초록 ▼

A fire control system for a boost phase threat missile includes sensors for generating target-missile representative signals, and a multi-hypothesis track filter, which estimates the states of various target hypotheses. The estimated states are typed to generate hypotheses and their likelihoods. The

A fire control system for a boost phase threat missile includes sensors for generating target-missile representative signals, and a multi-hypothesis track filter, which estimates the states of various target hypotheses. The estimated states are typed to generate hypotheses and their likelihoods. The states, hypotheses and likelihoods are applied to a multihypothesis track filter, and the resulting propagated states are applied to an engagement planner, together with the hypotheses and likelihoods. The engagement planner initializes the interceptor(s). Interceptor guidance uses the initialization and the propagated states and typing information to command the interceptor.

대표청구항 ▼

What is claimed is: 1. A method for determining acceleration commands for an interceptor missile, said method comprising the steps of: generating estimated propagated target states; generating estimated interceptor missile states; integrating said estimated interceptor missile states to generate pr

What is claimed is: 1. A method for determining acceleration commands for an interceptor missile, said method comprising the steps of: generating estimated propagated target states; generating estimated interceptor missile states; integrating said estimated interceptor missile states to generate propagated interceptor missile states; and from said propagated interceptor missile states and said propagated target states, determining desired interceptor missile acceleration; and controlling said interceptor missile to achieve said desired interceptor missile acceleration. 2. A method according to claim 1, wherein said determining step comprises the steps of: from said propagated interceptor missile states and said propagated target states, determining the zero effort miss distance between said interceptor missile and said target missile at their closest approach; comparing said zero effort miss distance with a predetermined threshold distance; if said zero effort miss distance is greater than said threshold distance, optimizing the heading of said interceptor missile to reduce said zero effort miss distance, and repeating said steps of generating estimated interceptor missile states, integrating said estimated interceptor missile states, determining the zero effort miss distance, and comparing said zero effort miss distance with a predetermined threshold distance; and if said zero effort miss distance is less than said threshold distance, selecting the optimized heading as the desired interceptor missile heading; determining the error between the desired interceptor missile heading and the actual interceptor missile heading to produce an angle; using an interceptor missile guidance law and said angle, determining said desired interceptor missile acceleration. 3. A method according to claim 2, wherein said step of generating estimated propagated target positions includes the step of integrating target positions. 4. A method for determining acceleration commands for an interceptor missile, said method comprising the steps of: generating estimated propagated target states; generating estimated interceptor missile states; integrating said estimated interceptor missile states to generate propagated interceptor missile states; from said propagated interceptor missile states and said propagated target states, determining the zero effort miss distance between said interceptor missile and said target missile at their closest approach; comparing said zero effort miss distance with a predetermined threshold distance; if said zero effort miss distance is greater than said threshold distance, optimizing the heading of said interceptor missile to reduce said zero effort miss distance, and repeating said steps of generating estimated interceptor missile states, integrating said estimated interceptor missile states, determining the zero effort miss distance, and comparing said zero effort miss distance with a predetermined threshold distance; and if said zero effort miss distance is less than said threshold distance, selecting the optimized heading as the desired interceptor missile heading; determining the error between the desired interceptor missile heading and the actual interceptor missile heading to produce an angle; using an interceptor missile guidance law and said angle, determining desired interceptor missile acceleration; and controlling said interceptor missile to achieve said desired interceptor missile acceleration. 5. A method for computing acceleration commands for an interceptor missile throughout the flight of the interceptor missile so as to put the interceptor missile on a collision course with a target missile, said method comprising the steps of: determining the current states of said interceptor missile; integrating the interceptor states forward in time using an interceptor model; generating a best estimated trajectory for the threat missile from n-m propagated threat state histories associated with n-m hypotheses of possible threat missile type and stage; determining the point of closest approach of said interceptor missile to said best estimated trajectory of said threat missile; and computing said acceleration commands to reduce the separation of said interceptor missile and said target missile at said point of closest approach; and controlling said interceptor missile to achieve said point of closest approach. 6. A method according to claim 5, wherein said step of generating a best estimated trajectory for the threat missile comprises the steps of: weighting the three-dimensional position, velocity, and acceleration states of the n-m hypothesis by the n-m likelihoods pursuant to where X is a propagated threat missile position for one hypothesis; V is a propagated threat missile velocity for one hypothesis; Ā is a propagated threat missile acceleration for one hypothesis; XBET is the best estimated threat missile position; VBET is the best estimated threat missile velocity; and ĀBET is the best estimated threat missile acceleration.