Experimental and Model Study of Agglomeration of Burning Aluminized Propellants
Author:
Affiliation:
1. Chung Shan Institute of Science and Technology, Taoyuan 325, Taiwan, Republic of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.11988
Reference31 articles.
1. Propellant MPa mm/s Facility µm points Suzuki and AP: 68-71%, Al: 18%, Al size: 6-35 µm, 2.03 4.09-5.52 Combustion 149-242 7
2. Chiba12HTPB: 11-14% photograph Christian13AP: 67-72%, Al: 15-20%, Al size: 5-30 µm, 1.38-3.45 3.3-7.3 QPCB 56-195a25b
3. (Figs. 5-9) HTPB: 11-18% Churchill et al.14AP: 65-73.2%, Al: 10-20%, Al size: 5-40 µm, 1.38-4.14 3-5.74 QPCB 50.7-136.1 14c
4. Aluminum agglomeration in ammonium perchlorate/cyclotrimethylene trinitramine/aluminum/hydroxy-terminated polybutadiene propellant combustion
5. Analysis of agglomerate size from burning aluminized AP/RDX/HTPB propellants in quench bomb
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