US3782668A - Ramp forward of control fin - Google Patents

Ramp forward of control fin Download PDF

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Publication number
US3782668A
US3782668A US00075661A US3782668DA US3782668A US 3782668 A US3782668 A US 3782668A US 00075661 A US00075661 A US 00075661A US 3782668D A US3782668D A US 3782668DA US 3782668 A US3782668 A US 3782668A
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United States
Prior art keywords
fin
ramp
missile
control fin
shielding
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Expired - Lifetime
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US00075661A
Inventor
R Womack
F Stooksberry
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US Department of Army
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US Department of Army
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Publication date
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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
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the invention relates to missile design.
  • an aerodynamic control fin Many missiles designed for attacking moving targets 5 1 is secured to a rotatable shaft 2 extending from a missuffer extremely high pressures on, and heating of, the aerodynamic control fin shaft mechanisms during critical flight maneuvers. Impact of the air and airborne particles has caused the control fin shaft to erode and the result has been as drastic as the shearing off of the shaft and failure of the missile. Prior attempts to alleviate this problem have led to unacceptable increases in missile drag and weight.
  • a purpose of this invention is to provide a ramp forward of the control fin to shield the mounting shaft of the fin from flow of particles and air during missile flight to minimize erosion of the mounting shaft.
  • FIG. 1 is a sectional view of the control fin area of a missile utilizing the invention.
  • FIG. 2 shows a missile utilizing the invention.
  • a shielding ramp 4 is installed on the missile body forwardly adjacent control fin l to deflect air and particle flow away from the gap 5 between missile body 3 and control fin l.
  • Ramp 4 preferably constructed of aluminum, is provided with an elevated aft end which projects laterally in front of the inner edge (leading edge) of fin 1. This laterally extending elevated end of the ramp is wide enough to cover the greatest deflections of fin 1 during critical flight maneuvers.
  • Ramp 4 is coated with a non-particle producing ablative material 6, preferably teflon.
  • FIG. 2 shows a missile having a plurality of control fins l and respective ramp structures 4.
  • a shielding ramp attached to said body forwardly adjacent said fin for reducing air and particle flow between said body and said fin, said ramp being disposed with its elevated end laterally extending in front of the inner edge of said fin.

Abstract

In a missile, a small ramp structure is installed forward of each aerodynamic control fin to deflect reduce air and particle flow away from the gap between the missile body and a control fin therefor.

Description

States Womack et al. Jan. 1, 1974 [54] RAM]? FORWARD OF CONTROL FIN 3,179,052 4/1965 Jasse 244/324 2,823,376 2/1958 Baldwin et al... 244/323 X [75] lnvemors- Franklm 3,215,109 11 1965 Dunn 114/23 f both of Angeles 3,058,422 10 1962 Olsson 244/329 Callf- 2,845,026 7/1958 Smith 244/324 [73] Assignee: The United States of America as represented f) the Secretary of the Primary ExaminerBenjamin A. Borchelt Army, g n, D-C. Assistant Examiner-James M. Hanley Att0rneyCharles K. Wright, William G. Gapcynski, 22 F l d. S t. 25 1970 l 1 ep Lawrence A. Neureither, Leonard Flank and William [21] Appl. No.: 75,661 P. Murphy [52] [1.5. CI. 244/3.24, 244/327 511 Int. Cl. F42b 15/16, F42b 13/32 [571 ABSTRACT [58] Field In a missile, a small ramp structure is installed forward of each aerodynamic control fin to deflect reduce air References Cited and particle flow away from the gap between the miss1le body and a control fin therefor. UNITED STATES PATENTS 3,063,375 1 H1962 Hawley et al. 244/327 3 Claims, 2 Drawing Figures PAIENTEDJAN 1 3.782.668
FIG. 2
FIG. I
Robert R.Womock Franklin Dsfooksbgrry,
lNVENTOR RAMP FORWARD OF CONTROL FIN BACKGROUND OF THE INVENTION The invention relates to missile design.
DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to FIG. 1, an aerodynamic control fin Many missiles designed for attacking moving targets 5 1 is secured to a rotatable shaft 2 extending from a missuffer extremely high pressures on, and heating of, the aerodynamic control fin shaft mechanisms during critical flight maneuvers. Impact of the air and airborne particles has caused the control fin shaft to erode and the result has been as drastic as the shearing off of the shaft and failure of the missile. Prior attempts to alleviate this problem have led to unacceptable increases in missile drag and weight.
PURPOSE OF THE INVENTION A purpose of this invention is to provide a ramp forward of the control fin to shield the mounting shaft of the fin from flow of particles and air during missile flight to minimize erosion of the mounting shaft.
SUMMARY OF THE INVENTION BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a sectional view of the control fin area of a missile utilizing the invention.
FIG. 2 shows a missile utilizing the invention.
sile body 3 for aerodynamic control of the missile. A shielding ramp 4 is installed on the missile body forwardly adjacent control fin l to deflect air and particle flow away from the gap 5 between missile body 3 and control fin l. Ramp 4, preferably constructed of aluminum, is provided with an elevated aft end which projects laterally in front of the inner edge (leading edge) of fin 1. This laterally extending elevated end of the ramp is wide enough to cover the greatest deflections of fin 1 during critical flight maneuvers. Ramp 4 is coated with a non-particle producing ablative material 6, preferably teflon.
FIG. 2 shows a missile having a plurality of control fins l and respective ramp structures 4.
We claim:
1. In a missile including a body having a nose end and at least one aerodynamic control fin mounted on a rotatable shaft extending from said body, a shielding ramp attached to said body forwardly adjacent said fin for reducing air and particle flow between said body and said fin, said ramp being disposed with its elevated end laterally extending in front of the inner edge of said fin.
2. The apparatus in claim 1, wherein said shielding ramp has width equal to the greatest deflection of said fin during flight.
3. The apparatus in claim 2, wherein said shielding ramp is coated with a non-particle producing ablative material.

