CN103278051A - Speed measuring method used in rocket sled test - Google Patents
Speed measuring method used in rocket sled test Download PDFInfo
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- CN103278051A CN103278051A CN2013102085936A CN201310208593A CN103278051A CN 103278051 A CN103278051 A CN 103278051A CN 2013102085936 A CN2013102085936 A CN 2013102085936A CN 201310208593 A CN201310208593 A CN 201310208593A CN 103278051 A CN103278051 A CN 103278051A
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Abstract
The invention discloses a speed measuring method used in a rocket sled test. According to the method, two sets of photoelectric assemblies are installed on a sled body in the rocket sled test at an accurate and known interval; when the sled body moves and passes through a light barrier pre-arranged beside a track, a blocking signal is given to the front photoelectric assembly and then a blocking signal is given to the back photoelectric assembly, the two sets of photoelectric assemblies record the time information of the blocking signals respectively through data recording devices, and then the known interval between the two sets of photoelectric assemblies is divided by the time difference between the two blocking signals to obtain the moving speed of the sled body. The speed measuring method used in the rocket sled test is low in cost, short in manufacturing cycle and easy to realize, provides an external measurement method with which the moving speed of the sled body can be measured accurately for the rocket sled test, saves the time for preparing for the test, saves testing expenses, saves labor and materials, and guarantees the reliability and stability of the test.
Description
Technical field
The present invention relates to a kind of rocket sledge test speed-measuring method, particularly based on the rocket sledge test speed-measuring method of 9km track, belong 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.After World War II, countries such as the U.S., Britain, France and the former Soviet Union are in order to promote missile armament, aerospace development, build the test site of number of different types in succession, and carried out the rocket sledge compbined test work of some core components that comprise inertial measuring unit.Along with the development of informationization operation and the demand of precision strike, inertial guidance and guider are had higher requirement at aspects such as reliability, practicality and precision, west military power launches successively to rocket sledge testing experiment for this reason.
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 testing equipment record is the rocket sledge through the time of S section operation, 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 running, 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, increased the cost of system, therefore, the method is used for early stage rocket sledge test.
The disconnected target method of testing in later stage has been developed into a kind of shadow shield method of testing, as shown in Figure 1, this method is by preset a lot of piece shadow shields on the track limit, each shadow shield needs installation one by one, leveling, straightening, and requiring itself and track to have higher perpendicularity, data file need accurately be measured and be recorded as to the spacing between each shadow shield.During when the motion of sledge body and one by one by each shadow shield, sledge is recorded recording apparatus can note time by each shadow shield, if L1, L2 ..., Li is the distance of the relative starting point of shadow shield, T1, T2 ..., Ti is moment of sledge body relative starting point when the shadow shield, then the instantaneous value of speed is:
But this method relatively depends on the distance between each shadow shield, and along with variation throughout the year, track can produce certain flexible with temperature, and each shadow shield can produce transmission error when measuring, and also there is certain error in the velocity amplitude of measurement.
Be example with existing shadow shield system, distance measurement error between adjacent two shadow shields is made up of following components: the Installation and Debugging precision of shadow shield: the deviation that has height when installing owing to shadow shield, the plane of distance measurement point and laser beam process there are differences, with shadow shield tilt 30 ', height differs 50mm and calculates, and the range error that causes is: Δ
1=± (sin30 ' * 50)=± 0.5mm.Between target apart from measure error: caused by the distance mearuring equipment error that mainly the measurement of each target spacing adopts total powerstation to carry out, the instrument test error is: Δ
2=± (1.2mm+1.1ppm) calculated according to existing 9Km track length, and its error amount is 11.1mm.Dynamic random error: when sledge carries the photoelectric subassembly dynamic error by any two shadow shields, owing to causing the time error that the inconsistency of triggering, circuit delay is brought, velocity jump is refracted to the last error of distance, demarcate by circuit analysis and laboratory, can be controlled in Δ
3=± 0.5mm.Two shadow shield interval errors:
And omnidistance shadow shield range measurement error is made up of following components: the Installation and Debugging precision of shadow shield: the deviation that has height when installing owing to shadow shield, the plane of distance measurement point and laser beam process there are differences, with shadow shield tilt 30 ', height differs 50mm and calculates, and the range error that causes is: Δ
1=± (sin30 ' * 50)=± 0.5mm; Between target apart from measure error: caused by the distance mearuring equipment error that mainly the measurement of each target spacing adopts total powerstation to carry out, the instrument test error is: Δ
2=± (1.2mm+1.1ppm) calculated according to existing 9Km track length, and its error amount is 11.1mm; Instrument sets up point tolerance: when mainly being set up by instrument and datum mark when positioning to point tolerance, generally can guarantee at Δ
3=± 2mm; Dynamic random error: when sledge carries the photoelectric subassembly dynamic error by any two shadow shields, owing to causing the time error that the inconsistency of triggering, circuit delay is brought, velocity jump is refracted to the last error of distance, demarcate by circuit analysis and laboratory, can be controlled in Δ
3=± 0.5mm; Omnidistance shadow shield range error:
This shows, owing to set up point tolerance, dynamic random error equal error apart from measure error, instrument between Installation and Debugging error, target, can be to constituting considerable influence apart from accuracy between target.In order to improve the outer examining system precision of shadow shield, demand seeking a kind of measuring method that does not rely on spacing between target urgently.
