US3776490A - Missile with thrust vector and aerodynamic control - Google Patents

Missile with thrust vector and aerodynamic control Download PDF

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Publication number
US3776490A
US3776490A US00275970A US3776490DA US3776490A US 3776490 A US3776490 A US 3776490A US 00275970 A US00275970 A US 00275970A US 3776490D A US3776490D A US 3776490DA US 3776490 A US3776490 A US 3776490A
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United States
Prior art keywords
missile
spoilers
operative position
jet
aerodynamic
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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 - Lifetime
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US00275970A
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English (en)
Inventor
D Weis
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Airbus Defence and Space GmbH
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Messerschmitt Bolkow Blohm AG
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    • 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

Definitions

  • ABSTRACT A jet propelled missile is provided with jet spoilers at its trailing end for thrust vector control and with other spoilers forwardly of its center of gravity for aerodynamic control. Both the jet spoilers and the other spoilers are operated from the same control device.
  • the other spoilers are located adjacent the trailing ends of fins located on the forward end of the missile and can be displaced between an inoperative position recessed in the surface of the missile and an operative position projecting outwardly from the outer surface of the missile.
  • the side edges of the other spoilers which extend outwardly from the missile can be recessed for a portion of their length for increasing the efficiency of aerodynamic control.
  • the present invention concerns a jet propelled missile provided with thrust vector controls and aerodynamic controls with both of the controls regulated by the same device and, more particularly, it is directed to the arrangement of the aerodynamic controls.
  • Missiles with both thrust vector and aerodynamic controls have the advantage, unlike missiles provided only with thrust vector control, that they can be controlled after the completion of the powered phase of jet propulsion and at the start of the trajectory, unlike missiles controlled only aerodynamically; see A4 in F. Mueller Leitfaden der Fernlenkung, Deutsche Radar-verlagsgesellschaft m.b.H., 1955, page 148. In this publication, the missile was controlled over mechanically coupled jet and rear surface controls. Such a solution requires, in addition to a higher mechanical expenditure, considerable space which is only available in larger missiles.
  • a missile is afforded with thrust vector control in the form of jet spoilers located at the rearward end of the missile and is provided with aerodynamic control by spoilers mounted on the missile forwardly of its center of gravity and at the trailing edge of fins projecting outwardly from the forward end of the missile.
  • the spoilers used for aerodynamic control can be moved from an inoperative position recessed in the outer surface of the missile to an operative position extending outwardly from the outer surface of the missile.
  • the arrangement and design of the thrust vector controls and the aerodynamic controls formed in accordance with the present invention are characterized in particular by their simple mechanical construction and the high degree of compatibility of the two different controls. Since the jet spoilers and the aerodynamic spoilers are operated by the same device, the magnets for the jet spoilers can also be used for positioning the aerodynamic spoilers so that the construction of the missile is simplified by reducing the number of parts required.
  • the aerodynamic spoilers are positioned forwardly of the center of gravity of the missile, the spoiler forces act on a long lever arm. Accordingly, the aerodynamic spoilers can be small in size so that the aerodynamic resistance of the missile is only slightly increased when the spoilers are moved into the operative position.
  • FIG. 1 is a side view of a missile embodying the present invention
  • FIG. 1a is a rear end view of the missile illustrated in FIG. 1;
  • FIG. 2 is an enlarged partial view, partly in section, of the missile shown in FIG. 1 disclosing the arrangement of an aerodynamic spoiler;
  • FIG. 3 is a view, taken transversely of the missile, showing one of the aerodynamic spoilers illustrated in FIG. 2;
  • FIG. 3a is a view of the aerodynamic spoiler shown in FIG. 3, in a displaced position;
  • FIG. 4 is a view, similar to FIG. 3, of another embodiment of the aerodynamic spoiler.
  • FIG. 4a is a view similar to FIG. 4 with the aerodynamic spoiler located in a displaced position.
  • a jet propelled missile l having a propulsion unit nozzle 2 and a pair of jet spoilers 3 at its trailing end for guiding the missile about two axes.
  • a propulsion unit nozzle 2 On the outer surface of the missile just ahead of its trailing end, four aerodynamic fins 4 are arranged spaced equiangularly apart.
  • destabilizer fins 5 At the forward end of the missile spaced rearwardly from its nose and ahead of its center of gravity are four destabilizer fins 5 also disposed equiangularly apart. These fins 5 impart favorable conditions to the missile at the commencement of its flight shortly after the launching and, as a result, make it easier to guide.
  • each fin in the fuselage or surface of the missile 1 is a trapezoidally shaped recess 6 containing a spoiler 7 having the same shape as the recess, see FIGS. 2 to 4.
  • the spoiler is pivotally mounted in the recess about an axis 8 so that it can be displaced between an inoperative position within the recess, shown in dashed lines, and an operative position, shown in full lines, extending outwardly from the outer surface of the missile and at the rearward end of the fin 5.
  • a latch 9 is arranged for holding the spoiler 7 in the inoperative position shown in dashed lines. The latch is operated by means of a magnet system, not shown.
  • the spoilers 7 are released by displacs ing the latches 9 and springs 10, note FIG. 2, bias the spoilers outwardly into the operative position at the rearward end of the fins 5. To prevent the spoilers from being driven back into the recess 6, due to windgusts and the like, in the operative position they are locked in place in a known manner.
  • the spoiler 7 is shown positioned symmetrically relative to the fin 5, however, it can be displaced through a plane extending transversely of the axis of the missile in the direction indicated by the double arrows 12.
  • the jet spoilers 3 and the spoilers 7 are compatible with a stabilizing system, not shown, of the missile so that they can be regulated and positioned by a single guide circuit 13 by means of the same control signals. Accordingly, the trajectory of the missile is controlled in the same manner, regardless of whether the jet spoilers 3 or the spoilers 7 are controlled by the same signal.
  • slitshaped recesses 21 are formed in the side or lateral edges of the spoilers which extend from the end adjacent to the outer surface of the missile to the other end spaced outwardly from the outer surface of the missile.
  • the recesses extend for the greater part of the length of the sides of the spoilers 7.
  • a jet propelled missile including first means for thrust vector control and second means for aerodynamic control for the application of transverse forces, control means for regulating both of said first and second means, and fins extending in the axial direction of said missile and positioned on and extending outwardly from said missile forwardly of its center of gravity; wherein the improvement comprises that said first means includes first spoilers located at the trailing end of said missile, and said second means includes second spoilers positioned adjacent the trailing edges of said fins and forwardly of the center of gravity of said missile, said spoilers arranged to be displaced between an inoperative position and an operative position and in the operative position said second spoilers project outwardly from the outer surface of said missile at the trailing edges of said fins.
  • a jet propelled missile as set forth in claim 1, wherein said second spoilers comprise a first end located adjacent the outer surface of said missile in the operative position, a second end located spaced outwardly from the outer surface of said missile in the operative position, and a pair of spaced side edges extending between said first end and said second end and said side edges being recessed inwardly toward one another for a portion of the length thereof between said first and second ends.
  • a jet propelled missile as set forth in claim 2, wherein said missile having recesses formed in its outer surface for receiving said second spoilers in the inoperative position, and the first ends of said second spoilers being pivotally secured to said missile within said recesses.
  • a jet propelled missile as set forth in claim 3, wherein a displaceable latch member is located within each of said recesses for holding said second spoilers in the inoperative position within said recesses.
  • a jet propelled missile as set forth in claim 4, wherein a spring means is arranged within said missile in engagement with said second spoiler for biasing said second spoiler into the operative position when said latch member is released.

