Abstract: Rocket components having internal heat fins are described herein. The disclosed components have internal heat fins that mitigate buckling and uneven force application by adding thermal capacity to the component without adding component stiffness. This reduces a thermal force fight (i.e., tension versus compression between cold and hot areas, respectively), which inhibits the buckling loads on the propellant tank. The internal heats fins also provide for a reduced mass of the propellant tank wall relative to a propellant tank wall without internal heat fins. By reducing the thermal force fight, as discussed above, less material can be used which further allows for thinner welds to be used (i.e., less welding material).

Abstract: Rocket components having internal heat fins are described herein. The disclosed components have internal heat fins that mitigate buckling and uneven force application by adding thermal capacity to the component without adding component stiffness. This reduces a thermal force fight (i.e., tension versus compression between cold and hot areas, respectively), which inhibits the buckling loads on the propellant tank. The internal heats fins also provide for a reduced mass of the propellant tank wall relative to a propellant tank wall without internal heat fins. By reducing the thermal force fight, as discussed above, less material can be used which further allows for thinner welds to be used (i.e., less welding material).