Study on Thermal Decomposition of Composite Propellants containing PCP polymer or PCP-HTPB copolymer as a binder
✍ Scribed by Chen-Chia Hung; Wen-Hwa Hwu; Chin-Sheng Cheng; Iou-Ning Shyy; Kuo-Kai Yang
- Publisher
- John Wiley and Sons
- Year
- 1995
- Tongue
- English
- Weight
- 473 KB
- Volume
- 20
- Category
- Article
- ISSN
- 0721-3115
No coin nor oath required. For personal study only.
✦ Synopsis
Abstract
A modified manometric vacuum stability test (MVST) apparatus as well as a differential thermal analyzer (DTA) and a thermogravimetric analyzer (TGA) were used to study thermal decomposition of a series of propellants. The solid propellants contained polycaprolactone (PCP) prepolymer or PCP‐HTPB copolymer as binder, ammonium perchlorate (AP) and a nitramine (RDX or HMX) as oxidants, aluminum as fuel, and bis(2,2‐dinitropropyl)acetal/formal (BDNPA/F) as plasticizer. The mixtures were cured with an isocyanate (Desmodur N‐100). It is found from MVST examinations that propellants containing PCP polymer are more stable than ones containing PCP‐HTPB copolymer. The PCP propellants were still stable after 40 hours heating at 135°C. The thermal decomposition reactions of prepared propellants during dynamic heating were indicated by two major stages of weight loss in the TGA traces.