Thermal Protection System Sizing Research Articles

Initial Sizing and Reentry Trajectory Design Methodologies for Dual-Mode-Propulsion Reusable Aerospace Vehicles

*† An evaluation of the current state of the commercial space sector coupled with the everincreasing presence of micro- and mini-satellites in the telecommunication market stresses the requirement to find an economically feasible launch opportunity for relatively small satellites. The aim of this paper is to present a series of design methodologies which will enable the initial design of a dual-propulsion uninhabited aerospace vehicle with horizontal take-off and landing capability, which will fill this niche in the space launch sector. A concept-specific initial sizing methodology is presented together with a design tool that integrates aerodynamic heating, descent trajectory optimisation and thermal protection system sizing, which form part of the development of a complete design methodology embedded in a visually-interfaced software program.

Integrated design system for dynamic thermal protection system sizing

In order to obtain a minimized weight design for a hypersonic vehicle, a design system that involves integrating aeroheating analysis with thermal protection system (TPS) sizing has been developed. The design system has the capability to analyse aeroheating and TPS thermal response and to provide an optimization capability to determine the minimum thickness of the TPS materials required to prevent the underlying structure from exceeding its operating temperature limit. Features of this system are the extended capability to analyse thermal response of metallic multi-layer TPS with non-grey insulation and the smart TPS for next generation or future TPS design. The application of the above design system to a model spacecraft is presented, showing good agreement with previously obtained results, and proving its reliability for future design use. The application of the extended capabilities also shows that the above design system has strong applicability to the following generations of TPS materials.

Trajectory-Based Thermal Protection System Sizing for an X-33 Winged Vehicle Concept

A trajectory-based thermal protection system sizing is implemented for an X-33 winged-body vehicle concept. The heat pulse is discretized at eight points along the suborbital trajectory. An aerothermal database is generated from both laminar and turbulent  ow calculations. With the aerothermal database and one-dimensional thermal protection system stackups, a number of thermal protection system (TPS) sizings are generated. Three major conclusions from the analysis in this study are as follows: 1) The procedure for performing the TPSmappingworks well, 2) for the TPS design, a number of traceability issues exist between the X-33 and the full-scale reusable launch vehicle, and 3) for the X-33 TPS material selection, predictions of transition to turbulence and turbulent heating are critical.

High-Fidelity Thermal Protection System Sizing of Reusable Launch Vehicle

Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.

Trajectory-Based Validation of the Shuttle Heating Environment

Chemically reacting,three-dimensional,fullNavier ‐Stokescalculationsaregenerated around theshuttleorbiter and are compared with the STS-2 e ight database at eight trajectory locations. Numerical estimates of quantities necessary for thermal protection system design, surface temperature and heating proe les, integrated heat load, bond-line temperatures, and thermal protection system thicknesses arecompared with theSTS-2 shuttledata. The effects of surface kinetics, turbulence, and grid resolution are investigated. It is concluded that trajectory-based thermal protection system sizing, the use of a Navier ‐Stokes e ow solver combined with a conduction analysis applied over an entry trajectory, is a benee cial tool for future thermal protection system design. This conclusion is based on a reasonable agreement between the e ight data and numerical predictions of surface heat transfer and temperature proe les, integrated heat loads and bond-line temperatures at most of the wind-side thermocouples. Theeffectsofturbulentheating on thermalprotection system designareillustrated.Forfuturelargeentry vehicles, it is concluded that the prediction of turbulent transition will be a major driver in the thermal protection system design process. Finally,onepotential payoff ofusingtrajectory-based thermalprotection system sizing,a reduction in thermal protection system mass, is illustrated. Nomenclature CT = heat transfer coefe cient, W/m 2 -K cp = heat capacity of solid cs