CN109632327A - A kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device and method - Google Patents
A kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device and method Download PDFInfo
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- CN109632327A CN109632327A CN201811598657.7A CN201811598657A CN109632327A CN 109632327 A CN109632327 A CN 109632327A CN 201811598657 A CN201811598657 A CN 201811598657A CN 109632327 A CN109632327 A CN 109632327A
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- blanking cover
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Combustion & Propulsion (AREA)
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Abstract
Provide a kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device, including firing tip blanking cover (1), simulated rocket engine (3), nozzle end blanking cover (4), witness plate (5), igniter pad (6), explosion velocity target line (7)；Simulated rocket engine (3) is the cylindrical shape of both ends open, and internal cavities are used for filling solid propellant (2)；Firing tip blanking cover (1) and nozzle end blanking cover (4) are connect by screw thread with the both ends of simulated rocket engine (3) respectively；There is reserved cavity on the inside of firing tip blanking cover (1), to place igniter pad (6), igniter pad (6) has lead to draw on the inside of firing tip blanking cover (1)；Explosion velocity target line (7) is fixed on the circumferential lateral surface surface of simulated rocket engine (3) and close to nozzle end blanking cover (4) one end；Witness plate (5) is fixed on nozzle end blanking cover (4) bottom.The deficiency that and explosion velocity signal cumbersome the invention avoids existing apparatus and burning signal interfere with each other.
Description
Technical field
The present invention relates generally to belong to solid propellant rocket security study and the field of test technology, is related to a kind of solid
Rocket engine COMBUSTION TO DETONATION TRANSITION simulation test device and method.
Background technique
Solid propellant rocket is the power source of missile armament, and safety determines the safety of missile armament.Solid
Rocket engine passes through SOLID PROPELLANT COMBUSTION in normal operation and generates the acting such as a large amount of high-temperature fuel gas, and then pushes and lead
Play the purpose that weapon realizes strike enemy.With the raising of solid propellant energy, the risk of solid propellant rocket is significant
Increase.If detonation occurs in normal working conditions for solid propellant rocket, one's own side's weapon system certainly will be generated serious
It destroys, causes the loss of a large amount of manpower, financial resources.Therefore, it is highly desirable to carry out solid propellant rocket COMBUSTION TO DETONATION TRANSITION
The research of energy.
It is reported about the experimental study of solid propellant rocket COMBUSTION TO DETONATION TRANSITION there is not yet disclosing the country.
In terms of the COMBUSTION TO DETONATION TRANSITION research of explosive wastewater etc., researchers at home and abroad have carried out a large amount of research.Burning turns
Three introduced in detonation test method Primary Reference " recommendation test and standard manual of the United Nations about Dangerous Goods Transport "
The test method of kind COMBUSTION TO DETONATION TRANSITION.That is France's DDT test method, U.S.'s DDT test method, the United Nations's DDT test method.Three
Kind test method mainly passes through the rupture of coupon, broken situation, whether determining sample detonation, and determines whether sample is sent out with this
Whether raw COMBUSTION TO DETONATION TRANSITION, 1.5 criterion should be divided into as sample." dangerous material detonation turns quick-fried to GB/T 21571-2008
Hong test method " it is consistent with France DDT test in " recommendation test and standard manual of the United Nations about Dangerous Goods Transport ".
COMBUSTION TO DETONATION TRANSITION test and " the United Nations pass in GB/T14372-2013 " approval and subitem test of Dangerous Goods Transport explosive "
In Dangerous Goods Transport recommendation test and standard manual " in U.S. DDT test it is consistent." chemicals Physical Danger test
Directive/guide " test of U.S.'s COMBUSTION TO DETONATION TRANSITION and " recommendation test and standard of the United Nations about Dangerous Goods Transport in (2014 editions)
Handbook " in U.S. DDT test it is consistent.
