Investigation of Spacer Fabric as Vibration Reduction Material in Rocket Avionic Systems by Using Finite Element Method


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Öz M. E. , Yıldırım Y. E. , Eryılmaz O.

8. International Fiber and Polymer Research Symposium (8. ULPAS), Eskişehir, Turkey, 18 - 19 June 2021, pp.1-2

  • Publication Type: Conference Paper / Summary Text
  • City: Eskişehir
  • Country: Turkey
  • Page Numbers: pp.1-2

Abstract

In rockets used to fulfil a specific purpose, avionics systems are exposed to vibration during flight due to engine thrust and aerodynamic forces and Accelerometers used to measure acceleration, which is an important parameter for the rocket, may be mistaken due to these vibrations and cannot operate the target mission or rescue systems properly. Especially, probe rockets using solid fuel engines are more exposed to these vibrations. Rocket technologies are developing in our country and in the world, and rockets are made that can perform certain tasks at university and high school levels. Generally, these rockets have low cost avionic modules therefore the possibility of faulty measurements increases. For the solution of this problem, in recent years, increasing use of spacer fabrics that can be used for different purposes will be used. The most important features of this fabric structure are lightness and low volume coverage, as well as the ability to adjust the elasticity performance [1] in the desired way with the sewing method and yarn material. These criteria are most important parameters in rocket design. The analysis of a vibration damper was carried out using spacer fabric damping model that minimized the rocket design and protect the avionic systems.