Integrated Systems Design of Composite Casings for Power Electronic Converters for Aircraft Applications

飞机电气化是实现减少飞机燃料燃烧和相关温室气体排放（包括一氧化二氮和二氧化碳）的宏伟目标的核心。该博士学位将开发和演示电力电子转换器（PEC）与碳纤维增强聚合物（CFRP）外壳的集成设计方法，以实现未来飞机中PEC的轻量化和体积最小化。这些集成系统将形成一个模块，可以很容易地插入和退出飞机的电气系统，增加了一个额外的好处，减少了时间的服务，由于维护。集成设计将考虑与更广泛的机载电力系统的相互依赖性。存在一个重要的研究机会来集成电气和结构系统，以优化整个飞机的性能。这包括在可能的情况下，在设计阈值内，开发具有多功能作用的材料。特别是模块化机载电力系统的设计，每个模块都集成了一段复合结构，可以很容易地插入和取出飞机或发动机。这不仅具有最小化体积和重量的优点，而且还具有最小化发动机或飞机停止服务的时间的优点。过去，航空航天工业已经提出了模块化筏的概念，但需要进一步了解将CFRP与电气系统和组件紧密集成的方法。 为了成功设计集成电力电子转换器CFRP模块，该项目将确定电力系统，电力电子转换器拓扑结构和CFRP的电气，热和机械性能的关键设计阈值。结构、热力和电气系统的集成带来了复杂的挑战，需要采用多学科方法。这包括转换器拓扑结构、热管理系统、控制电路、电磁屏蔽和适当滤波器的选择。更广泛的系统考虑因素包括系统参数、接地拓扑和故障管理策略。热管理系统可能经由空气冷却，或者可能需要液体冷却。设计与CFRP套管铺层的相互依赖性对于集成系统设计至关重要。另一个设计挑战是，集成系统必须足够坚固，能够承受恶劣的操作环境，系统会经历低压、极端温度、振动和潮湿的组合。最后，模块化水平也将被考虑在内。例如，将辅助系统集成到复合外壳中的限制。该项目中设计的集成系统将通过硬件原型的设计、测试和构建进行验证。

Electrification of aircraft is central to achieving ambitious targets for reduction of aircraft fuel burn and associated emissions of greenhouse gasses including Nitrous Oxides and Carbon Dioxide. This PhD will develop and demonstrate methods for the integrated design of power electronic converters (PEC) with carbon fibre reinforced polymer (CFRP) cases, for the light-weighting and minimised volume of PEC in future aircraft. These integrated systems will form a module that can be easily slotted in and out of an aircraft's electrical systems, adding an additional benefit of reduced time out of service due to maintenance. The integrated design will take into account interdependencies with the wider on-board electrical power system.A significant research opportunity exists to integrate the electrical and structural systems, to enable optimisation of the full aircraft performance. This includes, where possible within design thresholds, the development of materials with multifunctional roles. In particular the design of a modularised on-board electrical power system, with each module integrated with a section of composite structure that can be easily slotted in and out of the aircraft, or engine. This has the advantage of not only minimising volume and weight, but minimises the time an engine or aircraft is out of service. The concept of modular rafts has been proposed by the aerospace industry in the past, but further understanding of methods to closely integrate CFRP with electrical systems and components is required. For the successful design of an integrated power electronic converter CFRP module, the project will identify the key design thresholds for the electrical power system, power electronic converter topology and electrical, thermal and mechanical properties of CFRP. The integration of the structural, thermal and electrical system introduces complex challenges and requires a multi-disciplinary approach. This includes the choice of converter topology, thermal management system, control circuitry, electromagnetic shielding and appropriate filters. Wider systems considerations include the system parameters, grounding topology and fault management strategy. The thermal management system may be possibly via air cooling, or liquid cooling may be required. The design interdependencies with the layup of the CFRP casing are critical to the integrated system design. An additional design challenge is that the integrated system must be robust enough to withstand the harsh operating environment, with the system experiencing a combination of low pressure, extreme temperature, vibration and moisture. Finally, the level of modularisation will also be taken into account. For example, the limitations on integrating auxiliary systems into the composite casing. The integrated systems designed in the project will be verified by the design, test and build of hardware prototypes.