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  • 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)
US00275970A 1971-08-20 1972-07-28 Missile with thrust vector and aerodynamic control Expired - Lifetime US3776490A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2141744A DE2141744C3 (de) 1971-08-20 1971-08-20 Flugkörper mit Schubvektor- und aerodynamischer Steuerung

Publications (1)

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US3776490A true US3776490A (en) 1973-12-04

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US (1) US3776490A (enExample)
DE (1) DE2141744C3 (enExample)
FR (1) FR2150342A1 (enExample)

Cited By (6)

* 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
USD599854S1 (en) * 2008-06-09 2009-09-08 Lockheed Martin Corporation Writing instrument

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8611406D0 (en) * 1986-05-09 1986-08-20 Lucas Ind Plc Missile flight control system
US4867393A (en) * 1988-08-17 1989-09-19 Morton Thiokol, Inc. Reduced fin span thrust vector controlled pulsed tactical missile
FR2799833B1 (fr) * 1999-10-15 2002-10-25 Tda Armements Sas Dispositif de correction de trajectoire pour projectiles guides gyroscopes
FR2839360B1 (fr) * 2002-05-02 2006-05-19 Sagem Procede de controle de la trajectoire d'un objet largable, objet largable et module stabilisateur avant pour objet largable

Citations (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
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic 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

Patent Citations (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 (6)

* 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
USD599854S1 (en) * 2008-06-09 2009-09-08 Lockheed Martin Corporation Writing instrument

Also Published As

Publication number Publication date
DE2141744A1 (de) 1973-03-01
DE2141744C3 (de) 1978-09-14
DE2141744B2 (de) 1978-01-19
FR2150342A1 (enExample) 1973-04-06

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