Aircraft Active Inceptor Dynamics under Vibration Loads

具有电传操纵系统的飞机通常包括所谓的主动操纵器（操纵杆、油门、踏板等）。提供飞行员和飞机操纵面之间的接口。这些设备是复杂的机电万向节系统，利用电机，伺服致动器，扭转弹簧，线性弹簧，球轴承，球面轴承和位移和力传感器-所有这些都通过一系列机械连杆和飞行员的握把组件互连。该系统控制抓握力-位移关系，以允许感觉特性的真实的时间变化，从而支持飞机操作模式。发动机中各个元件的动态响应以及整个系统的动态响应对于在整个使用寿命期间保持所需的性能水平至关重要。虽然疲劳寿命部分由飞行员施加的循环载荷决定，但飞机振动载荷可能是主要的设计驱动因素。飞机谐波振动载荷的影响，如在直升机中，是很难评估的：一些由此产生的操纵系统共振可以落在飞机的频率范围内，必须避免。该博士项目涉及推导、开发和研究主动接收器的合适数学模型，该模型可用于评估其动态特性。BAE系统公司将提供一个开发直升机集体坚持单位和相关的CAD模型，为这项调查。数学模型，至少在最初，将集中在这个集体坚持。任何支持建模所需的实验测试都将由BAE系统公司或大学内部进行。这项研究的目的是加强对这一候选发动机系统的动力学的理解，包括在代表直升机振动的谐波激励的影响下，并探索确保避免共振频率响应的方法。摩擦建模、力传感和飞行员臂相互作用等相关主题可能会在稍后阶段纳入。

Aircraft with fly-by-wire control systems often incorporate so-called active inceptors (stick, throttle, pedals, etc.) that provide the interface between the pilot and the aircraft control surfaces. These devices are complex electro-mechanical gimbal systems utilising motors, servo-actuators, torsional springs, linear springs, ball bearings, spherical bearings and displacement and force transducers - all interconnected via a series of mechanical linkages and a pilot's grip assembly. The system controls the grip force-to-displacement relationship to allow real time variation in feel characteristics to support aircraft operational modes. The dynamic response of the individual elements in an inceptor, and of the system as a whole, is critical in maintaining the level of performance required throughout its service life. Whilst the fatigue life is partly driven by the pilot-applied cyclic loads, aircraft vibration loads can be the primary design driver. The effects of aircraft harmonic vibration loads, as in a helicopter, are difficult to assess: some of the resulting inceptor system resonances can fall within aircraft frequency ranges that must be avoided. This PhD project involves the derivation, development and study of a suitable mathematical model of an active inceptor, which can be used for assessing its dynamic characteristics. BAE Systems will provide a development helicopter collective stick unit and the associated CAD models for this investigation. The mathematical modelling, at least initially, be focused on this collective stick. Any experimental testing of this unit needed to support the modelling will be conducted either by BAE Systems or within the University. The objective of the study is to enhance the understanding of the dynamics of this candidate inceptor system, including under the influence of harmonic excitation representing helicopter vibration, and to explore methods for ensuring that resonant-frequency responses are avoided. Related topics such as friction modelling, force sensing and pilot arm interactions could potentially be incorporated at a later stage.