FR2405456A1 - MISSILE TELEGUIDE WITH DEVICE TO GENERATE A MOMENT OF TANGAGE, LACING AND ROLL - Google Patents
MISSILE TELEGUIDE WITH DEVICE TO GENERATE A MOMENT OF TANGAGE, LACING AND ROLLInfo
- Publication number
- FR2405456A1 FR2405456A1 FR7828241A FR7828241A FR2405456A1 FR 2405456 A1 FR2405456 A1 FR 2405456A1 FR 7828241 A FR7828241 A FR 7828241A FR 7828241 A FR7828241 A FR 7828241A FR 2405456 A1 FR2405456 A1 FR 2405456A1
- Authority
- FR
- France
- Prior art keywords
- moment
- thrust
- nozzle
- missile
- roll
- 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.)
- Withdrawn
Links
- 239000012530 fluid Substances 0.000 abstract 2
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 230000006835 compression Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 abstract 1
- 239000004449 solid propellant Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Nozzles (AREA)
- Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)
Abstract
Missile téléguidé comportant un statoréacteur, en particulier à propergol solide, constitué d'une partie chambre de combustion et d'une partie tuyère de poussée, et une commande du vecteur 5 de poussée agissant sur le jet et destinée à engendrer un moment de tangage, de lacet et de roulis. Le dispositif de commande du vecteur de poussée comporte, pour la commande du moment de tangage et de lacet, un mécanisme d'actionnement 22 réglant angulairement, par rapport à l'axe longitudinal A-A du missile 2, la partie de tuyère de poussé 10 réalisée sous la forme d'une tuyère pivotante 12, en combinaison avec un dispositif de commande à fluide, associé à la tuyère pivotante 12 et injectant dans le jet de poussée une quantité de fluide dosée avec production d'une impulsion de compression soumettant la tuyere 12 à un moment de roulis.Unmanned missile comprising a ramjet, in particular solid propellant, consisting of a combustion chamber part and a thrust nozzle part, and a thrust vector control acting on the jet and intended to generate a pitching moment, yaw and roll. The thrust vector control device comprises, for controlling the pitch and yaw moment, an actuating mechanism 22 angularly adjusting, with respect to the longitudinal axis AA of the missile 2, the thrust nozzle part 10 produced. in the form of a pivoting nozzle 12, in combination with a fluid control device, associated with the pivoting nozzle 12 and injecting into the thrust jet a metered quantity of fluid with production of a compression pulse subjecting the nozzle 12 at a rolling moment.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19772744897 DE2744897A1 (en) | 1977-10-06 | 1977-10-06 | STEERING BODY |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2405456A1 true FR2405456A1 (en) | 1979-05-04 |
Family
ID=6020761
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR7828241A Withdrawn FR2405456A1 (en) | 1977-10-06 | 1978-10-03 | MISSILE TELEGUIDE WITH DEVICE TO GENERATE A MOMENT OF TANGAGE, LACING AND ROLL |
Country Status (4)
Country | Link |
---|---|
DE (1) | DE2744897A1 (en) |
FR (1) | FR2405456A1 (en) |
GB (1) | GB2005606B (en) |
IT (1) | IT1099232B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112572840A (en) * | 2020-12-14 | 2021-03-30 | 兰州空间技术物理研究所 | Electric propulsion system storage and supply unit and manufacturing method thereof |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2533637C2 (en) * | 2010-07-22 | 2014-11-20 | Сааб Аб | Cooling device for cooling gaseous combustion products from recoilless anti-tank weapon |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1316191A (en) * | 1962-02-26 | 1963-01-25 | United Aircraft Corp | Control device for propellant |
US3147590A (en) * | 1961-03-16 | 1964-09-08 | Thompson Ramo Wooldridge Inc | Reaction motor with nozzle vector control having ablative port means and cooled valve means |
US3266732A (en) * | 1963-09-03 | 1966-08-16 | United Aircraft Corp | Roll control system |
