Closed Loop Control Law Stability and Performance Analysis Directly Using Open Loop Flight Test Data

摘要

This paper describes flight control law evaluation during the company flight test program of an executive transport aircraft. The business jet aircraft is operated with an augmented flight-by-wire system, which is constructed by pitch axis and lateral-directional axis controlled system. Before flight test on the system, it is necessary to demonstrate enough stability margins of the closed-loop system. Even though linear analysis and aeroservo eleastic analysis show that there are enough margins of stability for safety of flight test of the flight controlled system, there is still requirement to show that the linear analysis results are valid via flight test. This paper shows a simple method to demonstrate stability margins and predicted performance of closed-loop system using open-loop flight test in frequency domain.