US3603533A - Spin stabilized ring-wing canard controlled missile - Google Patents
Spin stabilized ring-wing canard controlled missile Download PDFInfo
- Publication number
- US3603533A US3603533A US861690A US3603533DA US3603533A US 3603533 A US3603533 A US 3603533A US 861690 A US861690 A US 861690A US 3603533D A US3603533D A US 3603533DA US 3603533 A US3603533 A US 3603533A
- Authority
- US
- United States
- Prior art keywords
- missile
- canard
- axis
- ring
- spin
- Prior art date
- 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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Classifications
-
- 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
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 on a 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.
Description
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.
Claims (2)
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; D. 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.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US86169069A | 1969-09-29 | 1969-09-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3603533A true US3603533A (en) | 1971-09-07 |
Family
ID=25336496
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US861690A Expired - Lifetime US3603533A (en) | 1969-09-29 | 1969-09-29 | Spin stabilized ring-wing canard controlled missile |
Country Status (2)
Country | Link |
---|---|
US (1) | US3603533A (en) |
CA (1) | CA933799A (en) |
Cited By (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4069990A (en) * | 1977-03-14 | 1978-01-24 | The United States Of America As Represented By The Secretary Of The Army | Ring-wing canard spin-up control mechanism |
WO1981000908A1 (en) * | 1979-09-27 | 1981-04-02 | K Andersson | Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized |
EP0076271A1 (en) * | 1981-04-08 | 1983-04-13 | Commw Of Australia | Directional control device for airborne or seaborne missiles. |
FR2554577A1 (en) * | 1983-11-05 | 1985-05-10 | Diehl Gmbh & Co | CONTROL SYSTEM FOR GUIDED MUNITION SPREADING IN AIR AT A SUPERSONIC SPEED |
US4565340A (en) * | 1984-08-15 | 1986-01-21 | Ford Aerospace & Communications Corporation | Guided projectile flight control fin system |
FR2662996A1 (en) * | 1990-06-06 | 1991-12-13 | British Aerospace | STABILIZATION DEVICE. |
US5417393A (en) * | 1993-04-27 | 1995-05-23 | Hughes Aircraft Company | Rotationally mounted flexible band wing |
US6644587B2 (en) * | 2001-02-09 | 2003-11-11 | Tom Kusic | Spiralling missile—A |
US6708923B2 (en) | 2000-06-26 | 2004-03-23 | Tom Kusic | Aircraft spiralling mechanism |
US20040108411A1 (en) * | 2002-12-04 | 2004-06-10 | Henry August | Survivable and reusable launch vehicle |
US6764044B2 (en) | 2001-06-20 | 2004-07-20 | Tom Kusic | Airplane spiralling mechanism |
US20040155144A1 (en) * | 2001-06-22 | 2004-08-12 | Tom Kusic | Aircraft spiralling mechanism - B |
US20050045768A1 (en) * | 2003-08-29 | 2005-03-03 | Smiths Detection-Edgewood, Inc. | Stabilization of a drogue body |
US20050116085A1 (en) * | 2001-06-22 | 2005-06-02 | Tom Kusic | Aircraft spiralling mechanism - c |
US20050224631A1 (en) * | 2004-03-05 | 2005-10-13 | The Boeing Company | Mortar shell ring tail and associated method |
US20060226293A1 (en) * | 2005-02-25 | 2006-10-12 | Smiths Aerospace Llc | Optical tracking system for refueling |
US20070069067A1 (en) * | 2001-06-22 | 2007-03-29 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - A |
US20070262203A1 (en) * | 2003-08-29 | 2007-11-15 | Smiths Aerospace, Inc. | Active stabilization of a refueling drogue |
US20080230649A1 (en) * | 2007-03-19 | 2008-09-25 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - D |
US7635104B1 (en) | 2001-06-22 | 2009-12-22 | Tom Kusic | Aircraft spiraling mechanism with jet assistance—B |
US20140263841A1 (en) * | 2013-03-15 | 2014-09-18 | Blue Origin, Llc | Launch vehicles with ring-shaped external elements, and associated systems and methods |
US9580191B2 (en) | 2009-02-24 | 2017-02-28 | Blue Origin, Llc | Control surfaces for use with high speed vehicles, and associated systems and methods |
