JPS56113029A - Injector of ram rocket - Google Patents

Injector of ram rocket

Info

Publication number
JPS56113029A
JPS56113029A JP1615880A JP1615880A JPS56113029A JP S56113029 A JPS56113029 A JP S56113029A JP 1615880 A JP1615880 A JP 1615880A JP 1615880 A JP1615880 A JP 1615880A JP S56113029 A JPS56113029 A JP S56113029A
Authority
JP
Japan
Prior art keywords
combustible gas
injector
gas
super
forming
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
Application number
JP1615880A
Other languages
Japanese (ja)
Inventor
Shinji Notake
Takuo Kuwabara
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nissan Motor Co Ltd
Original Assignee
Nissan Motor Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Nissan Motor Co Ltd filed Critical Nissan Motor Co Ltd
Priority to JP1615880A priority Critical patent/JPS56113029A/en
Priority to DE19813104680 priority patent/DE3104680C2/en
Priority to FR8102708A priority patent/FR2475634B1/en
Publication of JPS56113029A publication Critical patent/JPS56113029A/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/403—Solid propellant rocket engines
    • B64G1/404—Hybrid rocket engines
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/403—Solid propellant rocket engines

Abstract

PURPOSE: To maintain secondary combustion and increase propulsion force, by forming the super-expansion nozzle part in which combustion gas is dispersed positively at the top end side of an injector, and by forming the flame piloting part where fuel is mixed with air and ignited by forming a number of penetration holes, at the rear end side.
CONSTITUTION: When the combustible gas which passed inside an injector 25 passes through the super-expansion nozzle part 26, the gas super-exapands and is accelerated to a supersonic speed, and at the point P, is exfoliated from the inner surface of the sper-expansion nozzle part 26, and a part of the combustible gas flows in rectilinear form parallel to the axis line of a ram rocket 14 towards a tail nozzle 31 in the falme piloting part 27, and the rest of the combustible gas is dispersed violently in the negative pressure range between the inner wall of the injector 25 and the combustible gas in rectilinear flow at the back from the point P. At the same time, the outside air flows-in sharply from penetration holes 28, due to the negative pressure, and is mixed with the combustible gas, and ignition source can be kept. The combustible gas and outside air are combusted in the secondary combustion chamber 18, and the combustion gas in high temperature is jetted from a tail nozzle 31.
COPYRIGHT: (C)1981,JPO&Japio
JP1615880A 1980-02-12 1980-02-12 Injector of ram rocket Pending JPS56113029A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
JP1615880A JPS56113029A (en) 1980-02-12 1980-02-12 Injector of ram rocket
DE19813104680 DE3104680C2 (en) 1980-02-12 1981-02-10 Ramjet rocket engine
FR8102708A FR2475634B1 (en) 1980-02-12 1981-02-11 STATOREACTOR ROCKET

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1615880A JPS56113029A (en) 1980-02-12 1980-02-12 Injector of ram rocket

Publications (1)

Publication Number Publication Date
JPS56113029A true JPS56113029A (en) 1981-09-05

Family

ID=11908691

Family Applications (1)

Application Number Title Priority Date Filing Date
JP1615880A Pending JPS56113029A (en) 1980-02-12 1980-02-12 Injector of ram rocket

Country Status (3)

Country Link
JP (1) JPS56113029A (en)
DE (1) DE3104680C2 (en)
FR (1) FR2475634B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107795409A (en) * 2017-06-09 2018-03-13 胡建新 A kind of solid rocket ramjet gas flow adjusting means

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3502673A1 (en) * 1985-01-26 1986-07-31 Rheinmetall GmbH, 4000 Düsseldorf AIR-BREATHING SOLID STRAIGHT DRIVE
FR3006380B1 (en) * 2013-05-31 2017-05-19 Pierre Francois Yannick Agostini AEROBIC AND ANAEROBIC TYPE HYBRID PROPULSION DEVICE HAVING PERMANENT COMBINED TYPE AND SIMULTANEOUS TYPE OPERATION AND SYSTEM AND PROPULSED ASSEMBLIES INCLUDING SUCH A DEVICE
CN107795408B (en) * 2017-06-09 2019-08-06 胡建新 A kind of unchoked solid rocket ramjet gas flow regulating device

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2744384A (en) * 1952-08-09 1956-05-08 United Aircraft Corp Burner construction for high velocity gases
FR1112986A (en) * 1954-10-22 1956-03-21 Reactor
GB835295A (en) * 1957-04-10 1960-05-18 Napier & Son Ltd Gas generators of the hydrogen peroxide decomposer and fuel combustion chamber type
US2999672A (en) * 1958-04-09 1961-09-12 Curtiss Wright Corp Fluid mixing apparatus
US3055178A (en) * 1960-02-01 1962-09-25 Donald G Phillips Ramjet ignition system
US4063415A (en) * 1972-06-30 1977-12-20 The United States Of America As Represented By The Secretary Of The Army Apparatus for staged combustion in air augmented rockets
US3802192A (en) * 1972-10-04 1974-04-09 Us Air Force Integral rocket-ramjet with combustor plenum chamber
US3807169A (en) * 1973-06-13 1974-04-30 Us Air Force Integral precombustor/ramburner assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107795409A (en) * 2017-06-09 2018-03-13 胡建新 A kind of solid rocket ramjet gas flow adjusting means

Also Published As

Publication number Publication date
DE3104680A1 (en) 1981-12-24
FR2475634B1 (en) 1986-08-01
DE3104680C2 (en) 1983-05-11
FR2475634A1 (en) 1981-08-14

Similar Documents

Publication Publication Date Title
Schulte Fuel regression and flame stabilization studies of solid-fuel ramjets
GB1136543A (en) Liquid fuel combustion apparatus for gas turbine engines
GB669014A (en) Improvements relating to jet-propelled missiles
JPS54137128A (en) Combustion controller
JPS54116515A (en) Igniter with torch
US3008669A (en) Ramjet missile
JPS56113029A (en) Injector of ram rocket
GB577865A (en) Liquid-fuel combustion-chamber
US3124933A (en) Leroy stram
GB895015A (en) Improvements in or relating to jet propulsion devices
US2867979A (en) Apparatus for igniting fuels
GB704468A (en) Improvements in or relating to combustion chambers for liquid, gaseous or pulverisedsolid fuels
US5317866A (en) Free-flying tubular vehicle
US2658340A (en) Apparatus for igniting fuel in fast-moving hot gas streams
JPS562444A (en) Ram rocket
JPS57131845A (en) Ram rocket
SU1796040A3 (en) Device for producing thrust
US5125828A (en) Granite flame finishing internal burner
JPS57131846A (en) Ram rocket
JPS562445A (en) Ram rocket
FR2402773A1 (en) Combined rocket and ram jet engine - has common combustion chamber containing rocket fuel
US3841092A (en) Regenerative ram jet engine
JPS5735114A (en) Method of burning mixture in internal combustion engine and device for dividing said mixture
GB1046916A (en) Rocket combustion chamber and method of feeding liquid propellents thereto
GB618886A (en) Rocket