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Wednesday, July 22, 2020 | History

3 edition of Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system found in the catalog.

Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system

Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system

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Published by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, National Technical Information Service, distributor] in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Heat resistant alloys.,
  • Space vehicles -- Atmospheric entry.

  • Edition Notes

    StatementMark P. Gorton, John L. Shideler, and Granville L. Webb.
    SeriesNASA technical paper -- 3257., NASA technical paper -- 3257.
    ContributionsWebb, G. L., Shideler, John L., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14690129M

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Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system Download PDF EPUB FB2

Static and Aerothermal Tests of a Superalloy Honeycomb Prepackaged Thermal Protection System Mark P. Gorton Lockheed Engineering & Sciences Company Hampton, Virginia John L. Shideler and Granville L. Webb Langley Research Center Hampton, Virginia.

Get this from a library. Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system. [Mark P Gorton; G L Webb; John L Shideler; United States.

National Aeronautics and Space Administration. Scientific and Technical Information Program.]. Engineering Aerothermal Analysis for X Thermal Protection System Design Kathryn E.

Wurster, Christopher J. Riley, and E. Vincent Zoby NASA Langley Research Center Hampton, VA 36th Aerospace Sciences Meeting & Exhibit January/Reno, NV For permission to copy or republish, contact the American Institue of Aeronautics and File Size: 1MB.

Heat-transfer, thermal bending, and mechanical buckling analyses have been performed on a superalloy “honeycomb” thermal protection system (TPS) for future hypersonic flight vehicles.

The studies focus on the effect of honeycomb cell geometry on the TPS heat. thermal protection systems, and integrated system capability. The missile is comprised of a nose section, guidance section, and motor section. For the trajectory of interest, the missile nose and guidance sections are protected by a Chartek 4 [2] thermal protection system, and the motor section utilizes a sacrificial over wrap of fiberglass epoxy.

An array of metallic Thermal Protection System (TPS) panels developed for the windward surface the X vehicle was tested in the 8-Foot High Temperature Tunnel at the NASA Langley Research Center.

These tests were the first aerothermal tests of an X TPS array and the test results will be used to. A Ni-based superalloy honeycomb thermal protection system (TPS) panel has been fabricated. Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system.

Article. Appl. Mech. Lett. 4, () experimental studies on the thermal protection performance of superalloy honeycomb panels sub- jected to severe thermal shock conditions, with a high heating rate that occurs in the ï¬ rst stage of the launching, rising and reentry period of high-speed air vehicles, have not been by: 2.

This paper investigates heat-shielding performance and 3D thermal deformation behavior of two superalloy honeycomb-core sandwich panels in time-varying thermal environment by using a self-developed transient aerodynamic heating simulation system and a novel active imaging stereo-digital image correlation (stereo-DIC) by: ON EFFECTIVE THERMAL CONDUCTIVITY OF SUPER ALLOY HONEYCOMB CORE IN SANDWICH STRUCTURES * g k is the thermal conductivity of air, αis the accommodation factor, γis the specific heat ratio of air, Pr is the Prandtl number, c L is the core height,λ u File Size: KB.

The equivalent thermal conductivity of superalloy honeycomb core structures have been studied by experimental method. Test results show that the decrease in honeycomb core height and the increase in honeycomb core diameter would lead to a lower equivalent thermal conductivity for superalloy honeycomb cores.

Filling adiabatic materials such as ZrO2 fibers and SiO2 aerogels into core cells Author: Zong Hong Xie, Jun Feng Sun, Wei Li, Jian Zhao, Xi Shan Yue. An array of metallic Thermal Protection System (TPS) panels developed for the windward surface of the X vehicle was tested in the 8-Foot High Temperature Tunnel at the NASA Langley Research Center.

These tests were the first aerothermal tests of an X TPS array and the test results will be used to validate the TPS for the X flight by: 3. Results indicate that this thermal protection system, with a mass of lbm/ft(exp 2), can successfully prevent typical aluminum primary structure of an entry vehicle like the Space Shuttle.

Analysis and Testing of Heat Transfer through Honeycomb Panels Daniel D. Nguyen1 California Polytechnic State University, San Luis Obispo, CA, This projects attempts to simulate accurately the thermal conductivity of honeycomb panels in the normal direction. Due to the large empty space of the honeycomb core, the thermal radiation mode of.

Metallic thermal protection system (MTPS) offers significant improvements over the ceramic based TPS for reentry applications. Space shuttle refurbishment time is estimated to be around man hours between flights.

Metallic based TPS can be fabricated easily and provides wide range of design options for TPS. Adaptability and robustness of metallic thermal protection systems offers Cited by: 1.

These characteristics permit utilization of both thermal insulating and conducting properties, respectively, within a thermal management system. When properly designed, CFOAM® carbon foam and other forms of carbon, such as graphite and graphite foams, can be tailored to effectively shield and carry thermal energy away from numerous areas of a.

In this paper, a superalloy-refractory composite-container-“wall” combined with the wick and working fluid structure is proposed, which is proved to be a feasible design of a heat pipe for the semi-passive thermal protection system (TPS). The effects of different material of the exterior surface on the temperature distributions are Cited by: 2.

A self-developed transient aerodynamic thermal simulation system for high-speed aircraft was used to test the thermal protection performance of metallic honeycomb core panels in a dynamic high. This specification is for nonmetallic honeycomb core used in the manufacture of adhesively bonded sandwich panels for tactical shelters.

The materials are intended for adhesive bonding to aluminum facings using materials and processes defined by Practices E and E and Specifications E, E, and E   New design • New technology • Better than ever Features of the Olivia Garden ProThermal Anti-Static Brush Collection include: ∙ A vented cap design ∙ Anti-static, high heat resistant.

inTEST Thermal Solutions 41 Hampden Road Mansfield, MA TEL: part number SLB ISO Certiied inTEST Thermal Solutions 60Hz only, system does not operate at 50Hz - VAC (V nominal), 60Hz, 30 amp, 1phase Filtered to 5 micron particulate contamination. In this paper, a thermal analysis of the thermal protection system (TPS) of test launch vehicle (TLV) is explained.

TLV is heated during the flight due to engine exhaust plume gas by thermal radiation and a TPS is needed to protect the vehicle from the heating. The thermal analysis of the TPS is conducted to predict the heat flux from plume gas and temperature of the TPS during the by: 2.STATIC is able to measure the composition and velocity of ions, allowing us to determine escape rates at the present epoch.

(Courtesy NASA/GSFC/University of California Berkeley-SSL) The Suprathermal and Thermal Ion Composition (STATIC) instrument is part of the Particles and Fields (P & F) Package and measures thermal ions to moderate energy.