GPS guided munition
First Claim
Patent Images
1. A retrofit tail fin assembly for converting a munition into a global positioning system (GPS) guided munition for guidance to a selected target via a transition of at least one flight control surface, the tail fin assembly comprising:
- a tail fin housing engageable to the munition without disturbing activatable components thereof, the tail fin housing having a tail fin inside compartment;
a GPS receiver disposed within the tail fin compartment, the GPS receiver being operative to autonomously generate GPS navigational signals; and
an actuator mechanism disposed within the tail fin compartment and in communication with the GPS receiver and the flight control surface, the actuator mechanism being operative to regulate movement of the flight control surface in response to the GPS navigational signals.
1 Assignment
0 Petitions
Accused Products
Abstract
A tail fin assembly for a munition having a housing configured for attachment to the munition, at least one flight control surface, an actuator for effecting movement of the flight control surface(s), so as to facilitate guiding of the munition, and a guidance system for controlling the actuator mechanism. The guidance system has a global positioning system (GPS) receiver for effecting control of the actuator mechanism.
-
Citations
33 Claims
-
1. A retrofit tail fin assembly for converting a munition into a global positioning system (GPS) guided munition for guidance to a selected target via a transition of at least one flight control surface, the tail fin assembly comprising:
-
a tail fin housing engageable to the munition without disturbing activatable components thereof, the tail fin housing having a tail fin inside compartment;
a GPS receiver disposed within the tail fin compartment, the GPS receiver being operative to autonomously generate GPS navigational signals; and
an actuator mechanism disposed within the tail fin compartment and in communication with the GPS receiver and the flight control surface, the actuator mechanism being operative to regulate movement of the flight control surface in response to the GPS navigational signals. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
-
-
13. A global positioning system (GPS) guided weapon system for an aircraft for guidance to a selected target, the system comprising:
-
an autonomous control unit disposed in the aircraft, the control unit being operative to generate guidance information independent of aircraft on-board targeting processing unit to avoid disturbance of the aircraft avionics;
a retrofitable munition releasibly attached to the aircraft;
a tail fin assembly engaged to the munition without disturbing activatable components thereof, the tail fin assembly being operative to autonomously generate GPS navigational signals for guidance to the selected target, the tail fin assembly further being operative to receive the guidance information from the control unit when released from the aircraft. - View Dependent Claims (14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25)
-
-
26. A method of converting a munition into a global positioning system (GPS) guided munition for use in a strategic weapon system upon a selected target, the system defining a GPS receiver, an actuator mechanism, at least one flight control surface and a munition body attachable to an aircraft, the method comprising the steps of:
-
a) removing an original tail fin assembly from the munition body;
b) engaging a GPS guidable tail fin assembly to the munition body without disturbing activatable components thereof;
c) engaging the munition body to the aircraft;
d) autonomously generating GPS navigational signals representative of target coordinates of the selected target via the GPS receiver of the guidable tail fin assembly;
e) releasing the munition when the aircraft is in flight;
f) regulating movement of the flight surface via the actuator mechanism in response to the generated GPS navigational signals for guidance of the munition to the selected target;
g) generating guidance information representative of orientation of the munition independent of aircraft on-board targeting processing unit to avoid disturbance of the aircraft avionics; and
h) communicating the guidance information to the actuator mechanism to further regulate the movement of the flight surface for guidance of the munition to the selected target. - View Dependent Claims (27, 28, 29, 30, 31, 32, 33)
-
Specification