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Publication numberUS3603533 A
Publication typeGrant
Publication dateSep 7, 1971
Filing dateSep 29, 1969
Priority dateSep 29, 1969
Also published asCA933799A1
Publication numberUS 3603533 A, US 3603533A, US-A-3603533, US3603533 A, US3603533A
InventorsStripling William W
Original AssigneeUs Army
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Spin stabilized ring-wing canard controlled missile
US 3603533 A
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Description  (OCR text may contain errors)

United States Patent Inventor 72 William W. Stripling Huntsville, Ala. [2|] AppLNo. 861,690 [22] Filed Sept. 29, I969 [45] Patented Sept. 7, I971 [73] Assignee The United States 01 America as represented by the Secretary of the Army [54] SPIN STABILIZED RING-WING CANARD CONTROLLED MISSILE 2 Claims, 2 Drawing Figs.

[52] US. Cl 244/3.23 [51] Int. Cl F4211 13/00 [50] Field of Search 244/3. 1 6, 3.2, 3.23; 102/3 [56] References Cited UNITED STATES PATENTS 3.145.949 8/1964 Smith, Jr. 244/3.2l X

3,195.462 7/1965 Petre 244/3.2l X 3,262,655 7/1966 Gillespie,Jr 244/3.21 X FOREIGN PATENTS 941,108 6/1948 France 102/3 Primary ExaminerVerlin R. Pendegrass An0rneysHarry M. Saragovitz, Edward]. Kelly, Herbert Ber] and Charles R. Carter ABSTRACT: A spin stabilized circular canard control surface for attitude control of missiles. The canard control surface guides a missile along a path determined by the attitude of a space oriented spinning canard. The canard is spun free around a spherical bearing located ona boom projecting forward of the missile nose and is disposed with its spin axis pivoted about a point in the longitudinal axis of the missile. When a disturbing force causes rotation of the missile axis from the canard axis, the canard applies to the missile a restoring torque to thereby restore coincidence of the missile and canard axes.

PATENTEDSEP H9?! 3.603533 l IO 6 L A William W. Siripling, FIG. 2 INVENTOR m a l aYw n/aze IWM SPIN STABILIZED RING-WING CANARD CONTROLLED MISSILE SUMMARY OF THE INVENTION This invention relates to the field of missiles and more particularly to the flight control thereof. The present invention provides attitude control of missiles or rockets without internal guidance controls. The invention includes a ring-wing canard spin stabilized for gyroscope action to maintain the spin axis thereof in the trajectory of the missile despite disturbing wind forces that tend to cause rotation of the missile axis away from the canard spin axis. The canard is a gyroscope which has a large free gyro rotor to provide two degrees of freedom and thereby provide pitch and yaw control of the missile.

The invention may be better understood from the following detailed description taken in conjunction with the accompanying drawing.

FIG. 1 is a perspective view of the missile.

FIG. 2 is a sectional view showing the support bearing.

DESCRIPTION OF THE INVENTION around the boom surface for support of spin stabilized ring- 3 wing canard 8. The canard includes an aerodynamic lift ring 9 connected by ring support struts 10 to a bearing 11 which is mounted on hearing 7 for rotation. The canard is mounted with its spin axis pivoted about a point in the longitudinal axis of the missile. As the missile leaves the tube launcher, the canard may be spun up by riflings in the tube or by high-pressure gas carried by the canard itself to be spin stabilized for gyroscopic action to maintain the spin axis thereof in the trajectory of the missile. When a disturbing force causes rotation of the missile axis from the canard axis, an aerodynamic force acts on lift ring 9 and a restoring torque is applied to the missile having a lever arm that is the effective length from the center of the spherical bearing to the missile center of gravity thereby restoring coincidence of the missile and canard axes.

I claim:

1. A stabilized ring-wing canard controlled missile comprising:

a. a missile with a longitudinal centerline axis and a center of gravity;

b. a boom projecting forward of one end of said missile;

c. a spin stabilized ring-wing canard secured to said boom with a spherical bearing centered at a point in the center axis of the missile;

. the axis of the canard is directed in the trajectory of the missile and the canard is disposed for rotation to apply a restoring torque to said missile and restore coincidence of said missile and canard axes when a force disturbing the missile causes rotation of the missile axis from the canard axis.

