CN203928911U - A kind of structural parameters test macro for missile loading transport test - Google Patents
A kind of structural parameters test macro for missile loading transport test Download PDFInfo
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- CN203928911U CN203928911U CN201420347908.5U CN201420347908U CN203928911U CN 203928911 U CN203928911 U CN 203928911U CN 201420347908 U CN201420347908 U CN 201420347908U CN 203928911 U CN203928911 U CN 203928911U
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Abstract
The utility model relates to structural parameters technical field of measurement and test, a kind of structural parameters test macro for missile loading transport test, and object is to solve sensor and the unmatched problem of measurement device in existing missile loading transport test.It is characterized in that: comprise sensor electrical source adapter, testing equipment, switch, collecting computer, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor, stay wire displacement sensor and 220V alternating-current power supply.The utility model is compared with existing test macro, by using sensor electrical source adapter, can use a kind of testing equipment to measure multiple sensors signal, can also reduce the use of power supply unit, saves space.And only use a kind of testing equipment, just can to missile loading, extract and rise in perpendicular process each constantly the data of different sensors observe, improved efficiency and the reliability analyzed.
Description
Technical field
The utility model relates to structural parameters technical field of measurement and test, is specifically related to a kind of structural parameters test macro for missile loading transport test.
Background technology
Before the formal equipment of guided missile, need to load to guided missile, rise perpendicular, transport test, to investigate the harmony between body and suspender, harmony between body and horizontal loading car and launching tube, adapter, measure filling, extract in process, act on load on body, the corner circumferentially rotating, the distortion of adapter, act on the pressure on bullet, the strain of different parts on head-shield while extracting.When filling, need hood guide positioning pin to enter load suffered in dovetail groove process.While measuring the different speed that extracts, act on load, the blowing pressure and flow on body.
In missile erecting process, need to measure the leveling of load information flat pad and play time in perpendicular process, body barycenter place overload, act on load, flat pad supporting leg ground pressure on body.The adaptability of guided missile transport test examination guided missile to the motor-driven transportation environment of highway, measures the mechanical environment parameter of carrying under the motor-driven operating mode of bullet flat pad.The measurement of parameter need to be used multiple sensors, comprises displacement, load, angle etc.
Because guided missile Computer-Assisted Design, Manufacture And Test belongs to special industry, therefore very high to its reliability requirement, the sensor of its test, method are all different from conventional method of testing.In missile loading test in the past, test macro is comprised of the testing equipment of developing specially, special-purpose acquisition software, data processing software, special-purpose testing sensor and stube cable etc.Wherein the general employing of data acquisition is low-speed DAQ system, and what different sensors adopted is special-purpose separately electric power system, and test cable is also not quite similar, so testing equipment takes up room greatly.In the filling test of some models of this test macro before the several years, brought into play important function, the data of obtaining provide reliable reference for designing.But this filling test equipment, is the equipment of developing many years ago, due to time (for electronic equipment) remote.During this period of time, there is variation at full speed in sensor, measuring technology, and filling test has also proposed new demand to test, and testing scheme before and system can not meet design requirement.And in order to improve the survival probability of guided missile, guided missile, towards more motor-driven, miniaturization, lightweight future development, is therefore also like this to the requirement of test macro.
In missile loading test, need continuous measurement in filling, act on the load on body, the corner circumferentially rotating, the distortion of adapter in the overall process that extracts, act on the pressure on bullet while extracting, the strain of different parts on head-shield, needs hood guide positioning pin to enter load suffered in dovetail groove process.While measuring the different speed that extracts, act on load, the blowing pressure and flow on body.And in playing perpendicular test, also need all the sensors data in whole process to carry out continuous high sampling rate measurement.While measuring the distortion of body adapter, the non-contact displacement transducer of small-range need to be used, while measuring the distortion of launching tube nozzle, the tangent displacement sensor of wide range need to be used.When measurement is extracted, loaded, during body pressure, need to use the strain transducer by pasting after designing and calculating, and while measuring support reaction, need to use the load transducer of wide range, while measuring corner, need rotary angle transmitter etc.These sensors all belong to sensor special, so its supply voltage, output voltage are all not identical, and supporting measurement device is not identical yet with it.Therefore need to again to the test macro of missile loading transport test, design, to meet test demand.
Summary of the invention
The purpose of this utility model is to solve sensor and the unmatched problem of measurement device in existing missile loading transport test, and a kind of structural parameters test macro for missile loading transport test is provided.
