Boron Particle Combustion in Solid Rocket Ramjets

Author:

Liu Daoping1,Xia Zhixun2,Huang Liya3,Hu Jianxin4

Affiliation:

1. Ph.D. Candidate, Science and Technology, Scramjet Laboratory, National Univ. of Defense Technology, Changsha 410073, China.

2. Professor of Science and Technology, Scramjet Laboratory, National Univ. of Defense Technology, Changsha 410073, China (corresponding author).

3. Lecturer, College of Aerospace Science and Engineering, National Univ. of Defense Technology, Changsha 410073, China.

4. Professor, College of Aerospace Science and Engineering, National Univ. of Defense Technology, Changsha 410073, China.

Publisher

American Society of Civil Engineers (ASCE)

Subject

Mechanical Engineering,Aerospace Engineering,General Materials Science,Civil and Structural Engineering

Reference19 articles.

1. OVERVIEW OF BORON DUCTED ROCKET DEVELOPMENT

2. Gany A. (2013). “Thermodynamic limitation on boron energy realization in ramjet propulsion.” 64th Int. Astronautical Congress Beijing China.

3. Boron particle ignition in secondary chamber of ducted rocket;Jianxin H.;Int. J. Aerosp. Eng,2012

4. Kazaoka Y. Takahashi K. Tanabe M. and Kuwahara T. (2011). “Combustion characteristics of boron particles in the secondary combustor of ducted rockets.” 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit San Diego CA 1–6.

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