SPIN STABILIZED RING-WING CANARD CONTROLLED MISSILE
United States Patent 3603533
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.
US Patent References:
Missile guidance system
Smith, Jr. - August 1964 - 3145949
Pull rocket shroud
Petre - July 1965 - 3195462
Alleviation of divergence during rocket launch
Gillespie, Jr. - July 1966 - 3262655
Missile guidance system
Smith, Jr. - August 1964 - 3145949
Pull rocket shroud
Petre - July 1965 - 3195462
Alleviation of divergence during rocket launch
Gillespie, Jr. - July 1966 - 3262655
Application Number:
04/861690
Publication Date:
09/07/1971
Filing Date:
09/29/1969
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Export Citation:
Primary Class:
International Classes:
F42B10/64; F42B10/00; F42B13/00
Field of Search:
244/3.16,3.2,3.23 102/3
Primary Examiner:
Pendegrass, Verlin R.
Claims:
I claim
1. A stabilized ring-wing canard controlled missile comprising:
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.
1. A stabilized ring-wing canard controlled missile comprising:
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.
Description:
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
A missile generally indicated by reference numeral 1 includes an aft fin 2, a longitudinal centerline axis 3, a center of gravity 4 and a nose 5. A boom 6 projects forward of the missile and is provided with a spherical bearing 7 extending around the boom surface for support of spin stabilized ring-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 bearing 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.
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
A missile generally indicated by reference numeral 1 includes an aft fin 2, a longitudinal centerline axis 3, a center of gravity 4 and a nose 5. A boom 6 projects forward of the missile and is provided with a spherical bearing 7 extending around the boom surface for support of spin stabilized ring-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 bearing 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.