JPS562448A - Controlling method of thrust for missile - Google Patents
Controlling method of thrust for missileInfo
- Publication number
- JPS562448A JPS562448A JP7953279A JP7953279A JPS562448A JP S562448 A JPS562448 A JP S562448A JP 7953279 A JP7953279 A JP 7953279A JP 7953279 A JP7953279 A JP 7953279A JP S562448 A JPS562448 A JP S562448A
- Authority
- JP
- Japan
- Prior art keywords
- thrust
- missile
- combustion
- propellant
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
Abstract
PURPOSE:To control very easily the thrust of a missile to an optional value while the missile is flying, by supplying its propellant of slurry state into the combustion gas of solid propellant while adjusting its supply amount. CONSTITUTION:While a ram rocket 1 is flying, a solid propellant grain 2 is gradually burnt in a primary combustion chamber 6 with the inner face of its inner hole 2a as a combustion face. By this combustion, inflammable combustion gas contg. a large amount of CO, HC and H2 is generated and filled in a primary combustion chamber 6 at high pressure. Then the combustion gas is injected from a nozzle 8 into a secondary combustion chamber 7, mixed with the outside air inducted through a diffuser 9, ignited and then jetted from a tail nozzle 3. At this time, to increase its thrust, a valve 13 is opened to supply the propellant of slurry state in a slurry tank 11 into the inner hole 2a by the pressure of a high pressure source 14, thus to obtain an increase of the thrust.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP7953279A JPS562448A (en) | 1979-06-22 | 1979-06-22 | Controlling method of thrust for missile |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP7953279A JPS562448A (en) | 1979-06-22 | 1979-06-22 | Controlling method of thrust for missile |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS562448A true JPS562448A (en) | 1981-01-12 |
Family
ID=13692593
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP7953279A Pending JPS562448A (en) | 1979-06-22 | 1979-06-22 | Controlling method of thrust for missile |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS562448A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20160021381A (en) * | 2014-08-14 | 2016-02-25 | 현대로템 주식회사 | A Gas flow adjuster |
-
1979
- 1979-06-22 JP JP7953279A patent/JPS562448A/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20160021381A (en) * | 2014-08-14 | 2016-02-25 | 현대로템 주식회사 | A Gas flow adjuster |
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