CN104481735A - Pulse trigger - Google Patents
Pulse trigger Download PDFInfo
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- CN104481735A CN104481735A CN201410482191.XA CN201410482191A CN104481735A CN 104481735 A CN104481735 A CN 104481735A CN 201410482191 A CN201410482191 A CN 201410482191A CN 104481735 A CN104481735 A CN 104481735A
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- cavity
- cassette body
- drug cassette
- ignition tube
- plug
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Abstract
The invention provides a pulse trigger. A medicine box is a hollow chamber; a thermal insulating layer covers the internal wall of the chamber; the chamber is full of ignition powder; two ends of the medicine box are respectively connected with an end cap and a connecting chamber assembly; the middle of the end cap is fixedly connected with an ignition tube; the connecting chamber is a through hollow chamber; the thermal insulating layer covers the internal wall of the chamber; a separation plate is arranged and positioned inside the connecting chamber through a supporting ring; the separation plate is provided with a plurality of through holes; a communicating part of the medicine box and the connecting chamber positions a sealing piston assembly through a stepped hole; the sealing piston assembly comprises a sealing piston and a thermal insulating layer; the sealing piston seals the communicating position of the medicine box and the connecting chamber and can be separated under combustion pressure of ignition powder; the medicine box and the connecting chamber are guaranteed to be communicated; the thermal insulating layer covers the sealing piston. The pulse trigger can increase the working pressure strong pulse by 0 to 20% in 0 to 5millisecond short time at any time during working of and engine and saves target range test costs.
Description
Technical field
The present invention relates to Solid Rocket Engine Test checking field.
Background technique
Pulse trigger is one of important technology of solid propellant rocket pulse triggering rough burning ground validation, adopts pulse trigger effectively can verify solid propellant rocket pulse triggering rough burning phenomenon.Abroad carry out more for many years to solid propellant rocket pulse triggering rough burning research, corresponding research theory and analytical method are gradually improved, but all these research and analysis carried out all go back Shortcomings part for effective checking of rough burning, particularly domestic, at present for the rough burning ground validation technology famine of solid propellant rocket.
Secondly external research in pulse trigger is mainly used in the verification experimental verification of compression ratio engine, and the checking of big-block engine is less, due to technical know-how reason, can Query Result less.
Summary of the invention
In order to overcome the deficiencies in the prior art, the invention provides a kind of flip flop equipment, solve solid propellant rocket and do not occur rough burning in ground experiment, and a ground validation difficult problem for rough burning phenomenon appearring in flight test.As one of the deriving technology of Solid Rocket Motor Ground Test technology, pulse trigger achieves the test demand occurring the phenomenon ground validation of rough burning in solid propellant rocket flight test, has saved the cost of range test.
The technical solution adopted for the present invention to solve the technical problems is: comprise plug, ignition tube, drug cassette body assembly, ignition powder, sealing plug assembly, connect cavity components, support ring and dividing plate.
Described drug cassette body assembly comprises drug cassette body and thermal-protective coating, and drug cassette body is hollow cavity, cavity inner wall cover thermal-protective coating, filling point gunpowder in cavity, drug cassette body two ends be connected respectively plug be connected cavity components, perforate in the middle part of plug, connects firmly ignition tube in hole; Described connection cavity components comprises and connects cavity and thermal-protective coating, and connecting cavity is through hollow cavity, and thermal-protective coating covers cavity inner wall, and dividing plate is positioned at by support ring filling and connects in cavity, dividing plate has some through holes; Drug cassette body passes through step hole location sealing plug assembly with the connection position being connected cavity, sealing plug assembly comprises sealing plug and thermal-protective coating, sealing plug closes drug cassette body and the connection position being connected cavity, and can deviate under the firing pressure of ignition powder, guarantee drug cassette body and be connected cavity and be communicated with, sealing plug surface coverage thermal-protective coating.
Described ignition tube comprises connector, wire, ignition tube housing, bridge silk and main charge, and connector is by wire connecting bridge silk and ignition tube housing, and main charge is seated in ignition tube housing.
