Lockheed Martin Corporation

Mcdonnell Douglas Corporation

Lockhead Martin Corp.

Duane D Grosskrueger

Michael D Krohn

John J Smith

Bernie F Carpenter

Jim W Blain

Keith Y Hora

Robert Arthur Nelson

Jack Howard Jacobs

Matthew M Thomas

Alan R Perry

Jerry L Draper

Vittorio C Orsini

Terry J Oesch

Brian W Easom

Brett E Pisor

The present invention is generally directed to an environmental control system (and method of using the same) that is capable of conveying conditioned gases toward at least one target component (e.g., an electrical or propulsion component) of a flight vehicle such as an aircraft, spacecraft, or launch vehicle. The environmental control system of the invention generally includes a low-weight, flexible ducting. The low weight of the ducting may make it possible for the ducting to be installed into the flight vehicle utilizing one or more attachment assemblies that may be adhered to at least one surface of the flight vehicle simply by utilizing an appropriate adhesive rather than more invasive fasteners such as screws, bolts, and the like.

Environmental control system and method of using the same

The present invention generally relates to a multi-layered structure which for a given external geometry a section of interest may be integrally reinforced by varying the relative proportions of the layers in that section. That is, the layers making up the structure may have varying relative proportions to the structure's overall thickness between two or more positions while the structure maintains a constant thickness between the positions. By varying the relative proportions of the structure's layers, the mechanical properties of the structure may be selectively altered from a first position to a second position without altering the structure's external profile. This is especially desirable in composite sandwich structures used in aerospace applications which often require additional reinforcement at structural interfaces. By adjusting the relative proportions of the composite sandwich structure's layers, one or more structurally enhanced sections may be created for structural interfaces without altering the structure's profile.

Integrally reinforced composite sandwich joint and process for making the same

An acoustic blanket system for use in attenuating acoustic energy. The acoustic blanket system including an acoustic blanket and apparatus for mounting the acoustic blanket to a structure. The acoustic blanket includes first and second cover materials heat-sealed around at least a portion of their perimeter. At least one acoustic attenuating panel is disposed within the heat-sealed cover materials to form a fully encapsulated acoustic blanket. The system for mounting the blanket includes a plurality of fastener assemblies that connect the blanket to a structure to define a tunable air gap of pre-determined dimension between the blanket and the structure. The mounting system also provides dimensional control of the blanket relative to the structure to control the air gap and prevent slumping and/or deformation during maximum loading environments.

Acoustic blanket system

The present invention relates to a system for venting interior cores of composite structures. Generally, the venting system includes a mounting assembly and a venting medium. The mounting assembly generally interconnects the venting system to the composite structure generally with respect to a first air hole of the composite structure. The venting medium may have a perimeter region and an airflow region disposed inwardly of the perimeter region. In one aspect, this airflow region of the venting medium may be free from direct contact with any other portion of the venting system. In another aspect, the venting medium may be made of a fluorocarbon polymer/copolymer. Upon implementation of the present invention, airflow that is generally directed through the first air hole and that passes between the core of the composite structure and an exterior environment (e.g., a payload compartment) generally passes through the venting medium of the venting system.

Venting system for use with composite structures

A method for repairing a composite structure is herein disclosed, as well as a corresponding structure repaired using such methods. The structural repair method is a new fill-and-patch-type system that generally includes forming a recess in the structure and placing both a threaded insert and a potting material in the recess. Generally after the potting material has hardened, a patch is adhered to the potting material-filled recess, and a fixture is disposed over the recess. By directing a threaded fastener through the fixture and into the threaded insert, the fixture is drawn toward the structure and compresses the patch against the filled recess via the threaded fastener being tightened to supply sufficient compressional force to assist in bonding the patch to the repaired structure.

Method and apparatus for structural repair

A frangible access panel separation system for separating an access panel from a host structure is disclosed. In one embodiment, the system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, and first and second staggered grooves positioned on the first and second doublers, the first and second doublers severable along break planes defined by the first and second staggered grooves to facilitate a substantially collision-free separation and ejection of the first section relative to the second section, and a detonator member for initiating detonation thereof.

Frangible access panel system

A system for detuning from resonance a support structure which receives vibratory energy is disclosed. In one embodiment, the system includes a substrate actuator having at least a first wire embedded in a substrate matrix material, the actuator being couplable to the support structure. The system may further include a heater for heating at least the first wire from a first to a second temperature to increase the modulus of elasticity of the first wire, which in turn increases the stiffness of the substrate actuator. Such an increase in the stiffness of the substrate actuator detunes from resonance structures supporting a device from which vibratory energy emanates, and also inhibits transmission of vibratory energy of specific frequencies into structures supporting equipment sensitive to vibrations.

Apparatus and associated method for detuning from resonance a structure

A separation system for separating a first section from a second section is disclosed. In one embodiment, the separation system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, and first and second staggered grooves positioned on the first and second doublers, the first and second doublers severable along break planes defined by the first and second staggered grooves to facilitate a substantially collision-free separation and ejection of the first section relative to the second section.

Separation system

A separation system for separating a first section from a second section is disclosed. In one embodiment, the separation system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, and a slide plane including first and second slide members, the first and second slide members slidably engagable with each other for at least initially guiding the first section away from and relative to the second section upon severance of the first and second doublers.

A separation system for separating a first section from a second section is disclosed. In one embodiment, the separation system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, first and second grooves positioned on the first and second doublers, the first and second doublers severable along break planes defined by the first and second grooves, and bend augmenters associated with at least one of the first and second doublers to facilitate hinging of the doubler upon firing of the explosive, which thereby reduces separation shock.

A composite structure and related fabrication method is provided which has a plurality of composite material layers and at least one embedded shape memory alloy component for providing controlled structural deformation. The shape memory alloy component includes a shape memory alloy tendon having a relaxed shape at temperatures below a predetermined transition temperature and a contracted shape at temperatures above the predetermined transition temperature. The shape memory alloy component also comprises a pair of electrically insulating opposing face sheets adhered to opposite sides of the shape memory alloy tendon to electrically isolate the shape memory alloy tendon from the surrounding composite material layers. The shape memory alloy component is embedded within the plurality of composite material layers such that raising the temperature of the shape memory alloy tendon above the transition temperature creates a controlled structural deformation of both the shape memory alloy component and the surrounding composite material layers.

Growing community of inventors

Highlands Ranch, CO, United States of America

Duane D Grosskrueger