Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

In the present paper, a modelling procedure of the thermal protection system designed for a conceptual Reusable Launch Vehicle is presented. A special parametric model, featuring a scalar field irradiated by a set of bidimensional soft objects, is developed and used to assign an almost arbitrary distribution of insulating materials over the vehicle surface. The model fully exploits the autoblending capability of soft objects and allows a rational distribution of thermal coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map, and material layout show the flexibility of the model. The model is finally integrated in the framework of a multidisciplinary analysis to perform a trajectory-based TPS sizing, subjected to fixed thermal constraints.

[1]  Ernst Heinrich Hirschel,et al.  Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles , 2009 .

[2]  Robert D. Braun,et al.  Analytic Hypersonic Aerodynamics for Conceptual Design of Entry Vehicles , 2010 .

[3]  Claus Weiland.  Computational Space Flight Mechanics , 2010 .

[4]  Hugh L. Dryden,et al.  THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION , 1958 .

[5]  John R. Olds,et al.  Multidisciplinary Conceptual Design Optimization of Space Transportation Systems , 1999 .

[6]  Erwin Mooij,et al.  Optimization of entry-vehicle shapes during conceptual design , 2014 .

[7]  George S. Dulikravich,et al.  Three-Dimensional Aerodynamic Shape Optimization Using Genetic and Gradient Search Algorithms , 1997 .

[8]  James F. Blinn,et al.  A Generalization of Algebraic Surface Drawing , 1982, TOGS.

[9]  Andrea Aprovitola,et al.  Multi-objective optimization for re-entry spacecraft conceptual design using a free-form shape generator , 2017 .

[10]  David R. Olynick,et al.  Trajectory-Based Thermal Protection System Sizing for an X-33 Winged Vehicle Concept , 1998 .

[11]  Michael E. Tauber,et al.  Thermal environment of transatmospheric vehicles , 1988 .

[12]  Marcus A. Lobbia.  Multidisciplinary Design Optimization of Waverider-Derived Crew Reentry Vehicles , 2017 .

[13]  David E. Myers,et al.  Parametric Weight Comparison of Advanced Metallic, Ceramic Tile, and Ceramic Blanket Thermal Protect , 2000 .

[14]  Erwin Mooij,et al.  Conceptual Shape Optimization of Entry Vehicles , 2017 .

[15]  Sabrina Corpino,et al.  Robust Multi-Disciplinary Optimization of Unmanned Entry Capsules , 2012 .

[16]  H. W. Stone,et al.  Aerodynamic heating environment definition/thermal protection system selection for the HL-20 , 1993 .

[17]  Polina Chernukha.  Conceptual Shape Optimization of Entry Vehicles: Applied to Capsules and Winged Fuselage Vehicles D. Dirkx and E. Mooij Springer. 2017. 280pp. Illustrated. £109.99. ISBN 978-3-319-46054-3. , 2018 .

[18]  Brian Wyvill,et al.  Sketch-based implicit blending , 2017, ACM Trans. Graph..

[19]  Luigi Iuspa,et al.  Free topology generation of self-stiffened panels using skeleton-based integral soft objects , 2015 .

[20]  Howard Smith,et al.  A review of design issues specific to hypersonic flight vehicles , 2016 .

[21]  Sachin Kumar,et al.  Design of Thermal Protection System for Reusable Hypersonic Vehicle Using Inverse Approach , 2017 .

[22]  Brian Wyvill,et al.  A Gradient-Based Implicit Blend , 2012 .

[23]  Antonio M Mazzaracchio.  Thermal Protection System and Trajectory Optimization for Orbital Plane Change Aeroassisted Maneuver , 2013 .

[24]  Li Yan,et al.  Parameterization and optimization of hypersonic-gliding vehicle configurations during conceptual design , 2016 .

[25]  Andrea Aprovitola,et al.  An optimization-based procedure for self-generation of Re-entry Vehicles shape , 2017 .

[26]  Reuben R. Rohrschneider.  Development of a Mass Estimating Relationship Database for Launch Vehicle Conceptual Design , 2002 .

[27]  John R. Olds,et al.  The Emerging Orbital Space Tourism Industry: New Insight into Demand and Prospects for Success , 2006 .

[28]  W. Schuyler Hinman,et al.  Rapid prediction of hypersonic blunt body flows for parametric design studies , 2016 .

[29]  J. R. Olds.  Thermal Protection System Sizing and Selection for RLVs Using the Sentry Code , 2006 .