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System and method for guiding and controlling a missile using high order sliding mode control

a high-order sliding mode and missile technology, applied in process and machine control, instruments, navigation instruments, etc., can solve problems such as interceptions

Active Publication Date: 2013-04-18
DAVIDSON TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent is about using high order sliding mode control techniques to guide a missile with a seeker and lateral on-off divert thrusters. The controller uses a combination of main thrust, aerodynamic lift and lateral on-off divert thrusters to control the velocity of the missile, and uses continuous or on-off actuators to control the attitude of the missile. The controller is designed to be insensitive to disturbances and allows for the concurrent usage of divert mechanisms without affecting accuracy. It also provides control for all the major channels of the missile and ensures absolute robustness. The design should ideally incorporate the components of the guidance control method in an integrated fashion for better results.

Problems solved by technology

Further, the interception can occur while still boosting.
The jet flow coming out of the thrusters creates an obstacle to the airflow, thereby modifying the system of shock waves around the body and thus, aerodynamic forces.

Method used

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  • System and method for guiding and controlling a missile using high order sliding mode control
  • System and method for guiding and controlling a missile using high order sliding mode control
  • System and method for guiding and controlling a missile using high order sliding mode control

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Experimental program
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Effect test

second embodiment

Seeker Control

[0091]The second embodiment is illustrated in FIG. 6A. FIG. 6A illustrates an exemplary interceptor 602 with a seeker configured with a fixed mirror 604 and a rotating minor 606. Two types of seeker mounts are typically used in a missile; the first one places the seeker sensor, i.e. focal plane array on a gimbaled gyroscopically stabilized platform, the second, strap-down mount employs a rotating minor which reflects the incoming ray from the target onto the focal plane array fixed onto the missile structure as shown in FIG. 6. Note that the objects of FIG. 6A are not necessarily drawn to scale relative to one another. One should appreciate that the seeker subsystem is severable and may be used alone or in combination with one or more of the other subsystems of the present disclosure. Different element of this method, either compensate implicitly or explicitly for disturbing terms, the integrated design by accounting for the effects of multiple sources of uncertainty a...

third embodiment

[0118]The third embodiment is HOSM guidance. Guidance is the process that provides acceleration commands to the autopilot process.

[0119]The guidance process begins by generating a guidance strategy. The guidance strategy defines the sensor inputs, control outputs and the objectives for each of one or more phases of intercept. One exemplary guidance strategy may endeavor to minimize a line of sight rate. Another guidance strategy may endeavor to minimize time to intercept. Still another guidance strategy may minimize control effort. Any guidance strategy may be used with the present invention. In accordance with one embodiment of the present invention, a sliding surface for a high order sliding mode control is established to enforce the selected guidance strategy. Upon initiation, the guidance controller drives the system to the simultaneous sliding condition for the sliding surface and one or more derivatives of the sliding surface, whereupon the simultaneous sliding condition is ma...

fourth embodiment

[0136]The fourth embodiment is HOSM quaternion autopilot. Here the autopilot typically needs to steer the missile attitude to achieve some desired lateral acceleration. Alternatively, attitude may be directly commanded. Commanded attitude may be a directly commanded attitude such as at launch and shortly thereafter or before impact, or such as to enhance collision effectiveness as this could be done after interceptor booster burn-out and when dynamic pressure is small enough. Commanded attitude may be calculated in the autopilot subsystem such to achieve some prescribed lateral acceleration calculated by the guidance. Said prescribed lateral acceleration may the primary acceleration command, as this may be the case with an interceptor which divert is solely achieved by aerodynamic lift, orientation of main booster / sustainer body orientation or combination thereof or may be the secondary cooperative disturbance acceleration.

[0137]The relation of the autopilot with other elements of a...

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Abstract

Higher Order Sliding Mode (HOSM) control techniques are applied to the Guidance Control (G&C) of interceptor missile in which velocity may be steered by combination of main thrust, aerodynamic lift and lateral on-off divert thrusters, and attitude may be steered by continuous or on-off actuators. Methods include the pointing of the seeker, its associated estimation processes, a guidance law that uses concurrent divert mechanisms, and an attitude autopilot. The insensitivity of the controller to matched disturbances allows the concurrent usage of the divert mechanisms without adverse effect on the accuracy. The controller also allows the de-coupling of the control of roll, pitch and yaw channels, and usage quaternions to represent body attitude and it provides control perfect robustness. While it conceivable to design separately the components of the G&C method, it is widely accepted that designing them in an integrated fashion usually produces a better result.

Description

RELATED APPLICATIONS[0001]This application claims the benefit of U.S. Provisional Application 61 / 129,676, titled “High order sliding mode (HOSM) control method,” Filed Jul. 11, 2008, which is incorporated herein by reference in its entirety.GOVERNMENT RIGHTS[0002]This invention was made with Government support under Contract HQ0006-08-C-7824 awarded by Missile Defense Agency. The Government has certain rights in the invention.TECHNICAL FIELD OF THE INVENTION[0003]The present invention relates to the control of missile trajectories homing to collide with a maneuvering target. More particularly, the use of a High Order Sliding Mode (HOSM) control adapted to the control of one or more functional subsystems of the homing missile, including the guidance, seeker, and autopilot subsystems.BACKGROUND OF THE INVENTION[0004]Missile guidance and control has received considerable attention in the last 50 years. Proportional Navigation (PN) and its multiple variants has been the preferred guidan...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F41G7/22
CPCF41G7/22F41G7/2213G05D1/12F41G7/2293F41G7/2253
Inventor TOURNES, CHRISTIAN H.SHTESSEL, YURI B.
Owner DAVIDSON TECH
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