CN105547505A - Apparatus for simulating and monitoring temperature field of missile enclosed stern compartment - Google Patents
Apparatus for simulating and monitoring temperature field of missile enclosed stern compartment Download PDFInfo
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- CN105547505A CN105547505A CN201610004154.7A CN201610004154A CN105547505A CN 105547505 A CN105547505 A CN 105547505A CN 201610004154 A CN201610004154 A CN 201610004154A CN 105547505 A CN105547505 A CN 105547505A
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- deck store
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K3/00—Thermometers giving results other than momentary value of temperature
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
The invention discloses an apparatus for simulating and monitoring a temperature field of a missile enclosed stern compartment. The apparatus comprises a combustion gas generator, a heat insulation switching cover, a simulation stern compartment, a vacuum-pumping apparatus, a first pressure release apparatus, a second pressure release apparatus, a temperature sensor, a first pressure sensor and a second pressure sensor. According to the invention, temperature distribution conditions of the missile enclosed stern compartment at an engine normal working state and an engine rear leakage state can be visually simulated and monitored, and a temperature time-space distribution rule is obtained; the test apparatus is simple and can be repeatedly used, at the same time, the test method is simple and convenient, and the test cost is low; and a mode of presetting a pressure release instruction is employed, pressure can be released timely, and the response speed is fast.
Description
Technical field
The invention belongs to solid missile technical field, be specifically related to the device in the airtight deck store temperature field of a kind of analog monitoring guided missile.
Background technology
In the flight test of the development stage of solid missile, generally telemetry system can be installed, comprising remote measurement contents such as pressure, temperature, overload, vibrations.If telemetry is abnormal in flight course, then may cause the serious consequence of fatal crass, flight failure.In certain type of missile flight test failure case, find out from flight telemetry, thermal environment data exception in the airtight deck store of guided missile.Due to guided missile remains cannot be found, finally can not locate fault.Can analogue simulation by theory calculate, but must by the checking of test.And the method for existing dependence theory calculate carrys out the Changing Pattern in temperature field in the airtight deck store of simulated missile, has unicity and limitation.
Summary of the invention
In view of this, the object of this invention is to provide the device in the airtight deck store temperature field of a kind of analog monitoring guided missile, can the accurate analog monitoring airtight deck store temperature field of guided missile.
The device in the airtight deck store temperature field of analog monitoring guided missile of the present invention, it comprises: gas generator, adiabatic transition lid, simulation deck store, vacuum extractor, the first pressure relief device, the second pressure relief device, temperature sensor, the first pressure transducer and the second pressure transducer;
Vacuum means is set to simulation deck store and provides vacuum environment; Adiabatic transition covers between gas generator and simulation deck store, and adiabatic transition lid is connected with the tail end of gas generator and the head end of simulate deck store respectively by flange, and gas generator, adiabatic transition lid, to simulate deck store coaxial; Two link positions are all with the butt-end packing of O RunddichtringO, and the tail end of simulation deck store is sealed by afterbody blanking cover;
The adiabatic transition being positioned at gas generator covers the first pressure transducer being provided with and detecting gas generator internal pressure, also be provided with the first pressure relief device, and the first pressure relief device is when opening, gas generator and simulation deck store communicate, when first pressure relief device is closed, gas generator and each self sealss of simulation deck store;
Afterbody blanking cover in simulation deck store is provided with the second pressure relief device, the second pressure transducer, and the afterbody blanking cover of simulation deck store is provided with wire screw plug; Simulation deck store inherent diverse location set temperature sensor; The wire of temperature sensor, the first pressure transducer and the second pressure transducer is all picked out by the wire screw plug of simulating deck store;
The first pressure relief device that adiabatic transition covers for jet pipe in the simulated engine course of work or rear joint area leakage phenomenon, the distribution situation of pressure in the first pressure sensor monitoring gas generator that adiabatic transition covers; Reveal after occurring, the combustion gas revealed in gas generator enters simulation deck store, the distribution situation of temperature in deck store is simulated, the distribution situation of pressure in the second pressure sensor monitoring simulation deck store on simulation deck store when multi way temperature sensor record jet pipe in simulation deck store or rear joint area leakage phenomenon occur; The second pressure relief device on simulation deck store afterbody blanking cover works when in simulation deck store, pressure reaches margin of safety, and in simulation deck store, combustion gas is discharged.
Further, temperature sensor is fixed on the inwall of simulation deck store, or is fixed on the diverse location of simulation deck store inside by afterbody blanking cover bar.
Further, the quantity of afterbody blanking cover bar is two, and level is installed on afterbody blanking cover, and distance is between the two 200cm, and diameter is 10cm, the interior length exposed of simulation deck store is 255cm.
Further, first pressure relief device comprises: be located at the relief hole that adiabatic transition covers, the stifled film covered on relief hole, the initiator that is connected with stifled film, when initiator receives electric signal, initiator explodes, stifled film rupture, combustion gas enters simulation deck store from gas generator.
The present invention has following beneficial effect:
(1) visual simulation can monitor the profiling temperatures of the airtight deck store of guided missile under engine work and engine afterbody reveal two states, obtain temperature time space distribution.
