Hybrid Power Control Unit for Aircraft Hydraulic Redundancy
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft hydraulic power generation systems are weight-intensive due to the need for multiple hydraulic pumps and electric motors, which increases the overall weight of the aircraft while aiming to provide redundancy and handle peak load demands.
Innovation Solution
A method utilizing a hybrid power control unit (PCU) with an electric motor and a hydraulic displacement machine connected to a differential gear unit, where the electric motor drives the hydraulic displacement machine to generate hydraulic power, reducing the need for additional pump-motor combinations by leveraging existing components and arresting the output shaft with brakes to supply hydraulic energy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple hydraulic pumps and electric motors are installed to provide redundancy and handle peak load demands, then the reliability and load compensation capability are improved, but the total weight of the aircraft increases
Solution Approach 1:
The hybrid power control unit is designed to perform multiple functions: it can operate as a hydraulic motor during normal high lift operations, and as a hydraulic pump during non-operational phases to generate hydraulic power for the hydraulic system. This multi-functionality eliminates the need for separate dedicated pump-motor combinations, thereby providing redundancy without increasing weight.
Solution Approach 2:
The patent merges the hydraulic motor and hydraulic pump functions into a single hybrid power control unit. The electric motor and hydraulic displacement machine are combined in one assembly that can switch between motor mode and pump mode, consolidating what would traditionally require separate components and reducing overall system weight.
2Power
If additional hydraulic pumps driven by dedicated electric motors are provided to compensate for load peaks, then the hydraulic power capability is improved, but the device complexity increases
Solution Approach 1:
The hybrid power control unit serves dual purposes: during high lift operations, the hydraulic displacement machine operates as a motor driven by the electric motor; during non-operational phases, the same assembly operates as a pump to generate hydraulic power. This universal design provides enhanced hydraulic power capability without requiring separate dedicated pump-motor combinations, thereby reducing device complexity.
3Productivity
If the hydraulic displacement machine is driven during non-operational phases of high lift systems, then hydraulic power is generated without additional components, but the control complexity increases
Solution Approach 1:
The system dynamically switches between different operational modes based on the state of the high lift system. During operational phases, the hydraulic displacement machine functions as a motor; during non-operational phases, it functions as a pump. This dynamic reconfiguration allows the system to generate hydraulic power during idle periods without requiring permanent additional components, optimizing productivity while managing control complexity through state-dependent operation.
Data Source
AI summary
A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.