Development of a three-dimensionalthermal analysis tool for sounding rockets; Utveckling av ett tredimensionellt termiskberäkningsverktyg för sondraketer

by André Ryman

Institution: KTH Royal Institute of Technology
Year: 2014
Keywords: Three-dimensional heat transfer; Finite element method; Sounding rocket; Värmeledning; tredimensionellt; Finita elementmetoden; Sondraket; Simulering; Engineering and Technology; Teknik och teknologier
Record ID: 1352385
Full text PDF: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-157158


This thesis has been performed in collaboration with the Swedish Space Corporation at the department Science Services. SSC provides services in the areas of spacecraft subsystems, ground stations and sounding rockets to enable governments, companies and research institutes to benefit from space. Science Services are responsible for sounding rocket flight missions allowing customers to perform research in a microgravity environment. Currently, they have good knowledge how to design the sounding rockets experiment modules to minimize thermal effects within the system. However, no computational models are available to evaluate and verify the thermal heat transfer inside of the modules and as such the systems are designed primarily based on previous experience. The main purpose of this thesis was to develop a thermal computational model, which would work as a basis for designing experiment modules. The model would be used in an early stage of the design process before CAD parts have been designed. This required a flexible model allowing the user to evaluate different types of components and configurations. A finite element method (FEM) was used to perform heat transfer calculations in MATLAB. The development process was divided into three stages, which reduced the complexity of the problem formulation. The first version was made to approximate heat transfer solution in three dimensions using the Galerkin’s weighed residuals method. The second version was made to implement the dynamic environment occurring during flight missions. Based on the external environment, the dynamic process was divided into phases with different boundary conditions. In the final version internal convection, conductivity between air elements and a GUI was developed. The versions were verified with COMSOL (2013) and previous measured flight data. The results from the simulations showed that the internal convection coefficient and the element’s conductivity have a great impact on how the heat is distributed inside th e modules. A low convection will lead to internal temperature peaks, which can cause damage to sensitive experiment equipment. Also, the results indicated that the external environment does not have a significant impact on the internal temperatures. The assumptions made and recommendations are also covered in this thesis. Keywords: Three-dimensional heat transfer, Finite element method, Sounding rocket, Computational simulation ; Detta examensarbete har utförts i samarbete med Swedish Space Corporation på avdelningen Science Services. SSC är ett svenskt företag verksam inom rymdtekniksektorn som erbjuder myndigheter, företag och forskarlag runt om i världen möjlighet att dra nytta av rymden. Avdelningen Science Service är ansvariga för utvecklig samt uppskjutning av sondraketer. I dagsläget finns en god kunskap hur…