METHOD AND DEVICE FOR EVACUATION OF COMPRESSION CHAMBER DURING TESTS OF LIQUID LOW-THRUST ROCKET ENGINES IN MULTIPLE-START MODE

摘要

FIELD: rocket engineering. SUBSTANCE: in intervals between engine starts the compression chamber 1 is put in communication with vacuum space 9 through controllable start-stop device 10, thus reducing pressure in compression chamber below the preset level. Before starting the engine, the compression chamber is disconnected from vacuum space and vented to atmosphere; then pressure in chamber is raised to preset level and the chamber is connected to ejection system. EFFECT: provision of variable evacuation mode during tests of rocket engine. 2 cl, 2 dwg