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Introduction
Published in Sumit Sharma, Composite Materials, 2021
Solid rocket propellants consist of inorganic particles such as aluminum powder and perchlorate oxidizers in a flexible organic binder such as polyurethane or polysulfide rubber. The particles comprise nearly 75% of the propellant leaving only 25% for the binder. A steadily burning reaction is obtained which provides a controlled thrust. Another example is aluminum paint, which is actually aluminum flakes suspended in paint. Upon application, the flakes orient themselves parallel to the surface and give very good coverage. Silver flakes can also be applied to give good electrical conductivity.
Significance and Administration of Nanotechnology in the Armed Forces and Defense Sector
Published in Cherry Bhargava, Amit Sachdeva, Pardeep Kumar Sharma, Smart Nanotechnology with Applications, 2020
Ali Asgher Ali Hasan, Roshan Rajesh Bhatkar, Sarath Raj Nadarajan Assari Syamala
Other types of rocket propellants include gas propellants, electric (ion) propellants or electric thrusters and nuclear propellants. Further moving down through this chapter, we shall discuss about the status of contemporary research activities on the application of nanotechnology in developing efficient propellants that can be deployed successfully in the defense sector.
Introduction to Composite Materials
Published in Robert M. Jones, Mechanics of Composite Materials, 2018
Solid-rocket propellants consist of inorganic particles such as aluminum powder and perchlorate oxidizers in a flexible organic binder such as polyurethane or polysulfide rubber. The particles comprise as much as 75% of the propellant leaving only 25% for the binder. The objective is a steadily burning reaction to provide controlled thrust. Thus, the composite material must be uniform in character and must not crack; otherwise, burning would take place in unsteady bursts that could actually develop into explosions that would, at the very least, adversely affect the trajectory of the rocket. The instantaneous thrust of a rocket is proportional to the burning surface area; thus, solid propellants are cast with, for example, a star-shaped hole instead of a circular hole. Many stress-analysis problems arise in connection with support of the solid propellant in a rocket-motor casing and with internal stresses due to dissimilar particle and binder stiffnesses. The internal stresses can be reduced by attempting to optimize the shape of the burning cross section; again, a reason for a noncircular hole.
Critical Condition of AP/HTPB Explosion Induced in Near Flame Area of Fire
Published in Combustion Science and Technology, 2022
Jianbo Yu, Jianping Li, Qi Zhang
With the rapid development of aerospace and military fields, the research of rocket propellant which is known as the “heart” of aircraft and missile has a vital impact on their future development (Liang, Zhang, and Zheng 2003). At present, rocket propellants are divided into solid, liquid and solid-liquid mixture. Solid propellant has become the mainstream power source of small rockets and most military missiles because of its simple structure, low economic cost and high stability (Ding et al. 2022). The composite propellant with hydroxyl-terminated polybutadiene (HTPB) and ammonium perchlorate (AP) as raw materials is the main propellant in the military field (Wu et al. 2019). However, with the improvement of propellant in energy performance and loading capacity, its safety performance should also receive higher attention (Dennis and Bojko 2019; Luo and Liu 2007). In recent years, fire accidents occur frequently (Li and Fan 2010), and the high combustion and explosion hazard of rocket propellant make the storage environment more strict (Ye and Yu 2018).