The utility model is achieved in that
For a structural parameters test macro for missile loading transport test, comprise sensor electrical source adapter, testing equipment, switch, collecting computer, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor, stay wire displacement sensor and 220V alternating-current power supply, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor are arranged on guided missile and missile truck, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor is connected with sensor electrical source adapter by cable respectively with stay wire displacement sensor, sensor electrical source adapter is connected with testing equipment, switch is connected with collecting computer with testing equipment respectively, 220V alternating-current power supply respectively with sensor electrical source adapter, testing equipment is connected with switch, foil gauge and strain adapter are connected by cable with testing equipment, sensor electrical source adapter receives the power supply of 220V alternating-current power supply, and alternating voltage is converted to DC voltage, is respectively current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor power supply, guided missile and car launcher data-signal that current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor obtain detection send to respectively sensor electrical source adapter, sensor electrical source adapter receives guided missile and the car launcher data-signal that current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor send, it is converted to respectively to the receivable data-signal of testing equipment, sends to testing equipment, foil gauge and strain adapter send to testing equipment by the strain signal detecting, the strain signal that the data-signal that testing equipment receiving sensor power supply adaptor sends and foil gauge and strain adapter send, sends to switch by this data-signal and strain signal, switch receives data-signal and the strain signal that testing equipment sends, and this data-signal and strain signal are sent to collecting computer.
Testing equipment as above adopts EX1629 measurement device to realize; Switch adopts HUB to realize; Collecting computer adopts PC to realize.
Sensor electrical source adapter as above has 30 passages, uses altogether 5 passages wherein, and the input port of each passage is connected with the output port of a sensor respectively, and the output port of each passage is connected with testing equipment respectively.
Sensor electrical source adapter single channel as above comprises transformer, input port, change-over circuit A, change-over circuit B and output port; Transformer is connected with 220V alternating-current power supply, and input port is connected with transformer, and input port is connected with change-over circuit B with change-over circuit A, and change-over circuit A and change-over circuit B are connected in parallel, and change-over circuit A is connected with output port with change-over circuit B; Transformer is converted to DC voltage by 220V alternating current, and DC voltage is flowed to input port; The DC voltage that input port receiving transformer is carried, flows to the corresponding sensor connecting by DC voltage; Input port also receives guided missile and the car launcher data-signal of the corresponding sensor transmissions connecting, by guided missile and the output of car launcher data-signal; When guided missile and car launcher data-signal are current signal, disconnect change-over circuit B, change-over circuit A receives guided missile and the car launcher data-signal of the current forms of input port output, this signal is converted to the data-signal of voltage form, send to output port, output port sends to testing equipment by this signal after receiving data-signal; When guided missile and car launcher data-signal are that magnitude of voltage is while being greater than the voltage signal of 10V, disconnect change-over circuit A, change-over circuit B receives guided missile and the car launcher data-signal of the voltage form of input port output, this signal is converted to magnitude of voltage and is less than or equal to 10V data-signal, send to output port, output port sends to testing equipment by this signal after receiving data-signal; When guided missile and car launcher data-signal are that magnitude of voltage is while being less than or equal to the voltage signal of 10V, disconnect change-over circuit A and change-over circuit B, output port receives guided missile and the car launcher data-signal of the voltage form of input port transmission, data-signal is sent to testing equipment, and now guided missile and car launcher data-signal and data-signal are same signal.
Sensor electrical source adapter as above, inner at the sensor electrical source adapter single channel being connected with rotary angle transmitter, change-over circuit B is in off-state; Inner at the sensor electrical source adapter single channel being connected with stay wire displacement sensor, change-over circuit A is in off-state; Inner at the sensor electrical source adapter single channel being connected respectively with current vortex non-contact displacement sensor, bracket sensor and power sensor, change-over circuit A and change-over circuit B are all in off-state.
Input port as above adopts XS12 connector to realize; Output port adopts RJ45 Interface realization; 2 interchanges of transformer adopting turn commutator transformer and realize; Change-over circuit A adopts the resistance of one 1000 ohm to realize; Change-over circuit B adopts the resistance series connection of two 1000 ohm to realize.
