Multidisciplinary Design Optimization

*Hypersonic Vehicles - Past, Present and Future Developments*

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2002;**5**:58-68. ISSN: 1432-7643

**12**

Chapter 2

Abstract

1. Introduction

15

Parametric Integral Soft Objects-

based Procedure for Thermal

Andrea Aprovitola, Luigi Iuspa and Antonio Viviani

The present paper deals with a modeling procedure of a thermal protection system (TPS) designed for a conceptual reusable launch vehicle (RLV). A novel parametric model based on a scalar field created by a set of soft object primitives is used to assign an almost arbitrary seamless distribution of insulating materials over the vehicle surface. Macroaggregates of soft objects are created using suitable geometric supports allowing a distribution of coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map and materials layout show the flexibility of the model.

Keywords: reusable launch vehicles, reentry aerodynamics, integral soft objects,

Currently a number of projects related to the development of reusable launch vehicles (RLV) both single-stage-to-orbit (SSTO) and two-stage-to-orbit (TSTO) are ongoing. This trend relates to objectives of future space missions that demand to improve vehicle operability, reducing at the same time flight costs of putting payload into orbit. Several preliminary studies/experiments related to this design sce-

demonstrators, the EXPERT (European eXPErimental Re-entry Test-bed) program and the Intermediate eXperimental Vehicle (IXV), which performed an atmospheric lifting reentry from orbital speed [1]. Besides, an unmanned lifting body developed by Boeing X-37B has been put in orbit by an Atlas-5 rocket and

performed a successful lifting-guided reentry. Furthermore, a growing demand for space tourism has emerged also in recent years [2]; therefore, a great deal of research effort has been put to design RLV as blended wing bodies also allowing a conventional and more comfortable landing on runways. The main requirements currently considered for RLV design are (i) to perform very low-g (nearly 1.5 g) reentry; (ii) to adopt a lightweight (passive), fully reusable thermal protection system (TPS) to withstand several flights without any replacement; and

(iii) to provide vehicle autonomy to land at a predefined location for crew rescue

nario have been carried on. The European Space Agency developed two

Reusable Launch Vehicle

hypersonic flow, thermal protection system

Protection System Modeling of
