Results 31 to 40 of about 1,790,414 (217)

Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket

Journal of Fluid Science and Technology, 2014
The subject of this paper is to improve on parameterization for conceptual design method of three stage hybrid rocket. Multi-Objective Genetic Algorithm (MOGA) is employed to solve multi-disciplinary design exploration of a three-stage launch vehicle ...
Masahiro KANAZAKI, Fumio KANAMORI, Yosuke KITAGAWA, Masaki NAKAMIYA, Koki KITAGAWA, Toru SHIMADA   +5 more
doaj   +1 more source

Hybrid Rocket Engine Ignition and Control [PDF]

, 2020
Control of a hybrid rocket engine is dependent upon a robust system capable of executing commands at precise times. In order to accomplish this, hardware systems must be in place to control the flow of a pressurized gas and provide feedback to launch ...
Johnson, Megan, Letourneau, Benjamin, Blampied, Trevor, Pham, Thomas   +3 more
core   +1 more source

Design, Production and Evaluation of 3D-Printed Mold Geometries for a Hybrid Rocket Engine

Aerospace, 2021
The feasibility of 3D-printed molds for complex solid fuel block geometries of hybrid rocket engines is investigated. Additively produced molds offer more degrees of freedom in designing an optimized but easy to manufacture mold.
Benedict Grefen, Johannes Becker, Stefan Linke, Enrico Stoll   +3 more
doaj   +1 more source

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

System Design and Launch of a Hybrid Rocket with a Star-Fractal Swirl Fuel Grain Toward an Altitude of 15 km

Applied Sciences
To achieve low-cost and on-demand launches of microsatellites, the authors have been researching and developing a micro hybrid rocket since 2014. In 2018, a ballistic launch experiment was performed using the developed hybrid rocket, where it reached an ...
Atsushi Takano, Keita Yoshino, Yuki Fukushima, Ryuta Kitamura, Yuki Funami, Kenichi Takahashi, Akiyo Takahashi, Yoshihiko Kunihiro, Makoto Miyake, Takuma Masai, Shizuo Uemura   +10 more
doaj   +1 more source

Variability analysis of ABS solid fuel manufactured by fused deposition modeling for hybrid rocket motors

Journal of Mechanical Engineering and Sciences, 2021
The process of fused deposition material (FDM) was used to manufacture propellant grains of Acrylonitrile Butadiene Styrene (ABS) as novel rocket fuel grain, with three types of geometry in the burning port.
Jose Alejandro Urrego, Fabio Arturo Rojas, Jaime Roberto Muñoz   +2 more
doaj   +1 more source

Static hot-fire testing of a green hybrid rocket engine [PDF]

, 2014
This paper presents the conduct of the hot-fire testing for a green hybrid rocket engine. The hybrid rocket engine consists of liquid nitrous oxide (N2O) as the oxidizer, with the stearic acid as the solid fuel and the incorporation of carbon nanotube ...
Abidin, Razali, Ahmad, Mohamed Tarmizi, Jagannathan, Anudiipnath, Saniman, Muhammad Nur Farhan, Zhahir, Amzari   +4 more
core   +1 more source

Cross‐Scale Hierarchical Targeted Delivery System Based on Small‐Scale Magnetic Robots

Advanced Robotics Research, EarlyView.
This article reviews a cross‐scale hierarchical targeted delivery system that integrates magnetic continuum robots and magnetic microrobots. By combining rapid long‐range navigation with precise microscale targeting, the system overcomes key limitations of single‐scale approaches.
Junjian Zhou, Zhiqiang Chen, Yuanbiao Ma, Zhiqiang Tang, Qianqian Wang   +4 more
wiley   +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  

Convective and Film Cooled Nozzle Extension for a High Pressure Rocket Subscale Combustion Chamber [PDF]

, 2010
Experimental investigations have been carried out to study heat transfer, flow separation, and side loads in a subscale nozzle extension. A Vulcain 2-like nozzle geometry has been tested with combustion chamber pressures up to 13 MPa. A new manufacturing
Richard Arnold, Haidn, O. J., Oskar Haidn, Dmitry Suslov, Suslov, D. I., Arnold, R.   +5 more
core   +1 more source