FR2150342A1 - - Google Patents

Info

Publication number
FR2150342A1
FR2150342A1 FR7228973A FR7228973A FR2150342A1 FR 2150342 A1 FR2150342 A1 FR 2150342A1 FR 7228973 A FR7228973 A FR 7228973A FR 7228973 A FR7228973 A FR 7228973A FR 2150342 A1 FR2150342 A1 FR 2150342A1
Authority
FR
France
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Withdrawn
Application number
FR7228973A
Other languages
French (fr)
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of FR2150342A1 publication Critical patent/FR2150342A1/fr
Withdrawn legal-status Critical Current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
    • F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle
    • 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
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
FR7228973A 1971-08-20 1972-08-10 Withdrawn FR2150342A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2141744A DE2141744C3 (en) 1971-08-20 1971-08-20 Missile with thrust vector and aerodynamic controls

Publications (1)

Publication Number Publication Date
FR2150342A1 true FR2150342A1 (en) 1973-04-06

Family

ID=5817280

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7228973A Withdrawn FR2150342A1 (en) 1971-08-20 1972-08-10

Country Status (3)

Country Link
US (1) US3776490A (en)
DE (1) DE2141744C3 (en)
FR (1) FR2150342A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0244971A2 (en) * 1986-05-09 1987-11-11 LUCAS INDUSTRIES public limited company Missile flight control system
EP0364086A2 (en) * 1988-08-17 1990-04-18 THIOKOL CORPORATION (a Delaware corp. formerly called MORTON THIOKOL, INC.) Tactical missile steering by thrust vector control and fin movement
EP1092941A1 (en) * 1999-10-15 2001-04-18 Tda Armements S.A.S. Device for correcting the trajectory of a spin-stabilized guided projectile
FR2839360A1 (en) * 2002-05-02 2003-11-07 Sagem Air-launched guided missile has deployable deflector to create aerodynamic peturbation in launch phase

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4198016A (en) * 1978-06-12 1980-04-15 The United States Of America As Represented By The Secretary Of The Navy Floating canard with geared tab
US4274610A (en) * 1978-07-14 1981-06-23 General Dynamics, Pomona Division Jet tab control mechanism for thrust vector control
US4364531A (en) * 1980-10-09 1982-12-21 Knoski Jerry L Attachable airfoil with movable control surface
US5873549A (en) * 1996-09-25 1999-02-23 Mcdonnell Douglas Corporation Vehicle rotation and control mechanism
US6502785B1 (en) * 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2968454A (en) * 1951-10-29 1961-01-17 Martin Co Rocket control system
US3139033A (en) * 1959-07-23 1964-06-30 Ernst D Geissler Aerodynamically stable missile
US3305194A (en) * 1960-03-08 1967-02-21 Robert G Conard Wind-insensitive missile
GB1188651A (en) * 1962-03-05 1970-04-22 British Aircraft Corp Ltd Improvements in or relating to Missiles
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic missile

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0244971A2 (en) * 1986-05-09 1987-11-11 LUCAS INDUSTRIES public limited company Missile flight control system
EP0244971A3 (en) * 1986-05-09 1988-04-27 LUCAS INDUSTRIES public limited company Missile flight control system
EP0364086A2 (en) * 1988-08-17 1990-04-18 THIOKOL CORPORATION (a Delaware corp. formerly called MORTON THIOKOL, INC.) Tactical missile steering by thrust vector control and fin movement
EP0364086A3 (en) * 1988-08-17 1991-11-21 THIOKOL CORPORATION (a Delaware corp. formerly called MORTON THIOKOL, INC.) Tactical missile steering by thrust vector control and fin movement
EP1092941A1 (en) * 1999-10-15 2001-04-18 Tda Armements S.A.S. Device for correcting the trajectory of a spin-stabilized guided projectile
FR2799833A1 (en) * 1999-10-15 2001-04-20 Tda Armements Sas PATH CORRECTION DEVICE FOR GYROSCOPIC GUIDE PROJECTILES
FR2839360A1 (en) * 2002-05-02 2003-11-07 Sagem Air-launched guided missile has deployable deflector to create aerodynamic peturbation in launch phase

Also Published As

Publication number Publication date
DE2141744A1 (en) 1973-03-01
DE2141744B2 (en) 1978-01-19
DE2141744C3 (en) 1978-09-14
US3776490A (en) 1973-12-04

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Legal Events

Date Code Title Description
ST Notification of lapse