A method for guiding a multistage interceptor missile toward a target missile that may transition from a boost mode to a ballistic mode during the engagement. The method comprises the steps of tracking the position of the target missile with a sensor, generating a predicted intercept point and time,
A method for guiding a multistage interceptor missile toward a target missile that may transition from a boost mode to a ballistic mode during the engagement. The method comprises the steps of tracking the position of the target missile with a sensor, generating a predicted intercept point and time, and loading the predicted intercept point and time into the interceptor missile guidance system. The interceptor missile is launched and transition is made to the second stage of propulsion of the interceptor missile. Second-stage midcourse guidance acceleration commands are generated in response to an elevated predicted intercept point generated using the Runge-Kutta integration method working on predicted target missile position, velocity, and acceleration. During third stage propulsion said interceptor missile is guided toward an updated predicted intercept point of the target missile. During fourth stage, the kinetic warhead effects a hit-to-kill intercept of the target missile.
대표청구항▼
1. A method for guiding a multistage interceptor missile toward a target missile, said method comprising the steps of: tracking a position of said target missile with a sensor;generating a pre-interceptor-missile-launch predicted intercept point and a predicted intercept time, and loading the predic
1. A method for guiding a multistage interceptor missile toward a target missile, said method comprising the steps of: tracking a position of said target missile with a sensor;generating a pre-interceptor-missile-launch predicted intercept point and a predicted intercept time, and loading the predicted intercept point and time into an interceptor missile guidance;launching said interceptor missile, and controlling a first-stage guidance in response to target missile bearing and elevation at the predicted intercept point;transitioning to a second stage of propulsion of said interceptor missile;controlling second-stage guidance in response to second-stage acceleration commands;generating said second-stage acceleration commands in response to an elevated predicted intercept point generated by adjusting the predicted intercept point to account for effects of interceptor missile velocity at waypoint, interceptor missile propulsion beyond second stage, and gravity between the waypoint and the predicted intercept point, which predicted intercept point is generated using a Runge-Kutta integration method working on predicted target missile position, velocity, and acceleration;transitioning to a third stage of propulsion of said interceptor missile;guiding said third stage toward said target missile; andtransitioning to a fourth stage of interceptor missile flight and guiding interceptor missile to intercept said target missile. 2. A method according to claim 1, wherein said step of generating said second-stage acceleration commands includes the steps of: initializing a second-stage midcourse guidance algorithm with at least the pre-interceptor-missile-launch predicted intercept point, predicted intercept time, and waypoint;generating said elevated predicted intercept point by calculating a current estimate of target missile position and velocity at said predicted intercept point using the Runge-Kutta integration technique which uses current and future predictions of the target missile position, velocity, and acceleration including target missile boost acceleration, and estimating said elevated predicted intercept point by adjusting said predicted intercept point to account for effects of interceptor missile velocity at waypoint, interceptor missile propulsion beyond second stage, and gravity between the waypoint and the predicted intercept point;generating and updating an intercept triangle by calculating a direction of the interceptor missile's velocity vector at the waypoint, the time until the predicted intercept point, and the elevated predicted intercept point, using an average remaining interceptor missile velocity (VMAR) from the waypoint to the predicted intercept point, said intercept triangle being generated and updated with three vertices defined by the waypoint position of the interceptor missile, elevated linear target missile position, and the elevated predicted intercept point, where the elevated linear target missile position is calculated by taking the product of predicted target missile velocity at predicted intercept point and estimated time until predicted intercept point, and subtracting that product from the elevated predicted intercept point;determining an updated average remaining missile velocity (VMAR) from the interceptor missile's waypoint position to the updated elevated predicted intercept point, in a time interval between the waypoint and predicted intercept point; andgenerating the second-stage acceleration commands using a guidance law which calculates interceptor missile acceleration commands that cause the interceptor missile to fly through the waypoint position with its relative velocity vector pointing in the direction calculated as part of said process of generating and updating said intercept triangle. 3. A method according to claim 2, wherein, following said step of generating second-stage interceptor missile acceleration commands, iteratively repeating said steps of: generating said elevated predicted intercept point by calculating the current estimate of target missile position and velocity at said predicted intercept point using the Runge-Kutta integration technique which uses the current and future predictions of the target missile position, velocity, and acceleration including target missile boost acceleration, and estimating said elevated predicted intercept point by adjusting said predicted intercept point to account for the effects of interceptor missile velocity at waypoint, interceptor missile propulsion beyond second stage, and gravity between the waypoint and the predicted intercept point;generating and updating an intercept triangle by calculating the direction of the interceptor missile's velocity vector at the waypoint, the time until the predicted intercept point, and the elevated predicted intercept point, using the average remaining interceptor missile velocity (VMAR) from the waypoint to the predicted intercept point, said intercept triangle being generated and updated with the three vertices defined by the waypoint position of the interceptor missile, the elevated linear target missile position, and the elevated predicted intercept point, where the elevated linear target missile position is calculated by taking the product of predicted target missile velocity at predicted intercept point and estimated time until predicted intercept point, and subtracting that product from the elevated predicted intercept point;determining an updated average remaining missile velocity (VMAR) from the interceptor missile's waypoint position to the updated elevated predicted intercept point, in the time interval between the waypoint and predicted intercept point; andgenerating the second-stage acceleration commands using a guidance law which calculates interceptor missile acceleration commands that cause the interceptor missile to fly through the waypoint position with its relative velocity vector pointing in the direction calculated as part of said process of generating and updating said intercept triangle. 