A kind of Xu entire PLA, engineering university, ground force, the Chinese People's Liberation Army et al. application " COMBUSTION TO DETONATION TRANSITION cavity blasting dress
Set " patent of invention.It is ignited priming, under the action of booster explosive, high explosive, COMBUSTION TO DETONATION TRANSITION cumulative by high-voltage spark
Destructor can detonate with security and stability and generate effective energy-gathering jetting, and it is broken to be suitable for micro- sonic boom.Beijing Institute of Technology Wang Li
The patent of invention of fine jade et al. application " a kind of the experimental provision influenced for convective burning on COMBUSTION TO DETONATION TRANSITION and method ", provides
A kind of experimental provision that COMBUSTION TO DETONATION TRANSITION is influenced for convective burning and method, can quantitative assessment convective burning to burning
The influence and effect for turning detonation process can be used for analyzing combustion wave caused by COMBUSTION TO DETONATION TRANSITION process, compressional wave and by pressing
Contracting wave propagates the changing rule for merging and forming shock wave, and can analyze the pass of the change in location between combustion wave and compressional wave or shock wave
System.Xi'an Inst. of Modern Chemistry Qu Kepeng et al. has applied for a kind of " test for turning detonation property for measuring gun propellant combustion
Device " patent of invention, provide a kind of experimental rig for turning detonation property for measuring gun propellant combustion, can accurately obtain
Propellant powder wave surface position-time relation data, can " equivalent " analog transmissions pipe burning situation, improve measurement transmitting
The accuracy of medicine COMBUSTION TO DETONATION TRANSITION performance test results, and increase the confidence level of measurement result.Qin's energy et al. has applied for a kind of " combustion
Burning turns Explosion measurement device and method " patent of invention, a kind of explosive wastewater COMBUSTION TO DETONATION TRANSITION test device is provided.Above-mentioned four specially
Benefit pertains only to research and the experimental test of explosive wastewater COMBUSTION TO DETONATION TRANSITION.
In recent years, the COMBUSTION TO DETONATION TRANSITION experimental study of solid propellant is more, and experimental rig and method are used for reference fire substantially and fried
The device and method of medicine COMBUSTION TO DETONATION TRANSITION.
Above-mentioned apparatus and method are not applied for solid propellant rocket COMBUSTION TO DETONATION TRANSITION experimental study, existing explosive wastewater,
Propellant combustion is turned detonation test device and gunpowder, propellant is mainly promoted to realize from burning using the strong constraint ability of DDT pipe
To the transformation of detonation, such strong constraint does not meet the reality of solid propellant rocket.Meanwhile foil gauge is used in existing method
Explosion velocity signal and burning signal are monitored with photoelectric tube, it is cumbersome, and be easy mutually to interfere.
Summary of the invention
It is an object of the invention to overcome the prior art to be not suitable for the experimental study of solid propellant rocket COMBUSTION TO DETONATION TRANSITION
Defect and existing method and the deficiency that device is cumbersome and explosion velocity signal and burning signal interfere with each other, provide a kind of solid fire
Arrow engine combustion turns detonation test device and method, promotes the research of solid propellant rocket security performance, pushes solid fire
The development of arrow engine health technology.
One aspect of the present invention provides a kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device, including firing tip
Blanking cover, simulated rocket engine, nozzle end blanking cover, witness plate, igniter pad, explosion velocity target line；The simulated rocket engine is
The cylindrical shape of both ends open, internal cavities are used for filling solid propellant；The firing tip blanking cover and nozzle end blanking cover lead to respectively
Screw thread is crossed to connect with the both ends of simulated rocket engine；There is reserved cavity on the inside of the firing tip blanking cover, to place igniter pad,
Ignition charge is surrounded by lead and draws on the inside of firing tip blanking cover；The explosion velocity target line is fixed on the circumferential lateral surface of simulated rocket engine
Surface and close nozzle end blanking cover one end；The witness plate is fixed on nozzle end blanking cover bottom.
Further, the internal diameter of above-mentioned simulated rocket engine is 50mm, and wall thickness 10mm, length is in 200mm~500mm
In range.
