HVDC Bus Power Distribution Control in Hybrid Aircraft Propulsion
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current hybrid propulsion systems for VTOL aircraft face challenges in efficiently managing power distribution between electrical sources due to the complexity of existing control systems, which often seek local optima and lack adaptability to different flight phases and operating conditions.
Innovation Solution
A control system that manages power distribution through AC/DC controlled rectifiers using regulation loops for voltage and power setpoints, eliminating the need for a DC/DC converter and allowing indirect control of the battery, enabling adaptability to various operating regimes and power sources.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a DC/DC converter is used to control battery current in hybrid propulsion systems, then local optima can be achieved in power distribution, but the system complexity increases and adaptability to different operating regimes is reduced
Solution Approach 1:
The patent removes the DC/DC converter from the hybrid propulsion system, eliminating the complex dual-loop control structure while maintaining effective power distribution control through the AC/DC rectifier alone. This extraction of the unnecessary component resolves the contradiction by achieving reliable control without the added complexity.
Solution Approach 2:
The AC/DC rectifier is designed to perform multiple functions: it controls power distribution from the turbogenerator and simultaneously manages battery current control. This multi-functionality eliminates the need for a separate DC/DC converter, reducing system complexity while maintaining control reliability across different operating regimes.
2Manufacturing precision
If multiple converters and rectifiers are used for precise power control, then power distribution precision can be improved, but the ease of manufacture and system scalability are reduced
Solution Approach 1:
By removing the DC/DC converter, the patent simplifies the system architecture to a single AC/DC rectifier, making the system easier to manufacture, assemble, and install while maintaining sufficient power distribution precision through the unified control approach.
Solution Approach 2:
The patent combines the functions of the AC/DC rectifier and DC/DC converter into a single AC/DC rectifier unit. This merging of functions reduces the number of components that need to be manufactured and assembled, improving ease of manufacture while achieving the same control objectives.
3Adaptability or versatility
If separate control loops for voltage and power are implemented, then adaptability to different flight phases is improved, but the device complexity increases
Solution Approach 1:
The unified control loop in the AC/DC rectifier is designed to adapt to different flight phases and operating regimes by dynamically adjusting its control parameters. This single multi-functional control structure replaces the need for separate voltage and power control loops, maintaining adaptability while reducing complexity.
Solution Approach 2:
The control system dynamically adjusts its behavior based on the operating regime (e.g., charging, discharging, different flight phases) without requiring structural changes or separate control loops. The dynamic adaptation capability is embedded in the unified control algorithm, resolving the contradiction between adaptability and 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 provides a more efficient, scalable, and modular power distribution control that adapts to different flight phases and power requirements, optimizing reliability and integration on aircraft.
Implementation Method 1
an electrical source delivering an alternating voltage associated with an AC/DC controlled rectifier
Implementation Method 2
a regulation loop on a power setpoint from a measured power of the battery and a regulation loop on a voltage setpoint from a measured voltage of the HVDC bus
Data Source
Figure 1
Figure 2~3
Figure 4
AI summary
Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (VHVDC), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.