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Abstract
RLV TD is a lifting re-entry configuration with wing-body mounted on a solid booster. During atmospheric flight of RLV TD, which includes ascent as well as re entry into atmosphere, vehicles encounter severe thermal environment. The vehicle structure should be able to withstand this thermal load. Thermal environments were estimated for RLV TD and hot structures were designed.
To qualify the hot structures, thermo-structural testing has been undertaken. The demonstration of its fly-ability and qualification under the severe environment of thermal and structural loads acting simultaneously is carried out successfully for all hot structures.
Another critical area is the thermal management of electronic packages housed inside RLV fuselage. Thermal management of avionic packages inside RLV fuselage is also critical for the safe functioning of the packages. Detailed thermal analyses to estimate the prelaunch cooling requirements were carried out.
This paper gives the details of aero thermal design of various hot structures, Thermal Protection System (TPS) design of cold structures, thermo structural qualification of structures and thermal management of electronic packages. The comparison of estimated and flight measured temperatures is also provided. Fairly good comparison is seen between estimated and measured temperatures for hot structures and temperature of the windward and leeward region with TPS are well within limits. Safe functioning of packages was also ensured for the cooling design.
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References
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References
Hansen, C. F., "Approximations for the Thermodynamic and Transport Properties of High Temperature Air", NASA, TR R-50, 1959.
Fay, F.A. and Riddell, F.R., "Theory of Stagnation Point Heat Transfer in Dissociated Air", J. Aeronautical Science, Vol.25, 1958.
Van Driest E. R., "Turbulent Boundary Layer in Compressible Fluids", Journal of the Aeronautical Science, Vol.18, March 1951.
Van Driest E. R., "Investigation of Laminar Boundary Layer in Compressible Fluids Using the Cross Method", NACA TN 2597, 1957.
Beckwith, I. E and Gallagher, J.J., "Local Heat Transfer and Recovery Temperature on a Yawed Cylinder at a Mach Number of 4.15 and at High Reynolds Number", NASA-TR-R-104.
Kenneth M. Chadwick., "Plasma and Aero Thermal Measurements on a Hypervelocity Re-entry Vehicle", Journal of Spacecrafts and Rockets, Vol.34, No.5, Sep-Oct. 1997.
Wells, W. L., "Heating Measurements on Space Shuttle Orbiter Models with Deflected Elevons", AIAA-83-1534, AIAA 18th Thermo Physics Conference, 1983.
Users Manual ANSYS 13.0.
Henxel, E. and Gills, R.G., "An Initial Value Approach to Inverse Heat Conduction Problem", Journal of Heat Transfer, Vol.108, May, 1986.
"Thermal Performance of Silica Tile System Used for a Re-entry Mission", Proceedings of the 20th National and 9th International ISHMT-ASME Heat and Mass Transfer Conference, 4-6 January, 2010, Mumbai.
NX 9.0 Users Manual.