Patent ID: 8436283
Filing Date: 2013-05-07
Classification: F41G,G05D

Abstract:
1. A system for guiding a missile to intercept a target comprising: a target sensor providing line of sight information relating to a position of said target relative to said missile; an inertial measuring unit providing inertial states of said missile; an attitude autopilot controlling said missile attitude; a guidance processor, said guidance processor having a memory containing processing instructions for guiding said missile to said target based on said line of sight information and said inertial states of said missile; said processing instructions including a high order sliding mode control process wherein said high order sliding mode control process enforces a guidance strategy for guiding said missile to intercept said target; said guidance processor generating a total lateral divert acceleration command; at least one lateral divert actuator receiving said total lateral divert command and producing a primary lateral acceleration component directly responsive to said total lateral divert acceleration command; said attitude autopilot receiving said total lateral divert acceleration command and producing a secondary lateral acceleration component in accordance with said total lateral divert acceleration command; said primary lateral acceleration component and said secondary lateral acceleration command cooperating to produce a total acceleration corresponding to said total lateral divert command; said primary lateral acceleration component and said secondary lateral acceleration cooperate to produce a total acceleration corresponding to said total lateral divert acceleration command wherein said total lateral divert acceleration command is derived based on said high order sliding mode control process; wherein said secondary acceleration component is accommodated in said sliding mode control process as a cooperative component of bounded disturbance that reduces an upper Lipschitz bound of initial disturbance.