发明名称 |
High temperature resistant airfoil apparatus for a hypersonic space vehicle |
摘要 |
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.
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申请公布号 |
US2004056151(A1) |
申请公布日期 |
2004.03.25 |
申请号 |
US20030431414 |
申请日期 |
2003.05.07 |
申请人 |
DICHIARA ROBERT A.;FRENCH ROBERT E.;THATCHER CONLEY SIDDOWAY;ZADOROZNY EDWARD A.;HOGENSON PETER A. |
发明人 |
DICHIARA ROBERT A.;FRENCH ROBERT E.;THATCHER CONLEY SIDDOWAY;ZADOROZNY EDWARD A.;HOGENSON PETER A. |
分类号 |
B64C1/40;B64C5/00;B64C30/00;B64G1/00;B64G1/14;B64G1/22;B64G1/42;B64G1/50;B64G1/58;(IPC1-7):B64C1/00;B64D1/00 |
主分类号 |
B64C1/40 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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