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 test speed-measuring method, this method cost is low, the manufacturing cycle short, realization easily, has guaranteed the reliability and stability of test simultaneously.
Technical solution of the present invention: a kind of rocket sledge test speed-measuring method, step is as follows:
(1) two photoelectric subassemblys one in front and one in back is installed on the rocket sledge sledge body, and accurately measures two spacings between the photoelectric subassembly;
(2) when carrying out the test of rocket sled, the light barrier of installing in orbit makes two photoelectric subassemblys produce a disabling signal respectively, utilizes the data recording equipment that is connected with photoelectric subassembly to note the temporal information of two disabling signals;
(3) temporal information of the disabling signal that same light barrier is produced do poor, obtain the time difference of former and later two blocking-up temporal informations, spacing between two photoelectric subassemblys of recycling namely realizes the measurement to rocket sled sledge running body speed divided by the time difference of former and later two blocking-up temporal informations.
Photoelectric subassembly 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.
The present invention's advantage compared with prior art is:
(1) real-time method that tests the speed of the present invention has been broken away from the dependence to distance between each shadow shield of aging method, only need the mounting distance between the accurate known photoelectric subassembly to get final product, reduced a series of workloads such as installation shadow shield, straightening leveling, distance measurement greatly;
(2) measurement data point of the present invention is relevant with the number of light barrier, and is irrelevant with the spacing of light barrier, so can increase the number of light barrier, comes the abundant information that tests the speed, and the number of light barrier is more many, and the data point of measuring speed is more many;
When (3) the present invention is not subject to zero synchronously and restriction and the restriction of timing system, only need know that same shadow shield got final product to the time difference that photoelectric subassembly produces disabling signal, computational methods are simple and reliable, saved because the various integrity problem that causes of equipment;
(4) speed-measuring method precision height of the present invention, and only be subject to the distance measurement precision of photoelectric subassembly and the drift rate of internal clocking crystal oscillator, adopting accurate measurement means and high-quality crystal oscillator, rate accuracy can well be guaranteed;
(5) expensive device such as relative radar of the present invention easily up to ten million price compare, have advantages such as cheap for manufacturing cost, dependable performance, under the constant prerequisite of experimental condition, save test time, saved testing expenses, manpower and materials, guaranteed reliability and the continuity of test.
Description of drawings
Fig. 1 is shadow shield measuring principle schematic diagram;
Fig. 2 is photoelectric subassembly scheme of installation of the present invention;
The rate curve schematic diagram that Fig. 3 calculates for the present invention;
Fig. 4 is the circuit theory diagrams of photoelectric subassembly of the present invention.
The specific embodiment
Two photoelectric subassembly mounting means are installed on the side of rocket sledge with photoelectric subassembly as shown in Figure 2, and the direction that tests the speed of photoelectric subassembly is parallel to the traffic direction of rocket sledge, and departs from the track certain distance.The rest may be inferred for more photoelectric subassembly mounting means, present tandem mounting means according to the sledge body direction of motion, wherein the emission port of each photoelectric subassembly and receiving port point-blank, the spacing of photoelectric subassembly needs accurately to measure, count its value and be S, the m of unit.The photoelectric subassembly output signal that signal receiving end provides is noted the temporal information of pulse edge by data recording equipment, and the disabling signal that same light barrier produces is respectively T for the time of two photoelectric subassemblys
1And T
2, the s of unit can be like this in the hope of the speed of sledge body by this light barrier:
In like manner, when sledge body band the motion of photoelectric subassembly velocity-measuring system, by on the track limit during a series of light barrier, will obtain the sledge body in the velocity information at this light barrier place, method by integration, can also obtain the displacement information of the relative initial point of sledge body, thereby realize the measurement to rocket sledge sledge body speed.