US3270505A (en) * | 1964-10-21 | 1966-09-06 | Norman L Crabill | Control system for rocket vehicles |
GB1134835A (en) * | 1965-12-06 | 1968-11-27 | Us Navy | Liquid injection thrust vectoring |
US4063685A (en) * | 1976-07-30 | 1977-12-20 | The United States Of America As Represented By The Secretary Of The Army | Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle |
-
1977
- 1977-10-06 DE DE19772744897 patent/DE2744897A1/en not_active Withdrawn
-
1978
- 1978-10-03 FR FR7828241A patent/FR2405456A1/en not_active Withdrawn
- 1978-10-04 IT IT28403/78A patent/IT1099232B/en active
- 1978-10-04 GB GB7839345A patent/GB2005606B/en not_active Expired
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3147590A (en) * | 1961-03-16 | 1964-09-08 | Thompson Ramo Wooldridge Inc | Reaction motor with nozzle vector control having ablative port means and cooled valve means |
FR1316191A (en) * | 1962-02-26 | 1963-01-25 | United Aircraft Corp | Control device for propellant |
US3266732A (en) * | 1963-09-03 | 1966-08-16 | United Aircraft Corp | Roll control system |
US3270505A (en) * | 1964-10-21 | 1966-09-06 | Norman L Crabill | Control system for rocket vehicles |
GB1134835A (en) * | 1965-12-06 | 1968-11-27 | Us Navy | Liquid injection thrust vectoring |
US4063685A (en) * | 1976-07-30 | 1977-12-20 | The United States Of America As Represented By The Secretary Of The Army | Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle |
Non-Patent Citations (1)
Title |
---|
EXBK/73 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112572840A (en) * | 2020-12-14 | 2021-03-30 | 兰州空间技术物理研究所 | Electric propulsion system storage and supply unit and manufacturing method thereof |
Also Published As
Publication number | Publication date |
---|---|
GB2005606A (en) | 1979-04-25 |
IT1099232B (en) | 1985-09-18 |
GB2005606B (en) | 1982-06-30 |
IT7828403A0 (en) | 1978-10-04 |
DE2744897A1 (en) | 1979-04-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE3572786D1 (en) | Method for operating an ink jet device to obtain high resolution printing | |
GB1102625A (en) | Stabilisation and guidance device for sounding rockets and rocket-propelled ballistic vehicles | |
GB1348374A (en) | Ejection seat escape installations | |
GB960106A (en) | Jet propulsion engines with orientable jet nozzles | |
WO1994019047A3 (en) | Oxy-hydrogen propelled torpedo for introducing angioplasty guide wire | |
FR2405456A1 (en) | MISSILE TELEGUIDE WITH DEVICE TO GENERATE A MOMENT OF TANGAGE, LACING AND ROLL | |
ES8606634A1 (en) | A no-load missile restraint arrangement. | |
GB1185193A (en) | Improvements in or relating to Flying Bodies | |
DE959971C (en) | Recoil drive, especially for remote-controlled missiles | |
EP0595056A1 (en) | Watercraft propulsion by a jet produced by the reaction of water with a chemical | |
AU7949798A (en) | Method of generating a liquid mist | |
DE3204477C1 (en) | Missile with auxiliary fluid system | |
FR2412812A1 (en) | DEVICE ALLOWING TO MODIFY THE TRAJECTORY OF A PROJECTILE | |
DE1148913B (en) | Rocket projectile with spreading tail | |
DE3804931A1 (en) | Method for directional control of a missile flying in the relatively high supersonic domain, and such a missile | |
US3269662A (en) | Jet propulsion unit with movable nozzle | |
GB985944A (en) | Improvements in vertical take-off and landing aircraft | |
Bergmann | Method of continuous thrust variation for hybrid rocket engines. | |
JPS55139855A (en) | Atomizing nozzle | |
DE2057326C3 (en) | Liquid rocket engine | |
GB1062839A (en) | Improvements relating to thrust reversers | |
DE2057327A1 (en) | Jet engine for a missile | |
DE3563386D1 (en) | Artillery projectile with extended range | |
JPS6220662A (en) | Rocket permitting combustion control and speed control and being charged with solid fuel in kneaded form | |
AT228096B (en) | Missile projectile to be launched from a gun barrel with a twist |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
ST | Notification of lapse |