GB1134835A - Liquid injection thrust vectoring - Google Patents
Liquid injection thrust vectoringInfo
- 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
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.
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)
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 |
-
1965
- 1965-12-06 GB GB5164965A patent/GB1134835A/en not_active Expired
Cited By (6)
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 |
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