Systems and method for an electrical system on an aircraft are provided. In example aspects, the electrical system can be for an aircraft having a turbine engine. The turbine engine has a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to multiple high power demand loads. A propulsion system and a multiple aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the propulsion system, and the secondary aircraft systems bus.
提供了用于飞行器上的电气系统的系统和方法。在示例方面,电气系统可用于具有涡轮发动机的飞行器。涡轮发动机具有高压(HP)线轴和低压(LP)线轴。HP线轴可以被构造为驱动第一发电机以提供第一电输出。LP线轴可构造为驱动第二发电机以提供第二电输出。第一发电机和第二发电机可以联接到向多个高功率需求负载提供电力的配电总线。推进系统和多飞行器系统总线都可以联接到配电总线。电气系统还可以包括控制系统,该控制系统被构造为在第一发电机、第二发电机和推进系统以及辅助飞行器系统总线之间分配功率。
Systems and methods of power allocation for turboprop and turboshaft aircrafts
涡轮螺旋桨飞行器和涡轮轴飞行器的功率分配系统和方法
2022-01-25
Patent
Electronic Resource
Chinese
SYSTEMS AND METHODS OF POWER ALLOCATION FOR TURBOPROP AND TURBOSHAFT AIRCRAFTS
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