The Boeing Company

Teledyne Scientific and Imaging, LLC

Teledyne Instruments, Inc.

Sergio Luis Dos Santos E Lucato

David Bruce Marshall

Janet B Davis

Olivier H Sudre

Brian Nelson Cox

Alan David McCleary

John Bradley Hunter

Daniel Edward Driemeyer

Joseph R Tabarracci

Brock S McCabe

Alan D Mccleary

A penetrator device has an outer housing of non-conductive, insulating material having a through bore, at least one conductive pin formed in one or two parts extending through the housing and having a first end portion and a second end portion extending out of the respective first and second ends of the housing, a first cladding layer bonded over the first end portion of the pin to form a first bonded assembly, a second cladding layer bonded over the second end portion of the pin to form a second bonded assembly, and the material of the first and second cladding layer comprising a corrosion resistant conductive material different from the pin material.

Hermetically sealed electrical penetrator assembly

In one embodiment, a morphable composite three-dimensional structure is disclosed. The morphable composite three-dimensional structure comprises a flexible fiber-reinforced ceramic composite comprising a fiber preform and a ceramic matrix material infused therein. The flexible fiber-reinforced ceramic composite defines a flowpath having a three-dimensional cross-section. The cross-section of the flowpath is variable along the length of the flowpath. A plurality of anchors are integrally formed in the fiber preform. The plurality of anchors extend through a thickness of the ceramic matrix. The plurality of anchors are configured to couple to at least one actuator. The at least one actuator is actuatable to vary the three-dimensional cross-section of the flowpath.

Morphing ceramic composite components for hypersonic wind tunnel

An apparatus and method for an improved morphing flow path. A flexible structure has a plurality of sections which include a first section and a second section. An actuator system is connected to the flexible structure and includes a number of actuators. The actuator system is capable of changing a configuration of the flexible structure. A controller is connected to the actuator system. The controller is capable of changing a position of a number of actuators within the actuator system.

Tailorable stiffness shape morphing flow-path

A protective hybrid composite for a rotor blade is based on the use of tape cast ceramic layers densified by pre-ceramic polymer infiltration methods and laminated together with polymer matrix composite prepregs, with or without an embedded metallic mesh, to form a conforming helicopter blade cladding that is laminated to the blade surface for added erosion protection. The hybrid composite is fabricated to net shape and laminated to the blade using either an adhesive or a polymer composite prepreg inner layer. Installation is accomplished by a standard composite fabrication method of vacuum bagging the blade while the system is laminated to its surface. Repair methods based on removal of ceramic tiles is facilitated by incorporation of a metallic mesh element laminated beneath the ceramic tiles that can be used to heat the tile and decrease its adhesion strength.

Hybrid composite for erosion resistant helicopter blades

In one embodiment, a thermal protection device for dissipating heat includes a shell having an outer shell surface and an inner shell surface defining a hollow inner shell chamber. A plurality of porous wick structures are disposed against each other within the hollow inner shell chamber. Each porous wick structure comprises an outer wick surface which is disposed at least one of against and near the inner shell surface and a porous inner wick surface defining a hollow inner wick chamber. A plurality of porous wick lid members are provided. The porous wick lid members are disposed between the porous wick structures within the hollow inner shell chamber of the shell. A cooling substance is disposed within the plurality of porous wick structures.

Heat pipe apparatus and method

An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin may include a single-layer of three-dimensional woven fabric fibers and a ceramic matrix composite. The truss structure may include at least one actuatable element or an actuator may move a portion of the truss structure from a first position to a second position. A cooling component may be disposed in thermal communication with the skin. The cooling component may include thermal insulation or a cooling system that circulates cooling fluid in thermal communication with the skin. The morphable ceramic composite structure may be incorporated into any of an air inlet, combustor, exhaust nozzle, or control surfaces of a hypersonic aircraft.

Growing community of inventors

Thousand Oaks, CA, United States of America

Sergio Luis Dos Santos E Lucato