Modular aerodynamic gyrodynamic intelligent controlled projectile and method of operating same

• US 5,425,514 A
• Filed: 12/29/1993
• Issued: 06/20/1995
• Est. Priority Date: 12/29/1993
• Status: Expired due to Fees

• Current Assignee: Donald F. Mofford, Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Grosso, Vincent A.
• Primary Examiner(s): Pihulic, Daniel T.
• Application Number:
  US08/174,749
• Time in Patent Office: 538 Days
• Field of Search: 244/3.22, 244/3.21, 244/3.15, 244/3.1, 244/3.23
• US Class Current: 244/3.22
• CPC Class Codes: F41G 3/145 using a target illuminator
• CPC Class Codes: F41G 7/222 for spin-stabilized missiles
• CPC Class Codes: F41G 7/2253 Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
• CPC Class Codes: F41G 7/2293 using electromagnetic waves other than radio waves

Abstract

A spinning projectile is described including a roll rate sensor for providing a spin frequency signal, a nutation frequency signal and a precession frequency signal and a seeker for providing a boresight angle signal. The spinning projectile further includes a torquer assembly, responsive to a control signal, for selectively providing a force in a desired lateral direction and a digital signal processor, responsive to the spin frequency signal, the nutation frequency signal, the precession frequency signal and the boresight angle signal, for providing a control signal to the torquer assembly to control the desired direction of the force. With such an arrangement, a projectile is provided having greater maneuverability wherein an increase in maneuver footprint is obtained by having the maneuver force equal the sum of the rocket force and the body force rather than being a difference as in known projectiles.

Claims

1. A spinning projectile comprising:

(a) means for providing a spin frequency signal, a nutation frequency signal and a precession frequency signal;

(b) means for providing a boresight error angle signal;

(c) means, responsive to a control signal, for selectively providing a force in a desired lateral direction comprising;

(i) means for firing a thrust rocket to provide a constant thrust vector in a lateral direction spinning at the spin rate of the projectile;

(ii) means for inertially, stabilizing the constant thrust vector in a desired direction to maneuver the spinning projectile in a corresponding desired direction; and

(iii) means for respinning the constant thrust vector such that the thrust vector Spins at the spin rate of the projectile; and

(d) means, responsive to the spin frequency signal, the nutation frequency signal, the precession frequency signal and the boresight error angle signal, for providing the control signal to the selectively providing a force means to control the desired lateral direction of the force.

2. The spinning projectile as recited in claim 1 wherein the selectively providing a force means comprises means for providing a maneuver force equal to the sum of a rocket force and a body force.

3. The spinning projectile as recited in claim 1 wherein the means for providing a spin frequency signal, a nutation frequency signal and a precession frequency signal comprises a roll rate sensor.

4. A spinning projectile comprising:

(a) a roll rate sensor to provide a spin frequency signal, a nutation frequency signal and a precession frequency signal;

(b) a seeker to provide a bore sight error angle signal;

(c) a torquer assembly, responsive to a control signal, to provide a force in a desired direction, the torquer assembly comprising;

(i) a constant thrust rocket and a rotating ceramic disk having a nozzle connected to the thrust rocket;

(ii) a motor, coupled to the rotating ceramic disk, to rotate the rotating ceramic disk to control the position of the nozzle relative to the projectile; and

(iii) a brake, connected to the rotating ceramic disk, to selectively fix the position of the nozzle relative to the projectile; and

(d) a digital signal processor, responsive to the spin frequency signal, the nutation frequency signal, the precession frequency signal and the lead angle signal, to provide the control signal to the torquer assembly.

5. A method of operating a spinning projectile comprising the steps of:

(a) firing a thrust rocket to provide a constant thrust vector in a lateral direction spinning at the spin rate of the projectile;

(b) inertially stabilizing the constant thrust vector in a desired direction to maneuver the spinning projectile in a corresponding desired direction; and

(c) respinning the constant thrust vector such that the thrust vector spins at the spin rate of the projectile.

6. The method of operating a spinning projectile as recited in claim 5 wherein the firing a thrust rocket step comprises the steps of:

(a) firing a thrust rocket to provide the constant thrust vector;

(b) inertially stabilizing the thrust vector to trim the projectile to a desired angle of attack; and

(c) unstabilizing the thrust vector so that the thrust vector rotates at the spin rate of the projectile.

7. The method of operating a spinning projectile as recited in claim 5 wherein the inertially stabilizing the thrust vector step comprises the step of producing a maneuver force resulting from additive effects of a thrust rocket force and a body lift force.

8. The method of operating a spinning projectile as recited in claim 5 wherein the inertially stabilizing the thrust vector step comprises the step of rotating a nozzle relative to the projectile, the nozzle connected to a thrust rocket, such that the thrust vector is inertially stabilized.