A scale model of the Transall C160 military aircraft, 1/10 of the actual, was installed above a large copper ground plate and connected to it. The entry point at the nose was hard-wire connected to a 12- mu F/5-kV capacitor bank, and the current pulse launch was made using a triggered atmospheric-pressure spark gap. The exit point at the tail or at the left wing tip, depending on the configuration, was connected to the ground plate via an 80- Omega waveshaping resistor. The transient electromagnetic fields on the outer skin of the model were measured using D-dot and B-dot sensors. Three D-dot sensors were mounted on the forward upper fuselage, on the top and the bottom of the left wing. Two B-dot sensors were mounted on the forward upper fuselage and on the top of the left wing. The current was also measured using three i-dot sensors mounted on the nose boom, on the left wing tip, and on the tail boom. A comparison of experimental and computed electromagnetic fields on the scale model was performed for two experimental configurations of current injection: nose to tail and nose to left wing. As shown for one typical case, all the data were predicted with excellent frequency agreement and very good amplitude agreement.
Comparison of experimental and numerical results for transient electromagnetic fields induced on a scale model aircraft by current-injection technique
Vergleich der experimentellen und numerischen Ergebnisse von transienten elektromagnetischen Feldern, die durch ein Skalen-Flugzeug-Modell induziert wurden
AP-S International Symposium ; 3 ; 1751-1754
1989
4 Seiten
Conference paper
English
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