Initial microgravity research centered around solving space flight problems created by the reduction in gravity’s effects experienced on orbit. How do you get the proper amount of fuel to a rocket engine in space or water to an astronaut on a spacewalk? The brief periods of microgravity available in drop towers at the Lewis Research Center and the Marshall Space Flight Center were sufficient to...

An unprecedented combination of high propellant fraction and small size is required for affordable-scale Mars return, regardless of the number of stages, or whether Mars orbit rendezvous or in-situ propellant options are used. Conventional space propulsion technology is too heavy, even without structure or other stage subsystems. The application of launch vehicle design principles to the develo...

This paper describes an application of Sandia's non-contact capacitive sensing technology for collision avoidance during the manufacturing of rocket engine thrust chambers. The collision avoidance system consists of an octagon shaped collar with a capacitive proximity sensor mounted on each face. The sensors produce electric fields which extend several inches from the face of the colIar and det...

The supercritical turbulent flow of cryogenic methane flowing in a rocket engine cooing channel is numerically analysed by imposing constant heat flux at the bottom surface of the channel. The calculation scheme is validated by comparing the results obtained with experimental results reported in literature. The heat transfer coefficient is influenced by the strong variation in thermophysical pr...

A model has been developed for the behavior of all isolated fluid drop of a single component species inlrnersed into another single component species in finite, quiescent surroundings at supercritical conditions. ‘1’he model is based upon fluctuation theory which accounts for both Soret and Dufour effects in the calculation of the transport matrix relating molar and heat fluxes to the transport...

Abstract Although the low-thrust liquid oxygen/methane rocket engine has broad application prospects, low flame propagation speed and combustion rate of methane fuel make still face key technical challenges. Methane is partially converted into hydrogen ethane with higher before being injected chamber, which positive for use dielectric barrier to improve performance engine. Therefore, this paper...

Abstract A very short survey of research conducted in Poland on the development rotating detonation engine (RDE) is presented. Initial studies cooperation with Japanese partners lead to a joint patent RDE. Then, an intensive basic and applied was started at Institute Heat Engineering Warsaw University Technology. One first achievements demonstration performance rocket aerospike nozzle utilizing...

A comprehensive numerical analysis was conducted to study the internal flow development in an integrated rocket-ramjet (IRR) propulsion system. The study consists of two parts: transition from the rocket booster to the ramjet sustainer and combustion dynamics during ramjet operation. The physical model of concern includes the entire IRR flow path, extending from the leading edge of the inlet ce...

During the development stage of a space vehicle, instrumented tests are carried out on ground to prove operational capacity each liquid-propellant rocket engine, which is installed in this type vehicle. The task elaborating Test Bench project for propulsion unit with application complex and involves several steps, one these steps being related analysis bench meet algorithms rocket-engine full r...