Hybrid Power Plant Engine Failure Management
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Solution Overview
Problem
Rotary-wing aircraft equipped with single-engine power plants face performance degradation and restricted flight capabilities due to limited power reserves in case of engine failure, while twin-engine aircraft are overpowered in normal flight to account for single-engine operations, leading to increased fuel consumption and weight.
Innovation Solution
A hybrid power plant system comprising two internal combustion engines and an electric machine, where the electric machine supplies auxiliary power to the main power transmission box during engine failure, allowing safe operation without overstressing the remaining engines.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If twin-engine aircraft are sized to operate with one engine in case of failure, then flight safety is improved, but fuel consumption and weight increase
Solution Approach 1:
The invention changes the power source parameter from purely thermal engines to a hybrid system including electric motors. The electric motors provide auxiliary power during single-engine operation, allowing the thermal engines to be sized for normal operation rather than emergency operation, thus reducing fuel consumption while maintaining safety
Solution Approach 2:
The electric motors serve multiple functions: they provide auxiliary propulsion during normal flight, serve as backup power during engine failure, and can operate in generator mode to charge batteries. This multi-functionality allows the system to improve safety without proportionally increasing weight and energy consumption
2Ease of operation
If thermal engines operate in emergency power regimes during engine failure, then aircraft maneuverability is maintained, but engine stress and maintenance costs increase
Solution Approach 1:
The electric motors act as an intermediary power source between the thermal engines and the load. During engine failure, the electric motors compensate for the lost power, allowing the remaining thermal engine to operate within normal parameters rather than emergency regimes, thus reducing stress and maintenance requirements
Solution Approach 2:
Instead of relying on a single thermal engine operating at excessive emergency power levels, the invention uses partial action from the electric motors to supplement the remaining thermal engine, distributing the power demand and keeping the thermal engine within normal operating limits
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
This solution ensures safe maneuvering of the aircraft during engine failure by providing sufficient power without exceeding predetermined engine operating conditions, reducing the need for emergency power regimes and associated maintenance costs, and optimizing aircraft performance and weight.
Implementation Method 1
at least one electric machine (12) capable of driving said main rotor (2)
Implementation Method 2
a power plant which may comprise one or more heat engines
Data Source
Figure 1A~3
AI summary
The present invention relates to a method for managing an engine failure on a rotary-wing aircraft (1) comprising a hybrid propulsion system (5) equipped with at least two internal combustion engines (13, 13'), at least one electric machine (12), and a main power transmission unit (11). The aircraft (1) also comprises an electrical energy storage system (14) and a main rotor (2) mechanically linked to the hybrid propulsion system (5).According to the said method, the operation of said thermal engines (13,13') is monitored during each flight in order to detect a failure of one of them, then when a failure of one of said thermal engines (13,13') is detected, said electric machine (12) is commanded to provide, if necessary, an auxiliary power We in order to avoid the occurrence of a deficit in the total power WT of said hybrid propulsion system (5), thus allowing the pilot of said aircraft (1) to maneuver said aircraft (1) safely without degrading said hybrid propulsion system (5).