(2) this test unit is simple, and test unit is reusable, and test method is simple and convenient simultaneously, and experimentation cost is low.
(3) adopt the pattern presetting pressure release instruction, pressure release can be carried out, fast response time in good time.
Accompanying drawing explanation
Fig. 1 is the device schematic diagram in the airtight deck store temperature field of analog monitoring guided missile.
Embodiment
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
As shown in Figure 1, the device in the airtight deck store temperature field of a kind of analog monitoring guided missile comprises: gas generator 1, adiabatic transition lid 2, simulation deck store 3, vacuum extractor, the first pressure relief device, the second pressure relief device, temperature sensor 4, first pressure transducer and the second pressure transducer.Adiabatic transition lid 2 is between gas generator 1 and simulation deck store 3, adiabatic transition lid 2 is connected with the head end of simulating deck store 3 with the tail end of gas generator 1 respectively by flange, the seal form of two link positions is the butt-end packing of O RunddichtringO, and the tail end of simulation deck store 3 is sealed by afterbody blanking cover.Gas generator 1, adiabatic transition lid 2, simulation deck store 3 coaxial.
The adiabatic transition lid 2 being positioned at gas generator 1 is provided with the first pressure transducer detecting gas generator 1 internal pressure, also be provided with the first pressure relief device, when first pressure relief device is opened, gas generator 1 and simulation deck store 3 communicate, when first pressure relief device is closed, gas generator 1 and each self sealss of simulation deck store 3.
Afterbody blanking cover in simulation deck store 3 is provided with the second pressure relief device, the second pressure transducer.The afterbody blanking cover of simulation deck store 3 is provided with wire screw plug 5; Simulation deck store 3 inherent diverse location set temperature sensor 4.
Wherein, temperature sensor 4 is fixed on the inwall of simulation deck store 3, or is fixed on the diverse location of simulation deck store 3 inside by afterbody blanking cover bar.Effect is good, and the quantity of afterbody blanking cover bar is two, and level is installed on afterbody blanking cover, and distance is between the two 200cm, and diameter is 10cm, the interior length exposed of simulation deck store 3 is 255cm.
Wherein, the wire of temperature sensor 4, first pressure transducer and the second pressure transducer is all picked out by the wire screw plug 5 of simulating deck store 3.
Wherein the first pressure relief device comprises: be located at the relief hole on adiabatic transition lid 2, the stifled film covered on relief hole, the initiator that is connected with stifled film, when initiator receives electric signal, initiator explodes, stifled film rupture, and combustion gas enters simulation deck store 3 from gas generator 1.
The first pressure relief device on adiabatic transition lid 2 is used for jet pipe or rear joint area leakage phenomenon in the simulated engine course of work, the distribution situation of pressure in the first pressure sensor monitoring gas generator 1 on adiabatic transition lid 2; Reveal after occurring, the combustion gas revealed in gas generator 1 enters simulation deck store 3, the distribution situation of temperature in deck store 3 is simulated, the distribution situation of pressure in the second pressure sensor monitoring simulation deck store 3 on simulation deck store 3 when multi way temperature sensor 4 in simulation deck store 3 records jet pipe or rear joint area leakage phenomenon generation; The second pressure relief device on simulation deck store 3 afterbody blanking cover works when in simulation deck store 3, pressure reaches margin of safety, and in simulation deck store 3, combustion gas is discharged.Action is as follows:
Step 1, simulation deck store 3 is evacuated to 15kPa by vacuum extractor, closes vacuum extractor, the vacuum state in maintenance simulation deck store 35 minutes.
Step 2, open temp sensor 4, first pressure transducer and the second pressure transducer, the temperature of the diverse location of real time modelling deck store 3, and the pressure measuring gas generator 1 and simulation deck store 3 in real time.
Step 3, gas generator 1 is lighted a fire, and after burning terminates, after keeping the pressure voltage stabilizing 5s in gas generator 1, first via pressure relief device carries out pressure release, 10s after the pressure release of first via pressure relief device, and the second road pressure relief device carries out pressure release.
