The Boeing Company

Rockwell International Corporation

Peter A Hogenson

Robert A DiChiara

Charles L Hamermesh

Edward A Zadorozny

Conley Siddoway Thatcher

Robert E French

Vann Heng

Robert J Perez

Keith Y Chong

Mary Margaret Litwinski

Ben YoungSon Won

Paul J Dynes

Chiang-Ying M Tung

Dae H Kim

Peter Duong

A thermal protection system for a vehicle may include a substantially rigid, relatively thin outer aeroshell, a relatively low density insulation layer, and a resiliently compressible conformal layer. The vehicle may include a substructure. The aeroshell may be configured to be fastened to the substructure. The insulation layer may be disposed against the aeroshell. The conformal layer may be disposable against the insulation layer. The conformal layer may be compressively preloaded against the substructure when the aeroshell is fastened to the substructure.

Aeroshell thermal protection system and method

A cryogenic fuel tank assemblyis provided comprising a cryogenic fuel tank wall. A foam assemblyis affixed to the cryogenic fuel tank wall, the foam assemblyhaving an inner surfaceand an outer surface. A first solid filmbonded to the outer surfaceto provide a uniform outer bonding surface. A thermal protection system assemblyis bonded to the uniform outer bonding surface

Cryogenic fuel tank insulation assembly

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.

High temperature resistant airfoil apparatus for a hypersonic space vehicle

A ruddervator for an aerospacecraft. The ruddervator is formed by a plurality of airfoil sections nestably disposed in side by side fashion and supported by a pair of titanium box beam frame elements extending through central openings in each of the airfoil sections. Each airfoil section includes an oxide fiber/oxide matrix-based ceramic matrix composite (oxide-CMC) panel made up of multiple plies of oxide-CMC fabric which are fused over a rigid ceramic foam insulation member. The lower ends of the frame elements are secured to a transition component comprising a conventional torque box. The ruddervator can be manufactured with less cost and lower weight over previous ruddervator designs which require one or more large skin sections which are mechanically fastened to a substructure. The ruddervator of the present invention further minimizes fabrication costs by using a common design for the nesting airfoil sections so that a common female lay-up mold can be used for fabricating all of the airfoil sections.

Hot ruddervator apparatus and method for an aerospacecraft

A thermal insulation system comprising an insulator core formed of ceramic material and, an outer layer integrally connected on an inner surface to a first side of the insulator core, the outer layer comprising a woven material impregnated with a ceramic matrix. In one embodiment, a thermal insulation blanket is formed having a flexible insulator core formed of ceramic fibrous materials, an outer layer integrally connected to one side of the insulator core, and an inner layer connected to a second side of that core. The inner layer is formed of woven material. In a second embodiment, a thermal insulation tile is formed including a rigid insulator core formed of ceramic material and an outer layer integrally connected to an inner surface to a first side of insulator core. The outer layer comprises a woven ceramic material impregnated with a ceramic matrix.

Thermal insulation system and method of forming thereof

A polymeric or plastic coating is provided which protects coated structures by forming an intumescent insulative fire resistant barrier. The coating is formed from the product of mixing an aromatic polyisocyanate, an aromatic polycarboxylic compound and about 1 to about 20% by weight of furfuryl alcohol. The structure to be protected is coated with the product of the mixture and the coating is dried. An intumescent polyimide fire resistant foam is formed when the coating is exposed to a (non-flame) heat source at temperature ranging from about 110.degree. C. to about 140.degree. C.

Intumescent flame-resistant coating composition

A plastic coating is provided which protects coated structures from flame. The coating is a product resulting from mixing an aromatic polyisocyanate, an aromatic polycarboxylic compound, and furfuryl alcohol at a temperature less than 80.degree. C. The structure to be protected from flame is coated with the product and the product is then dried. If the coated structure is exposed to flame, the coating intumesces to form a flame-resistant foam which protects the structure.

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Long Beach, CA, United States of America

Peter A Hogenson