Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1976-01-12
1977-04-12
Tudor, Harold
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
60229, 102 89R, 23926527, 244122AD, F41G 700
Patent
active
040170403
ABSTRACT:
A steerable rocket motor for towing a load or extracting an aircrew member rom a disabled aircraft, regardless of aircarft attitude or altitude. The rocket motor is formed from a hollow cylindrical thin walled casing containing a high burn rate propellant and having a plurality of rocket nozzles at one end. The rocket nozzles are positioned around the circumference of the rocket body and are angled to thrust outward and toward the load or aircrew member being towed. A thrust control proportions thrust among the plurality of nozzles for controlling the pitch and yaw of the rocket. Position and rate sensing apparatus informs the thrust control regarding rocket attitude to enable the rocket to steer a predefined desirable flight trafectory. One or more lines are attached to the rocket and are adapted to be fastened to the load or aircrew member being towed.
REFERENCES:
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patent: 2974594 (1961-03-01), Boehm
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patent: 3353354 (1967-11-01), Friedman et al.
patent: 3648955 (1972-03-01), Steneel
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patent: 3802651 (1974-04-01), Axenborg et al.
patent: 3891166 (1975-06-01), May
patent: 3949676 (1976-04-01), Schmidt
Dillinger Robert B.
Stone W. James
Miller Roy
Sciascia R. S.
The United States of America as represented by the Secretary of
Tudor Harold
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