The Boeing Company

Porogen Corporation

Michael J Robinson

Michael Leslie Hand

Creed E Blevins

Benjamin Bikson

Douglas Alan McCarville

Juan C Guzman

James Ping Huang

Ivana Jojic

Donald Ray Snow, Jr

Brent Kenneth Theodore

Thomas L Andrews

Xavier D Simon

Creed Ernest Blevins

Donald R Snow

Brent K Theodore

Douglas A Mc Carville

A method and apparatus for forming a joint. A composite insert may be placed into a joint region for a first structure. The composite insert may comprise a structure having a first portion, a second portion, and a third portion all extending from a junction; and a resin impregnated into the structure to form the composite insert. The second structure may be laid up. The composite insert may be bonded to the first structure and the second structure.

Method for forming a fabric preform insert for a composite tank Y-joint

A composite resin tank includes a wall joined to a dome along a joint. A softening strip is located in the joint.

Composite tank having joint with softening strip

A composite resin tank includes a wall joined to a dome along a joint. A softening strip is used to control stress in the joint.

Method of making a device for controlling stress in joints at cryogenic temperatures

A hybrid softening strip for controlling stresses in a joint at low temperatures includes a layer of sacrificial material that can be tailored to fit the softening strip in the joint after the softening strip has been bonded to a structure.

Softening strip for controlling stress in joints at very low temperatures

A fluid separation assembly and method are provided. The assembly has a hollow fiber bundle with a plurality of hollow fiber membranes. The assembly further has a pair of tubesheets, each encapsulating respective ends of the hollow fiber bundle. The assembly further has a plurality of radial through openings formed along a circumference of one or both of the tubesheets and radially through a body portion in one or both of the tubesheets. The radial through openings include center connected radial through openings and partial radial through openings, and intersect each, or substantially each, of the hollow fiber membranes. The assembly further has a housing surrounding the hollow fiber bundle and the tubesheets. The housing has a feed inlet port, a permeate outlet port, and a non-permeate outlet port. The feed inlet port and the non-permeate outlet port are in parallel alignment with a longitudinal central axis of the housing.

Fluid separation assembly and method

Method of making a composite tank having joint with softening strip

In an embodiment there is provided a fluid separation assembly. The assembly has a hollow fiber bundle with a plurality of hollow fiber membranes. The assembly further has a first tubesheet and a second tubesheet encapsulating respective ends of the hollow fiber bundle, wherein one of the tubesheets has a plurality of radial through openings formed in the tubesheet. The assembly further has a housing surrounding the hollow fiber bundle and the first and second tubesheets, the housing having a feed inlet port, a permeate outlet port, and a non-permeate outlet port. The feed gas, permeate gas, or non-permeate gas are introduced into or removed from the hollow fiber membranes via the plurality of radial through openings formed in the tubesheet, such that the radial through openings of the tubesheet intersect each or substantially each of the hollow fiber membranes.

Fabric preform insert for a composite tank Y-joint

An apparatus comprising a first structure, a second structure, a first layer, and a second layer. The first structure has a first plurality of channels extending towards a number of edges of the first structure. The second structure has a second plurality of channels extending towards a number of edges of the second structure. A first side of the first structure is connected to a first side of the second structure. The first plurality of channels and the second plurality of channels have an orientation with respect to each other. The first layer is connected to a second side of the first structure. The second layer is connected to a second side of the second structure.

Common bulkhead for composite propellant tanks

The thermal protection system disclosed herein is suitable for use with a spacecraft such as a reentry module or vehicle, where the spacecraft has a convex surface to be protected. An embodiment of the thermal protection system includes a plurality of heat resistant panels, each having an outer surface configured for exposure to atmosphere, an inner surface opposite the outer surface and configured for attachment to the convex surface of the spacecraft, and a joint edge defined between the outer surface and the inner surface. The joint edges of adjacent ones of the heat resistant panels are configured to mate with each other to form staggered joints that run between the peak of the convex surface and the base section of the convex surface.

Thermal protection system with staggered joints

A composite truss structure employs a sandwich-in-sandwich construction in which a composite fluted core is sandwiched between two facesheets, and at least one structural foam stiffener is sandwiched within the core or between the facesheets and/or the core.

Growing community of inventors

Huntington Beach, CA, United States of America

Michael J Robinson