Described plug with between ignition tube, between plug with drug cassette body, between sealing plug with drug cassette body, drug cassette body all sealed by Sealing with being connected between cavity.
Described plug, drug cassette body, connection cavity, dividing plate and support ring selected materials are 45 steel, T250, D6AC or 30CrMnSiA.
Described ignition tube selects No. 1 point ignition tube, Y8C, Y8D or DHQ-3E ignition tube, and ignition tube D.C. resistance is 0.8 Ω ~ 1.0 Ω, and insulation resistance is greater than 5M Ω.
Described thermal-protective coating selected materials has Ethylene Propylene Terpolymer or silicone rubber.
Described ignition powder selects boron potassium nitrate aluminium potassium perchlorate, magnesium teflon or black gunpowder.
2A12 aluminium selected by described sealing plug.
Sealing member material copper between described plug and ignition tube, all the other Sealings select silicone rubber or fluorine rubber.
The invention has the beneficial effects as follows: a kind of device that the invention belongs to solid propellant rocket pulse triggering rough burning checking, structure is simple, compact, clear principle, reliability is high, engine head and afterbody can be arranged on, realize engine operation any time increase by 0 ~ 5ms in short-term 0 ~ 20% operating pressure pulse, thus checking solid propellant rocket pulse triggering rough burning.By the needs adopting pulse trigger to can be implemented in the triggering of predetermined instant multiple pulses.Realize unstable ground and the checking of engine operation stability.For the design improvement of solid propellant rocket provides technical support.Verified by the pulse triggering of multiple model solid propellant rocket, prove this invention Be very effective.A kind of effective verification method is provided to the ground validation of rough burning.
The material that the present invention adopts all domesticizes, and wide material sources, good manufacturability, the process-cycle is shorter, and conforming product rate is high, and cost is low, high conformity.
Present invention also extends to other solid propellant rockets, as a kind of means of the demonstration test of pulse triggering rough burning.Pulse trigger technology is one of key technology of China's following solid propellant rocket checking rough burning, and the present invention's invention is that important tests verification technique basis is established in the development of following high-performance anti-air defence sky guided missile solid propellant rocket.
Accompanying drawing explanation
Fig. 1 is trigger structure schematic diagram;
Fig. 2 is stopper structure schematic diagram;
Fig. 3 is drug cassette body structural section figure;
Fig. 4 is plug construction sectional view;
Fig. 5 is connection chamber body section figure;
Fig. 6 is diaphragm structure sectional view, and wherein, (a) is sectional view, and (b) is plan view;
Fig. 7 is that the engine impulse device of embodiment 1 triggers pressure curve figure;
Fig. 8 is that the engine impulse device of embodiment 2 triggers pressure curve figure;
In figure, 1-plug; 2-Sealing; 3-ignition tube; 4-Sealing; 5-drug cassette body assembly; 6-ignition powder; 7-Sealing; 8-Sealing; 9-sealing plug; 10-connects cavity components; 11-support ring; 12-dividing plate.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described, the present invention includes but be not limited only to following embodiment.
The invention provides a kind of pulse trigger, have in short-term, the instantaneous feature that pressure pulse is provided.Novel pulse trigger of the present invention can provide the hot operation pressure pulse of instantaneous (0 ~ 5ms) 0 ~ 20% to schedule, and can long time.Between stand the requirement of solar heat protection under solid propellant rocket work high temperature (about 3600K), high pressure (0 ~ 20MPa) property, sealing.
The technical solution adopted for the present invention to solve the technical problems is, comprises plug, ignition tube, drug cassette body assembly, ignition powder, sealing plug assembly, connects cavity components, support ring, dividing plate and Sealing composition.Installation relation is as follows: plug and ignition tube adopt M14 × 1 to be threaded, and plug and drug cassette body assembly adopt M48 × 1 to be threaded, and drug cassette body assembly is connected cavity components and adopts M45 × 1.5 to be threaded with part.
