Store separation autopilot

Patent metadata

Field	Value
Publication number	US-9665104-B2
Application number	US-201414332529-A
Country	US
Kind code	B2
Filing date	Jul 16, 2014
Priority date	Jul 22, 2013
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

A method and apparatus are presented for guiding a store, represented by a dynamic system having transitory nonlinear characteristics, between release from a platform and an activation of a mission autopilot along an optimal path. A nominal reference trajectory is determined that optimizes a desired performance index for the dynamic system using optimal control theory. A feedback control system is implemented that optimizes an original performance index to second order in a presence of disturbances along the optimal path using neighboring optimal control. The feedback control system converges to a linear time invariant regulator approaching the desired operating condition along the optimal path. Finally, control of the store is transitioned to the mission autopilot.

First claim

What is claimed is:

1. An air-to-ground guided munition, comprising:
flight control surfaces; and
a flight management system configured to manipulate the flight control surfaces and having a store separation autopilot and a mission autopilot,
wherein the store separation autopilot is activated when the air-to-ground munition is released from a platform, and
further wherein the store separation autopilot is configured to:
determine a nominal reference trajectory that optimizes a desired performance index for the air-to-ground guided munition using optimal control theory;
implement a feedback control system that optimizes an original performance index to second order in a presence of disturbances along an optimal path using neighboring optimal control and corresponding manipulation of the flight control surfaces;
converge, via the feedback control system, to a linear time invariant regulator approaching the desired operating condition along the optimal path; and
transition control of the flight management system of the air-to-ground munition to the mission autopilot.

2. The air-to-ground guided munition of claim 1 , wherein control of the flight management system of the air-to-ground munition is transitioned to the mission autopilot after a specific interval of time.

3. The air-to-ground guided munition of claim 2 , wherein the specific interval of time is one second.

4. An air-to-ground guided munition, comprising:
flight control surfaces; and
a flight management system configured to manipulate the flight control surfaces and having a store separation autopilot and a mission autopilot,
wherein the store separation autopilot is activated when the air-to-ground munition is released from a platform, and
further wherein the store separation autopilot is configured to:
determine a nominal reference trajectory that optimizes a desired performance index for the air-to-ground guided munition using optimal control theory by:
determining an optimal trajectory including an optimal flight path and open-loop inputs using a high fidelity model; and
generating a local model by linearizing the high fidelity model along a prescribed flight path,
wherein the local model is used to determine time-varying feedback gains;

implement a feedback control system that optimizes an original performance index to second order in a presence of disturbances along an optimal path using neighboring optimal control and corresponding manipulation of the flight control surfaces;
converge, via the feedback control system, to a linear time invariant regulator approaching the desired operating condition along the optimal path; and
transition control of the flight management system of the air-to-ground munition to the mission autopilot.

5. The air-to-ground guided munition of claim 4 , wherein control of the flight management system of the air-to-ground munition is transitioned to the mission autopilot after a specific interval of time.

6. The air-to-ground guided munition of claim 5 , wherein the specific interval of time is one second.

7. The air-to-ground guided munition of claim 4 , wherein the high fidelity model includes dynamic system information and safety and acceptability criteria.

Assignees

• Us Air Force
• Us Air Force

Inventors

• Carter Ryan E

Classifications

• G05D1/107 Primary

  specially adapted for missiles · CPC title