GB2010760A - Changing the trajectory of a missile - Google Patents

Changing the trajectory of a missile

Info

Publication number
GB2010760A
GB2010760A GB7850054A GB7850054A GB2010760A GB 2010760 A GB2010760 A GB 2010760A GB 7850054 A GB7850054 A GB 7850054A GB 7850054 A GB7850054 A GB 7850054A GB 2010760 A GB2010760 A GB 2010760A
Authority
GB
United Kingdom
Prior art keywords
missile
thrust
nozzles
rocket drive
centre
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.)
Granted
Application number
GB7850054A
Other versions
GB2010760B (en
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of GB2010760A publication Critical patent/GB2010760A/en
Application granted granted Critical
Publication of GB2010760B publication Critical patent/GB2010760B/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
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves

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)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

A missile 1 is arranged to be guided during the final phase of the trajectory using a rocket drive of which the thrust may be selectively directed in an appropriate direction to steer the missile to the target. The missile may include a hollow charge 4 with a stand- off detonator head 8 and guidance means 12,14, or may be guided from the launch point. The rocket drive has a solid charge 20 within a chamber with combustion zone 21 communicating with three thrust nozzles 17 evenly spaced and which can be selectively opened for directional control. The rocket drive is aligned along the missile axis and faces forwardly with the thrust line of the nozzles extending forwardly to meet on the missile axis between the centre of pressure and centre of mass. Tracer compositions 23 are located immediately adjacent the nozzles 17, and each composition emits a radiation of a different visible wavelength. <IMAGE>
GB7850054A 1977-12-23 1978-12-27 Changing the trajectory of a missile Expired GB2010760B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19772757664 DE2757664A1 (en) 1977-12-23 1977-12-23 DEVICE FOR CHANGING THE AIRWAY OF ONE FLOOR

Publications (2)

Publication Number Publication Date
GB2010760A true GB2010760A (en) 1979-07-04
GB2010760B GB2010760B (en) 1982-06-16

Family

ID=6027105

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7850054A Expired GB2010760B (en) 1977-12-23 1978-12-27 Changing the trajectory of a missile

Country Status (5)

Country Link
DE (1) DE2757664A1 (en)
FR (1) FR2412812A1 (en)
GB (1) GB2010760B (en)
IT (1) IT1099287B (en)
SE (1) SE7812955L (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2163837A (en) * 1984-07-24 1986-03-05 Diehl Gmbh & Co Flight-controlled munition
GB2172383A (en) * 1981-06-04 1986-09-17 Aerospatiale Guided missile system
GB2251834A (en) * 1983-02-22 1992-07-22 George Alexander Tarrant Guided missiles and like devices
CN111350615A (en) * 2020-03-27 2020-06-30 惠州学院 Integral turning device suitable for vertical launching aircraft

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3231528C1 (en) * 1982-08-25 1983-10-27 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Control system for wingless steering ammunition
DE3603497C1 (en) * 1986-02-05 1993-01-07 Rheinmetall Gmbh Bullet for an anti-tank weapon to fight a tank from above

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE428854A (en) * 1937-06-28
DE1158846B (en) * 1961-07-20 1963-12-05 Dornier System Gmbh Aircraft, especially unmanned missiles
SE429064B (en) * 1976-04-02 1983-08-08 Bofors Ab FINAL PHASE CORRECTION OF ROTATING PROJECTILE

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2172383A (en) * 1981-06-04 1986-09-17 Aerospatiale Guided missile system
GB2251834A (en) * 1983-02-22 1992-07-22 George Alexander Tarrant Guided missiles and like devices
GB2251834B (en) * 1983-02-22 1992-12-16 George Alexander Tarrant Guided missiles
GB2163837A (en) * 1984-07-24 1986-03-05 Diehl Gmbh & Co Flight-controlled munition
US4674408A (en) * 1984-07-24 1987-06-23 Diehl Gmbh & Co. Ammunition article controllable during its final flight phase and method for navigation thereof towards a target
CN111350615A (en) * 2020-03-27 2020-06-30 惠州学院 Integral turning device suitable for vertical launching aircraft
CN111350615B (en) * 2020-03-27 2023-09-05 惠州学院 Integral turning device suitable for vertical launch aircraft

Also Published As

Publication number Publication date
IT1099287B (en) 1985-09-18
FR2412812B1 (en) 1982-11-12
FR2412812A1 (en) 1979-07-20
GB2010760B (en) 1982-06-16
IT7828694A0 (en) 1978-10-12
SE7812955L (en) 1979-06-24
DE2757664A1 (en) 1979-06-28

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee