Being constrained by the onboard power source makes it more challenging to dissipate heat fast and dependably on satellite thermal control. Flexible heat pipes are proposed as a design solution to mitigate this problem. Designing and fabricating a suitable boundary topology to minimize the average stresses near the boundary in a heat pipe system of a spacecraft or satellite has been a prime research interest for industries and space organizations. The Heat pipe structure used in satellites and large spacecraft structures to dissipate heat is analogous to a cantilever beam supported at a hinge joint or fixed support. These joints of the cantilever beams in large structures are generally minimally damped due to the inadequate structural damping of the materials used and the lacking of other forms of damping, like air drag. In this research work, the flexible structure has been designed to increase the heat transfer rate and better resist stress concentration at the joint. The sinusoidal wavy surface is considered a conical frustum solid structure that connects the heat source and heat transfer pipe. One of the viscoelastic materials has been selected under the contemplation of the design solution. This paper aims to design a joint to reduce stress transfer from a heat pipe system to a host structure. And the joint should be conducted to transfer heat to the heat sink for dissipation.

PDF (Download Full text)

| Download Citation (XML)