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...

While NASA’s current next-generation launch vehicle research has largely focused on advanced allrocket single-stage-to-orbit vehicles (i.e. the X-33 and it’s RLV operational follow-on), some attention is being given to advanced propulsion concepts suitable for “next-generation-and-a-half” vehicles. Rocketbased combined-cycle (RBCC) engines combining rocket and airbreathing elements are one cand...

In the paper short information about advantages of introduction detonation combustion to propulsion systems is briefly discussed and then research conducted at ?ukasiewicz-Institute Aviation on development rotating engines (RDE) presented. Special attention focused continuously (CRD), since it offers significant over pulsed (PD). Basic aspects initiation stability CRD are discussed. Examples ap...

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...

Cryogenic liquid propellants are used in rocket engines to obtain high specific impulse. The flow rates controlled by turbopumps that deliver propellant the engine at pressure levels. Due very low saturation temperature of cryogenic propellant, first phases transient operation, which is ambient temperature, its surfaces subject boiling conditions. effect on heat transfer between solid and fluid...

The liquid rocket propellant burns inadequately in the combustion chamber; therefore, exhaust gas reacts with oxygen and heat that was generated, which turn affects thermal environment. By using finite-rate chemical kinetics discrete ordinates method, calculation model for four-engine flowfield is established, numerically investigates afterburning effect on environment of engine plume under dif...

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...

The work focuses on optimizing the pressurization system’s operating performance for a fuel tank of turbo-pumped liquid propellant rocket engine. This system is most complex and expensive in medium-size launch vehicle, after A new patented methodology reducing final mass stage proposed, studied, validated. application proposed method efficient at end engine operation sequence during throttling ...