GB1134835A - Liquid injection thrust vectoring - Google Patents

Liquid injection thrust vectoring

Info

Publication number
GB1134835A
GB1134835A GB5164965A GB5164965A GB1134835A GB 1134835 A GB1134835 A GB 1134835A GB 5164965 A GB5164965 A GB 5164965A GB 5164965 A GB5164965 A GB 5164965A GB 1134835 A GB1134835 A GB 1134835A
Authority
GB
United Kingdom
Prior art keywords
exhaust
orifices
shock wave
nozzle
liquid injection
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.)
Expired
Application number
GB5164965A
Inventor
Lester Therman Bankston
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.)
US Department of Navy
Original Assignee
US Department of Navy
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 US Department of Navy filed Critical US Department of Navy
Priority to GB5164965A priority Critical patent/GB1134835A/en
Publication of GB1134835A publication Critical patent/GB1134835A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

1,134,835. Deflecting propulsive jets. UNITED STATES OF AMERICA. NAVY, SECRETARY OF. 6 Dec., 1965, No. 51649/65. The thrust vector of the supersonic exhaust of, for example, a rocket motor, is deflected by the injection of liquid, e.g. N 2 O 4 or "Freon" (Registered Trade Mark), through radially directed orifices 14 in the wall of the divergent portion of the exhaust nozzle 10. This liquid increases the thrust of the rocket and produces an oblique shock wave which deflects the exhaust. For maximum effect, the shock wave should lie as far downstream as possible, but wholly within the nozzle. Four orifices are provided, arranged 90 degrees apart, and the flow from them is controlled by valves to give pitch and yaw control. Four further circumferentially directed orifices 14a, 14b are arranged in radially extending vanes 22 and provide control in roll.
GB5164965A 1965-12-06 1965-12-06 Liquid injection thrust vectoring Expired GB1134835A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5164965A GB1134835A (en) 1965-12-06 1965-12-06 Liquid injection thrust vectoring

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5164965A GB1134835A (en) 1965-12-06 1965-12-06 Liquid injection thrust vectoring

Publications (1)

Publication Number Publication Date
GB1134835A true GB1134835A (en) 1968-11-27

Family

ID=10460855

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5164965A Expired GB1134835A (en) 1965-12-06 1965-12-06 Liquid injection thrust vectoring

Country Status (1)

Country Link
GB (1) GB1134835A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2405456A1 (en) * 1977-10-06 1979-05-04 Bayern Chemie Gmbh Flugchemie MISSILE TELEGUIDE WITH DEVICE TO GENERATE A MOMENT OF TANGAGE, LACING AND ROLL
GB2428413A (en) * 2005-02-24 2007-01-31 Rolls Royce Plc Fluid vectoring nozzle
US7658337B2 (en) 2005-02-24 2010-02-09 Rolls-Royce Plc Fluid vectoring nozzle
CN116929159A (en) * 2023-09-18 2023-10-24 北京星河动力装备科技有限公司 Carrier rocket with solid-liquid hybrid power and launching method thereof

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2405456A1 (en) * 1977-10-06 1979-05-04 Bayern Chemie Gmbh Flugchemie MISSILE TELEGUIDE WITH DEVICE TO GENERATE A MOMENT OF TANGAGE, LACING AND ROLL
GB2428413A (en) * 2005-02-24 2007-01-31 Rolls Royce Plc Fluid vectoring nozzle
GB2428413B (en) * 2005-02-24 2008-02-20 Rolls Royce Plc Fluid vectoring nozzle
US7658337B2 (en) 2005-02-24 2010-02-09 Rolls-Royce Plc Fluid vectoring nozzle
CN116929159A (en) * 2023-09-18 2023-10-24 北京星河动力装备科技有限公司 Carrier rocket with solid-liquid hybrid power and launching method thereof
CN116929159B (en) * 2023-09-18 2024-01-09 北京星河动力装备科技有限公司 Carrier rocket with solid-liquid hybrid power and launching method thereof

Similar Documents

Publication Publication Date Title
US3204405A (en) Three dimensional jet vectoring system
US2943821A (en) Directional control means for a supersonic vehicle
US3135291A (en) Bistable fluid valve
US3285262A (en) Aerodynamic or hydrodynamic servovalve, especially for use for the guidance and stabilisation of rockets
US3468487A (en) Variable thrust injector
GB1102625A (en) Stabilisation and guidance device for sounding rockets and rocket-propelled ballistic vehicles
RU2004103185A (en) INCREASING THE ROCKET OF THE ROCKET OF THE AIRCRAFT INSIDE THE EXPANDING PART OF THE NOZZLE
US3740003A (en) Secondary injection/jet reaction control
US3144751A (en) Hybrid rocket
US3132476A (en) Thrust vector control apparatus
GB982440A (en) Rocket propelled missile
US3325103A (en) Thrust vector control for reaction engines
US3221498A (en) Secondary fluid injection thrust vectoring methods and apparatus
GB1134835A (en) Liquid injection thrust vectoring
GB1185193A (en) Improvements in or relating to Flying Bodies
US3093157A (en) Metering and mixing apparatus
US3606165A (en) Jet reaction control system for rockets
US3292865A (en) Thrust vector control with clustered nozzles
US3255971A (en) Jet thrust vector control apparatus
US3229460A (en) Tertiary injector for propulsion system roll control
US3144752A (en) Injection thrust vectoring
GB900040A (en) Exhaust nozzle with thrust deflector
US3645475A (en) Fluid amplifier with direct-coupled gyrocontrol
US3273801A (en) Rocket acceleration and direction control by fluid injection
US4003531A (en) Reverse flow reaction control system