The beneficial effects of the utility model are:
The utility model comprises sensor electrical source adapter, testing equipment, switch, collecting computer, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor, compare with existing test macro, the utility model is by being used sensor electrical source adapter, can use a kind of testing equipment to measure multiple sensors signal, can also reduce the use of power supply unit, save space.And only use a kind of testing equipment, just can to missile loading, extract and rise in perpendicular process each constantly the data of different sensors observe, improved efficiency and the reliability analyzed.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of structural parameters test macro for missile loading transport test of the present utility model;
Fig. 2 is the inside single channel structural representation of the sensor electrical source adapter of a kind of structural parameters test macro for missile loading transport test of the present utility model.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, a kind of structural parameters test macro for missile loading transport test of the present utility model is described in detail:
As shown in Figure 1, for a structural parameters test macro for missile loading transport test, comprise sensor electrical source adapter, testing equipment, switch, collecting computer, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor, stay wire displacement sensor and 220V alternating-current power supply.Foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor are arranged on guided missile and missile truck, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor is connected with sensor electrical source adapter by cable respectively with stay wire displacement sensor, sensor electrical source adapter is connected with testing equipment, switch is connected with collecting computer with testing equipment respectively, 220V alternating-current power supply respectively with sensor electrical source adapter, testing equipment is connected with switch, foil gauge and strain adapter are connected by cable with testing equipment.Sensor electrical source adapter receives the power supply of 220V alternating-current power supply, and alternating voltage is converted to DC voltage, is respectively current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor power supply; Guided missile and car launcher data-signal that current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor obtain detection send to respectively sensor electrical source adapter; Sensor electrical source adapter receives guided missile and the car launcher data-signal that current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor send, it is converted to respectively to the receivable data-signal of testing equipment, sends to testing equipment; Foil gauge and strain adapter send to testing equipment by the strain signal detecting, the strain signal that the data-signal that testing equipment receiving sensor power supply adaptor sends and foil gauge and strain adapter send, sends to switch by this data-signal and strain signal; Switch receives data-signal and the strain signal that testing equipment sends, and this data-signal and strain signal are sent to collecting computer.
In the present embodiment, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor all adopt existing equipment to realize, and are commercially available; Testing equipment adopts EX1629 measurement device to realize; Switch adopts HUB to realize; Collecting computer adopts PC to realize.
Sensor electrical source adapter has 30 passages, in the present embodiment, uses altogether 5 passages wherein, and the input of each passage is connected by cable with the output of a sensor respectively, and the output of each passage is connected with testing equipment by cable respectively.
As shown in Figure 2, sensor electrical source adapter single channel comprises transformer, input port, change-over circuit A, change-over circuit B and output port.Transformer is connected with 220V alternating-current power supply, and input port is connected with transformer, and input port is connected with change-over circuit B with change-over circuit A, and change-over circuit A and change-over circuit B are connected in parallel, and change-over circuit A is connected with output port with change-over circuit B.Transformer is converted to DC voltage by 220V alternating current, and DC voltage is flowed to input port; The DC voltage that input port receiving transformer is carried, flows to the corresponding sensor connecting by DC voltage; Input port also receives guided missile and the car launcher data-signal of the corresponding sensor transmissions connecting, by guided missile and the output of car launcher data-signal; When guided missile and car launcher data-signal are current signal, disconnect change-over circuit B, change-over circuit A receives guided missile and the car launcher data-signal of the current forms of input port output, this signal is converted to the data-signal of voltage form, send to output port, output port sends to testing equipment by this signal after receiving data-signal; When guided missile and car launcher data-signal are that magnitude of voltage is while being greater than the voltage signal of 10V, disconnect change-over circuit A, change-over circuit B receives guided missile and the car launcher data-signal of the voltage form of input port output, this signal is converted to magnitude of voltage and is less than or equal to 10V data-signal, send to output port, output port sends to testing equipment by this signal after receiving data-signal; When guided missile and car launcher data-signal are that magnitude of voltage is while being less than or equal to the voltage signal of 10V, disconnect change-over circuit A and change-over circuit B, output port receives guided missile and the car launcher data-signal of the voltage form of input port transmission, data-signal is sent to testing equipment, and now guided missile and car launcher data-signal and data-signal are same signal.
In the present embodiment, inner at the sensor electrical source adapter single channel being connected with rotary angle transmitter, change-over circuit B is in off-state; Inner at the sensor electrical source adapter single channel being connected with stay wire displacement sensor, change-over circuit A is in off-state; Inner at the sensor electrical source adapter single channel being connected respectively with current vortex non-contact displacement sensor, bracket sensor and power sensor, change-over circuit A and change-over circuit B are all in off-state.
Input port adopts XS12 connector to realize; Output port adopts RJ45 Interface realization; 2 existing interchanges of transformer adopting turn commutator transformer and realize, and are commercially available; Change-over circuit A adopts the resistance of one 1000 ohm to realize; Change-over circuit B adopts the resistance series connection of two 1000 ohm to realize.
The utility model comprises sensor electrical source adapter, testing equipment, switch, collecting computer, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor, compare with existing test macro, the utility model is by being used sensor electrical source adapter, can use a kind of testing equipment to measure multiple sensors signal, can also reduce the use of power supply unit, save space.And only use a kind of testing equipment, just can to missile loading, extract and rise in perpendicular process each constantly the data of different sensors observe, improved efficiency and the reliability analyzed.
