The Wall Temperature Measurement and Effects on the Missile Complex Surfaсe Based on the Semiconductor Diode and Electronic System

Authors A.M. Pavliuchenko, O.M. Shyiko, T.I. Klochkova
Affiliations

Sumy National Agrarian University, 160, H. Kondratiev St., 40021 Sumy, Ukraine

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Issue Volume 11, Year 2019, Number 3
Dates Received 22 March 2019; revised manuscript received 20 June 2019; published online 25 June 2019
Citation A.M. Pavliuchenko, O.M. Shyiko, T.I. Klochkova, J. Nano- Electron. Phys. 11 No 3, 03004 (2019)
DOI https://doi.org/10.21272/jnep.11(3).03004
PACS Number(s) 47.85.Gj
Keywords Aerophysical missile complex, Complex forebody, Wall temperature, Semiconductor diode, Airborne electronic system, Telemetry, Supersonic separated and unseparated wall flow, Laminar-turbulent transition in the wall jet, Heat flux, Local peaks of the wall temperature and heat flux.
Annotation

The problem of high-precision measurement of the temperature of the forebody wall of an aerophysical missile complex in flight along the trajectory to the altitude of Н ≤ 8 km in response to changes in the numbers of Mach М∞ ≤ 2.0, Reynolds ReL,∞ ≤ 2·107, non-isothermicity, solid-fuel jet engine (SFJE) operation with acceleration of a ≤ 12 g that are not simultaneously simulated in modern supersonic aerodynamic units, has been solved. Semiconductor diodes KD-521 from different materials have been used to measure the wall temperature of this object along the forebody length. The sensitivity of KD-521 is equal to 2.5 mV/deg. The airborne electronic and telemetry systems have a high degree of accuracy and high-speed action. The survey of semiconductor diodes KD-521 has been carried out consistently in time at intervals of 5 ms, and the error of measurement of the temperature of the forebody wall of the missile aerophysic complex does not exceed 1 %. The airborne electronic and telemetry systems, semiconductor diodes KD-521 and data on the wall temperature along the forebody length have enabled to resolve aerophysical challenges associated with the supersonic separated and unseparated flow of the missile complex forebody under the laminar-turbulent transition in the wall jet and in its interaction with the separated wall flow.

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