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An advanced composite housing for the F/A-18C/D Generator Converter Unit (GCU) has been developed. The composite housing directly replaces the existing aluminum housing, and provides lighter weight and improved thermal performance. ...The composite housing directly replaces the existing aluminum housing, and provides lighter weight and improved thermal performance. The composite housing uses IM7/954-2A material, with embedded aluminum pin fins in selected areas for thermal management. ...A fabrication procedure for the composite housing was developed, using matched metal compression molding, with adhesive bonding of secondary components.

A heat transfer analysis was made of a composite wall shroud consisting of a ceramic thermal barrier layer bonded to a porous metal layer which, in turn, is bonded to a metal base. ...Analysis showed that the composite wall offered significant air cooling flow reductions compared to an all-impingement air-cooled all-metal shroud.

The performance of an electrically heated aircraft ice protection system for a composite leading edge was evaluated. The composite leading edge of the model is equipped with a Ni alloy resistance heater. ...The computational model was then applied to the composite leading edge wing section at various metrological conditions selected from FAR Part 25 Appendix C.

A landmark study of Synerjet propulsion for fully-reusable Earth/orbit transport missions was conducted for NASA in 1965-67 by a study team of Marquardt, Rocketdyne, and Lockheed (the present author led this effort). Synerjet propulsion systems are fully integrated aerospace vehicle power-plants, comprising both airbreathing and rocket hardware subsystems and technologies. They are thereby capable of multimode operation using airbreathing, rocket, and certain mixed airbreathing/rocket thermodynamic operating cycles. The final report (9 volumes) deriving from this 20-year ago study could have applicability to post-Shuttle systems assessments currently underway. However, for reasons of passage-of-time and the (then) classified nature of the study, its documentation seems not well known, and to be in scarce availability today. This paper ameliorates this limited information-availability situation by providing a readily accessible, study overview for the interested reader.

This report discusses the design implications for spacecraft radiators made possible by the successful fabrication and proof-of-concept testing of a graphite-fiber-carbon-matrix composite (i.e., carbon-carbon (CC)) heat pipe. The prototype heat pipe, or space radiator element, consists of a C-C composite shell with integrally woven fins. ...The prototype heat pipe, or space radiator element, consists of a C-C composite shell with integrally woven fins. It has a thin-walled furnace-brazed metallic (Nb-1%Zr) liner with end caps for containment of the potassium working fluid. ...From geometric and thermal transport properties of the C-C composite heat pipe tested, a specific radiator mass of 1.45 kg/m2 can be derived. This is less than one-fourth the specific mass of present day satellite radiators.

This Aerospace Recommended Practice (ARP) describes methods of vacuum bagging, a process used to apply pressure in adhesive bonding and heat curing of thermosetting epoxy and polyester matrix fabrications for commercial aircraft composite parts. If this document is used for the vacuum bagging of other than thermosetting epoxy and polyester materials, the fitness for this purpose must be determined by the user.

Test panels were fabricated by Teledyne Ryan Aeronautical which incorporated processed LHP condenser tubing into the composite skin material of the Global Hawk. The thermal characteristics of the composite structure as heat rejection fin were experimentally determined. ...This Paper reports a recently completed Phase I SBIR program which showed that Loop Heat Pipe (LHP) condenser tubing can be embedded into the composite skin of a UAV, essentially turning the aircraft skin into a radiator. Test panels were fabricated by Teledyne Ryan Aeronautical which incorporated processed LHP condenser tubing into the composite skin material of the Global Hawk.

One of the key elements of a recently proposed composite porous media condensing heat exchanger for space systems is to utilize capillary pressure for collecting and removing water from the condensing unit. ...Experiments were conducted with a composite porous system comprised of porous graphite block and porous ceramic tubes. It was demonstrated that the liquid phase could be preferentially separated from the unsaturated porous graphite block as proposed. ...A flow model was also presented for predicting the phase separation by the composite porous system.

This material, designated “diamond/carbon/carbon composite,” consists of a carbon/carbon composite that is partially infiltrated with CVD diamond in the surface region.

A high performance MMC (Metal Matrix Composite) AlBeMet-AM162 was used and material manufacturing was performed by HIP (Hot Isostatic Pressing) powder metallurgy surrounding special shaped removable kernels.

For the ice protection of such parts manufactured with low thermal conductivity polymer-based composite material, the combined heating method using interior jet impingement and exterior ejection film has certain advantages. ...Besides that, the ratio of the composite material is almost six times higher than of the aluminum material. This research reveals some basic heat transfer process caused by the curved geometry, ejection slots and anisotropic heat conduction and will be helpful reference for the conceptual design of such ice protection systems.

The use of carbon fiber reinforced composite materials in unit-carrying satellite radiator panels was studied. Different panel architectures and component materials were identified.

Aircraft thermal management (ATM) is increasingly important to the design and operation of commercial and military aircraft due to rising heat loads from expanded electronic functionality, electric systems architectures, and the greater temperature sensitivity of composite materials compared to metallic structures. It also impacts engine fuel consumption associated with removing waste heat from an aircraft.

Metal matrix composites (MMCs) reinforced with vapor-grown carbon fiber (VGCF) may offer thermal conductivity superior to materials currently used for thermal management while also providing an adjustable coefficient of thermal expansion (CTE) and low density.

The use of thermally resistant composite skins and the desire for low observability, reduced ram inlet size and number, have reduced the ability to transfer heat generated by the aircraft to the environment.

Transfer Vehicle (TV), a propulsion module designed to supply means and resources for the vehicle orbital manoeuvres and attitude control from launcher separation up to de-orbitation, when the RM + TV composite is jettisoned. The thermal control of the CTV requires the adoption of technical solutions compatible with extremely different environmental conditions (ranging from the cold boundaries of orbital exposure to the high aerothermal fluxes during re-entry) and various operational modes (the vehicle is fully active in free-flying phases, but it is in dormant mode when ISSA docked, with most of equipment switched off).

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.

Ceramic matrix composite (CMC) use is up across the aerospace market, and among the fastest-growing trends in the global aviation industry.

This specification and its supplementary detail specifications cover rigid, cellular polyurethane or polyisocyanurate (polyether only) foam in the form of board or block.

Complicating this further is that the use of structural composites which are not efficient conductors of heat and the mission requirements of small heat signatures.