Development of nondestructive testing techniques for honeycomb heat shields Annual program report, 1 Jul. 1964 - 30 May 1965
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Botsco, R. J.↗
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Results for “Honeycomb”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Radial honeycomb core
Core alleviates many limitations of conventional nacelle construction methods. Radical core, made of metals or nonmetals, is fabricated either by joining nodes and then expanding, or by performing each layer and then joining nodes. Core may also be produced from ribbons or strips with joined nodes or ribbons oriented in longitudinal planes.
Cantley, R. B.↗
New concept in brazing metallic honeycomb panels
Aluminum oxide coating provides surface which will not be wetted by brazing alloy and which stops metallic diffusion welding of tooling materials to part being produced. This method eliminates loss of tooling materials and parts from braze wetting and allows fall-apart disassembly of tooling after brazing.
Carter, P. D.↗
Honeycomb battery plaque
Performance of porous electrodes in batteries and other electrochemical cells is greatly improved when supports for active material have pores of uniform size, extending completely through electrodes, from side to side, with no interconnections between pores.
Schaer, G. R.↗
Fabrication of tungsten-uranium dioxide honeycomb structures, phase 1
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White, D. E.↗
Improved bonding of honeycomb panels
Technique, using angular metal braces bonded onto panels, lowers construction costs. Technique improves overall structural strength, decreases assembly time, and avoids wear points created by bolts and rivets.
Sobkiewicz, S. A.↗
Interpreting honeycomb climbing-drum peel tests
Drum-peel tests are made more meaningful by use of approximations to derive analytical expressions relating failures due to bond flatwise tension, inplane tension, and shear, to adhesive weight and method of bond cure.
Ferdie, R. D.↗
Bismaleimide resins for flame resistant honeycomb sandwich panels
A 60 kg batch of Resin M751 was produced in pilot plant scale. The resin was delivered to the prepreg company as an NMP solution. 100 kg of glass-fabric prepregs were fabricated. Prepreg characteristics and curing cycles for laminate fabrication were provided. A new batch of Resin M756 (Code M756 - 2) was synthesized.
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Design and fabrication of a radiative actively cooled honeycomb sandwich panel
The mass of a radiative actively cooled panel was compared to the mass of a bare actively cooled panel designed to the same conditions and constraints. The approach was to design and optimize a 0.61 x 6.1 m full scale panel which combines radiative and active cooling to control structural temperatures to levels compatible with use of lightweight materials and to fabricate a 0.61 x 1.22 m panel for performance testing. Results of the design and optimization of the full scale radiative actively cooled structural panel, including radiative concept selection, final configuration details, test panel description, and conclusions are summarized.
Koch, L. C.↗
Catalytic honeycomb combustor - Steady-state model and comparison with experiment
A steady-state lean combustion model for monolithic catalytic combustors is given. The model, consisting of several semi-global chemical reaction steps in the gas-phase and on the surface, is capable of analyzing CO and THC emissions. In the model computation presented, the influence of operating and design parameters on the minimum combustor length is studied. Special attention is given to the effect of after-bed gas-phase reaction space. Comparison with experimental data indicates good agreement in the range of parameters covered.
Tien, J. S.↗
Honeycomb sandwich structure for future space transportation systems with integral cryogenic tankage
Previously cited in issue 13, p. 2029, Accession no. A82-30084
Shideler, J. L.↗
Noise transmission through an acoustically treated and honeycomb-stiffened aircraft sidewall
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Grosveld, F. W.↗
Steps towards 8m honeycomb mirrors. V - A method for polishing aspheres as fast as f/1
The present method for the polishing of near-f/1 aspherics employs a lap whose shape is continuously changed under computer control as it moves over the rigid mirror blank. Required changes of radius, astigmatism, and coma in a circular lap are accomplished by means of edge-bending levers and tensioning members that use screw actuators. Attention is given to the case of an f/1, 8-m diameter paraboloid whose mirror blank has been cast in a centrifugally stressed, rotating furnace to within 1 mm of the desired optical figure. Attention is also given to the mechanical design of the active lap.
Angel, J. R. P.↗
High capacity demonstration of honeycomb panel heat pipes
The feasibility of performance enhancing the sandwich panel heat pipe was investigated for moderate temperature range heat rejection radiators on future-high-power spacecraft. The hardware development program consisted of performance prediction modeling, fabrication, ground test, and data correlation. Using available sandwich panel materials, a series of subscale test panels were augumented with high-capacity sideflow and temperature control variable conductance features, and test evaluated for correlation with performance prediction codes. Using the correlated prediction model, a 50-kW full size radiator was defined using methanol working fluid and closely spaced sideflows. A new concept called the hybrid radiator individually optimizes heat pipe components. A 2.44-m long hybrid test vehicle demonstrated proof-of-principle performance.
Tanzer, H. J.↗
Design considerations for honeycomb double-bubble tanks utilized in aerospace vehicles
Future earth-to-orbit vehicles will utilize reusable internal fuel tanks requiring most of the vehicle volume. Because weight reduction and volumetric efficiency are essential, these tanks will be integral to the vehicle structure, and the vehicle cross section will dictate the size and shape of the tank. For a fuselage with a noncircular cross section, a multibubble tank configuration may be employed. Multibubble tanks offer a reduction in tank weight over a single-lobe tank or several cylindrical tanks in a noncircular cross section but sacrifice the efficiency of utilizing the entire fuselage cross section. This paper includes a general configuration analysis of a double-bubble tank, a materials and efficiency study, and a complete mission design analysis centers on sizing the tank to withstand ascent and reentry loads while minimizing the structural weight.
Lentz, Christopher A.↗
Impact testing of glass/phenolic honeycomb panels with graphite/epoxy facesheets
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Nettles, Alan T.↗
Thermal behavior of a titanium honeycomb-core sandwich panel
Finite element thermal stress analysis was performed on a rectangular titanium honecomb-core sandwich panel which is subjected to thermal load with a temperature gradient across its depth. The distributions of normal stresses in the face sheets and the face-sheet/sandwich-core interfacial shear stresses are presented. The thermal buckling of the heated face sheet was analyzed by assuming the face sheet to be resting on an elastic foundation representing the sandwich core. Thermal buckling curves and thermal buckling load surface are presented for setting the limit for temperature gradient across the panel depth.
Ko, William L.↗
Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system
A reusable metallic thermal protection system has been developed for vehicles with maximum surface temperatures of up to 2000 F. An array of two 12- by 12-in. panels was subjected to radiant heating tests that simulated Space Shuttle entry temperature and pressure histories. Results indicate that this thermal protection system, with a mass of 2.201 lbm/ft(exp 2), can successfully prevent typical aluminum primary structure of an entry vehicle like the Space Shuttle from exceeding temperatures greater than 350 F at a location on the vehicle where the maximum surface temperature is 1900 F. A flat array of 20 panels was exposed to aerothermal flow conditions, at a Mach number of 6.75. The panels were installed in a worst-case orientation with the gaps between panels parallel to the flow. Results from the aerothermal tests indicated that convective heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating include orienting panels so that gaps are not parallel to the flow and using a packaged, compressible gap-filler material between panels to block hot gas flow in the gaps.
Gorton, Mark P.↗