Demise Characteristics Evaluation for Melting Promotion-Type Tank
Author:
Affiliation:
1. ARD Propulsion Group, Japan Aerospace Exploration Agency, Tsukuba City, Ibaraki Prefecture 305-8505, Japan
2. Department LNG Propulsion Office, IHI Aerospace Co., Ltd., Tomioka City, Gunma Prefecture 370-2398, Japan
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.B35398
Reference9 articles.
1. Demise Characteristics Evaluation for Melting Promotion Type Tank
2. KajiwaraK.MasudaI.MasuokaT.FujiiG.SaitohN. “Basic Design of Reentry Melting-Promotion Type Satellite’s Propellant Tank,” Space Propulsion, SP2012-2364507, 2012.
3. Basic Design and Fundamental Data Acquisition Test of Reentry Melting Promotion Type Satellite's Propellant Tank
4. Summary of the Development of a Demiseable Composite Overwrapped Hydrazine Tank for the Global Precipitation Measurement Mission from Concept to Delivery
5. Development and Implementation of a Process for Producing a Highly Wettable Aluminum PMD for the GPM Hydrazine Tank
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