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Publication numberUS3782668 A
Publication typeGrant
Publication dateJan 1, 1974
Filing dateSep 25, 1970
Priority dateSep 25, 1970
Publication numberUS 3782668 A, US 3782668A, US-A-3782668, US3782668 A, US3782668A
InventorsStooksberry F, Womack R
Original AssigneeUs Army
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Ramp forward of control fin
US 3782668 A
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.
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Claims  available in
Description  (OCR text may contain errors)

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.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2823376 *May 28, 1956Feb 11, 1958Baldwin Robert PStringer radar reflective tow target
US2845026 *Nov 17, 1953Jul 29, 1958Bernard SmithMultiple box fin
US3058422 *Apr 11, 1960Oct 16, 1962Bofors AbWing assembly for missiles
US3063375 *May 19, 1960Nov 13, 1962Hawley Wilbur WFolding fin
US3179052 *Jun 21, 1962Apr 20, 1965Hotchkiss BrandtDrag collar for varying the range of rockets
US3215109 *Jun 22, 1943Nov 2, 1965Bell Telephone Labor IncSignal controlled steering systems
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4231536 *Oct 11, 1977Nov 4, 1980The Boeing CompanyAirfoil for controlling refueling boom
US5062585 *Jun 26, 1990Nov 5, 1991The United States Of America As Represented By The Secretary Of The ArmyDetached and attached thermal spoilers for kinetic energy projectile fins
Classifications
U.S. Classification244/3.24, 244/3.27
International ClassificationF42B10/64, F42B10/00
Cooperative ClassificationF42B10/64
European ClassificationF42B10/64