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Solid Rocket Motor Design Using Hybrid Optimization [PDF]

International Journal of Aerospace Engineering, 2012
A particle swarm/pattern search hybrid optimizer was used to drive a solid rocket motor modeling code to an optimal solution. The solid motor code models tapered motor geometries using analytical burn back methods by slicing the grain into thin sections ...
Kevin Albarado, Roy Hartfield, Wade Hurston, Rhonald Jenkins   +3 more
doaj   +2 more sources

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Aerospace
Hybrid rocket motors have great development potential due to their outstanding thrust adjustment flexibility and long-term operation ability. However, nozzle erosion during the motor operation can cause an increase in the throat area of the nozzle, which
Xiangyu Meng, Hui Tian, Xiaoting Niu, Hao Zhu, Jingfei Gao, Guobiao Cai   +5 more
doaj   +1 more source

Hydrogen peroxide – A promising oxidizer for rocket propulsion and its application in solid rocket propellants

FirePhysChem, 2022
This paper discusses the potential use of hydrogen peroxide as oxidizer for solid rocket propulsion. While hydrogen peroxide is a liquid in normal conditions, it may be used in solid rocket motor grains.
Wioleta Kopacz, Adam Okninski, Anna Kasztankiewicz, Paweł Nowakowski, Grzegorz Rarata, Pawel Maksimowski   +5 more
doaj   +1 more source

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Aerospace, 2023
This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works ...
Jihyoung Cha
doaj   +1 more source

Numerical Simulations of Flow and Fuel Regression Rate Coupling in Hybrid Rocket Motors [PDF]

INCAS Bulletin, 2017
The hybrid propulsion offers some remarkable advantages like high safety and high specific impulse and thus it is considered a promising technology for the next generation launchers and space systems. The purpose of this work is to validate a design tool
Marius STOIA-DJESKA, Florin FRUNZULICA, Florin MINGIREANU   +2 more
doaj   +1 more source

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

Fire, 2023
As the research on hybrid rocket motors advances, more accurate tools are needed to estimate the performance of the system by determining its fundamental parameters. One of them is certainly the regression rate of the solid fuel.
Alessandro Rampazzo, Francesco Barato
doaj   +1 more source

Launch and Recovery of a Hybrid Rocket Intended for Reuse

Aerospace
The objective of the project was to develop a hybrid rocket with a recovery system that would facilitate reuse. The rocket was successfully developed, launched and recovered.
Atsushi Takano, Shintaro Hatano, Akane Fujita, Yuki Funami, Kenichi Takahashi, Akiyo Takahashi, Apollo B. Fukuchi, Yoshihiko Kunihiro, Makoto Miyake, Takuma Masai, Shizuo Uemura, Akiya Onzuka, Shunichi Kawamura   +12 more
doaj   +1 more source

Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor

FirePhysChem, 2021
The showerhead is the most common type of injector used in hybrid rocket motors due to its design and manufacture simplicity. The main drawback of the showerheads (SH) is the relatively low performance in terms of combustion efficiency because of the ...
M. Bouziane, A.E.M. Bertoldi, P. Hendrick, M. Lefebvre   +3 more
doaj   +1 more source

Comprehensive Data Reduction for N₂O/HDPE Hybrid Rocket Motor Performance Evaluation

Aerospace, 2019
Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle ...
Landon Kamps, Kazuhito Sakurai, Yuji Saito, Harunori Nagata   +3 more
doaj   +1 more source

The Three-Dimensional Transient Simulation of Cross-Shaped Grains in Hybrid Rocket Motors

Aerospace
The process of spacecraft entry, deceleration, landing, and ascent requires high specific impulse, high reliability, and high-precision thrust adjustments for the power system.
Xiangyu Meng, Huihuang Huang, Yifei Chen, Mingsen Yao, Jianyuan Wang, Hui Tian   +5 more
doaj   +1 more source