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OwnerRobert A. DiChiara JR., Robert E. French +3inventors
InventorsRobert A. DiChiara JR., Robert E. French, Conley Siddoway Thatcher, Edward A. Zadorozny, Peter A. Hogenson
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A ruddervator for an aerospacecraft including a monolithic, one-piece, oxide/oxide-based ceramic matrix composite (Oxide-CMC) shell having a hollowed interior area. A graphite composite structural member is inserted into the hollowed interior area and bonded thereto. The Oxide-CMC shell is comprised of one or more plies of Oxide-CMC fabric which are fused over a thick substrate of rigid ceramic foam insulation to form the monolithic shell. An outer mold line ply of the Oxide-CMC shell is further infused with a high-emissivity coating such as reaction-cured glass (RCG) to provide plasma heating re-radiation outward to reduce internal temperatures in the ruddervator. A torque box transition structure is secured to the graphite composite structural member to interface the ruddervator to a fuselage actuator spindle of the aerospacecraft. The ruddervator is reusable and formed from a reduced number of independent component parts, and weighs less than previously developed ruddervators. The manufacturing cost of the ruddervator is reduced by utilizing the reduced tooling complexities of Oxide-CMC over CMC fabrication processes.
A high temperature resistant airfoil apparatus for a hypersonic space vehicle, comprising:
A high temperature resistant ruddervator apparatus for a hypersonic space vehicle, comprising:
A method of manufacturing a ruddervator for a hypersonic space vehicle, comprising the steps of:
Dependencies are inferred from the claim text.