Compound Motor Generator Pump for Aircraft Backup Power
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Solution Overview
Problem
Modern aircraft face challenges in maintaining continuous power supply during engine and auxiliary power unit failures, leading to increased weight, complexity, and reduced efficiency due to reliance on mechanical backups and external Ram Air Turbines, which are inefficient and impractical for supersonic flight.
Innovation Solution
A rotatively combined electrical power/generator and hydraulic motor/pump system, integrated with a ducted ram air turbine, provides simultaneous electrical and hydraulic backup power through a CMGP unit, reducing complexity and weight by eliminating redundant power sources and enabling continuous operation, including supersonic flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional Ram Air Turbine (RAT) system is used for backup power, then emergency power can be provided, but the weight, cost, and complexity of the aircraft increase significantly
Solution Approach 1:
The patent combines the electrical motor/generator and hydraulic motor/pump into a single compound unit sharing a common shaft and housing. This merging eliminates redundant structures and reduces overall system weight while maintaining the ability to provide both electrical and hydraulic backup power through a single integrated device
Solution Approach 2:
The compound motor generator pump unit is designed to perform multiple functions: it can operate as an electrical motor driven by hydraulic power, as an electrical generator driving hydraulic power, as a hydraulic motor, or as a hydraulic pump. This multi-functionality eliminates the need for separate backup systems, reducing weight and complexity
2Reliability
If a conventional Ram Air Turbine (RAT) is deployed outside the aircraft for emergency power, then backup power can be generated, but excessive drag and loads occur at relatively low airspeeds
Solution Approach 1:
The air turbine is nested within a duct that is integrated into the aircraft fuselage, with the turbine housing contained within the duct structure. This nesting allows the turbine to be aerodynamically fairingd, reducing drag compared to an external deployment, while still allowing air to drive the turbine for power generation
Solution Approach 2:
The patent replaces the conventional external windmill-type RAT mechanical system with an internal ducted turbine system that uses controlled air flow through flaps to drive the turbine. This substitution reduces the mechanical loads and drag associated with external propeller-type turbines
3Loss of energy
If the RAT is stowed within the aircraft during normal flight to reduce drag, then drag is minimized, but the RAT becomes inoperable except for emergency situations
Solution Approach 1:
The patent employs dynamically controllable flaps (inlet flap and exit flap) that can adjust the air flow to the turbine during flight. These flaps allow the system to transition between a stowed, low-drag configuration and an operational configuration, enabling the turbine to be used for power generation when needed while minimizing drag during normal flight
Solution Approach 2:
The system uses feedback control through the flap mechanisms to monitor and adjust air flow to the turbine based on power requirements. The flaps can be opened or closed to regulate the amount of air reaching the turbine, providing continuous control over power generation while maintaining aerodynamic efficiency
4Reliability
If multiple engine driven generators and hydraulic pumps are installed to meet power requirements, then power availability improves, but aircraft complexity and weight increase
Solution Approach 1:
The compound motor generator pump unit merges multiple power conversion functions into a single device. By combining the electrical motor/generator and hydraulic motor/pump on a common shaft, the system reduces the number of separate components needed, simplifying the overall power system architecture while maintaining the ability to provide both electrical and hydraulic power
Solution Approach 2:
The compound unit provides universal power conversion capability, able to convert between electrical and hydraulic power in either direction. This multi-functionality allows a single device to replace what would traditionally require multiple separate generators and pumps, reducing system complexity
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The system ensures continuous power availability during flight, reducing fuel consumption and emissions, and eliminating the need for APU operation during extended over-water flights, while minimizing drag and weight, thus enhancing aircraft reliability and range.
Implementation Method 1
a ducted ram air turbine drive
Data Source
AI summary
In combination, an aircraft and a rotatively combined electrical power/generator and hydraulic motor/pump configured to provide either hydraulic power from electrical power, or electrical power from hydraulic power, installed in said aircraft.