Impact Analysis of Roll Maneuver Load about Civil Aircraft after Considering Control Law

In order to ensure the aircraft structure safety during the rapid roll maneuver process of the aircraft, the design requirements for the roll maneuvering load are provided in article 25.349 of Chinese Civil Aviation Regulation Part 25 (CCAR-25) and in article 25.349 of Certification Specification 25 (CS-25). This paper firstly makes an understanding and comparative analysis of article CCAR25.349 and CS25.349. And then, in order to analysis the influence of control law on roll maneuver load about the large civil aircraft, a maneuver load simulation method for considering control law has been developed combining with the flight motion dynamics equations in this paper. Subsequently, based on roll maneuver situation stipulated in article 25.349 of CCAR-25 and in article 25.349 of CS-25, roll maneuver simulation calculation with/without the consideration of control law respectively is carried out. Finally, the important influence of control law properties on roll maneuver load is described by comparative analysis of the roll maneuver flight response parameters. The results of calculation and analysis show that: 1) after the control law is taken into account, the aileron deflection of the aircraft changes greatly during the rapid roll maneuver process; 2) for the roll maneuver with the rapidly moving cockpit operating device, the roll response attitude of the aircraft is reduced after considering the control law, resulting in the roll maneuver load is reduced significantly; 3)after considering the control law, the aileron deflection has an obvious overshoot when the cockpit lateral control device returns to neutral.