Robust Flight Control System Design Verification & Validation for Launchers

Abstract

This article presents the motivation, goals and benchmark problems of a study from the European Space Agency entitled "Robust Flight Control System Design Verification and Validation Framework" (RFCS). The objective of the study is to develop, demonstrate and compare the potential of modern control design, analysis and modeling techniques to address complex issues currently not well covered in the traditional launchers' verification and validation (V&V) process. The identification of these V&V gaps have resulted in a set of benchmark problems that allow comparing the standard results with those arising from the application of the advanced techniques. The benchmark problems are extracted from the VEGA launcher and its V&V process, but their significance is more general as they represent common issues found in most launchers.

Time‐varying robustness analysis of launch vehicles under thrust perturbations

“…Simultaneously, the absolute values of the developing aerodynamic loads |Q(t)𝛼(t)| and |Q(t)𝛽(t)| in the pitch and yaw plane never exceed the Mach dependent structural limit load under test scenarios suggested by the European Space Agency (ESA). 37 The linear launcher models G LV,pitch,nom and G LV,yaw,nom are extended with the TVC dynamics. In feedback interconnection with the controller, they build the nominal closed loop models G pitch,nom , with input d pitch = [w z , T] T and output e pitch = Q𝛼, and G yaw,nom , with input d yaw = w y and output e yaw = y b .…”