Results 11 to 20 of about 5,412,680 (360)

Experimental Investigation of Flame Anchoring Behavior in a LOX/LNG Rocket Combustor

Aerospace, 2023
Hot fire tests of a multi-injector research combustor were performed with liquid-oxygen and liquefied-natural-gas (LOX/LNG) propellants at chamber pressures from 30 up to 67 bar, hence at conditions similar to an upper stage rocket engine.
Jan Martin, Michael Börner, Justin Hardi, Dmitry Suslov, Michael Oschwald   +4 more
doaj   +1 more source

Experimental Investigation of Rotating Detonation Rocket Engines for Space Propulsion

Journal of Propulsion and Power, 2021
The performance (specific impulse, Isp) of a modular, 150-lbf-class rotating detonation rocket engine (RDRE) was measured with three gaseous fuels (methane, ethane, and ethylene) and gaseous oxygen...
Richard D. Smith, Steven B. Stanley
semanticscholar   +1 more source

Metal-Organic Frameworks Promoted Hydrogen Storage Properties of Magnesium Hydride for In-Situ Resource Utilization (ISRU) on Mars

Frontiers in Materials, 2021
Hydrogen is regarded as a promising solution to fulfill the energy demand of Mars human base in the future. Through in-situ resource utilization (ISRU) on Mars, the composite of metal-organic frameworks (MOFs) and magnesium hydride which demonstrates ...
Ze Zhang, Ze Zhang, Yuanding Wang, Yuanding Wang, Haoming Wang, Haoming Wang, Xiang Xue, Xiang Xue, Qingguo Lin, Qingguo Lin   +9 more
doaj   +1 more source

Control of opening duration in a pneumatically operated valve with two-fluid combination and quadratic damping

Journal of Engineering and Applied Science, 2023
In this paper, opening characteristics of a pneumatically operated valve and methodology for controlling the valve opening duration have been investigated through numerical simulation.
Debanjan Das, Shrey Waghmare, P. Padmanabhan, V. Kumaresan, D. P. Sudhakar   +4 more
doaj   +1 more source

SITAEL HC1 Low-Current Hollow Cathode

Aerospace, 2020
SITAEL is active in the field of electric propulsion and is involved in the development of different thruster technologies—mainly Hall thrusters (HTs)—of power levels ranging from 100 W up to 20 kW.
Daniela Pedrini, Cosimo Ducci, Ugo Cesari, Tommaso Misuri, Mariano Andrenucci   +4 more
doaj   +1 more source

Improved Wall Temperature Prediction for the LUMEN Rocket Combustion Chamber with Neural Networks

Aerospace, 2023
Accurate calculations of the heat transfer and the resulting maximum wall temperature are essential for the optimal design of reliable and efficient regenerative cooling systems.
Kai Dresia, Eldin Kurudzija, Jan Deeken, Günther Waxenegger-Wilfing   +3 more
doaj   +1 more source

Combustion Characteristics of HTPB-Based Hybrid Rocket Fuels: Using Nickel Oxide as the Polymer Matrix Pyrolysis Catalyst

Aerospace, 2023
The slow regression rate induced by the high pyrolysis difficulty has limited the application and development of hydroxyl-terminated polybutadiene (HTPB)-based fuels in hybrid rocket propulsion.
Hongsheng Yu, Xiaodong Yu, Hongwei Gao, Luigi T. DeLuca, Wei Zhang, Ruiqi Shen   +5 more
doaj   +1 more source

Derivation of Navier–Stokes equation in rotational frame for engineering flow analysis

International Journal of Thermofluids, 2021
One of the most frequently used governing equations underpinning engineering flow analysis is the renowned Navier–Stokes (NS) equation. Several references regarding the derivation of equation of motion in Cartesian coordinates are available in standard ...
Sananth H. Menon, Ramachandra Rao A, Jojo Mathew, Jayaprakash J   +3 more
doaj   +1 more source

Research on performance of PBT/Bu-NENA low-vulnerability propellant

FirePhysChem, 2022
Large-size program temperature controller was used to carry out the slow cook-off test study of PBT, Bu-NENA, PBT/Bu-NENA mixture and PBT/Bu-NENA propellant in the range of gram and kilogram scale.
Miaomiao Li, Zhipeng Zhou, Jingjing Chen, Tingting Zheng, Lianchao Cheng, Sen Xu   +5 more
doaj   +1 more source

Orifice Flow Dynamics in a Rocket Injector as an Excitation Source of Injector-Driven Combustion Instabilities

Aerospace, 2023
To investigate a hypothesis of the orifice flow-induced instability in rocket engine thrust chambers, a single liquid oxygen (LOX) injector with an optically accessible orifice module was used for experiments, with water as a simulant for LOX.
Min Son, Michael Börner, Wolfgang Armbruster, Justin S. Hardi   +3 more
doaj   +1 more source