Experimental studies of performance of the manned transportation spaceship’s landing propulsion system and its jets’ gasdynamic effects on the landing surface

The paper presents results of the model experimental studies of the discharge and specific impulse coefficients of the vertical braking nozzle of the future manned transportation spaceship’s reentry vehicle’s landing solid-rocket motor, flow pattern in this nozzle and pressure distribution on the landing surface’s jet impinging area. The experimental studies have been conducted on a 1:1,5 scaled model of the vertical braking nozzle having a controlled rectangular throat at presence of the reentry vehicle’s afterbody fragment model and the landing surface’s model in the Keldysh Center’s Nozzle Differential Facility. The working body’s total pressure have been varied in the 60...120 kgf/cm2 range. The tests have been conducted on high-temperature air-ethanol combustion products and on cold air. The obtained experimental data have been scaled to the full-scale conditions.