| 摘要 |
The present invention provides an improved hot gas control valve (20) which is adapted to apportion a gas flow, such as that issuing from a solid propellent gas generator, among a plurality of outlets communicating with rocket thruster nozzles (36). The improved valve has a body (21) and a valve member (22). The body has an inlet (24) communicating with an internal cavity. The cavity is partially bounded by a partially-spherical concave surface (32). The body has a plurality of outlet passages terminating in ports at the concave body surface. The valve member is operatively arranged within the cavity for omni-directional pivotal movement therewithin. The valve member has a surface (40) sealingly engaging the body concave surface and terminating in an edge (41). This valve member edge cooperates with the body ports to form variable-area metering orifices (A, B, C and D) therebetween. These orifices are so configured and arranged as to vary the areas of the orifices as a function of the angular position of the valve member relative to the body such that sum of the individual open areas of the metering orifices is substantially independent of valve member position over an operating range of valve member movement relative to the body.
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