FIELD: aircraft engineering.
SUBSTANCE: proposed device is composed of packs with every sensor arranged at electrically insulating substrate. Said packs are composed of n panels arranged in parallel opposed planes (where: n>=2) interconnected by threads in frame carcass. Sensor of every panel is secured with thermal contact to thin-wall plate. Said panels are arranged wit clearance between adjacent panels with the help of point contacts. Invention covers also the method of measurement of incident heat flows at surface heat vacuum tests of spacecraft based on measurement of temperatures at heat receivers designed to measure continuously the temperatures Tf and Tr for face and rear thin-wall plates located in parallel planes. Gradients for Tf and Tr are defined to register quasi stationary heat state of the device. At gradients ∂T/∂τ≤1°/h registered are final temperatures to be allowed for in definition of incident heat flows at surface heat vacuum tests.
EFFECT: higher accuracy and validity.
2 cl, 5 dwg
