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The Advanced Composites Repair Analysis Tool (ACRAT) has been under development for the USAF Advanced Composites Program Office under an Ogden ALC Design Engineering Program (DEP) Contractual Engineering Task (CET) Order. ...The objective has been to develop Beta versions of this computer aided composite repair design and assessment engineering tool following the provisions and procedures of the ASTM Standard E 1340-90 (Reference 1). ...Four (4) customized database schemas (M&P, Aircraft Design, Composite Repair, Component Test) were designed and sufficiently populated to evaluate each data model's ability to meet specific ACRAT system requirements.

This document describes a standard method to collect and report dielectric data for the purpose of monitoring or studying the cure of composites.

Use of new alloys, 2. greater use of “near-net-shape” parts, 3. employment of low cost alloys modified by ion implantation or by laser glazing, and 4. greater use of fiber reinforced plastics, thermoformable plastics, reinforced stampable plastics and fiber reinforced metal matrix composites.

This paper develops a robot automatic drilling system for processing the titanium alloy, aluminum alloy and laminated composites component of aircraft. The accurate robot drilling system is comprised of ABB IRB6640-235 robot, drilling end-effector, end-effctor control system and vision system.

Environmental Control Systems (ECS) ducts on airplanes are primarily fabricated from aluminum or thermoset composites, depending on temperature and pressure requirements. It is imperative to fabricate lightweight, cost effective, durable, and repairable systems with minimal tooling.

Bell Helicopter Textron has used fiber reinforced plastic materials in many applications since the earliest appearance of these materials. An overview of past, present and future usage is presented. The discussion includes examples of fuselage, control system, main rotor, energy attenuator and engine cowling/firewall applications.

Nowadays LHP (CPL) is widely used in thermal control systems for space and ground applications. Wick structure is a key element which plays at least two roles: capillary pump to move a working fluid from condenser to the heat loaded zone and thermal and hydraulic breaker between liquid and vapor in LHP (CPL). This paper is devoted to the R&D of LHP with advanced low-cost ceramic wick structure, which has a high capillary pressure head and low thermal conductivity. First set of tests with acetone as a working fluid was done in Porous Media Laboratory, Minsk, Belarus to prove the possibility to use such kind of wick in present and future designs of LHP (CPL).

Microsatellite BIRD (Bispectral InfraRed Detection), mass 92 kg, sizes 550×610×620 mm was put on October 22, 2001 in a sun-synchronous orbit. The passive thermal control system (TCS) provided a temperature range of −10…+30 °C for a payload. It is assembled from precision optical instruments and housekeeping equipment with average power about 35 W. In the observation mode a power consumption peak of 200 W is occurred during 10-20 min. The TCS ensured a thermal stable design of the payload structure and is realised by heat transfer elements (conductors and grooved heat pipes), which thermally connected the satellite segments, two radiators, multilayer insulation and low-conductive stand-offs. Three years in space have brought an enormous volume of telemetric data about thermal performance of the TCS, based on information from temperature sensors, power consumption, attitude relative to Sun and Earth.

Such metal nanoparticle-fluid composite materials are referred to as nanofluids and their use as coolants has the potential to reduce the weight and power requirements of spacecraft thermal control systems.

Emphasis will be placed on design and manufacturing decisions relating to the extensive use of composite materials throughout the aircraft.

The MFS concept is based on an efficient use of advanced composite materials and components, on disruptive solutions for integrated design, dedicated modeling and simulation tools so as advanced assembly/manufacturing approaches.

The MFS concept is based on an efficient use of advanced composite materials and components, on innovative solutions for integrated design, dedicated modeling and simulation tools as well as advanced assembly/manufacturing approaches.

As a point of reference, the ALRDU is sized to meet the requirements captured during an early design iteration of the Crew Exploration Vehicle (CEV). The composite radiator panel development included an evaluation of various tubing and composite panel attachment methods previously performed at NASA Glenn Research Center (GRC). ...The Advanced Lightweight Radiator Development Unit (ALRDU) is a composite radiator panel built for the Advanced Thermal Exploration Technology Development Project. ...The resulting lessons learned combined with previous composite radiator experiences were used to support the ALRDU design. The aforementioned experience was used to determine key CEV radiator design requirements used by Ball Aerospace and XCA for the ALRDU development.

The thrust vectoring hardware was nearly 100% graphite epoxy composite construction. It held the engine operating line in both forward and vertical thrust. The data showed high efficiency, low thrust losses, in both forward and 90 degree vectored thrust. ...The ability to vector the thrust for control was also demonstrated. Composite structure held up well during several hours of testing. The only structural problem was caused by differential thermal expansion of the steel bearing attachment fittings.

This SAE Aerospace Information Report (AIR) reviews the precautions that must be taken and the corrections which must be evaluated and applied if the experimental error in measuring the temperature of a hot gas stream with a thermocouple is to be kept to a practicable minimum. Discussions will focus on Type K thermocouples, as defined in National Institute of Standards and Technology (NIST) Monograph 175 as Type K, nickel-chromium (Kp) alloy versus nickel-aluminium (Kn) alloy (or nickel-silicon alloy) thermocouples. However, the majority of the content is relevant to any thermocouple type used in gas turbine applications.

As one answer of these questions, a new innovative robot cell has been developed for drilling and fastener insertion in the inner structure of aircraft parts consisting of composite, titanium and aluminum. The new robot cell is based on a scalable 840D system configuration.

Advanced composite structures, advanced wing geometries, and active control systems all promise substantial benefits in fuel efficiency and direct operating cost for derivative and new aircraft introduced by 1985.

Variability in composite manufacture and the limitations in positional accuracy of common industrial robots have hampered automation of assembly tasks within aircraft manufacturing.

Some of the test articles identified thus far are a solar vapor compression heat pump, composite coldplate shelves, prototypic cooling jackets, and various devices that utilize waste heat.

The thermoplastic material acts as a dielectric material between the layers of PZT; and adds durability to the final PZT-thermoplastic composite. Based on the mathematical characterization and fabrication technology developed during the course of past work, it is now possible to envision improved design concepts.