Hughes Electronics Corporation

The Boeing Company

Other

David Bronson

Kurt B Kreiner

Joel M Neiderman

Carl R Stechman

Peter E Woll

Robert D Evans

Don K Fulkerson

Peter W Woll

Richard E Smith

Peter Woll

Carl R Stechmann

A hydrogen diffusion port for use in a packaged electronic device. In one embodiment, the hydrogen window is characterized by a substantial absence of plating from the external surfaces of the cover the base. The hydrogen diffusion port is selected from the group of materials consisting of palladium and its alloys, platinum and its alloys and titanium and its alloys The cover is welded to the base, and the hydrogen diffusion port is affixed to an aperture in the cover. The port is affixed by a low temperature process that can be accomplished after the cover is attached to the base to form a housing and the housing is degassed, without compromising the electronics within the housing and that does not require a partial pressure of hydrogen (which may be reintroduced into the materials) to accomplish, such as by soldering the diffusion port into the cover aperture, or by swaging the diffusion port into the cover aperture.

Hydrogen diffusion hybrid port and method of making

Hydrogen diffusion hybrid port and method of forming

A rocket engine has a combustion chamber, an injector, and an attachment between the combustion chamber and the injector. The attachment includes an annular metallic deposit joined to the chamber wall outer surface, and an annular transition ring structure. The transition ring structure has an annular step collar, and an annular adaptor ring brazed to the annular step collar. The adaptor ring is welded on one end to the injector and on the other end to the metallic deposit.

Rocket engine having a transition attachment between a combustion chamber and an injector

A rocket engine includes a generally cylindrical annular combustion chamber, an injector attached to an injector end of the combustion chamber, a generally cylindrical annular step collar fitting within the combustion chamber at the injector end thereof, and an attachment of the combustion chamber, the injector, and the step collar. The maximum outer diameter of the step collar is from about 0.020 inches to about 0.024 inches smaller than the inner diameter of the combustion chamber, and has a length of from about 21 to about 31 percent of the length of the combustion chamber. The step collar is made of a material having a melting point greater than that of the combustion chamber. The attachment preferably includes a clip structure joining the combustion chamber and the step collar. The clip structure includes a C-shaped annular clip having a first leg extending parallel to the chamber length and with an inner diameter of about that of the outer diameter of the combustion chamber and affixed thereto, a second leg extending parallel to the chamber length and with an outer diameter of no greater than that of the outer diameter of the step collar and affixed thereto, and a web extending between the first leg and the second leg.

Rocket engine with internal chamber step structure

A rocket engine is fabricated by a multistep brazing and welding technique. An annular step collar is fns brazed to a trnnsition joint. This first subassembly is second brazed to the combustion chamber. This second subassembly is third brezed to an annular adaptor to form a third subassembly. The succeeding brazing steps are performed at successively lower temperatures. The third subassembly is welded to an injector.

Fabrication of a rocket engine with a transition structure between the combustion chamber and the injector

A rocket engine has a combustion chamber formed of an annular wall made of an annular wall material, and an annular insert made of an annular insert material that is of substantially the same thermal expansion coefficient as the annular wall material. The annular insert has an insert outer surface sized to fit within and contact the wall inner surface along less than the wall length. The annular wall and the annular insert are welded together. There is further an attachment between the combustion chamber and an injector. The attachment includes an annular metallic deposit bonded to the combustion chamber, an annular adaptor ring, a weld joint between the adaptor ring and the metallic deposit, and a joint between the adaptor ring and the injector.

Rocket engine with combustion chamber step structure insert, and its

A rocket engine is prepared by fabricating a combustion chamber having an annular wall as a single piece of material. The wall has a first axial region with a first inner diameter, a second axial region with a second inner diameter greater than the first inner diameter, and an inner wall step transition between the first axial region and the second axial region. The combustion chamber is attached to an injector by bonding an annular metallic deposit to the first axial region of the combustion chamber, providing an annular adaptor ring, first welding the adaptor ring to the metallic deposit, and second welding the adaptor ring to the injector.

Rocket engine with integral combustion chamber step structure and its

A rocket engine is prepared by fabricating a combustion chamber having an annular wall as a single piece of material. The wall has a first axial region with a first inner diameter, a second axial region with a second inner diameter greater than the first inner diameter, and an inner wall step transition between the first axial region and the second axial region. The wall is formed by furnishing an oversize blank of the wall material and electrical discharge machining or grinding it to the final size. The combustion chamber is attached to an injector by bonding an annular metallic deposit to the first axial region of the combustion chamber, providing an annular adaptor ring, first welding the adaptor ring to the metallic deposit, and second welding the adaptor ring to the injector.

Rocket engine with one-piece combustion chamber step structure, and its

A method is provided for removing metal oxide debris from various types of surfaces, both metallic and nonmetallic. Specifically, the surface to be cleaned is treated (preferably by immersion) with a preheated solution of 65 to 71 wt % (55.3 to 62.0 vol %) nitric acid, which is roughly equivalent to reagent grade nitric acid. The temperature of the solution is within the range of about 160.degree. to 175.degree. F. (71.degree. to 79.degree. C.). The preheated solution dissolves any metal oxide debris present on the surface, which may then be rinsed away following treatment. The method effects the removal of metal oxide residue from surfaces without further degrading the surfaces being cleaned. Further, the method is capable of cleaning internal surfaces of components without requiring disassembly of sealed or welded components, since all that is needed to effect cleaning is contact between the surface to be cleaned and the preheated solution. Finally, the method is easily implemented since it involves only the simple steps of contacting the component with a single preheated component that is widely available, namely reagent grade nitric acid, followed by rinsing and drying.

Growing community of inventors

San Marino, CA, United States of America

David Bronson