The Comparative Analysis of External Heat Transfer Calculation Methods for a Solar Aircraft Spacesuit

Abstract

This article presents an assessment of the external thermal load on the life support system of a solar aircraft under extreme operating conditions. The calculation was carried out for the maximum and minimum possible heat flows in the key points of the aircraft flight. In this article the conditions on the Earth’s surface and at the operating altitude of the aircraft were taken as calculated. The dependence of the quantitative changes in the heat load on the aircraft from altitude was revealed, taking into account changes of thermal properties of the environment and mechanisms of heat transfer.

Numerical Simulation of the Transient Thermal Load of a Sightseeing Airship Cockpit

“…Rezanov investigated the effect of the thermal properties of the environment and mechanisms of heat transfer, which revealed the dependence of thermal properties quantitatively on the thermal load of the aircraft at different altitudes. However, the influence of different heat fluxes on each surface was not considered [8]. Wu established a dynamical thermal load model based on the response factor method [9].…”