Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1982-08-30
1985-08-27
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F41G 700
Patent
active
045373710
ABSTRACT:
A small caliber guided projectile (20) includes a maneuvering unit (22) having a forward opening inlet (36) which provides diffused air to a flow control mechanism (70) prior to exhausting such air through diametrically opposed exhaust nozzles (74, 76). The flow control mechanism (70) includes a primary flow passageway (78) and an upper orifice switching device (100) for controlling bypass flow to one of the exhaust nozzles (76). An orifice switching device (120) controls bypass flow to the other exhaust nozzle (74). In one embodiment, a small, rearward facing step or other means of vortex generation, such as boundary layer energization, is located upstream of the discharge of the flow through switching devices into the nozzles. When the switching devices are closed, flow over the rearwardly facing steps generates a small vortex which enhances flow attachment as a result of the Coanda effect and increases flow through the nozzle. Opening of the orifice switching device results in aspiration through the nozzle, thereby impeding flow. By controlling the respective switching devices, flow through the opposed nozzles may be varied to produce a resultant lateral force on the projectile, permitting control of the trajectory of the projectile.
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IBM Technical Disclosure, B. J. Greenblott, Fluid Controlled Device, vol. 6, No. 5 (Oct. 1963).
Clinkenbeard Ivan L.
Lawhorn William S.
Cate J. M.
Jordan Charles T.
LTV Aerospace and Defense Company
Sadacca S. S.
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