US10668332B2 (en) | 2010-03-26 | 2020-06-02 | Marc Gregory Martino | Electric motor and propeller driven toy rocket |
US10822122B2 (en) | 2016-12-28 | 2020-11-03 | Blue Origin, Llc | Vertical landing systems for space vehicles and associated methods |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR941108A (en) * | 1945-05-04 | 1949-01-03 | Method of guiding a mobile towards an objective emitting radiation, and its means of implementation | |
US3145949A (en) * | 1957-06-27 | 1964-08-25 | Jr E Quimby Smith | Missile guidance system |
US3195462A (en) * | 1961-05-17 | 1965-07-20 | Aerojet General Co | Pull rocket shroud |
US3262655A (en) * | 1963-12-26 | 1966-07-26 | Jr Warren Gillespie | Alleviation of divergence during rocket launch |
-
1969
- 1969-09-29 US US861690A patent/US3603533A/en not_active Expired - Lifetime
-
1970
- 1970-08-26 CA CA091620A patent/CA933799A/en not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR941108A (en) * | 1945-05-04 | 1949-01-03 | Method of guiding a mobile towards an objective emitting radiation, and its means of implementation | |
US3145949A (en) * | 1957-06-27 | 1964-08-25 | Jr E Quimby Smith | Missile guidance system |
US3195462A (en) * | 1961-05-17 | 1965-07-20 | Aerojet General Co | Pull rocket shroud |
US3262655A (en) * | 1963-12-26 | 1966-07-26 | Jr Warren Gillespie | Alleviation of divergence during rocket launch |
Cited By (56)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4069990A (en) * | 1977-03-14 | 1978-01-24 | The United States Of America As Represented By The Secretary Of The Army | Ring-wing canard spin-up control mechanism |
WO1981000908A1 (en) * | 1979-09-27 | 1981-04-02 | K Andersson | Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized |
US4546940A (en) * | 1979-09-27 | 1985-10-15 | Kurt Andersson | Projectile, adapted to be given a rotation on firing, which makes the projectile spin-stabilized |
EP0076271A1 (en) * | 1981-04-08 | 1983-04-13 | Commw Of Australia | Directional control device for airborne or seaborne missiles. |
EP0076271A4 (en) * | 1981-04-08 | 1983-06-08 | Commw Of Australia | Directional control device for airborne or seaborne missiles. |
FR2554577A1 (en) * | 1983-11-05 | 1985-05-10 | Diehl Gmbh & Co | CONTROL SYSTEM FOR GUIDED MUNITION SPREADING IN AIR AT A SUPERSONIC SPEED |
US4565340A (en) * | 1984-08-15 | 1986-01-21 | Ford Aerospace & Communications Corporation | Guided projectile flight control fin system |
FR2662996A1 (en) * | 1990-06-06 | 1991-12-13 | British Aerospace | STABILIZATION DEVICE. |
US5186413A (en) * | 1990-06-06 | 1993-02-16 | British Aerospace Plc | Stabilization systems |
DE4117009C2 (en) * | 1990-06-06 | 2000-02-24 | British Aerospace | Aerodynamic body |
US5417393A (en) * | 1993-04-27 | 1995-05-23 | Hughes Aircraft Company | Rotationally mounted flexible band wing |
US6708923B2 (en) | 2000-06-26 | 2004-03-23 | Tom Kusic | Aircraft spiralling mechanism |
US6648433B2 (en) | 2001-02-09 | 2003-11-18 | Tom Kusic | Spiralling missile—B |
US6644587B2 (en) * | 2001-02-09 | 2003-11-11 | Tom Kusic | Spiralling missile—A |
US6764044B2 (en) | 2001-06-20 | 2004-07-20 | Tom Kusic | Airplane spiralling mechanism |
US20100001117A1 (en) * | 2001-06-22 | 2010-01-07 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - b |
US20040155144A1 (en) * | 2001-06-22 | 2004-08-12 | Tom Kusic | Aircraft spiralling mechanism - B |
US7165742B2 (en) | 2001-06-22 | 2007-01-23 | Tom Kusic | Aircraft spiralling mechanism - B |
US20050116085A1 (en) * | 2001-06-22 | 2005-06-02 | Tom Kusic | Aircraft spiralling mechanism - c |
US7637453B2 (en) | 2001-06-22 | 2009-12-29 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - A |
US7635104B1 (en) | 2001-06-22 | 2009-12-22 | Tom Kusic | Aircraft spiraling mechanism with jet assistance—B |
US7093791B2 (en) | 2001-06-22 | 2006-08-22 | Tom Kusic | Aircraft spiralling mechanism—c |
US20070069067A1 (en) * | 2001-06-22 | 2007-03-29 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - A |
US6749153B1 (en) * | 2002-12-04 | 2004-06-15 | The Boeing Company | Survivable and reusable launch vehicle |
