초록 ▼

The present invention relates to a system for guiding a missile in alignment onto a moving target. In particular, the guidance computer of the system has a first unit for estimating the state of the missile and the movements of a target on the basis of the measurement of the position of the missile

The present invention relates to a system for guiding a missile in alignment onto a moving target. In particular, the guidance computer of the system has a first unit for estimating the state of the missile and the movements of a target on the basis of the measurement of the position of the missile with respect to a datum axis, obtained by angular deviation measuring means, and by using a model of the dynamic behavior of the missile as well as kinematic model of the target. Additionally, the guidance computer has a second unit linked to the first unit for deriving tracking orders and datum values for slaving the missile, and a third unit linked to the first and second units for deriving the control order applied to the missile and the first unit.

대표청구항 ▼

[ I claim:] [1.] A system for guiding a missile in alignment onto a moving target, said system comprising an angular deviation measuring means for measuring a position of the missile with respect to a datum axis, and a guidance computer for supplying control orders to said missile as a function of s

[ I claim:] [1.] A system for guiding a missile in alignment onto a moving target, said system comprising an angular deviation measuring means for measuring a position of the missile with respect to a datum axis, and a guidance computer for supplying control orders to said missile as a function of said angular deviation measurements, wherein said guidance computer comprises:first means for estimating a state of the missile and movements of the target according to a measured position of the missile with respect to the datum axis, obtained by said angular deviation measuring means, and by using a model of dynamic behavior of the missile and a kinematic model of the target;second means for deriving tracking orders and datum values for slaving the missile to cancel out a lag in the tracking orders and the datum values with respect to the moving target, the tracking orders and datum values determining a nominal perfect trajectory of the missile with respect to the moving target by resolving equations for flight mechanics of the missile with equilibrium conditions of the missile, the second means being linked to said first means; andthird means for deriving a control order applied to the missile, which are linked to said first and second means for supplying said first means with said control order and for receiving the estimated state of the missile from said first means and the tracking orders and the slaving datum values from said second means.