4. A method according to claim 2, wherein the guidance law comprises a vector gravity-optimized orthogonal navigation algorithm. 5. A guidance system for guiding a multistage interceptor missile toward a target missile, said guidance system comprising: a target missile tracking sensor for determining a location of said target missile;a processor associated with said target missile tracking sensor for determining a pre-interceptor-launch predicted intercept point and a predicted intercept time, and for loading the pre-interceptor-missile-launch predicted intercept point and time into an interceptor missile guidance;a launching arrangement coupled to the processor arrangement, for launching said interceptor missile, and for controlling a first-stage guidance of said interceptor missile in response to at least target missile bearing and elevation at said pre-interceptor-missile-launch predicted intercept point;a control transitioner for transitioning said propulsion of said interceptor missile to a second stage of propulsion of said interceptor missile;a second-stage guidance controller for controlling the second-stage guidance of said interceptor missile toward a waypoint in response to second-stage acceleration commands;a second-stage acceleration command generator for generating a predicted intercept point using a Runge-Kutta integration method, using predicted target missile position, velocity, and acceleration, and for generating said second-stage acceleration commands in response to an elevated predicted intercept point generated by adjusting said predicted intercept point to account for effects of interceptor missile velocity at said waypoint, interceptor missile propulsion beyond second stage, and gravity between said waypoint and said predicted intercept point; anda further guidance processor coupled to said interceptor missile for guiding stages of said interceptor missile beyond said second stage toward said target missile. 6. The guidance system of claim 5, wherein the target missile tracking sensor comprises a radar system. 7. The guidance system of claim 5, wherein the target missile tracking sensor comprises an overhead non-imaging infrared sensor. 8. The guidance system of claim 5, wherein the target missile tracking sensor comprises a space based sensor. 9. The guidance system of claim 5, wherein the launching arrangement comprises a shipboard launcher. 10. The guidance system of claim 5, wherein the launching arrangement comprises a land-based launcher. 11. The guidance system of claim 5, wherein the target missile tracking sensor and the launching arrangement are co-located. 12. A method for guiding a multistage interceptor missile toward a target missile, said method comprising the steps of: tracking a position of said target missile;generating a pre-interceptor-missile-launch predicted intercept point and a predicted intercept time;launching said interceptor missile and controlling a first-stage guidance of said interceptor missile in response to a bearing and an elevation of the target missile at the predicted intercept point;transitioning to a second stage of propulsion of said interceptor missile;controlling a second-stage guidance of said interceptor missile by generating second-stage acceleration commands in response to a modified predicted intercept point generated by adjusting the predicted intercept point to account for effects of interceptor missile velocity at a waypoint, interceptor missile propulsion beyond second stage, and gravity between the waypoint and the predicted intercept point;transitioning to a third stage of propulsion of said interceptor missile;guiding said third stage toward said target missile; andtransitioning to a fourth stage of interceptor missile flight and guiding said interceptor missile to intercept the target missile. 13. The method of claim 12, wherein the predicted intercept point is generated using a Runge-Kutta integration method. 14. The method of claim 12, wherein said step of generating second-stage acceleration commands includes the steps of: initializing a second-stage midcourse guidance algorithm with at least the pre-interceptor-missile-launch predicted intercept point, predicted intercept time, and waypoint;generating said elevated predicted intercept point by calculating the current estimate of target missile position and velocity at said predicted intercept point using a Runge-Kutta integration technique;generating and updating an intercept triangle by calculating a desired direction of the interceptor missile's velocity vector at the waypoint, the time until the predicted intercept point, and the elevated predicted intercept point, using the average remaining interceptor missile velocity (VMAR) from the waypoint to the predicted intercept point;determining an updated average remaining missile velocity (VMAR) from the interceptor missile's waypoint position to the updated elevated predicted intercept point, in the time interval between the waypoint and predicted intercept point; andgenerating the second-stage acceleration commands using a guidance law. 15. The method of claim 14, wherein said intercept triangle is generated and updated with the three vertices defined by the waypoint position of the interceptor missile, the elevated linear target missile position, and the elevated predicted intercept point. 16. The method of claim 15, wherein the elevated linear target missile position is determined by taking the product of predicted target missile velocity at predicted intercept point and estimated time until predicted intercept point, and subtracting that product from the elevated predicted intercept point. 17. The method of claim 14, wherein the guidance law calculates interceptor missile acceleration commands that cause the interceptor missile to fly through the waypoint position with its relative velocity vector pointing in the direction calculated as part of said process of generating and updating said intercept triangle. 18. The method of claim 17, wherein the guidance law is a vector gravity-optimized orthogonal navigation algorithm.
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이 특허에 인용된 특허 (7)
Pedersen,Christian E.; Boka,Jeffrey B.; Patel,Naresh R.; Bishop,Peter N.; Bauer,Carl J.; Bae,Koeunyi, Boost phase intercept missile fire control system architecture.
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