This invention relates to the field of aircraft
fire resistance testing technology, and discloses a device,
system, and method for acquiring the
surface heat flux density of a fire-resistant test specimen. The
system initialization includes: total
heat flux measurement (obtaining the theoretical total
heat flux value q0); actual pure radiative
heat measurement (setting a
glass cover around the
heat flux sensor without changing its position, shielding convective heat through the
glass cover, and then collecting the theoretical radiative heat flux value q1 measured by the
heat flux sensor); and multiplying the pre-measured
emissivity of the test specimen surface by the theoretical radiative heat flux value q1 to obtain the actual pure radiative heat flux value q. r Actual heat flux calculation: Actual convective heat value q c The actual heat flux q is obtained by subtracting the theoretical radiative heat flux q1 from the theoretical heat flux q0. a Equal to the actual pure radiative heat flux value q r and actual convective heat value q c The sum of radiative heat and convective heat is achieved through precise measurement of these two heat sources under actual aircraft fire conditions, providing high-fidelity, multi-
scenario, and highly consistent thermal flow data for twin experiments.