Plug machine of the present invention adds shaping, is connected with medicine frame set by screw thread; Described ignition tube mainly comprises connector, wire, ignition tube housing, bridge silk and main charge, and connector is connected with bridge silk, ignition tube housing by wire, and main charge is seated in ignition tube housing, and the screw thread that ignition tube passes through is connected with plug; Described drug cassette body assembly comprises drug cassette body, thermal-protective coating, and drug cassette body machine adds shaping, and thermal-protective coating is molding, and thermal-protective coating is bonded in drug cassette body by adhesive glue, and drug cassette body is connected with plug, connection cavity components by screw thread; Described ignition powder outsourcing, is seated in drug cassette body assembly; Sealing plug assembly comprises sealing plug and thermal-protective coating, and thermal-protective coating is molding, and by being bonded on sealing plug, sealing plug is that machine adds shaping, and sealing plug assembly is seated on drug cassette body assembly; Described connection cavity components comprises and connects cavity, thermal-protective coating and heat insulating tube, connecting cavity is that machine adds shaping, thermal-protective coating and heat insulating tube die forming, and thermal-protective coating connects on cavity by gluing being connected on, connect cavity machine and add shaping, connection cavity components is crossed and is threaded on drug cassette body assembly; Support ring machine adds shaping, and be seated in and connect in cavity components, partition machine adds shaping, and be seated in and connect in cavity, Sealing is made up of frame member and molding.
2) plug, drug cassette body, connection cavity, dividing plate and support ring, according to above-mentioned characteristic, selected materials has 45 steel, T250, D6AC or 30CrMnSiA.
3) ignition tube, according to above-mentioned characteristic, selected ignition tube has No. 1 point ignition tube, Y8C, Y8D, DHQ-3E ignition tube, and ignition tube D.C. resistance is 0.8 Ω ~ 1.0 Ω, and insulation resistance is greater than 5M Ω.
5) thermal-protective coating, according to above-mentioned characteristic, selected materials has Ethylene Propylene Terpolymer, silicone rubber.
6) ignition powder, according to above-mentioned characteristic, can select boron potassium nitrate aluminium potassium perchlorate or magnesium teflon and black gunpowder, concrete dose is according to following formulae discovery:
wherein K is correction factor, and K gets 1, P herein
igfor igniter pressure, ε is the percentage of solid particle in igniting combustion gas, and R is universal gas constant, and M is igniting combustion gas mean molecule quantity, T
igfor igniting fuel gas temperature, Vc is initial free volume.
7) sealing plug, according to above-mentioned characteristic, selects 2A12 aluminium.
8) Sealing, according to above-mentioned characteristic, ignition tube sealing member material copper, all the other can select silicone rubber, fluorine rubber.
Before pulse trigger does not work, rely on when engine operation the indoor pressure of engine combustion by sealing plug assembly tightly be arranged in drug cassette body, when flip-flop operation, sealing plug assembly is opened, combustion gas proceeds to engine chamber by dividing plate and heat insulating tube, realizes transient pulse and triggers.Fig. 2 is shown in by pulse trigger structural drawing.
Motor triggers embodiment 1:
Engine impulse device triggers pressure curve as shown in Figure 7.
Pulse trigger overall size: Φ 60mm × 205.5mm; Fuel gas inlet diameter: Φ 14mm; Trigger dose: 45g; Triggering times: 2 times; Triggered time engine operation: 15s, 17s; Activation pressure: 0.22MPa, 0.28MPa; The trigger action time: 2ms.
Motor triggers embodiment 2:
Engine impulse device triggers pressure curve as shown in Figure 8.
Pulse trigger overall size: Φ 60mm × 205.5mm; Fuel gas inlet diameter: Φ 14mm; Trigger dose: 65g; Triggering times: 1 time; Triggered time engine operation: 4.5s; Activation pressure: 2.59MPa; The trigger action time: 2.3ms.
