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The surface effect flight adaptive flight control system design has been analyzed by root locus method and gain scheduling on Tune PID controller in the low speed, V and surface effect altitude, h. The several parameters in the Single Input Single Output (SISO) system that has been analyzed and gave the good level stability. The verification of the adaptive flight control system on this paper has been done during cruise phase by using back propagation computational technique on the neural networks by using the elevator deflection, δe as input control and pitch angle, θ as output response in the longitudinal mode of WISE L8. The pitch angle, θ as output response is easier than others parameter due to the hardware instrument sensory as feedback on the closed loop of adaptive control system as Pitch Attitude Hold. Rancangan sistem kendali terbang adaptif efek permukaan telah diananlisis sebelumnya dengan menggunakan metoda root locus dan gain scheduling pada kontroler Tune PID pada ketinggian, h dan kecepatan, V di surface effect. Beberapa parameter pada sistem Single Input Single Output (SISO) telah dianalisis dan memberikan respons stabilitas dengan berbagai tingkatan kestabilan yang lebih baik. Verifikasi sistem kendali terbang adaptif yang dilakukan pada tulisan ini menggunakan metoda neural networks dengan komputasional back propagation terhadap parameter defleksi elevator, δe sebagai input dan defleksi sudut pitch, θ sebagai respons output pada gerak matra longitudinal pesawat WISE L8. Hal ini disebabkan, parameter sudut pitch, θ sebagai respons output yang mudah dalam hal pemasangan peralatan instrumentasi, sebagai sensor yang digunakan dalam perancangan sistem umpan balik kendali terbang adaptif sebagai Pitch Attitude Hold.

Sistem Kendali Terbang Adaptif Neural Networks Pesawat Efek Permukaan di Ketinggian Rendah