2. A missile as set forth in claim 1 wherein said canard includes a ring, a bearing and support struts connecting said ring to said bearing.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US3145949 *Jun 27, 1957Aug 25, 1964Smith Jr E QuimbyMissile guidance system
US3195462 *May 17, 1961Jul 20, 1965Aerojet General CoPull rocket shroud
US3262655 *Dec 26, 1963Jul 26, 1966Gillespie Jr WarrenAlleviation of divergence during rocket launch
FR941108A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4069990 *Mar 14, 1977Jan 24, 1978The United States Of America As Represented By The Secretary Of The ArmyRing-wing canard spin-up control mechanism
US4546940 *Sep 25, 1980Oct 15, 1985Kurt AnderssonProjectile, adapted to be given a rotation on firing, which makes the projectile spin-stabilized
US4565340 *Aug 15, 1984Jan 21, 1986Ford Aerospace & Communications CorporationGuided projectile flight control fin system
US5186413 *May 28, 1991Feb 16, 1993British Aerospace PlcAerodynamic body
US5417393 *Apr 27, 1993May 23, 1995Hughes Aircraft CompanyVehicle
US6644587 *Feb 8, 2002Nov 11, 2003Tom KusicSpiralling missile—A
US6648433Feb 8, 2002Nov 18, 2003Tom KusicSpiralling missile—B
US6708923Jun 22, 2001Mar 23, 2004Tom KusicAircraft spiralling mechanism
US6749153 *Dec 4, 2002Jun 15, 2004The Boeing CompanySurvivable and reusable launch vehicle
US6764044Jun 20, 2002Jul 20, 2004Tom KusicAirplane spiralling mechanism
US6845937 *Jun 3, 2003Jan 25, 2005The Boeing CompanySurvivable and reusable launch vehicle
US6994294 *Oct 31, 2003Feb 7, 2006Smiths Aerospace, Inc.Stabilization of a drogue body
US7093791Jan 23, 2004Aug 22, 2006Tom KusicAircraft spiralling mechanism—c
US7165742Jan 20, 2004Jan 23, 2007Tom KusicAircraft spiralling mechanism - B
US7262394 *Mar 5, 2004Aug 28, 2007The Boeing CompanyMortar shell ring tail and associated method
US7275718Jul 15, 2004Oct 2, 2007Smiths Aerospace LlcActive control of a drogue body
US7377468May 21, 2004May 27, 2008Smiths Aerospace LlcActive stabilization of a refueling drogue
US7635104Nov 20, 2006Dec 22, 2009Tom KusicAircraft spiraling mechanism with jet assistance—B
US7637453Nov 29, 2006Dec 29, 2009Tom KusicAircraft spiraling mechanism with jet assistance - A
US7642491Mar 19, 2007Jan 5, 2010Tom KusicAircraft spiraling mechanism with jet assistance—D
US7681839Oct 14, 2005Mar 23, 2010Smiths Aerospace LlcOptical tracking system for refueling
US7686252 *Aug 30, 2007Mar 30, 2010Smiths Aerospace, LlcOptical tracking system for airborne objects
US7800033Dec 11, 2009Sep 21, 2010Tom KusicSeparation activated missile spiraling mechanism—FA
US7812294Jul 20, 2009Oct 12, 2010Tom KusicAircraft spiraling mechanism with jet assistance-f
US7825359Jul 17, 2009Nov 2, 2010Tom KusicAircraft spiraling mechanism with jet assistance - E
US8104716Feb 10, 2010Jan 31, 2012Ge Aviation Systems LlcOptical tracking system for airborne objects
DE4117009C2 *May 24, 1991Feb 24, 2000British AerospaceAerodynamischer Körper
EP0076271A1 *Mar 30, 1982Apr 13, 1983Commw Of AustraliaDirectional control device for airborne or seaborne missiles.
WO1981000908A1 *Sep 25, 1980Apr 2, 1981K AnderssonProjectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized
Classifications
U.S. Classification244/3.23
International ClassificationF42B10/00, F42B10/64
Cooperative ClassificationF42B10/64
European ClassificationF42B10/64