Claims (9)
1. a pulse trigger, comprise plug, ignition tube, drug cassette body assembly, ignition powder, sealing plug assembly, connect cavity components, support ring and dividing plate, it is characterized in that: described drug cassette body assembly comprises drug cassette body and thermal-protective coating, drug cassette body is hollow cavity, cavity inner wall cover thermal-protective coating, filling point gunpowder in cavity, drug cassette body two ends be connected respectively plug be connected cavity components, perforate in the middle part of plug, connects firmly ignition tube in hole; Described connection cavity components comprises and connects cavity and thermal-protective coating, and connecting cavity is through hollow cavity, and thermal-protective coating covers cavity inner wall, and dividing plate is positioned at by support ring filling and connects in cavity, dividing plate has some through holes; Drug cassette body passes through step hole location sealing plug assembly with the connection position being connected cavity, sealing plug assembly comprises sealing plug and thermal-protective coating, sealing plug closes drug cassette body and the connection position being connected cavity, and can deviate under the firing pressure of ignition powder, guarantee drug cassette body and be connected cavity and be communicated with, sealing plug surface coverage thermal-protective coating.
2. pulse trigger according to claim 1, is characterized in that: described ignition tube comprises connector, wire, ignition tube housing, bridge silk and main charge, and connector is by wire connecting bridge silk and ignition tube housing, and main charge is seated in ignition tube housing.
3. pulse trigger according to claim 1, is characterized in that: described plug with between ignition tube, between plug with drug cassette body, between sealing plug with drug cassette body, drug cassette body all sealed by Sealing with being connected between cavity.
4. pulse trigger according to claim 1, is characterized in that: described plug, drug cassette body, connection cavity, dividing plate and support ring selected materials are 45 steel, T250, D6AC or 30CrMnSiA.
5. pulse trigger according to claim 1, is characterized in that: described ignition tube selects No. 1 point ignition tube, Y8C, Y8D or DHQ-3E ignition tube, and ignition tube D.C. resistance is 0.8 Ω ~ 1.0 Ω, and insulation resistance is greater than 5M Ω.
6. pulse trigger according to claim 1, is characterized in that: described thermal-protective coating selected materials has Ethylene Propylene Terpolymer or silicone rubber.
7. pulse trigger according to claim 1, is characterized in that: described ignition powder selects boron potassium nitrate aluminium potassium perchlorate, magnesium teflon or black gunpowder.
8. pulse trigger according to claim 1, is characterized in that: 2A12 aluminium selected by described sealing plug.
9. pulse trigger according to claim 1, is characterized in that: the sealing member material copper between described plug and ignition tube, all the other Sealings select silicone rubber or fluorine rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410482191.XA CN104481735A (en) | 2014-09-19 | 2014-09-19 | Pulse trigger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410482191.XA CN104481735A (en) | 2014-09-19 | 2014-09-19 | Pulse trigger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104481735A true CN104481735A (en) | 2015-04-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410482191.XA Pending CN104481735A (en) | 2014-09-19 | 2014-09-19 | Pulse trigger |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300875A (en) * | 2015-10-23 | 2016-02-03 | 西安近代化学研究所 | Explosive loading continuous multi-pulse-load loading experiment device |
| CN107044362A (en) * | 2016-12-07 | 2017-08-15 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN107061050A (en) * | 2017-04-20 | 2017-08-18 | 西安航天动力研究所 | A kind of pulse rifle |
