Thermal Design of Missile Airframe with Circumferential Variation in Wall Temperature

Abstract:

Missile airframe experiences large variations in wall temperature along the circumference due to high angle of attack, especially at hypersonic speeds, which leads to large thermal stresses and bending loads. Such a situation with large wall temperature variations occurs due to high angle of attack during flight. Thermal design of the airframe involves the estimation of local flow parameters and heat flux distribution. Kinetic heating analysis has been carried out for the prediction of heat load distribution on missile airframe considering hypersonic flow with high angle of attack for a particular flight trajectory. Out of a set of possible flight trajectories, a trajectory producing minimum circumferential variation in wall temperature, as concluded through kinetic heating analysis, is finalized. Transient three dimensional heat transfer analysis of the airframe is carried out for prediction of wall temperature distribution for proper selection of material of construction of airframe so that it retains its strength at elevated temperatures. Parametric study has been carried out considering various combinations of airframe wall thickness in presence of external thermal protection coating and internal insulation for the finalized trajectory. Based on the present analysis, airframe configuration having axially variable wall thickness corresponding to the selected flight trajectory is finalized. The validation of the methodology adopted for the analysis has been carried out with respect to airframe temperature data acquired during flight.

• Periodical: Applied Mechanics and Materials (Volumes 592-594)
• Pages: 1807-1814
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.592-594.1807
• Online since: July 2014
• Authors: G. Vijayakumar*, Ashwani Kumar Kachroo
• Keywords: Angle of Attack, Heat Flux, Hypersonic, Kinetic Heating, Missile Airframe, Thermal Barrier Coating (TBC), Thermal Radiation, Wall Temperature

References

[1] John J. Bertin: Hypersonic Aerothermodynamics, AIAA Education Series, Washington DC (1994).

[2] Robert D. Quinn and Leslie Gong.: Real-Time Aerodynamic Heating and Surface Temperature Calculations for Hypersonic Flight Simulation, NASA Technical Memorandum-4222 (1990).

[3] Michael R. Mendenhall: Tactical Missile Aerodynamics: Prediction Methodology, Edited Vol. 142, Progress in Astronautics and Aeronautics, AIAA Tactical Missile Series (1991).

DOI: 10.2514/4.470165

[4] G. Vijayakumar: A Report on Methodology for Kinetic Heating Analysis, Internal Technical Report, DRDL/DOP/HTD/2007-190 (2007).

[5] G. Vijayakumar and A. K. Kachroo: Kinetic Heating Analysis for Control Surfaces of Hypersonic Technology Demonstrator Vehicle, International Conference on Recent Advances in Heat Transfer, Karunya Institute of Science and Technology, Coimbatore (2006).

[6] J. D. Anderson,: Hypersonic and High temperature Gas Dynamics, McGraw-Hill Inc, New York (1989).

[7] T. C. Lin, et. al: High Angle of Attack Aerodynamics and Aerothermodynamic, AIAA 2006- 663, 44th AIAA Aerospace Sciences Meeting and Exhibit, Nevada (2006).

DOI: 10.2514/6.2006-663

[8] Heiser William H. Heiser and David T. Pratt: Hypersonic Airbreathing Propulsion, AIAA Education Series, Washington DC (1994).

DOI: 10.2514/4.470356

[9] HAP computer programs, Hypersonic Airbreathing Propulsion, AIAA Education Series, Washington DC (1994).

[10] J.P. Holman, Heat Transfer, 8th Ed., McGraw-Hill Book Co. (1997).

[11] ANSYS User's Manual, Thermal analysis guide, ANSYS USA (2010).

[12] G. Vijayakumar: Thermal design and Post Flight Analysis, Internal Technical report, DRDL/DOP/HTD/2013- 561 (2013).