• Title/Summary/Keyword: Solid Rocket Propulsion

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Design of Fastener for Solid Rocket Motor Using Solid CAD System (CAD 시스템에서의 고체추진기관 체결류 설계에 대한 연구)

  • Lee, Kang-Soo;Kim, Won-Hoon;Seok, Jung-Ho
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.34 no.7
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    • pp.805-811
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    • 2010
  • When we design a product, we spend a considerable amount of time in designing fasteners and their mating parts. Fasteners have special features because of which they are widely used and well standardized. Although we use some equations to design the fasteners, we should select these fasteners from the standardized table. In order to design them quickly using the CAD system, we proceeded as follows. First, we prepared some standardized shapes of fasteners to design them automatically. Next, we built a database of some fasteners such as a tension bolt, lock wire, thread, pin, and snap ring. Then, we used the design equations to quickly and precisely calculate the various parameters. Finally, we used a configuration design method to generate the shapes automatically using the results of the calculation and the values retrieved from the database. We applied this approach to the design of a propulsion structure, and demonstrated that this approach worked well and saved considerable time.

Fracture Characteristics of C/SiC Composites for Rocket Nozzle at Elevated Temperature (로켓 노즐목 소재 C/SiC 복합재 고온 파괴 특성)

  • Yoon, Dong Hyun;Lee, Jeong Won;Kim, Jae Hoon;Sihn, Ihn Cheol;Lim, Byung Joo
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.40 no.11
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    • pp.927-933
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    • 2016
  • In a solid propulsion system, the rocket nozzle is exposed to high temperature combustion gas. Hence, choosing an appropriate material that could demonstrate adequate performance at high temperature is important. As advanced materials, carbon/silicon carbide composites (C/SiC) have been studied with the aim of using them for the rocket nozzle throat. However, when compared with typical structural materials, C/SiC composites are relatively weak in terms of both strength and toughness, owing to their quasi-brittle behavior and oxidation at high temperatures. Therefore, it is important to evaluate the thermal and mechanical properties of this material before using it in this application. This study presents an experimental method to investigate the fracture behavior of C/SiC composite material manufactured using liquid silicon infiltration (LSI) method at elevated temperatures. In particular, the effects of major parameters, such as temperature, loading, oxidation conditions, and fiber direction on strength and fracture characteristics were investigated. Fractography analysis of the fractured specimens was performed using an SEM.