U.S. patents available from 1976 to present.
U.S. patent applications available from 2005 to present.

Modular aerodynamic gyrodynamic intelligent controlled projectile and method of operating same

Patent 5379968 Issued on January 10, 1995. Estimated Expiration Date: Icon_subject December 29, 2013. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.

Patent References

3843076

3905563

Spin-stabilized projectile and guidance system therefor
Patent #: 4347996
Issued on: 09/07/1982
Inventor: Grosso

Active nutation control system for space vehicle
Patent #: 4370716
Issued on: 01/25/1983
Inventor: Amieux

Control of nutation in a spacecraft
Patent #: 4504032
Issued on: 03/12/1985
Inventor: Phillips ,   et al.

SSICM guidance and control concept
Patent #: 4542870
Issued on: 09/24/1985
Inventor: Howell

Strap down roll reference
Patent #: 4676456
Issued on: 06/30/1987
Inventor: Grosso ,   et al.

Infrared seeker
Patent #: 4690351
Issued on: 09/01/1987
Inventor: Beckerleg ,   et al.

Apparatus for transmititng data to a projectile positioned within a gun tube
Patent #: 4711152
Issued on: 12/08/1987
Inventor: Fortunko

Device for controlling aerodynamic bodies
Patent #: 5065957
Issued on: 11/19/1991
Inventor: Kranz

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Inventor

Assignee

Application

No. 175090 filed on 12/29/1993

US Classes:

244/3.21Attitude control mechanisms

Examiners

Primary: Pihulic, Daniel T.

Attorney, Agent or Firm

International Class

F42B 015/01

Abstract

A spinning projectile is described including a body having a fore section and an aft section and a seeker, connected to the fore section, for providing guidance signals. The spinning projectile further includes a rocket control system, connected to the aft section, for controlling the course of the spinning projectile and means for acoustically coupling through the body of the projectile the guidance signals from the seeker to the rocket control system. With such an arrangement, existing projectiles can be retrofitted with a seeker and a rocket control system without affecting the body of the projectile.

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