초록 ▼

An ignition delay timing system, and corresponding method, for adjusting the position of an in-flight missile during its boost phase along its flight path according to a pre-launch flight path solution. The ignition delay system of the present invention is applied by navigating missile position betw

An ignition delay timing system, and corresponding method, for adjusting the position of an in-flight missile during its boost phase along its flight path according to a pre-launch flight path solution. The ignition delay system of the present invention is applied by navigating missile position between burnout of a given booster stage and ignition of a subsequent booster stage, and modifying ignition time of the subsequent boost stage so that the missile position along its flight path follows a pre-launch solution after all booster stages are burned. Nominal missile coast phases, which occur between burnout of one booster stage and ignition of subsequent booster stage are either increased or decreased for earlier or later booster stage ignitions to maintain the missile position along its flight path in accordance with the pre-launch solution.

대표청구항 ▼

[ What is claimed is:] [4.] A method of guiding a missile to an intended target, comprising the steps of:providing onboard missile control electronics including a memory and a processor, and missile navigation electronics;storing a plurality of missile guidance commands including booster stage ignit

[ What is claimed is:] [4.] A method of guiding a missile to an intended target, comprising the steps of:providing onboard missile control electronics including a memory and a processor, and missile navigation electronics;storing a plurality of missile guidance commands including booster stage ignition times in said memory in accordance with a pre-launch flight path;measuring missile flight path position data through said missile navigation electronics;calculating missile position error from data collected in said step of measuring missile flight path position; andadjusting ignition times of successive missile booster stages to compensate for missile position errors accrued in a prior booster stage and a prior coast phase as determined in said step of calculating missile position error.