This paper presents the results of an effort to optimize a conceptual design of a conical (wingedcone) single-stage-to-orbit launch vehicle. The vehicle employs a rocket-based combined-cycle (RBCC) engine capable of four different operating modes ejector, ramjet, scramjet, and rocket. The RBCC engine offers higher engine thrust-to-weight ratios than competing airbreathing engine cycles while ma...

The performances of a dual-combustion ramjet (DCR) and scramjet were compared via computational fluid dynamics numerical simulation to provide theoretical guidance for engine selection hypersonic vehicle. Kerosene, C12H23, with an equivalence ratio 0.8, was employed as the fuel, reactive flow modeled using six-species four-step chemistry. results show that DCR has central combustion mode, which...

This paper will discuss Air Force Research Laboratory (AFRL) Propulsion Directorate’s theoretical and computational results regarding trajectory simulations, qualitative analyses and parametric studies of a 25-cm focal diameter Laser Ramjet (X-25LR) using Optimal Trajectories by Implicit Simulation (OTIS). OTIS has been used to produce an optimized trajectory simulation of a laser ramjet’s flig...

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...

Abstract In this paper, to improve the combustion characteristics and working performance of solid fuel ramjet, a ramjet with gas generator is proposed. Based on k − ω SST Eddy-Dissipation equations, turbulent model established, internal flow field as well regression rate, species, were numerically analyzed. The results show that temperature rate increased. When airflow 0.4kg/s, increase will l...

The performance of ramjet engines with a supersonic combustion is one the main directions hypersonic aircraft development research studied. Researchers around world create special experimental facilities for testing engine models, investigate fuels and classify new scientific data. Since ambient temperature oxidizer flow in air duct are low at flight altitude aircraft, melting materials can be ...