection of receiver U2, power port connects power supply, output port connects the input port of signal conditioning circuit U2A, another input port ground connection of signal conditioning circuit U2A, and the output port of signal conditioning circuit U2A connects data processing equipment.
Described multivibrator U1 adopts LMC555CN type timer, and receiver U2 adopts AT138 type photosensor, and signal conditioning circuit U2A adopts rejection gate exclusive disjunction amplifier to constitute.
The present invention's advantage compared with prior art is: photoemission end flexible design of the present invention, adopt variable resistor, and can regulate Laser emission frequency and the Laser emission intensity of transmitting terminal, to adapt to different working environments; The photoelectric subassembly that tests the speed of the present invention also can be used as optoelectronic switch and is used for other environment, and the treatment circuit of its receiving end also can be selected coupling according to different environment, has widely and uses.Synchronously and restriction and the restriction of timing system, only need not know that shadow shield got final product to the time that photoelectric subassembly produces disabling signal when not being subject to zero, computing method are simple and reliable, saved owing to the various integrity problem that causes of equipment; , relatively expensive device such as radar easily up to ten million price compare, have cheap for manufacturing cost, advantages such as dependable performance, under the constant prerequisite of test condition, save test setup time, saved testing expenses, manpower and materials, guaranteed reliability and the continuity of test.
Description of drawings
Fig. 1 is measuring principle synoptic diagram of the present invention;
Fig. 2 is the circuit theory diagrams of photoelectric subassembly among the present invention;
Fig. 3 is the circuit theory diagrams of photoemission end of the present invention;
Fig. 4 is the circuit theory diagrams of signal receiving end of the present invention.
Embodiment
Principle of work of the present invention is: as shown in Figure 1, this photoelectric subassembly that tests the speed is followed the motion of sledge body in rocket sledge process of the test, the sledge that belongs to a kind of noncontact class carries test suite, when the sledge body orbits, the photoelectric subassembly output low level, when by light barrier, cause the photoelectric subassembly light flux variations, photoelectric subassembly output high level, by the timer equipment that is connected with the rear end, the temporal information that the sledge body moves to the light barrier place can be obtained, and then sledge speed of moving body and positional information can be obtained.
According to rocket sledge experimental enviroment, need in the selective light constriction, point to the little light source in angle, and corresponding receiver is not subjected to the interference of light such as sunshine, bulb, need to select infrared modulated light or infrared light so.Photoelectric subassembly needs first selective light electric signal receiver, and the receiver according to light designs radiating circuit again.Because the data acquisition system (DAS) of shadow shield rear end is the terminal of data, needs simultaneously according to the corresponding output signal of design of data acquisition system.Concrete circuit structure comprises photoemission end and signal receiving end as shown in Figure 2; The photoemission end is by first resistance R 1, second resistance R 2, the 3rd resistance R 3, the 4th resistance R 4, the 5th resistance R 5, the 6th resistance R 6, the 7th resistance R 7, light emitting diode D1, LASER Discharge Tube D2, first capacitor C 1, the first triode Q1 and multivibrator U1 form, wherein, one end ground connection of first capacitor C 1, low triggering end mouth 2 and the high-triggering end mouth 6 of another termination multivibrator U1, first resistance R 1 one terminates to the power port 8 of multivibrator U1, the other end is connected in series the discharge port 7 that connects multivibrator after second resistance R 2, the 3rd resistance R 3 is with in parallel with the first light emitting diode D1 again after the 4th resistance R 4 is connected, circuit one after the parallel connection terminates to the discharge port 7 of multivibrator U1, the other end is received low triggering end mouth 2 and the high-triggering end mouth 6 of multivibrator U1, grounding ports 1 ground connection of multivibrator U1, one termination power of the 5th resistance R 5, the other end connects the positive pole of LASER Discharge Tube D2 by the 6th resistance R 6, the negative pole of LASER Discharge Tube D2 connects the drain electrode of the first triode Q1, the source ground of the first triode Q1, grid connects the output port 3 of multivibrator U1 by the 7th resistance R 7, the control port 5 of multivibrator U1 is unsettled or by capacity earth, the replacement port 4 of multivibrator U1 connects power supply by direct current; Signal receiving end is made up of second capacitor C 2, receiver U2, signal conditioning circuit U2A, an end ground connection of second capacitor C 2 wherein, another termination power, the grounding ports ground connection of receiver U2, power port connects power supply, output port connects the input port of signal conditioning circuit U2A, another input port ground connection of signal conditioning circuit U2A, and the output port of signal conditioning circuit U2A connects data processing equipment.Wherein multivibrator U1 can adopt LMC555CN type timer, and receiver U2 can adopt AT138 type photosensor, and signal conditioning circuit U2A can adopt the SN74LS02N gate circuit.
