| 摘要 |
A large power-flueric amplifier is controlled by selective restriction of opposing control parts. An inertially stabilized wheel serves to orifice the amplifier control ports to generate a control moment for directional control of a rocket or missile. A hot gas generator furnishes output gases that exhaust through the fluid amplifier, exiting through opposing exhaust ports around the periphery of the missile to maintain the missile on the original flight path. The inertially stabilized wheel, spinning in a plane normal to the missile flight path, spins on a sleeve or bearing through which the nozzle of the flueric amplifier passes. Tubular members extend radially from the flueric amplifier interaction chamber and terminate adjacent the interior annular surface of the spinning wheel. The wheel covers a portion of each tube inlet and varies the opening of each control inlet in response to relative motion between the spinning wheel and the missile. Ambient air pressure at each control inlet is constantly applied to uniformly exhausting gases when the missile is aligned with the spinning gyrowheel. Deviation in missile direction results in increased ambient pressure at one control port and decreased pressure at the opposing control port, causing the exhaust gases to move toward one wall, thus, producing an imbalance in the exhaust port gases which restore the missile to the flight path.
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