Results 81 to 90 of about 1,431,155 (187)

3D printed hybrid rocket fuels with μAl core-shell particles coated with polyvinylidene fluoride and polydopamine: Enhanced combustion characteristics

Defence Technology
3D printing technology enhances the combustion characteristics of hybrid rocket fuels by enabling complex geometries. However, improvements in regression rates and energy properties of monotonous 3D printed fuels have been limited.
Qihang Chen, Xiaolong Fu, Weitao Yang, Suhang Chen, Zhiming Guo, Rui Hu, Huijie Zhang, Lianpeng Cui, Xu Xia   +8 more
doaj   +1 more source

On Soot and Its Environmental Impact in Hybrid Rocket Engines

Aerospace
Hybrid rocket engines (HREs) are increasingly considered for space transportation due to their inherent safety, cost-effectiveness, and operational flexibility.
Valerio Santolini, Christian Paravan
doaj   +1 more source

Experimental Investigation on a Throttleable Pintle-Centrifugal Injector

Applied Sciences
This paper presents the design and experimental evaluation of a throttleable pintle-centrifugal injector system tailored for hybrid rocket engines, aimed at improving combustion efficiency and enabling precise throttling control.
Tianwen Li, Nanjia Yu, Zeng Zhao, Yaming Zhao   +3 more
doaj   +1 more source

Analysis of advanced cooling strategies for rocket engines conveying ternary hybrid nanofluids with second slip conditions and melting heat transfer

Case Studies in Thermal Engineering
Effective cooling in rocket engines is essential to prevent overheating and ensure efficient performance under extreme operating conditions. This study presents a comprehensive investigation into advanced cooling strategies for rocket engines utilizing ...
Hatem Gasmi, A.M. Obalalu, Umair Khan, Anuar Ishak, Hami Gündoğdu, Nermeen Abdullah, Samia Elattar, Ahmed M. Galal   +7 more
doaj   +1 more source

Development and Testing of a Fast-Acting, 8-Bit, Digital Throttle for Hybrid Rocket Motors

Fire
The potential for throttle control of hybrid rocket systems has long been known as a potential advantage for a variety of applications. Because only a single flow path is controlled, theoretically, hybrids should be significantly easier to throttle than ...
Stephen A. Whitmore
doaj   +1 more source

Levenberg–Marquardt neural network prediction of MHD hybrid nanofluid flow between parallel plates: Aerospace applications

Ain Shams Engineering Journal
Thermal performance is an important and common issue for today’s aeronautic technology and electrically powered devices. The following problems are commonly encountered due to increased heat generation or decreased surface area for cooling (limitation ...
Gunisetty Ramasekhar, Maddina Dinesh Kumar, A. Divya, Nehad Ali Shah, Se-Jin Yook   +4 more
doaj   +1 more source

Staged Combustion Cycle Rocket Engine Design Trade-Offs for Future Advanced Passenger Transport [PDF]

, 2012
Staged combustion cycle rocket engines with a moderate nominal 16 MPa chamber pressure have been selected as the baseline propulsion system for the visionary intercontinental passenger transport SpaceLiner. Several technical engine design trade-offs are
Yamashiro, Ryoma, Sippel, Martin
core  

Neural Network-Based Optimization of Hybrid Rocket Design for Modular Multistage Launch Vehicle

Aerospace
In this paper, an integrated optimization is carried out to find the optimal hybrid rocket engine design for a modular multistage launch vehicle targeting a 500 km polar circular orbit. A single hybrid rocket engine unit is reused across the whole launch
Paolo Maria Zolla, Alessandro Zavoli, Mario Tindaro Migliorino, Daniele Bianchi   +3 more
doaj   +1 more source

AN OPTIMIZED HYBRID ROCKET MOTOR FOR THE SARA PLATFORM REENTRY SYSTEM DOI 10.5028/jatm.2012.04032312

Journal of Aerospace Technology and Management, 2012
This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the
Pedro Luiz Kaled Da Cás, Cristiano Queiroz Vilanova, Manuel Nascimento Dias Barcelos Jr., Carlos Alberto Gurgel Veras   +3 more
doaj  

Using Hydrogen Peroxide for Rocket Fuel Tank Pressurization: Innovations, Advantages, and Challenges

Challenges and Issues of Modern Science
This paper explores the innovative use of hydrogen peroxide (H₂O₂) as a pressurizing agent for rocket fuel tanks, highlighting its potential to enhance efficiency and performance in rocket propulsion systems.
Mykhailo Vorobei, Mykola Bondarenko
doaj