Designed signal receiver, just needed the outwards frequency of emission of design transmitting terminal, this frequency should be consistent with the receiver response frequency of optoelectronic switch, constitutes multivibrator by the design related circuit, and the oscillation frequency computing formula of multivibrator is:
t
1=ln2·(R
1+R
2)·C
1
t
2=ln2·(R
3+R
4)·C
1
f=1/(t
1+t
2)
As shown in Figure 3, R1 and R3 select fixed value resistance, and R2 and R4 select variable resistor, C1 set point value electric capacity, calculate and can get by formula 3, the resistance of R2 and R4, wherein first resistance R 1 is 1K Ω, the 3rd resistance R 3 is 1K Ω, and the 6th resistance R 6 is 100 Ω, and the 7th resistance R 7 is 2.2K Ω.Output terminal 3 by multivibrator U1 is outwards exported modulation signal, NPN triode control output signal by the Q1 type, add R5 and R6 is in order to control the electric current of power valve D2 at the infrared transmitting tube front end, just can control the size of the detection range of this circuit by regulating electric current like this, the more big detection range of electric current is more big, the more little detection range of electric current is more little, if do not need to regulate detection range, R5 and R6 can replace with a fixed value resistance so.
For the receiving circuit of infrared light, because receiver U2 is high level output receiving infrared signal, when disabling signal, the low level pulse signal appears, return to high level output again.But according to the input requirement of data acquisition system (DAS), the high level pulse signal of need coming in and going out when disabling signal is arranged is the low level input when operate as normal, so just need carry out oppositely or other processing the output signal of receiver U2.Consider the reliability of signal and response requirement fast, adopt OR-NOT circuit U2A to carry out logical process, wherein an input end grounding provides low level, and the output of a termination receiver U2 has so just reached the requirement of data acquisition system (DAS).Between the feeder ear of receiver U2 chip and ground end, insert the high withstand voltage electric capacity of C2, the smooth working that can keep receiver U2.
After circuit designs fully and puts up, need adjust the R7 among Fig. 2 and R5, R5 and R7 control the input end of infrared transmitting tube and the base current of Q1 triode respectively, should make the dutycycle of waveform of output as far as possible near 1:1 during adjustment, find through repetition test, be 1:1 in dutycycle, the response frequency of the luminous point receiver U2 of transmission frequency and type selecting is known, effective detection range satisfies the testing requirements of rocket sledge and gets final product, and dutycycle depart from and departing from of modulating frequency can make detection accuracy decline to a great extent, for this reason, we are decided to be the adjustable potential meter with R7, adjust resistance and satisfy transmitting range, transmission frequency, requirements such as dutycycle.The another one main points of optoelectronic switch need transmitting terminal is made the probe shape exactly, can guarantee that like this light beam launches along a direction, have guaranteed the centrality of light beam.Need simultaneously the optical axis of infrared transmitting tube D2 and infrared receiving tube U2 is guaranteed on same straight line, depart from only to make circuit response malfunctioning even lose function.
The present invention not detailed description is technology as well known to those skilled in the art.
