DEVICE AND METHOD FOR MEASURING THE DENSITY AT incident heat flux thermal vacuum testing of spacecraft

摘要

1. A measuring device the density of the incident heat fluxes during thermal vacuum test spacecraft assembly comprising, in each of which the sensor element is placed on an electrically insulating substrate, characterized in that said assembly formed therein as mounted in parallel planes opposite each other panel n (wherein : n = 2), fastened together and fixed by means of threads in the box-frame, wherein in each sensor panel is attached with thermal contact to a thin walled plate is endowed ennoy stiffener perimeter and made of high thermal conductivity material, wherein the panels are installed with a gap δmezhdu adjacent panels by means of point contacts made of heat resistant and nizkoteploprovodnoy thread connecting all of the panels together, the condition must be fulfilled (n · δ + ( n-1) · δ) · U S, where: S- sectional area of ​​the front panel, mm; U- perimeter panel length, mm; δ- panel thickness, mm; δ- value of the gap between adjacent panels, mm, and each sensitive element of the thermometer with the external side of sleep wives and a layer of protective material on all coated surfaces of the panels thermal control coating of black color with a maximum uniform emissivity coating ε≥0,95.2. A method of measuring the density of the incident heat fluxes at spacecraft thermal vacuum tests based on the measurement values ​​of temperatures on the assemblies, characterized in that they produce a continuous measurement of temperature with time Ti Tdlya disposed in parallel planes of the front and rear panels of thin-walled, determine the values ​​for Ti gradients