| CN107529585A (en) * | 2017-03-30 | 2018-01-02 | 内蒙动力机械研究所 | A kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket |
| CN109505712A (en) * | 2019-01-15 | 2019-03-22 | 北京理工大学 | It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability |
| CN110027373A (en) * | 2019-05-14 | 2019-07-19 | 北京理工大学 | A kind of hovercar safety assisting system based on pulse high explosive powder attitude regulation |
| CN110153260A (en) * | 2019-06-06 | 2019-08-23 | 南京理工大学 | A kind of igniter cartridge mold |
| CN110595782A (en) * | 2019-08-18 | 2019-12-20 | 南京理工大学 | Shaft-diameter mixed double-pulse soft interlayer work simulation device |
| CN110596180A (en) * | 2019-08-18 | 2019-12-20 | 南京理工大学 | Ablation simulation fixing device for engine interstage protective material |
| CN113153579A (en) * | 2021-05-24 | 2021-07-23 | 北京理工大学 | Pulse trigger for measuring pressure coupling response function of composite propellant |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1057996A2 (en) * | 1999-05-31 | 2000-12-06 | DaimlerChrysler AG | Solid propellant device for a ram jet |
| CN2497060Y (en) * | 2001-06-18 | 2002-06-26 | 内蒙古北方保安民爆器材有限公司 | Assembled rain-increasing anti-hail rocket engine |
| CN202900445U (en) * | 2012-09-17 | 2013-04-24 | 浙江大学 | Boryl solid fuel propulsion device using plasma generator to ignite |
| CN103075270A (en) * | 2013-01-15 | 2013-05-01 | 西北工业大学 | High-pressure-intensity external pulse excitation device for T-shaped burner |
-
2014
- 2014-09-19 CN CN201410482191.XA patent/CN104481735A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1057996A2 (en) * | 1999-05-31 | 2000-12-06 | DaimlerChrysler AG | Solid propellant device for a ram jet |
| CN2497060Y (en) * | 2001-06-18 | 2002-06-26 | 内蒙古北方保安民爆器材有限公司 | Assembled rain-increasing anti-hail rocket engine |
| CN202900445U (en) * | 2012-09-17 | 2013-04-24 | 浙江大学 | Boryl solid fuel propulsion device using plasma generator to ignite |
| CN103075270A (en) * | 2013-01-15 | 2013-05-01 | 西北工业大学 | High-pressure-intensity external pulse excitation device for T-shaped burner |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300875B (en) * | 2015-10-23 | 2018-04-20 | 西安近代化学研究所 | The continuous multiple-pulse load loading experimental apparatus of explosive loading |
| CN105300875A (en) * | 2015-10-23 | 2016-02-03 | 西安近代化学研究所 | Explosive loading continuous multi-pulse-load loading experiment device |
| CN107044362A (en) * | 2016-12-07 | 2017-08-15 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN107044362B (en) * | 2016-12-07 | 2018-12-11 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN107529585B (en) * | 2017-03-30 | 2023-05-05 | 内蒙动力机械研究所 | Melt film type partition plate suitable for multi-pulse solid rocket engine |
| CN107529585A (en) * | 2017-03-30 | 2018-01-02 | 内蒙动力机械研究所 | A kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket |
| CN107061050A (en) * | 2017-04-20 | 2017-08-18 | 西安航天动力研究所 | A kind of pulse rifle |
| CN109505712A (en) * | 2019-01-15 | 2019-03-22 | 北京理工大学 | It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability |
| CN110027373A (en) * | 2019-05-14 | 2019-07-19 | 北京理工大学 | A kind of hovercar safety assisting system based on pulse high explosive powder attitude regulation |
| CN110153260A (en) * | 2019-06-06 | 2019-08-23 | 南京理工大学 | A kind of igniter cartridge mold |
| CN110595782A (en) * | 2019-08-18 | 2019-12-20 | 南京理工大学 | Shaft-diameter mixed double-pulse soft interlayer work simulation device |
| CN110596180A (en) * | 2019-08-18 | 2019-12-20 | 南京理工大学 | Ablation simulation fixing device for engine interstage protective material |
| CN113153579A (en) * | 2021-05-24 | 2021-07-23 | 北京理工大学 | Pulse trigger for measuring pressure coupling response function of composite propellant |
| CN113153579B (en) * | 2021-05-24 | 2022-05-27 | 北京理工大学 | Pulse trigger for measuring pressure coupling response function of composite propellant |
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Application publication date: 20150401 |