Claims (6)
1. for a structural parameters test macro for missile loading transport test, it is characterized in that: it comprises sensor electrical source adapter, testing equipment, switch, collecting computer, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor, stay wire displacement sensor and 220V alternating-current power supply, foil gauge and strain adapter, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor and stay wire displacement sensor are arranged on guided missile and missile truck, current vortex non-contact displacement sensor, bracket sensor, rotary angle transmitter, power sensor is connected with sensor electrical source adapter by cable respectively with stay wire displacement sensor, sensor electrical source adapter is connected with testing equipment, switch is connected with collecting computer with testing equipment respectively, 220V alternating-current power supply respectively with sensor electrical source adapter, testing equipment is connected with switch, foil gauge and strain adapter are connected by cable with testing equipment.
2. a kind of structural parameters test macro for missile loading transport test according to claim 1, is characterized in that: described testing equipment adopts EX1629 measurement device to realize; Switch adopts HUB to realize; Collecting computer adopts PC to realize.
3. a kind of structural parameters test macro for missile loading transport test according to claim 1, it is characterized in that: described sensor electrical source adapter has 30 passages, use altogether 5 passages wherein, the input port of each passage is connected with the output port of a sensor respectively, and the output port of each passage is connected with testing equipment respectively.
4. a kind of structural parameters test macro for missile loading transport test according to claim 3, is characterized in that: described sensor electrical source adapter single channel comprises transformer, input port, change-over circuit A, change-over circuit B and output port; Transformer is connected with 220V alternating-current power supply, and input port is connected with transformer, and input port is connected with change-over circuit B with change-over circuit A, and change-over circuit A and change-over circuit B are connected in parallel, and change-over circuit A is connected with output port with change-over circuit B.
5. a kind of structural parameters test macro for missile loading transport test according to claim 4, it is characterized in that: described sensor electrical source adapter, inner at the sensor electrical source adapter single channel being connected with rotary angle transmitter, change-over circuit B is in off-state; Inner at the sensor electrical source adapter single channel being connected with stay wire displacement sensor, change-over circuit A is in off-state; Inner at the sensor electrical source adapter single channel being connected respectively with current vortex non-contact displacement sensor, bracket sensor and power sensor, change-over circuit A and change-over circuit B are all in off-state.
6. a kind of structural parameters test macro for missile loading transport test according to claim 4, is characterized in that: described input port adopts XS12 connector to realize; Output port adopts RJ45 Interface realization; 2 interchanges of transformer adopting turn commutator transformer and realize; Change-over circuit A adopts the resistance of one 1000 ohm to realize; Change-over circuit B adopts the resistance series connection of two 1000 ohm to realize.
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| CN201420347908.5U CN203928911U (en) | 2014-06-25 | 2014-06-25 | A kind of structural parameters test macro for missile loading transport test |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105241597A (en) * | 2015-09-29 | 2016-01-13 | 北京航天发射技术研究所 | Large-tonnage high-precision platform force measuring system and force measuring method |
| CN106440974A (en) * | 2016-08-02 | 2017-02-22 | 上海航天设备制造总厂 | Missile binning device |
| CN106524838A (en) * | 2016-10-14 | 2017-03-22 | 湖北航天技术研究院总体设计所 | Single-soldier rapid rocket battle field testing method and system based on network communication |
| CN114414378A (en) * | 2022-03-29 | 2022-04-29 | 北京航天和兴科技股份有限公司 | Detection system and method for missile adapter of missile packing box |
-
2014
- 2014-06-25 CN CN201420347908.5U patent/CN203928911U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105241597A (en) * | 2015-09-29 | 2016-01-13 | 北京航天发射技术研究所 | Large-tonnage high-precision platform force measuring system and force measuring method |
| CN106440974A (en) * | 2016-08-02 | 2017-02-22 | 上海航天设备制造总厂 | Missile binning device |
| CN106440974B (en) * | 2016-08-02 | 2018-01-19 | 上海航天设备制造总厂 | Guided missile boxing apparatus |
| CN106524838A (en) * | 2016-10-14 | 2017-03-22 | 湖北航天技术研究院总体设计所 | Single-soldier rapid rocket battle field testing method and system based on network communication |
| CN106524838B (en) * | 2016-10-14 | 2018-05-18 | 湖北航天技术研究院总体设计所 | A kind of quick rocket position testing method and system of individual soldier based on network communication |
| CN114414378A (en) * | 2022-03-29 | 2022-04-29 | 北京航天和兴科技股份有限公司 | Detection system and method for missile adapter of missile packing box |
| CN114414378B (en) * | 2022-03-29 | 2022-06-03 | 北京航天和兴科技股份有限公司 | Detection system and method for missile adapter of missile packing box |
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