Rocket engine nozzle that is steerable by means of a moving...

Details Rocket engine nozzle that is steerable by means of a moving... Rocket engine nozzle that is steerable by means of a moving...

2005-09-27

2005-09-27

Rodriquez, William H. (Department: 3746)

Power plants

Reaction motor

With thrust direction modifying means

C060S228000, C060S200100

Reexamination Certificate

active

06948307

ABSTRACT:
The nozzle comprises a moving diverging portion (20) and a static portion (16) secured to the rear end wall of the combustion chamber (12) of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to the static portion, the moving diverging portion and the static portion being in mutual contact via respective spherical surfaces (24a,16a), and an actuator device (50a,50b) acts on the moving diverging portion of the nozzle so as to be able to vary the direction of the thrust vector of the engine by modifying the orientation of the nozzle with sliding of the spherical surfaces one on the other. Resilient return means (62, 64) are interposed between the moving diverging portion (20) of the nozzle and the static portion (16) and act on the moving diverging portion in order to urge it towards the static portion so as to keep the spherical surfaces (24a,16a) in mutual contact for any desired orientation of the nozzle.

REFERENCES:
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patent: 3140584 (1964-07-01), Ritchey et al.
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patent: 3401887 (1968-09-01), Sheppard
patent: 3436021 (1969-04-01), Walton et al.
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patent: 3811713 (1974-05-01), Barrett et al.
patent: 4350297 (1982-09-01), Martin
patent: 31 19 183 (1982-12-01), None

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