Aeronautics and astronautics – Missile stabilization or trajectory control – Stabilized by rotation
Reexamination Certificate
2000-07-06
2002-04-02
Poon, Peter M. (Department: 3644)
Aeronautics and astronautics
Missile stabilization or trajectory control
Stabilized by rotation
C266S093000
Reexamination Certificate
active
06364248
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Technical Field of the Invention
The invention relates to directional control systems and methods for missiles.
2. Description of the Related Art
Steering control of missiles may be achieved by deflecting a set of control surfaces attached to the rear of the missile body, each control surface having its own respective control actuator to provide the necessary deflection torque. However, a class of missiles and projectiles exists for which this approach is inadequate, due to the relatively large volume and increased package size for separate deflectable control surfaces. In the past, canards, jet plume diverters, and articulated nose controls have been used as alternatives to rear-body control surface steering. However, canards may have the disadvantage of requiring unacceptable amounts of external volume, thereby creating difficulties for missile storage and/or launch. In some such cases, the canards may be designed as folding or “pop-out” control surfaces; however, this often adds significant complexity, cost, and missile volume.
Jet divert mechanisms may have the disadvantages of being able to provide only a discrete nature of control, of inducing increased drag, and/or of inducing oscillations in the missile.
In many applications, nose control may provide significant advantages over either rear steering, canard, or jet divert designs. The articulated nose may provide steering with minimal effect on the external missile/projectile packaging, minimum drag characteristics, and smooth, continuous steering. It is understood that a simple steering mechanism can be achieved by always pointing the nose toward the target, therefore allowing resulting aerodynamic forces to fly the missile toward the target.
Prior actuation implementation systems to effect nose deflection or articulation have generally utilized pyrotechnic, piezo-electric, or electro-magnetic actuators. An exemplary prior art pyrotechnic nose cone actuation system contains two banks of pyrotechnic actuating cylinders, each of the cylinders attached to an individual ignitor. Actuation is achieved by firing the cylinders to extend and lock a corresponding piston, thereby causing angular deflection of a pivot-mounted nose cone. Pyrotechnic systems have the disadvantage of being discrete by nature, since they typically require the firing of a piston to full stroke. Therefore, changes in the nose cone deflection are discrete and sudden. Small trajectory errors are therefore more difficult to correct and accuracy is correspondingly diminished.
An exemplary piezo-electric actuated nose cone contains a pair of piezo-actuators for each desired axis of nose deflection or articulation. Such piezo-actuators are relatively fragile and are typically limited to providing small displacements. Therefore, such actuation systems are typically restricted to applications where small nose deflections are acceptable.
It will be appreciated from the foregoing that improved mechanisms and methods for steering a missile are needed.
SUMMARY OF THE INVENTION
A missile nose is tiltable and rotatable relative to a missile body through the action of an actuator system. In an exemplary embodiment, the actuator system uses two electromechanical actuators mounted co-axially and having the output shaft of one actuator fed through the shaft of the other. One of the actuators controls a tilt angle between a longitudinal axis of the body and a longitudinal axis of the nose. The other actuator rotates the nose about the longitudinal axis of the body. A method of steering a missile includes using the actuator system to maintain the missile nose pointed at a target or other desired destination.
According to an aspect of the invention, a missile includes a pair of rotary actuation devices for positioning a missile nose relative to a missile body.
According to another aspect of the invention, a missile includes a pair of actuators for positioning a missile nose relative to a missile body, at least part of one of the actuators being co-axial with at least part of the other actuator.
According to yet another aspect of the invention, a missile includes a pair of actuators for positioning a missile nose relative to a missile body, at least part of one of the actuators nested in at least part of the other actuator.
According to still another aspect of the invention, a missile includes a tilt actuator for tilting a nose of the missile relative to a body of the missile, the tilt actuator including a rotary actuation device operatively coupled to a translatable member.
According to a further aspect of the invention, a missile includes an actuator system for articulating a nose of the missile relative to a body of the missile, at least part of the actuator system being located in a nose cavity of the nose.
According to a still further aspect of the invention, a missile includes an a pair of actuators for articulating a nose of the missile relative to a body of the missile, at least part of each of the actuators being located in a nose cavity of the nose.
According to another aspect of the invention, a missile includes a missile nose having a longitudinal nose axis; and a missile body having a longitudinal body axis, the body including an actuator system hingedly coupled to the nose at a central connection on the nose which is at an intersection between the longitudinal nose axis and the longitudinal body axis. The actuator system is operationally configured to rotate the nose about the longitudinal body axis relative to the body.
According to yet another aspect of the invention, a missile includes means for tilting a missile nose relative to a missile body in a fixed plane relative to the body, and means for rolling or spinning the missile.
According to still another aspect of the invention, a missile includes a missile nose and a missile body which includes a tilt actuator with a translatable member mechanically linked to an offset connection point on the nose. The offset connection point is offset from a longitudinal body axis.
To the accomplishment of the foregoing and related ends, the invention comprises the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages, and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the drawings.
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Adams Robert J.
Spate Wayne V.
Williams Donald P.
Dinh T.
Poon Peter M.
Raytheon Company
Renner , Otto, Boisselle & Sklar, LLP
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