DIGITAL ADAPTIVE FLIGHT CONTROL SYSTEM, PHASE II.

Abstract : An investigation was made to determine if the dynamics of an aerospace vehicle might be identified more readily if represented in some other form than a z-transform. An analysis and simulation performed indicate that a representation in terms of linear band-pass filters is preferable. An investigation was made of an implicit response matching technique applicable to both identification and synthesis, which form the bases for self-adaptive control. In a digital simulation the implicit technique was able to simultaneously identify five parameters of a typical aerospace vehicle within 2 seconds without noise, and within 5 seconds with 30 percent noise. An investigation and digital simulation was made of a hybrid digital adaptive flight control system which uses the implicit technique. The system identified 4 parameters of a typical vehicle, and adjusted 2 parameters of the flight control system to provide optimum response. (Author)