Step 4, by video monitoring, to obtain in sealing deck store not in the same time, the thermo parameters method curve of diverse location.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. the device in the airtight deck store temperature field of analog monitoring guided missile, it is characterized in that, comprising: gas generator (1), adiabatic transition lid (2), simulation deck store (3), vacuum extractor, the first pressure relief device, the second pressure relief device, temperature sensor (4), the first pressure transducer and the second pressure transducer;
Vacuum means is set to simulation deck store (3) and provides vacuum environment; Adiabatic transition lid (2) is positioned between gas generator (1) and simulation deck store (3), and adiabatic transition lid (2) is connected with the tail end of gas generator (1) and the head end of simulate deck store (3) respectively by flange, and gas generator (1), adiabatic transition lid (2), simulate deck store (3) coaxially; Two link positions are all with the butt-end packing of O RunddichtringO, and the tail end of simulation deck store (3) is sealed by afterbody blanking cover;
The adiabatic transition lid (2) being positioned at gas generator (1) is provided with the first pressure transducer detecting gas generator (1) internal pressure, also be provided with the first pressure relief device, and the first pressure relief device is when opening, gas generator (1) and simulation deck store (3) communicate, when first pressure relief device is closed, gas generator (1) and simulation deck store (3) each self sealss;
Afterbody blanking cover in simulation deck store (3) is provided with the second pressure relief device, the second pressure transducer, and the afterbody blanking cover of simulation deck store (3) is provided with wire screw plug (5); Simulation deck store (3) inherent diverse location set temperature sensor (4); The wire of temperature sensor (4), the first pressure transducer and the second pressure transducer is all picked out by the wire screw plug (5) of simulation deck store (3);
The first pressure relief device on adiabatic transition lid (2) is used for jet pipe or rear joint area leakage phenomenon in the simulated engine course of work, the distribution situation of the first pressure sensor monitoring gas generator (1) interior pressure on adiabatic transition lid (2); Reveal after occurring, the combustion gas revealed in gas generator (1) enters simulation deck store (3), the distribution situation of simulation deck store (3) interior temperature when multi way temperature sensor (4) record jet pipe in simulation deck store (3) or rear joint area leakage phenomenon occur, the distribution situation of the second pressure sensor monitoring simulation deck store (3) interior pressure in simulation deck store (3); The second pressure relief device on simulation deck store (3) afterbody blanking cover works when in simulation deck store (3), pressure reaches margin of safety, and the interior combustion gas of simulation deck store (3) is discharged.
2. the device in the airtight deck store temperature field of analog monitoring guided missile as claimed in claim 1, is characterized in that,
Temperature sensor (4) is fixed on the inwall of simulation deck store (3), or is fixed on the inner diverse location of simulation deck store (3) by afterbody blanking cover bar.
3. the device in the airtight deck store temperature field of analog monitoring guided missile as claimed in claim 2, is characterized in that,
The quantity of afterbody blanking cover bar is two, and level is installed on afterbody blanking cover, and distance is between the two 200cm, and diameter is 10cm, the interior length exposed of simulation deck store (3) is 255cm.
4. the device in the airtight deck store temperature field of analog monitoring guided missile as claimed in claim 1, is characterized in that,
First pressure relief device comprises: be located at the relief hole on adiabatic transition lid (2), the stifled film covered on relief hole, the initiator that is connected with stifled film, when initiator receives electric signal, initiator explodes, stifled film rupture, combustion gas enters simulation deck store (3) from gas generator (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610004154.7A CN105547505B (en) | 2016-01-05 | 2016-01-05 | A kind of device for simulating the closed deck store temperature field of monitoring guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610004154.7A CN105547505B (en) | 2016-01-05 | 2016-01-05 | A kind of device for simulating the closed deck store temperature field of monitoring guided missile |
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| CN105547505A true CN105547505A (en) | 2016-05-04 |
| CN105547505B CN105547505B (en) | 2018-02-16 |
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| CN201610004154.7A Active CN105547505B (en) | 2016-01-05 | 2016-01-05 | A kind of device for simulating the closed deck store temperature field of monitoring guided missile |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108007280A (en) * | 2017-12-28 | 2018-05-08 | 北京威标至远科技发展有限公司 | A kind of steering engine thermal protection struc ture |
| CN110132761A (en) * | 2019-05-06 | 2019-08-16 | 南京理工大学 | The measuring device of pressure needed for metallic membrane is realized pressure-bearing and ruptured |
| CN117145655A (en) * | 2023-10-27 | 2023-12-01 | 西安现代控制技术研究所 | Flexible heat-proof sealing structure for jet pipe and tail cabin of solid rocket engine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110132761A (en) * | 2019-05-06 | 2019-08-16 | 南京理工大学 | The measuring device of pressure needed for metallic membrane is realized pressure-bearing and ruptured |
| CN110132761B (en) * | 2019-05-06 | 2021-11-09 | 南京理工大学 | Use method of measuring device for realizing pressure required by pressure bearing and rupture of metal diaphragm |
| CN117145655A (en) * | 2023-10-27 | 2023-12-01 | 西安现代控制技术研究所 | Flexible heat-proof sealing structure for jet pipe and tail cabin of solid rocket engine |
| CN117145655B (en) * | 2023-10-27 | 2024-03-19 | 西安现代控制技术研究所 | Flexible heat-proof sealing structure for jet pipe and tail cabin of solid rocket engine |
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| CN105547505B (en) | 2018-02-16 |
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Inventor after: Zhang Tao Inventor after: Li Zuoshe Inventor after: Huang Chaohui Inventor after: Du Beibei Inventor after: Yang Xuan Inventor after: Hao Yanli Inventor after: Wang Yunxia Inventor after: Hui Liqin Inventor after: Zhang Yingwu Inventor before: Zhang Tao Inventor before: Li Zuoshe Inventor before: Du Beibei Inventor before: Hui Liqin Inventor before: Yang Xuan Inventor before: Wang Yunxia Inventor before: Zhang Yingwu |
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