Further, above-mentioned explosion velocity target line is the open close target line of common enameled wire composition, work of the target line in detonation wave
Conducting electric signal can be ionized under.
Further, above-mentioned explosion velocity target line is same on cylinder heights direction on simulated rocket engine circumferential lateral surface surface
The setting of one straight line is multiple.
Further, above-mentioned explosion velocity target line setting is multiple refers to that the spacing not less than 3, between every two is not less than
50mm。
Further, above-mentioned igniter pad is made of igniter head and black powder.
The present invention also provides carry out solid fire using above-mentioned solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device
The method that arrow engine combustion turns detonation simulation test, comprising the following steps:
A) solid propellant is cast in simulated rocket engine, curing molding under the conditions of 55 DEG C~60 DEG C, and passed through
Inspection ensures pore-free inside solid propellant；
B) igniter pad is placed in firing tip blanking cover to reserve in cavity, draws the lead of igniter pad from firing tip blanking cover
Out, and by firing tip blanking cover and nozzle end blanking cover with the both ends of simulated rocket engine it is fixedly connected；
C) witness plate is fixed on nozzle end blanking cover bottom outside；
D) explosion velocity target line is fixed on simulated rocket engine circumferential lateral surface surface and close nozzle end blanking cover one end；
E) lead that lead fire pack is drawn, starts to test；
F) explosion velocity of record witness plate perforation situation and explosion velocity target line；
G) according to step f's) as a result, determine solid propellant rocket whether COMBUSTION TO DETONATION TRANSITION occurs.
Further, simulation fire is determined in step g) if apparent perforation occurs in witness plate in above-mentioned steps f)
COMBUSTION TO DETONATION TRANSITION has occurred in arrow engine.
Further, in above-mentioned steps g), if being not more than 35m/s by the explosion velocity standard deviation that explosion velocity target line is tested,
Then determine that simulated rocket engine has occurred burning and turns steady detonation in step f).
The present invention determines the ruler of simulated rocket engine according to the actual condition of solid propellant rocket and performance parameter etc.
Very little, wherein internal diameter is 50mm, and wall thickness 10mm, length is 200mm~500mm.Solid propellant is cast in simulated rocket hair
In motivation, curing molding under the conditions of 55 DEG C~60 DEG C, and ensure pore-free inside solid propellant through examining.In simulated rocket
Place one block of witness plate in engine jet pipe end bottom.Explosion velocity target line is made using enameled wire, explosion velocity target line is fixed on simulation fire
Close to nozzle-end on the axis of arrow engine outer surface, explosion velocity target line spacing is not less than 50mm, and quantity is not less than 3.Using
Igniter head and black powder etc. make igniter pad.When test, pass through igniter pad igniting solid rocket engine, observation witness plate
Perforation situation, records explosion velocity target line test result.It such as witnesses plate perforation or measures stationary detonation velocity, then can be determined that solid-rocket
COMBUSTION TO DETONATION TRANSITION has occurred in engine.
The present invention has the advantage that
1) a kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION experimental rig and method are provided, the prior art is overcome and is not suitable for
The defect of solid propellant rocket COMBUSTION TO DETONATION TRANSITION research；
2) existing method is avoided and device is cumbersome and explosion velocity signal and burning signal interfere with each other deficiency；
3) design parameter etc. that experimental rig is determined according to the actual conditions of solid propellant rocket, improves experimental rig
Applicability；
4) use is qualitative and quantitatively combines criterion of the method as solid propellant rocket COMBUSTION TO DETONATION TRANSITION, it is ensured that examination
Test the accuracy of result judgement.
Detailed description of the invention
From the detailed description with reference to the accompanying drawing to the embodiment of the present invention, these and/or other aspects of the invention and
Advantage will become clearer and be easier to understand, in which:
Fig. 1 is the structural schematic diagram of the solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device of the embodiment of the present invention；
In figure, 1- firing tip blanking cover, 2- solid propellant, 3- simulated rocket engine, 4- nozzle end blanking cover, 5- witness
Plate, 6- igniter pad, 7- explosion velocity target line.