Claims (3)

1. In a missile including a body having a nose end and at least one aerodynamic control fin mounted on a rotatable shaft extending from said body, a shielding ramp attached to said body forwardly adjacent said fin for reducing air and particle flow between said body and said fin, said ramp being disposed with its elevated end laterally extending in front of the inner edge of said fin.
2. The apparatus in claim 1, wherein said shielding ramp has width equal to the greatest deflection of said fin during flight.
3. The apparatus in Claim 2, wherein said shielding ramp is coated with a non-particle producing ablative material.
US00075661A 1970-09-25 1970-09-25 Ramp forward of control fin Expired - Lifetime US3782668A (en)

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US7566170A 1970-09-25 1970-09-25

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4231536A (en) * 1977-10-11 1980-11-04 The Boeing Company Airfoil for controlling refueling boom
US5062585A (en) * 1990-06-26 1991-11-05 The United States Of America As Represented By The Secretary Of The Army Detached and attached thermal spoilers for kinetic energy projectile fins
FR2669995A1 (en) * 1982-05-18 1992-06-05 Onera (Off Nat Aerospatiale) Variable-effectiveness control surface for missiles, especially supersonic missiles

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823376A (en) * 1956-05-28 1958-02-11 Robert P Baldwin Stringer radar reflective tow target
US2845026A (en) * 1953-11-17 1958-07-29 Smith Bernard Multiple box fin
US3058422A (en) * 1959-04-13 1962-10-16 Bofors Ab Wing assembly for missiles
US3063375A (en) * 1960-05-19 1962-11-13 Wilbur W Hawley Folding fin
US3179052A (en) * 1961-06-29 1965-04-20 Hotchkiss Brandt Drag collar for varying the range of rockets
US3215109A (en) * 1943-06-22 1965-11-02 Bell Telephone Labor Inc Signal controlled steering systems

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3215109A (en) * 1943-06-22 1965-11-02 Bell Telephone Labor Inc Signal controlled steering systems
US2845026A (en) * 1953-11-17 1958-07-29 Smith Bernard Multiple box fin
US2823376A (en) * 1956-05-28 1958-02-11 Robert P Baldwin Stringer radar reflective tow target
US3058422A (en) * 1959-04-13 1962-10-16 Bofors Ab Wing assembly for missiles
US3063375A (en) * 1960-05-19 1962-11-13 Wilbur W Hawley Folding fin
US3179052A (en) * 1961-06-29 1965-04-20 Hotchkiss Brandt Drag collar for varying the range of rockets

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4231536A (en) * 1977-10-11 1980-11-04 The Boeing Company Airfoil for controlling refueling boom
FR2669995A1 (en) * 1982-05-18 1992-06-05 Onera (Off Nat Aerospatiale) Variable-effectiveness control surface for missiles, especially supersonic missiles
US5062585A (en) * 1990-06-26 1991-11-05 The United States Of America As Represented By The Secretary Of The Army Detached and attached thermal spoilers for kinetic energy projectile fins

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