| 摘要 |
A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. One or more hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain produces exhaust gas only when oxidizer is provided. The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. The fuel grain can thus react quickly to a substantial flow of oxidizer. When the thrust vector is to be modified, the appropriate one of the hybrid gas generators receives a flow of oxidizer, and the resulting exhaust gas is injected through the side of the nozzle to disrupt the flow of propulsion fluid and modify the thrust vector. (147)
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