Aircraft Spool-Based Power Allocation for High-Demand Electrical Loads
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Solution Overview
Problem
Conventional aircraft electrical systems face challenges in efficiently managing power distribution to meet the high power demands of multiple systems such as flight controls, propulsion, and environmental control, often requiring larger engines and separate power sources, which can impact fuel efficiency and flight performance.
Innovation Solution
An electrical system utilizing multiple spools of turboprop or turboshaft engines with intelligent controllers like Propulsion System Controller (PSC) and Bus Power Control Unit (BPCU) to optimize power allocation across different loads, interfacing with Full Authority Digital Engine Control (FADEC) to ensure full flight envelope performance, and incorporating energy storage devices and power conditioners for efficient power distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional aircraft electrical systems use separate power sources for high power demand systems, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent combines multiple power sources (engine generators and auxiliary power units) into a single integrated electrical system with a unified control architecture. The power management controller coordinates power from multiple engines and APU, merging them into a common electrical network that serves all aircraft systems, thereby reducing the need for separate dedicated power sources while maintaining reliability
Solution Approach 2:
The electrical system is designed with universal power distribution capability where any power source (engine generator or APU) can serve multiple functions and multiple aircraft systems simultaneously. The system allows dynamic allocation of power resources to different loads based on operational requirements, enabling one power source to fulfill multiple roles rather than requiring dedicated separate sources
2Power
If larger engines are used to meet high power demands, then power availability is improved, but fuel efficiency deteriorates
Solution Approach 1:
The system dynamically adjusts power allocation between multiple sources based on real-time aircraft operational conditions. The power management controller continuously monitors power demands from various systems (flight controls, propulsion, environmental control) and optimally distributes power between engine generators and APU, ensuring power availability is matched precisely to actual needs rather than providing constant maximum capacity
Solution Approach 2:
The system changes operational parameters by varying the power output levels of different generators and selecting which power source operates at what capacity. The controller can adjust generator load percentages, switch between power sources, and modify power distribution to different systems, optimizing the balance between power availability and fuel consumption based on flight phase and system demands
3Use of energy by moving object
If intelligent controllers optimize power allocation across multiple systems, then fuel efficiency is improved, but device complexity increases
Solution Approach 1:
The power management controller implements feedback mechanisms by continuously monitoring power output from generators, power consumption by various aircraft systems, and operational status of power sources. This feedback enables the controller to make real-time adjustments to power allocation, optimizing fuel efficiency through data-driven decisions rather than fixed or manual control
Solution Approach 2:
The control system performs self-service by automatically managing power allocation without requiring manual intervention. The power management controller independently monitors system status, calculates optimal power distribution, and executes control actions to balance power supply and demand, thereby achieving fuel efficiency optimization through autonomous operation
Data Source
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AI summary
Systems and method (400) for an electrical system on an aircraft (10) are provided. In example aspects, the electrical system can be for an aircraft (10) having a turbine engine (102, 104). The turbine engine having a high pressure (HP) spool (34, 35) and a low pressure (LP) spool (36, 37). The HP spool (34,35) can be configured to drive a first generator (350, 351) to provide a first electrical output. The LP spool (36, 37) can be configured to drive a second generator (352, 353) to provide a second electrical output. The first generator (350, 351) and the second generator (352, 353) can be coupled to an electrical power distribution bus (310) that provides electrical power to multiple high power demand loads (382a-c). A propulsion system (320) and a multiple aircraft systems bus (380) can both be coupled to the electrical power distribution bus (310). The electrical system can further include a control system (500) configured to allocate power among the first generator (350, 351), the second generator (352, 353), and the propulsion system (320), and the secondary aircraft systems bus (380).