Modeling external thermal influence of infrared radiation sources during tests of rocket and space equipment in VK-600/300

Abstract

The paper presents the solution of the problem of simulation of the effect of radiant heat fluxes from infrared sources (IRS) on the surface of spacecraft and their modules during complex tests in a vacuum chamber (VC) 600/300. We suggest using empirical dependences as a solution to the problem of promptly obtaining the results of calculating the density of thermal radiation fluxes on the elements of the surface of a space vehicle when performing complex tests. A brief description of the design features of the IRS module is presented, which is necessary for constructing a mathematical model of thermal radiation distribution. The layout of IRS modules accommodation in VC 600/300 is shown and the main energy characteristics calculated in the modeling of radiant heat fluxes are determined. The article shows the empirical dependences obtained for calculating the energy characteristics of the IRS modules on the electric power supplied to the radiating elements. The results of calculating the distribution of the IR flux density using empirical relationships are shown in comparison with the results of calculations using a software package and with the experimental measurements obtained.

Keywords

• vacuum chamber
• density of a thermal radiation flux
• spacecraft
• infrared radiation module
• software package