FIELD: transport.
SUBSTANCE: invention relates aerospace engineering, namely, to design of rocket engines with pneumatic systems. Engine plant comprises oxidiser tank filled with low-boiling component, fuel tank filled with high-boiling component, sustainer engine, actuator, high-pressure gas cylinder arrange in oxidiser tank, heat exchanger comprising said tank and heat exchange pipelines arranged therein. Heat exchanger incorporates receiver and coil with T-band. One end of coil is communicated with receiver and another one is communicated with common outlet of heat exchange pipelines. Receiver and coil are secured on fuel tank to stay in thermal contact therewith. Said T-bend in coil is mounted downstream of heat exchange pipelines. T-band side union communicates with engine plant actuators. Coil, receiver and fuel tank are enclosed in rocket pod shield-vacuum heat insulation.
EFFECT: reduced dynamic properties of gas component flow and higher reliability of heat exchanger.
1 dwg
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