CN104454237A - Thrust tailing residual inhibition time control device for solid rocket engine - Google Patents
Thrust tailing residual inhibition time control device for solid rocket engine Download PDFInfo
- Publication number
- CN104454237A CN104454237A CN201410674929.2A CN201410674929A CN104454237A CN 104454237 A CN104454237 A CN 104454237A CN 201410674929 A CN201410674929 A CN 201410674929A CN 104454237 A CN104454237 A CN 104454237A
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- thrust
- solid rocket
- control device
- tailing
- engine
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Abstract
The invention relates to the field of solid rocket propulsion technologies, in particular to a thrust tailing residual inhibition time control device for a solid rocket engine. A plurality of false residual gunpowder strips are arranged on the inner wall of a solid rocket combustion chamber and are made of EPDM rubber or B703-4/5-III materials. The control device has the advantages that the time at the thrust tailing stage of the solid rocket engine can be effectively shortened, the effect of inhibiting the thrust tailing stage of the engine is achieved, and stage separation between the engine and projectiles is more facilitated.
Description
Technical field
The present invention relates to Solid Rocket Propulsion field, relate to a kind of Thrust of Solid Rocket Motor hangover aftereffect specifically and suppress time-controlling arrangement.
Background technique
For the bullet solid propellant rocket needing stage separation, usually require that engine operation later stage thrust rapidly disappears, so that being separated smoothly of motor and body, therefore need to study a kind of method that solid propellant rocket suppresses thrust hangover section.Adopt the solid propellant rocket of adherent cast powder charge in its work later stage, certainly exist medicine more than certain propellant agent; Such as star hole powder charge, at the position corresponding to each star paddy, finally all can be left certain remaining powder charge, along with the burning of remaining powder charge, and motor pressure and thrust continuous decrease, the hangover section that formation time is longer, thrust is less; In order to meet the requirement of motor stage separation, generally there is strict restriction to hangover time, requiring that thrust disappears as early as possible within the as far as possible short time.
Summary of the invention
The object of the invention is to solve the problem, provide a kind of Thrust of Solid Rocket Motor hangover aftereffect to suppress time-controlling arrangement.
In order to realize object of the present invention, the technical solution used in the present invention is:
A kind of Thrust of Solid Rocket Motor hangover aftereffect suppresses time-controlling arrangement, arranges the residual medicinal strip of some vacations at grain chamber inwall.
False residual medicinal strip is EPDM rubber or B703-4 or 5-III material.
Beneficial effect of the present invention is: effectively can shorten the Thrust of Solid Rocket Motor hangover section time, plays the effect suppressing motor power hangover section, advantageously separation process between motor and body level.
Accompanying drawing explanation
Fig. 1 is the schematic diagram that the present invention is arranged on firing chamber,
Fig. 2 is schematic diagram of the present invention,
Fig. 3 is Fig. 2 left view.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: see Fig. 1, Fig. 2, Fig. 3.
A kind of Thrust of Solid Rocket Motor hangover aftereffect suppresses time-controlling arrangement, arranges the residual medicinal strip 1 of some vacations at grain chamber 3 inwall.
False residual medicinal strip 1 is EPDM rubber or B703-4 or 5-III material.
Specification of the present invention: for adherent cast propellant agent 2, before propellant agent 2 is poured into a mould, by imbedding the residual medicinal strip 1 of incombustible vacation of some in advance at firing chamber 3 inwall, false residual medicinal strip 1 can choose the material identical with firing chamber ablation layer, in engine working process, when propellant loading is burned to end, due to the existence of the residual medicinal strip 1 of vacation, effectively can reduce residue medicine block, thus shorten the motor power hangover section time, play the effect suppressing motor power hangover section.
What embodiments of the invention were announced is one of preferred embodiment; but be not limited thereto; those of ordinary skill in the art; very easily according to above-described embodiment; understand spirit of the present invention; and make different amplifications and change, but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.
Claims (2)
1. Thrust of Solid Rocket Motor hangover aftereffect suppresses a time-controlling arrangement, it is characterized in that: arrange the residual medicinal strip of some vacations at grain chamber inwall.
2. a kind of Thrust of Solid Rocket Motor hangover aftereffect according to claim 1 suppresses time-controlling arrangement, it is characterized in that: false residual medicinal strip is EPDM rubber or B703-4 or 5-III material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410674929.2A CN104454237A (en) | 2014-11-24 | 2014-11-24 | Thrust tailing residual inhibition time control device for solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410674929.2A CN104454237A (en) | 2014-11-24 | 2014-11-24 | Thrust tailing residual inhibition time control device for solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104454237A true CN104454237A (en) | 2015-03-25 |
Family
ID=52900866
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410674929.2A Pending CN104454237A (en) | 2014-11-24 | 2014-11-24 | Thrust tailing residual inhibition time control device for solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104454237A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529288A (en) * | 2019-08-28 | 2019-12-03 | 湖北三江航天江北机械工程有限公司 | Solid propellant rocket, the method and chamber structure for inhibiting medicine more than its powder charge |
| CN114060168A (en) * | 2021-11-05 | 2022-02-18 | 江西洪都航空工业集团有限责任公司 | Large initial thrust end-combustion charge solid rocket engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4972673A (en) * | 1984-10-29 | 1990-11-27 | Her Majesty The Queen As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government | Solid rocket motor with dual interrupted thrust |
| US5123355A (en) * | 1990-05-01 | 1992-06-23 | Aerotech, Inc. | Rocket ignition assembly and means and methods for making and using same |
| US20110023449A1 (en) * | 2008-10-30 | 2011-02-03 | Loehr Richard D | Insensitive Rocket Motor |
| CN204253211U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of Thrust of Solid Rocket Motor hangover aftereffect suppresses time-controlling arrangement |
-
2014
- 2014-11-24 CN CN201410674929.2A patent/CN104454237A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4972673A (en) * | 1984-10-29 | 1990-11-27 | Her Majesty The Queen As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government | Solid rocket motor with dual interrupted thrust |
| US5123355A (en) * | 1990-05-01 | 1992-06-23 | Aerotech, Inc. | Rocket ignition assembly and means and methods for making and using same |
| US20110023449A1 (en) * | 2008-10-30 | 2011-02-03 | Loehr Richard D | Insensitive Rocket Motor |
| CN204253211U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of Thrust of Solid Rocket Motor hangover aftereffect suppresses time-controlling arrangement |
Non-Patent Citations (1)
| Title |
|---|
| 夏志全: "《端面燃烧发动机研制中应注意的几个问题》", 《固体火箭技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529288A (en) * | 2019-08-28 | 2019-12-03 | 湖北三江航天江北机械工程有限公司 | Solid propellant rocket, the method and chamber structure for inhibiting medicine more than its powder charge |
| CN114060168A (en) * | 2021-11-05 | 2022-02-18 | 江西洪都航空工业集团有限责任公司 | Large initial thrust end-combustion charge solid rocket engine |
| CN114060168B (en) * | 2021-11-05 | 2024-01-19 | 江西洪都航空工业集团有限责任公司 | Large initial thrust end-combustion charge solid rocket engine |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150325 |