Results 11 to 20 of about 17,267 (230)

Numerical modelling of the hybrid rocket engine performance

Propulsion and Power Research, 2021
The purpose of this paper is to present method of the numerical modeling of the hybrid rocket engine's work as a tool for designing engines of this type.
Marian Gieras, Aleksander Gorgeri
doaj   +3 more sources

Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

Aerospace, 2021
Optimization of Hybrid Rocket Engines at Politecnico di Torino began in the 1990s. A comprehensive review of the related research activities carried out in the last three decades is here presented.
Lorenzo Casalino, Filippo Masseni, Dario Pastrone   +2 more
doaj   +3 more sources

Experimental Firing Test Campaign and Nozzle Heat Transfer Reconstruction in a 200 N Hybrid Rocket Engine with Different Paraffin-Based Fuel Grain Lengths

Aerospace, 2023
Firing test campaigns were carried out on a 200 N thrust-class hybrid rocket engine, using gaseous oxygen as an oxidizer and a paraffin-wax-based fuel.
Daniele Cardillo, Francesco Battista, Giuseppe Gallo, Stefano Mungiguerra, Raffaele Savino   +4 more
doaj   +3 more sources

Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers

Aerospace, 2022
Hybrid rocket engines are a green alternative to solid rocket motors and may represent a low-cost alternative to kerosene fueled rockets, while granting performance and control features similar to that of typical storable liquid rocket engines.
Lorenzo Casalino, Andrea Ferrero, Filippo Masseni, Dario Pastrone   +3 more
doaj   +1 more source

Ascent trajectory optimisation for a single-stage-to-orbit vehicle with hybrid propulsion [PDF]

, 2012
This paper addresses the design of ascent trajectories for a hybrid-engine, high performance, unmanned, single-stage-to-orbit vehicle for payload deployment into low Earth orbit. A hybrid optimisation technique that couples a population-based, stochastic
Brown, Richard, Maddock, Christie, Minisci, Edmondo, Pescetelli, Fabrizio, Taylor, Ian   +4 more
core   +1 more source

Effect of tangential swirl air inlet angle on the combustion efficiency of a hybrid powder-solid ramjet [PDF]

, 2019
A new ramjet configuration using powder and solid fuel as propellant is investigated, namely, hybrid powder-solid ramjet (HPSR). Boron particles were used as the powder in this study.
ANSYS Inc, Ao, Betelin, Cai, Chang, Chelaru, Chen, dawara, Gany, Gany, Glassman, Goroshin, Haijun Sun, Hu, Humberto Medina, Hussmann, Hussmann, Jung, Kalpakli, Kazaoka, King, Li, Li, Liang, Loftus, Magnussen, Meinköhn, Morsi, Musa, Musa, NASA, Natan, Nie, Pern, Pern, Povitsky, Rashkovskiy, Rodić, Rui Jia, Sandall, Sender, Shih, Shorr, Varghese, Wang, Xia, Xia, Xu, Yeh, Yihua Xu   +49 more
core   +1 more source

DESIGN FEATURES OF ENGINES WITH PULSED DETONATION CAMERAS

Авіаційно-космічна техніка та технологія, 2020
The pressure of the products of chemical reactions in the chamber of a rocket engine increases significantly if the rocket fuel components burn in the detonation mode.
Олександр Євгенович Золотько, Олена Василівна Золотько, Олександра Валеріївна Сосновська, Олександр Сергійович Аксьонов, Ірина Сергіївна Савченко   +4 more
doaj   +1 more source

Verification of Model of Calculation of Intra-Chamber Parameters In Hybrid Solid-Propellant Rocket Engines

MATEC Web of Conferences, 2016
On the basis of obtained analytical estimate of characteristics of hybrid solid-propellant rocket engine verification of earlier developed physical and mathematical model of processes in a hybrid solid-propellant rocket engine for quasi-steady-state flow
Zhukov Ilya S., Borisov Boris V., Bondarchuk Sergey S., Zhukov Alexander S.   +3 more
doaj   +1 more source

Far Field Deposition Of Scoured Regolith Resulting From Lunar Landings [PDF]

, 2012
As a lunar lander approaches a dusty surface, the plume from the descent engine impinges on the ground, entraining loose regolith into a high velocity dust spray.
Goldstein, D. B., Morris, A. B., Trafton, L. M., Varghese, P. L.   +3 more
core   +1 more source

Viability of an Electrically Driven Pump-Fed Hybrid Rocket for Small Launcher Upper Stages

Aerospace, 2019
An electrically driven pump-fed cycle for a hybrid rocket engine is proposed and compared to a simpler gas-pressurized feed system. A liquid-oxygen/paraffin-based fuel hybrid rocket engine which powers the third stage of a Vega-like launcher is ...
Lorenzo Casalino, Filippo Masseni, Dario Pastrone   +2 more
doaj   +1 more source