초록 ▼

Trajectory is controlled by a control system having fins that de-spin a section of the control system relative to a projectile or missile. The control system also includes aero-surfaces that produce a lift when brought to rotation speed of about 0 Hz relative to a reference frame and a brake that c

Trajectory is controlled by a control system having fins that de-spin a section of the control system relative to a projectile or missile. The control system also includes aero-surfaces that produce a lift when brought to rotation speed of about 0 Hz relative to a reference frame and a brake that couples the guidance package to the rotational inertia of the projectile or missile. In one example, no electric motor is used in the trajectory control system, saving weight and increasing reliability.

대표청구항 ▼

What is claimed is: 1. A spin-stabilized projectile comprising: a projectile body induced to spin in a first direction about a longitudinal axis of the projectile; a guidance package; and a control section rotatably connected with the projectile body for rotation relative to the projectile body abo

What is claimed is: 1. A spin-stabilized projectile comprising: a projectile body induced to spin in a first direction about a longitudinal axis of the projectile; a guidance package; and a control section rotatably connected with the projectile body for rotation relative to the projectile body about the longitudinal axis of the projectile, the control section comprising: a first aerodynamic surface extending from an exterior of the control section for applying torque to the control section about the longitudinal axis of the projectile in a direction opposite to the direction of spin of the projectile body; and a brake acting between the projectile body and the control section; wherein the brake is applied between the control section and the projectile body such that the torque applied by the brake balances the torque applied by the first aerodynamic surface in order to control the rotation of the control section relative to a frame of reference. 2. The spin stabilized projectile of claim 1, the control section further comprising a second aerodynamic surface capable of producing lift in a direction transverse to the longitudinal axis of the projectile. 3. The spin stabilized projectile of claim 2, wherein the second aerodynamic surface produces lift only when the rotation of the control section relative to the reference frame is approximately 0 (zero) Hz. 4. The spin stabilized projectile of claim 1, wherein the brake is a magnetically actuated friction brake. 5. The spin stabilized projectile of claim 1, wherein the brake is a magneto-rheological fluid proportional break. 6. The spin stabilized projectile of claim 1, wherein the projectile body has a large rotational inertia relative to the control section. 7. The spin stabilized projectile of claim 1, wherein the guidance package comprises at least one system selected from the group consisting of: a system based on the Global Positioning System, an inertial navigation system, a semi-active laser, and a radio frequency guidance system. 8. The spin stabilized projectile of claim 1 wherein at least a portion of the guidance package is positioned within the control section. 9. The spin stabilized projectile of claim 1 wherein at least a portion of the guidance package is positioned within the projectile body outside the control section. 10. The spin stabilized projectile of claim 1 further comprising a fuse element, wherein the control section is positioned between the fuse element and the projectile body. 11. A method of controlling the trajectory of a projectile during flight, the projectile having a projectile body with a longitudinal axis and a control section rotatable relative to the projectile body, the method comprising: launching the projectile; spinning the control section relative to the projectile body by applying a torque to the control section to rotate the control section about the longitudinal axis of the projectile without the use of an electric motor; applying a brake between the control section and the projectile body to slow the rotation of the control section to 0 (zero) Hz relative to a frame of reference; orienting the control section relative to the frame of reference; and applying a lateral force to the control section to alter the trajectory of the projectile. 12. The method of claim 11, wherein the projectile comprises a guidance package and the method further comprises orienting the control section relative to the reference frame in response to information provided by the guidance package. 13. The method of claim 12 further comprising re-orienting the control section relative to the reference frame in response to further information provided by the guidance package. 14. The method of claim 12 further comprising re-spinning the control section relative to the reference frame by reducing the brake force between the control section and the projectile body. 15. The method of claim 12, wherein applying a torque to the control section to rotate the control section about the longitudinal axis of the projectile without the use of an electric motor comprises: providing a first aerodynamic surface extending from an exterior of the control section for applying torque to the control section about the longitudinal axis of the projectile. 16. The method of claim 15, wherein orienting the control section relative to the Earth inertial reference frame comprises: balancing the brake torque with the torque provided by the first aerodynamic surface in order to position the control section at an appropriate rotational angle relative to the reference frame. 17. The method of claim 16, wherein applying a lateral force to the control section comprises providing a second aerodynamic surface on the control section capable of producing lift in a direction transverse to the longitudinal axis of the projectile. 18. A projectile trajectory control system for controlling the trajectory of a projectile having a projectile body with a longitudinal axis, the control system comprising: a control section rotatably connected with the projectile body for rotation relative to the projectile body about the longitudinal axis, the control section comprising: a first aerodynamic surface extending from an exterior of the control section for applying torque to the control section to induce spin about the longitudinal axis of the projectile in a first direction; and a second aerodynamic surface capable of producing lift in a direction transverse to the longitudinal axis of the projectile when the rotation of the control section relative to a frame of reference is approximately 0 (zero) Hz; and a counter-spin section rotatably connected with the projectile body for rotation relative to the projectile body about the longitudinal axis, the counter-spin section comprising a third aerodynamic surface extending from an exterior of the counter-spin section for applying torque to the counter-spin section to induce spin about the longitudinal axis of the projectile in a second direction opposite the first direction. 19. The control system of claim 18, wherein the angular moment of the control section and the angular moment of the counter-spin section are substantially balanced. 20. The control system of claim 19 further comprising a brake system capable of controlling the spin of the control section relative to the projectile body and the counter-spin section and capable of controlling the spin of the counter-spin section relative to the projectile body and the control section. 21. The control system of claim 20, wherein the brake system comprises: a first roll brake acting to control the spin of the control section relative to the projectile body; and a second roll brake acting separately to control the spin of the counter-spin section relative to the projectile body. 22. The control system of claim 20, wherein the brake system comprises a first brake acting differentially between the control section and the counter-spin section for controlling the relative spin of the sections. 23. The control system of claim 19, wherein changes to the spin of the control section are substantially balanced by changes to the spin of the counter-spin section such that substantially no angular momentum is transferred to the projectile body.