This article introduces an original model-based design methodology addressing a high-performance aircraft design challenge: conflicting performance requirements. The case study of the Global 7500 elevator actuation system also provides in-depth insight into the complex design process of today’s fly-by-wire flight control systems. The methodology presented here redefines the aircraft manufacturer’s involvement in the design process of the systems, implementing analysis and iteration capabilities early in system development. To this end, it introduces a novel modeling approach for analyzing loaded rate requirements by simulating closed-loop performance with a generic nonlinear second-order state filter, including the main performance limitations without requiring a preliminary design definition. In this way, it provides means to mature the system requirements and addresses requirement conflicts upfront. Then, a simulation-based preliminary sizing and performance assessment validates the candidate design concept. It also secures the preliminary design phase by implementing advanced design uncertainties and involving interfacing systems and disciplines early in the process. The redefined methodology identified directly that the problem’s root cause was a conflict between stability and control and flutter protection requirements. It also indicated that the first sizing driver is the response time required under a specific failure case. These findings lead to an optimal elevator actuator design compliant with matured performance requirements. Thus, the methodology resolved a design challenge blocking the Global 7500 aircraft development and prevented redesign occurrences later during the detailed design phase. In this way, it directly contributed to the successful development of the Global 7500 and its optimal operational performance. This methodology applies to future aircraft design challenges, and the technical insight provides valuable lessons learned for high-performance T-tail business jets.

本文介绍了一种基于模型的原始设计方法，可解决高性能飞机设计挑战：性能要求冲突。Global 7500 升降舵驱动系统的案例研究还提供了对当今电传飞行控制系统复杂设计过程的深入了解。这里介绍的方法重新定义了飞机制造商在系统设计过程中的参与，在系统开发的早期实施分析和迭代功能。为此，它引入了一种新颖的建模方法，通过使用通用非线性二阶状态滤波器模拟闭环性能来分析负载速率要求，包括主要性能限制，而无需初步设计定义。这样，它提供了使系统需求成熟并预先解决需求冲突的方法。然后，基于模拟的初步尺寸和性能评估验证候选设计概念。它还通过实施高级设计不确定性并在流程早期涉及接口系统和学科来确保初步设计阶段的安全。重新定义的方法直接确定了问题的根本原因是稳定性和控制以及颤振保护要求之间的冲突。它还表明，第一个大小调整驱动程序是特定故障情况下所需的响应时间。这些发现导致了符合成熟性能要求的最佳电梯执行器设计。因此，该方法解决了阻碍 Global 7500 飞机开发的设计挑战，并防止在详细设计阶段后期发生重新设计。通过这种方式，它直接促成了环球 7500 的成功开发及其最佳运行性能。这种方法适用于未来的飞机设计挑战，技术洞察力为高性能 T 型尾翼公务机提供了宝贵的经验教训。