Stage on-test is connected to the sledge borne computer with the output of photoelectric subassembly or sledge carries data recording equipment, and input supply terminal connects power supply, the start of sledge borne computer, and photoelectric subassembly works on power, and all are ready, and the emission of rocket sledge enters armed state.In the process of the test, photoelectric subassembly together moves with the sledge body, during whenever by a light barrier, produce two signals, carry the temporal information that data recording equipment is noted two photoelectric subassemblys by sledge, owing to no longer rely on the distance between the light barrier, can suitably increase the number of light barrier, enrich the number of measurement data point, reduce workload, got rid of interval error, can guarantee with high rate accuracy.After the test, from the sledge borne computer, obtain a series of temporal information, by formula 1 and formula 2, can obtain velocity information and the positional information of rocket sled prying body, because design reasons, there is singular value in indivedual points, show as to trigger in triggering early or evening, for eliminating singular point, adopt following algorithm to time value T
iRevise:
Revised result can obtain the velocity information of rocket sledge test as shown in Figure 3, to realize speed-measuring method.
As shown in Figure 4, photoelectric subassembly 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 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.
R1 and R3 select fixed value resistance, and R2 and R4 select variable resistor, and C1 set point value electric capacity calculates and can get by formula 3, the resistance of R2 and R4, and wherein first resistance R 1 is 1K Ω, and 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 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 transmitting tube 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 collecting system, 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 collecting system.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 R7 and R5, R5 and R7 control the input 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 tranmitting frequency and type selecting is known, effective detection range satisfies the test requirements document 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, tranmitting 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 (5)
1. a rocket sledge is tested speed-measuring method, it is characterized in that step is as follows:
(1) two photoelectric subassemblys one in front and one in back is installed on the rocket sledge sledge body, and accurately measures two spacings between the photoelectric subassembly;
(2) when carrying out the test of rocket sled, the light barrier of installing in orbit makes two photoelectric subassemblys produce a disabling signal respectively, utilizes the data recording equipment that is connected with photoelectric subassembly to note the temporal information of two disabling signals;
(3) temporal information of the disabling signal that same light barrier is produced do poor, obtain the time difference of former and later two blocking-up temporal informations, spacing between two photoelectric subassemblys of recycling namely realizes the measurement to rocket sled sledge running body speed divided by the time difference of former and later two blocking-up temporal informations.
2. a kind of rocket sledge according to claim 1 is tested speed-measuring method, and it is characterized in that: described photoelectric subassembly 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, 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.
3. a kind of rocket sledge according to claim 1 is tested the photoelectric subassembly that tests the speed, and it is characterized in that: described first resistance R 1 is 1K Ω, and 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.
4. a kind of rocket sledge according to claim 1 is tested the photoelectric subassembly that tests the speed, and it is characterized in that: second resistance R 2, the 4th resistance R 4 and the 5th resistance R 5 are variable resistor.
5. a kind of rocket sledge according to claim 1 is tested the photoelectric subassembly that tests the speed, and it is characterized in that: described signal conditioning circuit U2A adopts nor gate exclusive disjunction amplifier to constitute.
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| CN106440973A (en) * | 2016-09-07 | 2017-02-22 | 南京理工大学 | Portable distribution type velocity-measuring system for networking rocket sled test |
| CN106771320A (en) * | 2016-11-23 | 2017-05-31 | 北京航天控制仪器研究所 | A kind of rocket sledge image speed measurement method |
| CN113970652A (en) * | 2021-10-20 | 2022-01-25 | 陕西鼎泰光宇科技有限公司 | Laser sensing simulation speed measurement method and system, computer equipment, terminal and medium |
| CN114136336A (en) * | 2021-11-05 | 2022-03-04 | 江西洪都航空工业股份有限公司 | Acceleration and rocket sled testing device and method |
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| CN106771320B (en) * | 2016-11-23 | 2019-03-12 | 北京航天控制仪器研究所 | A kind of rocket sledge image speed measurement method |
| CN113970652A (en) * | 2021-10-20 | 2022-01-25 | 陕西鼎泰光宇科技有限公司 | Laser sensing simulation speed measurement method and system, computer equipment, terminal and medium |
| CN113970652B (en) * | 2021-10-20 | 2024-05-28 | 陕西鼎泰光宇科技有限公司 | Laser sensing simulation speed measuring method, system, computer equipment, terminal and medium |
| CN114136336A (en) * | 2021-11-05 | 2022-03-04 | 江西洪都航空工业股份有限公司 | Acceleration and rocket sled testing device and method |
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