LIGHTWEIGHT MISSILE GUIDANCE SYSTEM

摘要

A lightweight missile terminal guidance system(14)is disclosed which includes a seeker (16) for providing a first signal indicative of a first angle .epsilon. between a line-of-sight (15) from the missile(10)to a target(12)and a longitudinal axis (9) extending through the missile(10). The seeker(16)also provides a second signal indicative of a second angle .delta. between the longitudinal axis (9) extending through the missile(10)and a line-of-sight(11) between the missile (10) and a celestial body (13). A processor (18) is included for computing the line-of-sight angle a between the line-of-sight (15) from the missile (10) to the target (12) and the line-of-sight (11) from the missile(10)to the celestial body (13) from the first and second angles .epsilon. and .delta.. A terminal guidance subsystem(24) computes acceleration commands from the line-of-sight .sigma. angle which are used by a propulsion system(26)to change the velocity vector of the missile(10) in response thereto.