Specific embodiment
In order to make those skilled in the art more fully understand the present invention, with reference to the accompanying drawings and detailed description to this hair
It is bright to be described in further detail.
Embodiment 1
A kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device, including firing tip blanking cover 1, simulated rocket start
Machine 3, nozzle end blanking cover 4, witness plate 5, igniter pad 6, explosion velocity target line 7；The simulated rocket engine 3 is the circle of both ends open
Tubular, internal diameter 50mm, wall thickness 10mm, within the scope of 200mm~500mm, internal cavities promote length for filling solid
Agent 2；The firing tip blanking cover 1 and nozzle end blanking cover 4 are connect by screw thread with the both ends of simulated rocket engine 3 respectively；It is described
Firing tip blanking cover 1) inside have reserved cavity, to place igniter pad 6, igniter pad 6 is made of igniter head and black powder, and is had
Lead is drawn on the inside of firing tip blanking cover 1；The open close target line of the explosion velocity target line 7 common enameled wire composition, the target line is in detonation
Conducting electric signal can be ionized under the action of wave, it is fixed on the circumferential lateral surface surface of simulated rocket engine 3 and close to jet pipe
Hold blanking cover one end；And it is arranged 3 and 3 or more along the same straight line in cylinder heights direction, the spacing between every two is not less than
50mm；The witness plate 5 is fixed on 4 bottom of nozzle end blanking cover.
Embodiment 2
By taking certain solid propellant rocket COMBUSTION TO DETONATION TRANSITION experimental study as an example, carried out using the device of the embodiment of the present invention 1
The step of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test, is as follows:
Step 1: determining that the internal diameter of simulated rocket engine 3 is according to the actual conditions of certain solid propellant rocket
50mm, wall thickness 10mm, length 500mm；
Step 2: by propellant casting in simulated rocket engine, curing molding under the conditions of 55 DEG C~60 DEG C, and pass through
Inspection ensures pore-free inside solid propellant；
Step 3: igniter pad 6 is placed in the reserved cavity of firing tip blanking cover 1, and by firing tip blanking cover 1 and two blanking covers
It is closely connect with nozzle end blanking cover 4 with the both ends of simulated rocket engine 4；
Step 4: placing one block of witness plate 5 in 3 nozzle end bottom of simulated rocket engine；
Step 6: the straight line that simulated rocket engine periphery will be fixed on using the explosion velocity target line 7 of enameled wire production
On surface and close to 4 part of nozzle end blanking cover；
Step 8: lead fire pack starts to test；
Step 9: record witness plate perforation situation and explosion velocity target line test result；
Step 10: it is puncherless according to witness plate and do not monitor the test result of explosion velocity, determine that the solid-rocket starts
COMBUSTION TO DETONATION TRANSITION does not occur for machine.
Various embodiments of the present invention are described above, above description is exemplary, and non-exclusive, and
It is not limited to disclosed each embodiment.Without departing from the scope and spirit of illustrated each embodiment, for this skill
Many modifications and changes are obvious for the those of ordinary skill in art field.Therefore, protection scope of the present invention is answered
This is subject to the protection scope in claims.
Claims (9)
1. a kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device, which is characterized in that including firing tip blanking cover (1),
Simulated rocket engine (3), nozzle end blanking cover (4), witness plate (5), igniter pad (6), explosion velocity target line (7)；
The simulated rocket engine (3) is the cylindrical shape of both ends open, and internal cavities are used for filling solid propellant (2)；Institute
Firing tip blanking cover (1) and nozzle end blanking cover (4) is stated to connect by screw thread with the both ends of simulated rocket engine (3) respectively；It is described
There is reserved cavity on the inside of firing tip blanking cover (1), to place igniter pad (6), igniter pad (6) has lead from firing tip blanking cover
(1) inside is drawn；The explosion velocity target line (7) is fixed on the circumferential lateral surface surface of simulated rocket engine (3) and close to nozzle end
Blanking cover (4) one end；The witness plate (5) is fixed on nozzle end blanking cover (4) bottom.
2. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device as claimed in claim 2, which is characterized in that the mould
The internal diameter of quasi- rocket engine (3) is 50mm, and wall thickness 10mm, length is within the scope of 200mm~500mm.
3. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device as claimed in claim 2, which is characterized in that described quick-fried
Fast target line (7) is the open close target line of common enameled wire composition, which can ionize conducting electric signal under the action of detonation wave.
4. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device according to claim 2, it is characterised in that: described
Explosion velocity target line (7) is multiple in same straight line setting of simulated rocket engine (3) the circumferential lateral surface surface on cylinder heights direction.
5. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device according to claim 4, it is characterised in that: described
Explosion velocity target line (7) is arranged multiple spacing referred to not less than 3, between every two and is not less than 50mm.
6. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device according to claim 2, it is characterised in that: described
Igniter pad (6) is made of igniter head and black powder.
7. a kind of solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation experiment method, which is characterized in that it is using such as claim 1-5
The solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation test device, comprising the following steps:
A) solid propellant is cast in simulated rocket engine (3), curing molding under the conditions of 55 DEG C~60 DEG C, and through examining
Testing ensures pore-free inside solid propellant；
B) igniter pad (6) is placed in firing tip blanking cover (1) to reserve in cavity, keeps the lead of igniter pad (6) stifled from firing tip
It covers (1) to draw, and firing tip blanking cover (1) and nozzle end blanking cover (4) is fixedly connected with the both ends of simulated rocket engine (3)；
C) witness plate (5) is fixed on nozzle end blanking cover (4) bottom outside；
D) explosion velocity target line (7) is fixed on simulated rocket engine (3) circumferential lateral surface surface and close nozzle end blanking cover (4) one
End；
E) lead that lead fire pack (6) is drawn, starts to test；
F) explosion velocity of record witness plate (5) perforation situation and explosion velocity target line (6)；
G) according to step f's) as a result, determine solid propellant rocket whether COMBUSTION TO DETONATION TRANSITION occurs.
8. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation experiment method according to claim 7, it is characterised in that: described
If apparent perforation occurs in witness plate (5) in step f), determine that (3) simulated rocket engine is fired in step g)
Burning turns detonation.
9. solid propellant rocket COMBUSTION TO DETONATION TRANSITION simulation experiment method according to claim 7, it is characterised in that: described
In step g), if the explosion velocity standard deviation tested by explosion velocity target line (7) determines mould no more than 35m/s in step f)
Quasi- rocket engine (3) have occurred burning and turn steady detonation.
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| CN110554163A (en) * | 2019-09-17 | 2019-12-10 | 西安近代化学研究所 | Sample tube for combustion-to-detonation test |
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| CN110568017A (en) * | 2019-09-03 | 2019-12-13 | 西安近代化学研究所 | Device and method for testing parameters of combustion-to-detonation process |
| CN110687162A (en) * | 2019-10-08 | 2020-01-14 | 张光辉 | Device and method for testing conversion from firework powder combustion to detonation for fireworks and crackers |
| CN110768685A (en) * | 2019-09-23 | 2020-02-07 | 四川航天川南火工技术有限公司 | Ionization signal receiver, preparation tool, preparation method and testing system of initiating device |
| CN114460222A (en) * | 2022-01-28 | 2022-05-10 | 青海青乐化工机械有限责任公司 | Smoke generating time testing device of smoke generating tank |
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| CN110687162A (en) * | 2019-10-08 | 2020-01-14 | 张光辉 | Device and method for testing conversion from firework powder combustion to detonation for fireworks and crackers |
| CN114460222A (en) * | 2022-01-28 | 2022-05-10 | 青海青乐化工机械有限责任公司 | Smoke generating time testing device of smoke generating tank |
| CN114460222B (en) * | 2022-01-28 | 2023-11-17 | 青海青乐化工机械有限责任公司 | Smoke generating time testing device of smoke generating tank |
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Application publication date: 20190416 |