RU2007125086A - DEVICE FOR MEASURING THE INTENSITY OF RADIUS FLOWS DURING HEAT AND VACUUM TESTS OF SPACE VEHICLES AND METHOD OF ITS OPERATION - Google Patents

Claims (2)

1. A device for measuring the intensity of radiant flux during thermal vacuum tests of spacecraft, including a metal conductive thermally sensitive element placed on an electrically insulating substrate, characterized in that the thermally sensitive element on the substrate is installed inside the housing made of a material with high thermal conductivity, and is electrically insulated from the housing; the casing is made in the form of a regular straight prism or circular straight cylinder, in which the height h and the characteristic size of the bases L correspond to the relation h <<L; the surface of one base of the casing is made with the highest possible coefficient of thermal radiation (ε _T ^max > 0.5), and the surface of the other base and the side surface of the casing is made with the minimum coefficient of thermal radiation (ε _T ^min <0.5). 2. A method of operating a device for measuring the intensity of radiant flux during thermal vacuum tests of spacecraft, including measuring the electrical resistance of an electrically conductive thermosensitive element, characterized in that the device for measuring the intensity of radiant flux is installed in one of two positions so that for each position of the surface of the bases of its body made from a material with high thermal conductivity in the form of a regular straight prism or circular straight cylinder, were pa allelic surface spacecraft controlled section; in position No. 1, the surface of the base of the casing, made with a minimum coefficient of thermal radiation (ε _T ^min ), is directed towards the controlled area, and the surface of the other base, made with the highest coefficient of thermal radiation (ε _T ^max ), was directed opposite to it side; in position No. 2, the surface of the base of the body with ε _T ^{max is} directed towards the controlled area, and the surface of the other base with ε _T ^{min is} directed to the opposite side from it; install a device for measuring the intensity of radiant fluxes in one of these positions and after reaching the equilibrium thermal state, measure the resistance of the electrically conductive heat-sensitive element installed inside the housing, and the temperature of the housing previously measured for this heat-sensitive element, determine the temperature of the housing for this position (in the case of position No. 1 - temperature T ₁ or in the case of position No. 2 - temperature T ₂ ); then, by rotating the housing relative to its axis of symmetry by 180 °, a device for measuring the intensity of radiant fluxes is set to another position and after reaching the equilibrium thermal state, the temperature of the housing for this position is similarly determined (in the case of position No. 1, temperature T ₁ or in case of position No. 2, temperature T ₂ ); the intensity of the radiant flux of incident radiation to the controlled portion of the spacecraft (q _TVK ) and the effective radiation of the controlled portion of the spacecraft (q _SC ), is determined from the relations

Where

- relative optical parameter;

- relative geometric parameter is the ratio of the lateral surface area (s _b ) of the housing to the area of its base (s _o );

- dimensionless coefficient; σ is the Stefan-Boltzmann constant.