ALTITUDE STAND TO TEST ROCKET ENGINES Russian patent published in 1997 - IPC

FIELD: rocket engineering. SUBSTANCE: invention can be used for ground treatment of engine under altitude conditions. Altitude stand is equipped with actuating mechanism manufactured in the form of hydraulic switch 8 with drive 7 and gate valve 6. Altitude chamber has window. Gate valve 6 is installed on outer wall of altitude chamber for overlapping of window and is connected to drive 7 of actuating mechanism. Hydraulic switch includes case 1 inside which pistons with shanks are installed in cylindrical spaces communicating through space of cylindrical sleeve 2. Operation of the latter is controlled by pressure of tested engine with participation of stopper, pushers and controllers which bodies are installed on body 1 of hydraulic switch. Rods of controllers interact with contact system of hydraulic switch ensuring programmed connection of power winding of drive to power supply source. At start of engine window is open and gas driven by gas piston from gas path of diffuser is relieved through it into altitude chamber. This prevents peak of pressure in altitude chamber at start of operation of engine. Before start of diffuser window closes as result of operation of hydraulic switch and drive. Immediately before break-down of diffuser window opens automatically thanks to repeat operation of hydraulic switch and drive and cool gas of environment fills altitude chamber. Flow rate of cool gas exceeds more than 60 times flow rate of hot gas streaming into altitude chamber from gas path of diffuser is relieved through in into altitude chamber. This prevents peak of pressure in altitude chamber at start of operation of engine. Before start of diffuser window closes as result of operation of hydraulic switch and drive. Immediately before break-down of diffuser window opens automatically thanks to repeat operation of hydraulic switch and drive and cool gas of environment fills altitude chamber. Flow rate of cool gas exceeds more than 60 times flow rate of hot gas streaming into altitude chamber from diffuser after break-down. Thanks to it peak of temperature in altitude chamber is avoided at finish of operation of engine. EFFECT: enhanced testing efficiency. 2 cl, 16 dwg