Hybrid Rotorcraft Electrical Architecture Segmentation
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Solution Overview
Problem
Current rotary-wing aircraft face challenges in implementing a lightweight, efficient, and modular hybrid electrical architecture that does not complicate or weigh down existing systems, particularly in providing energy for additional functionalities like de-icing and air conditioning while meeting ecological and regulatory requirements, and in offering hybridization as an optional feature without exceeding weight limits.
Innovation Solution
A rotary-wing aircraft with a segregated electrical network featuring a main combustion engine and an auxiliary electric hybridization system, where the auxiliary electric machine acts as both a generator and motor, connected to the transmission system, allowing for selective energy exchange between the main and auxiliary electrical networks through a selective adaptation interface, enabling efficient energy distribution and redundancy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a hybrid electrical architecture is implemented with additional electric machines and batteries, then energy availability for additional functionalities is improved, but device complexity and weight increase
Solution Approach 1:
The electrical architecture is segmented into a main electrical network powered by the combustion engine and an auxiliary electrical network powered by batteries and electric machines. This segmentation allows independent management of power sources, enabling the system to provide additional energy for functionalities like de-icing and air conditioning without overcomplicating the overall architecture. Each network can be optimized separately for its specific functions.
Solution Approach 2:
The auxiliary electric machine is designed with multi-functionality, serving as both a motor to drive the transmission and a generator to charge the batteries. This universal component performs multiple roles within the hybrid architecture, providing energy availability for additional functionalities while minimizing the number of separate components needed, thereby controlling device complexity.
2Adaptability or versatility
If hybridization is offered as an optional feature with additional equipment, then adaptability is improved, but weight increases
Solution Approach 1:
The hybridization system is designed as a dynamic, optional configuration that can be adapted to different aircraft models and mission requirements. The system allows operators to select hybrid mode only when additional energy for functionalities like de-icing is needed, rather than carrying the full weight of hybrid equipment continuously. This dynamic adaptability enables weight optimization while maintaining versatility.
3Power
If the combustion engine is overloaded to provide energy for additional functionalities, then power availability is improved, but fuel consumption and emissions increase
Solution Approach 1:
Batteries serve as an intermediary energy storage device between the combustion engine and the additional energy-consuming functionalities. Instead of overloading the combustion engine directly, the system uses the batteries to store excess energy during low-demand periods and discharge it during high-demand periods (such as de-icing operations). This intermediary approach provides the necessary power availability while allowing the combustion engine to operate efficiently, reducing fuel consumption and emissions.
4Productivity
If a segregated electrical network with selective adaptation interface is implemented, then energy management efficiency is improved, but device complexity increases
Solution Approach 1:
The selective adaptation interface incorporates feedback mechanisms that continuously monitor the state of the main and auxiliary electrical networks, including battery charge levels, engine power output, and energy demand from various functionalities. This feedback enables the system to automatically optimize energy management by switching between power sources and adjusting load distribution in real-time, improving energy management efficiency while keeping the control logic integrated and manageable.
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 allows for efficient energy management, reduced weight, improved safety, and compliance with ecological and regulatory standards by enabling the integration of high-energy functionalities without overloading the combustion engine, and can be adapted to various aircraft models without complicating the electrical architecture.
Implementation Method 1
The auxiliary electric machine is arranged as a current generator and placed within the hybrid motorization assembly by constituting alternately a mechanical drive member of the transmission or a current generator member under the effect of its mechanical drive by said transmission
Data Source
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AI summary
An aircraft hybrid propulsion system (1) (5) comprises at least: a hybrid system (37) with a main onboard electrical network (16) and an auxiliary electrical network (34); a selective matching interface (38) arranged to selectively allow the exchange of electrical energy between the main and auxiliary electrical networks (16; 34). At least one combustion engine and auxiliary electric machine (7) of the hybrid system (31) are mechanically connected to a transmission (8); said machine (7) being electrically connected to at least one auxiliary electrical bus (36), in parallel with at least one auxiliary electrical charging device.