초록 ▼

A multi-node Lambert Guidance System that controls missile velocity along a missile flight path through adjustment of missile attitude during guidance of the missile through an intercept point and one or more way points. The system utilizes a linear Lambert solution in that it is derived from a plur

A multi-node Lambert Guidance System that controls missile velocity along a missile flight path through adjustment of missile attitude during guidance of the missile through an intercept point and one or more way points. The system utilizes a linear Lambert solution in that it is derived from a plurality of Lambert solutions each corresponding to a particular node along the prelaunch flight path solution and each including corresponding time varying weights on the accuracy at several flight path nodes. The present invention allows direct translation of guidance velocity corrections into vehicle attitude adjustment commands, and thereby avoids additional computation required in prior predictive integration guidance approaches.

대표청구항 ▼

[ What is claimed is:] [5.] A multi-node Lambert Guidance System for a missile, comprising:navigation means for generating missile coordinate data;a memory programmed with a plurality of prelaunch Lambert solutions for a plurality of nodes along a missile prelaunch solution flight path;a processor f

[ What is claimed is:] [5.] A multi-node Lambert Guidance System for a missile, comprising:navigation means for generating missile coordinate data;a memory programmed with a plurality of prelaunch Lambert solutions for a plurality of nodes along a missile prelaunch solution flight path;a processor for determining a solution for a weighted linear combination of said Lambert solutions for correction of missile flight path errors based on data input from said navigation means; andsteering means for correcting said missile flight path errors in response to flight path error correction commands output from said processor.