Imbibition of liquids into porous media has significant importance to many processes. For example one application is the propellant management device (PMD), or liquid acquisition device (LAD), located within spacecraft tanks [1, 7]. The PMDs are designed to ensure gas free delivery of propellant during all mission accelerations. This is done by using a porous medium, a metallic mesh, which prev...

A new dual-fluid concept was studied that could eventually find application for cold-gas propulsion for small space satellites or other constant flow applications. In basic form, the concept uses two different refrigerant working fluids, each having a different saturation vapor pressure. The higher vapor pressure refrigerant remains in the saturation phase and is used to pressurize the lower sa...

This paper describes the design of a liquid-propellantpowered hot-gas actuator appropriate for human-scale power-autonomous robots. A prototype of the actuation system is described, and closed-loop tracking data is shown that demonstrates good motion control. Experiments to characterize the energetic performance of the actuation system indicate that the proposed system with a diluted propellant...

This article is devoted to an important problem of calculation of deflected mode of the combustion chamber and the nozzle end of a new liquid-propellant rocket cruise engine. A special attention is given to the methodology of calculation. Three operating modes are considered. The analysis has been conducted in ANSYS software. The methods of conducted research are mathematical modeling, substruc...

A theoretical study analyzing three-dimensional combustion acoustic instabilities in a liquid propellant rocket engine combustor has been conducted. A linear theory based on Crocco’s pressure sensitive time lag model is used. To apply this theory the combustor is divided into two main components, including the combustion chamber and the converging part of the nozzle. The assumption of concentra...

Environmental impact assessment of liquid rocket motor exhaust obtained due to mainly liquid propellant combustion have been highlighted. Exhaust product analysis has been carried out theoretically by computer software NASA CEC -71 to identify toxic emissions of rocket combustion. In the present study a high volume Air Samplers (APM-430) was deployed at predetermined locations near launch pad f...