Lightweight missile guidance system

Details Lightweight missile guidance system Lightweight missile guidance system

1990-01-08

1991-06-11

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

F41G 736

Patent

active

050226088

ABSTRACT:
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 .sigma. 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.

REFERENCES:
patent: 3025023 (1962-03-01), Barghausen

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