The Development of a Carbon Fiber Supersonic Missile Control Surface

摘要

This paper describes the results of a study designed to develop a supersonic missile control surface manufactured from an advanced carbon fiber composite material. The new design concept proposed utilizes a centrally located metallic blade that is imbedded and interlocked into the composite material. The base of the blade transitions into a round shaft designed to connect to the missile's control surface. The study first used finite element analysis (FEA) calculations that were then verified with experimental results using a composite control surface manufactured from a Cyanate Ester chopped carbon fiber compound and a stainless steel blade. The prototype parts were manufactured to half-scale using a thermo-compression molding process. Limited structural testing was performed with the half-scale components that were manufactured. The structural testing consisted in applying lateral concentrated loads to four different points on the control surfaces. The experimental results obtained agreed well with the FEA results. The composite control surfaces proved to be stiffer than conventional units manufactured using Inconel. Preliminary thermal analyses of flight temperatures indicated that high supersonic flight temperatures at the leading edge of the composite control surface are manageable and that design features can be incorporated to counter high flight temperatures at the leading edge. It is concluded that control surfaces fabricated from the Cyanate Ester carbon fiber composite material are viable. The composite control surface will be about 25 percent lighter and can be fabricated at a fraction of the cost of Inconel units.