Claims (3)
1. a rocket sledge is tested the photoelectric subassembly that tests the speed, and it is characterized in that: comprise photoemission end and signal receiving end; The photoemission end is by first resistance R 1, second resistance R 2, the 3rd resistance R 3, the 4th resistance R 4, the 5th resistance R 5, the 6th resistance R 6, the 7th resistance R 7, light emitting diode D1, LASER Discharge Tube D2, first capacitor C 1, the first triode Q1 and multivibrator U1 form, wherein, one end ground connection of first capacitor C 1, the low triggering end mouth (2) of another termination multivibrator U1 and high-triggering end mouth (6), first resistance R 1 one terminates to the power port (8) of multivibrator U1, the other end is connected in series the discharge port (7) that connects multivibrator after second resistance R 2, the 3rd resistance R 3 is with in parallel with the first light emitting diode D1 again after the 4th resistance R 4 is connected, circuit one after the parallel connection terminates to the discharge port (7) of multivibrator U1, the other end is received low triggering end mouth (2) and the high-triggering end mouth (6) of multivibrator U1, the grounding ports of multivibrator U1 (1) ground connection, one termination power of the 5th resistance R 5, the other end connects the positive pole of LASER Discharge Tube D2 by the 6th resistance R 6, the negative pole of LASER Discharge Tube D2 connects the drain electrode of the first triode Q1, the source ground of the first triode Q1, grid connects the output port (3) of multivibrator U1 by the 7th resistance R 7, the control port of multivibrator U1 (5) is unsettled or by capacity earth, the replacement port (4) of multivibrator U1 connects power supply by direct current; Signal receiving end is made up of second capacitor C 2, receiver U2, signal conditioning circuit U2A, an end ground connection of second capacitor C 2 wherein, another termination power, the grounding ports ground connection of receiver U2, power port connects power supply, output port connects the input port of signal conditioning circuit U2A, another input port ground connection of signal conditioning circuit U2A, and the output port of signal conditioning circuit U2A connects data processing equipment.
2. a kind of rocket sledge according to claim 1 is tested the photoelectric subassembly that tests the speed, it is characterized in that: described first resistance R 1 is 1K Ω, the 3rd resistance R 3 is 1K Ω, the 6th resistance R 6 is 100 Ω, the 7th resistance R 7 is 2.2K Ω, and second resistance R 2, the 4th resistance R 4 and the 5th resistance R 5 are variable resistor.
3. a kind of rocket sledge according to claim 1 is tested the photoelectric subassembly that tests the speed, it is characterized in that: described multivibrator U1 adopts LMC555CN type timer, receiver U2 adopts AT138 type photosensor, and signal conditioning circuit U2A adopts rejection gate exclusive disjunction amplifier to constitute.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102102170A CN103293332A (en) | 2013-05-30 | 2013-05-30 | Speed measurement photoelectric component for socket sled test |
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| CN2013102102170A CN103293332A (en) | 2013-05-30 | 2013-05-30 | Speed measurement photoelectric component for socket sled test |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2824697B1 (en) * | 1978-06-06 | 1979-10-04 | Uranit Gmbh | Photoelectric speed sensor |
| US20080100822A1 (en) * | 2002-11-26 | 2008-05-01 | Munro James F | Apparatus for high accuracy distance and velocity measurement and methods thereof |
| CN202083397U (en) * | 2011-04-13 | 2011-12-21 | 北京航天控制仪器研究所 | Rocket sled test data acquiring system of inertia measurement device |
| CN102901517A (en) * | 2012-09-29 | 2013-01-30 | 北京航天控制仪器研究所 | Measurement system based on time synchronization for rocket sled test |
-
2013
- 2013-05-30 CN CN2013102102170A patent/CN103293332A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2824697B1 (en) * | 1978-06-06 | 1979-10-04 | Uranit Gmbh | Photoelectric speed sensor |
| US20080100822A1 (en) * | 2002-11-26 | 2008-05-01 | Munro James F | Apparatus for high accuracy distance and velocity measurement and methods thereof |
| CN202083397U (en) * | 2011-04-13 | 2011-12-21 | 北京航天控制仪器研究所 | Rocket sled test data acquiring system of inertia measurement device |
| CN102901517A (en) * | 2012-09-29 | 2013-01-30 | 北京航天控制仪器研究所 | Measurement system based on time synchronization for rocket sled test |
Non-Patent Citations (2)
| Title |
|---|
| 李菊叶等: "光电测速装置的设计", 《海南大学学报自然科学版》, vol. 30, no. 1, 31 March 2012 (2012-03-31) * |
| 赵建军等: "基于激光技术的高炮涉及训练模拟***", 《激光技术》, vol. 27, no. 6, 31 December 2003 (2003-12-31) * |
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Application publication date: 20130911 |