US6845937B2 (en) * | 2002-12-04 | 2005-01-25 | The Boeing Company | Survivable and reusable launch vehicle |
US20040108411A1 (en) * | 2002-12-04 | 2004-06-10 | Henry August | Survivable and reusable launch vehicle |
US7275718B2 (en) | 2003-08-29 | 2007-10-02 | Smiths Aerospace Llc | Active control of a drogue body |
US20050269456A1 (en) * | 2003-08-29 | 2005-12-08 | Smiths Aerospace, Inc. | Stabilization of a drogue body |
US6994294B2 (en) * | 2003-08-29 | 2006-02-07 | Smiths Aerospace, Inc. | Stabilization of a drogue body |
US20070262203A1 (en) * | 2003-08-29 | 2007-11-15 | Smiths Aerospace, Inc. | Active stabilization of a refueling drogue |
US20050045768A1 (en) * | 2003-08-29 | 2005-03-03 | Smiths Detection-Edgewood, Inc. | Stabilization of a drogue body |
US7377468B2 (en) | 2003-08-29 | 2008-05-27 | Smiths Aerospace Llc | Active stabilization of a refueling drogue |
US7262394B2 (en) * | 2004-03-05 | 2007-08-28 | The Boeing Company | Mortar shell ring tail and associated method |
US20050224631A1 (en) * | 2004-03-05 | 2005-10-13 | The Boeing Company | Mortar shell ring tail and associated method |
US20080067290A1 (en) * | 2005-02-25 | 2008-03-20 | Mickley Joseph G | Optical tracking system for airborne objects |
US8104716B2 (en) | 2005-02-25 | 2012-01-31 | Ge Aviation Systems Llc | Optical tracking system for airborne objects |
US20060226293A1 (en) * | 2005-02-25 | 2006-10-12 | Smiths Aerospace Llc | Optical tracking system for refueling |
US20080075467A1 (en) * | 2005-02-25 | 2008-03-27 | Smiths Aerospace Llc | Optical tracking system for airborne objects |
US20100163679A1 (en) * | 2005-02-25 | 2010-07-01 | Mickley Joseph G | Optical tracking system for airborne objects |
US7681839B2 (en) | 2005-02-25 | 2010-03-23 | Smiths Aerospace Llc | Optical tracking system for refueling |
US7686252B2 (en) * | 2005-02-25 | 2010-03-30 | Smiths Aerospace, Llc | Optical tracking system for airborne objects |
US7825359B2 (en) | 2006-11-20 | 2010-11-02 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - E |
US20100123038A1 (en) * | 2006-11-20 | 2010-05-20 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - E |
US20080230649A1 (en) * | 2007-03-19 | 2008-09-25 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - D |
US7800033B1 (en) | 2007-03-19 | 2010-09-21 | Tom Kusic | Separation activated missile spiraling mechanism—FA |
US7812294B2 (en) | 2007-03-19 | 2010-10-12 | Tom Kusic | Aircraft spiraling mechanism with jet assistance-f |
US7642491B2 (en) | 2007-03-19 | 2010-01-05 | Tom Kusic | Aircraft spiraling mechanism with jet assistance—D |
US20090277990A1 (en) * | 2007-03-19 | 2009-11-12 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - f |
US9580191B2 (en) | 2009-02-24 | 2017-02-28 | Blue Origin, Llc | Control surfaces for use with high speed vehicles, and associated systems and methods |
US10518911B2 (en) | 2009-02-24 | 2019-12-31 | Blue Origin, Llc | Control surfaces for use with high speed vehicles, and associated systems and methods |
US11649073B2 (en) | 2009-02-24 | 2023-05-16 | Blue Origin, Llc | Control surfaces for use with high speed vehicles, and associated systems and methods |
US10668332B2 (en) | 2010-03-26 | 2020-06-02 | Marc Gregory Martino | Electric motor and propeller driven toy rocket |
US20140263841A1 (en) * | 2013-03-15 | 2014-09-18 | Blue Origin, Llc | Launch vehicles with ring-shaped external elements, and associated systems and methods |
US9487308B2 (en) * | 2013-03-15 | 2016-11-08 | Blue Origin, Llc | Launch vehicles with ring-shaped external elements, and associated systems and methods |
US10266282B2 (en) | 2013-03-15 | 2019-04-23 | Blue Origin, Llc | Launch vehicles with ring-shaped external elements, and associated systems and methods |
US10822122B2 (en) | 2016-12-28 | 2020-11-03 | Blue Origin, Llc | Vertical landing systems for space vehicles and associated methods |
Also Published As
Publication number | Publication date |
---|---|
CA933799A (en) | 1973-09-18 |
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