|Publication number||US3782668 A|
|Publication date||Jan 1, 1974|
|Filing date||Sep 25, 1970|
|Priority date||Sep 25, 1970|
|Publication number||US 3782668 A, US 3782668A, US-A-3782668, US3782668 A, US3782668A|
|Inventors||Stooksberry F, Womack R|
|Original Assignee||Us Army|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (6), Referenced by (2), Classifications (6)|
|External Links: USPTO, USPTO Assignment, Espacenet|
States Womack et al. Jan. 1, 1974  RAM]? FORWARD OF CONTROL FIN 3,179,052 4/1965 Jasse 244/324 2,823,376 2/1958 Baldwin et al... 244/323 X  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  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  Appl. No.: 75,661 P. Murphy  [1.5. CI. 244/3.24, 244/327 511 Int. Cl. F42b 15/16, F42b 13/32 [571 ABSTRACT  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
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.
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.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US2823376 *||May 28, 1956||Feb 11, 1958||Baldwin Robert P||Stringer radar reflective tow target|
|US2845026 *||Nov 17, 1953||Jul 29, 1958||Bernard Smith||Multiple box fin|
|US3058422 *||Apr 11, 1960||Oct 16, 1962||Bofors Ab||Wing assembly for missiles|
|US3063375 *||May 19, 1960||Nov 13, 1962||Hawley Wilbur W||Folding fin|
|US3179052 *||Jun 21, 1962||Apr 20, 1965||Hotchkiss Brandt||Drag collar for varying the range of rockets|
|US3215109 *||Jun 22, 1943||Nov 2, 1965||Bell Telephone Labor Inc||Signal controlled steering systems|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US4231536 *||Oct 11, 1977||Nov 4, 1980||The Boeing Company||Airfoil for controlling refueling boom|
|US5062585 *||Jun 26, 1990||Nov 5, 1991||The United States Of America As Represented By The Secretary Of The Army||Detached and attached thermal spoilers for kinetic energy projectile fins|
|U.S. Classification||244/3.24, 244/3.27|
|International Classification||F42B10/64, F42B10/00|