English  |  正體中文  |  简体中文  |  Items with full text/Total items : 25459/26053 (98%)
Visitors : 6690362      Online Users : 111
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library IR team.
Scope Tips:
  • please add "double quotation mark" for query phrases to get precise results
  • please goto advance search for comprehansive author search
  • Adv. Search
    HomeLoginUploadHelpAboutAdminister Goto mobile version

    Please use this identifier to cite or link to this item: https://ir.lib.ksu.edu.tw/handle/987654321/10146

    Title: Numerical and Experimental Investigation of a Hybrid Rocket Combustion System
    Authors: Yen-Sen Chen
    T.H Chou
    B.R. Gu
    J. S. Wu
    Bill Wu
    Luke Yang
    Contributor: 圖書資訊館
    Keywords: Hybrid Rocket Combustion
    N2O-HTPB System
    Real-Fluid Model
    Finite-Rate Chemistry
    Date: 2010-03-20
    Issue Date: 2010-05-18 16:02:37 (UTC+8)
    Abstract: Recently, the hybrid rocket propulsion has become attractive to the research community and has developed the trend to become an alternative to the conventional liquid and solid rockets. The hybrid rocket is a combination of both the solid and liquid
    systems with half of the plumbing of the liquid rocket but retaining the flexibility of operation and avoiding the explosive nature of the solid rocket.Among available hybrid systems, the N2O-HTPB hybrid propulsion represents the simplest but
    sufficiently efficient design. Unfortunately, even until now, research in developing hybrid N2OHTPB propulsion system still strongly depends on trials-and-errors, which are time-consuming and expensive. Thus, detailed understanding of the
    fundamental combustion processes that are
    involved in the N2O-HTPB propulsion system can greatly impact the research community in this field.This may further facilitate the successful modeling of the combustion processes and help improving the design of N2O-HTPB propulsion system in the future. A comprehensive numerical model with real-fluid properties and finite-rate chemistry is
    developed in this research to predict the combustion flowfield inside a N2O-HTPB hybrid rocket system.Good numerical predictions as compared to experimental data are also presented.
    Appears in Collections:[機械工程系所] 中華民國第二十屆燃燒與能源學術研討會

    Files in This Item:

    File Description SizeFormat
    H-011.pdf641KbAdobe PDF21View/Open

    All items in KSUIR are protected by copyright, with all rights reserved.

    ©Kun Shan University Library and Information Center
    DSpace Software Copyright © 2002-2004  MIT &  Hewlett-Packard  /   Enhanced by   NTU Library IR team Copyright ©   - Feedback