METHOD FOR REPRODUCING AERODYNAMIC HEATING OF AIRCRAFT ELEMENTS Russian patent published in 2022 - IPC G01M9/00 G01N25/72 G01N25/18 G01K13/00 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to ground tests of elements of aircraft, namely to methods for reproducing aerodynamic thermal effects on the surface of aircraft elements, for example, fairings of homing heads of aircraft missiles, antenna fairings, compartments with a rocket, in ground conditions. The proposed method for reproducing aerodynamic heating of aircraft elements by conducting a thermal experiment on a stand using a hot casing includes several cycles of heating aircraft elements with a heated air flow and radiant heat flow from the hot casing. Before conducting a thermal experiment, the air flow recovery temperature in flight and the heat transfer coefficient on the stand and in flight are calculated, provided that the heat transfer coefficient on the stand is less than the heat transfer coefficient in flight, then the first heating cycle of the aircraft elements is carried out with the stand heat transfer coefficient and the recovery temperature of the heated air flow equal to the recovery temperature in flight. The peculiarity of the proposed method is that the first heating cycle is carried out under the additional condition of a thermal experiment, according to which the temperature of the hot casing is equal to the temperature of the environment receiving thermal radiation from the aircraft elements in flight. Moreover, during the first heating cycle of the aircraft element, the surface temperature of the aircraft element is measured. Then, the second and subsequent heating cycles are carried out with a heated airflow and radiant heat flow from the hot casing at a constant stand heat transfer coefficient and recovery temperature equal to the recovery temperature in flight while maintaining the surface temperature of the hot casing, which is calculated before each current heating cycle of the aircraft element. Moreover, the thermal experiment is completed when the measured temperature of the aircraft element at the current heating cycle will differ from the measured temperature of the aircraft element at the previous heating cycle by no more than the value of the permissible measurement error or the temperatures are equal to each other.

EFFECT: increase in the accuracy and reliability of reproducing the thermal effect on the surface of the aircraft elements during aerodynamic heating while reducing the complexity of the experiment.

1 cl, 1 dwg