Parallel Converter Modules for Regulated Aircraft DC Power
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Solution Overview
Problem
Current electrical power systems on aircraft lack regulated AC-to-DC power conversion, leading to unsteady and heavy DC power sources, which increase aircraft weight and reduce efficiency due to variable output performance and separate fault protection mechanisms.
Innovation Solution
A regulated transformer rectifier unit with multiple converter modules connected in parallel, controlled by a controller to provide stable and regulated DC power, addressing the instability and weight issues by improving power quality and fault tolerance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If unregulated AC-to-DC power conversion is used, then device complexity is reduced, but power quality and stability deteriorate
Solution Approach 1:
The power conversion system is divided into multiple independent converter modules (first converter module, second converter module, etc.) that can operate independently. Each module has its own control circuitry and fault protection mechanisms, allowing the system to maintain power quality and stability even when individual modules fail or are adjusted.
Solution Approach 2:
The control circuit dynamically adjusts operating parameters of the converter modules based on system conditions. The controller monitors the electrical characteristics and modifies control parameters to optimize power conversion performance, maintain voltage stability, and ensure reliable operation under varying load conditions.
2Reliability
If multiple converter modules are used in parallel, then power quality and reliability are improved, but device complexity increases
Solution Approach 1:
Multiple converter modules are connected in parallel to form an integrated power conversion system. The control circuit combines the output of individual modules and coordinates their operation, achieving improved reliability and power quality while managing complexity through unified control architecture.
Solution Approach 2:
The converter modules are designed with universal functionality to perform multiple roles: normal power conversion, fault isolation, and system stabilization. Each module can operate independently or in combination with others, providing flexible configuration options that reduce overall system complexity while maintaining high reliability.
3Device complexity
If traditional separate fault protection mechanisms are used, then device complexity is reduced, but reliability deteriorates
Solution Approach 1:
Fault protection functionality is merged into the control circuit of each converter module. The control circuit integrates multiple protection mechanisms (over-current, over-voltage, fault detection) that work together with the parallel module architecture to provide comprehensive fault tolerance without requiring separate external protection systems.
Solution Approach 2:
Each converter module incorporates self-diagnosis and self-protection capabilities through its control circuit. The modules can detect faults in themselves and in other modules, automatically isolate problematic units, and continue operation with remaining healthy modules, providing reliable fault protection without external intervention.
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 solution provides stable and high-quality DC power, reduces aircraft weight by optimizing power conversion, and enhances reliability by integrating fault protection within the AC-to-DC conversion process.
Implementation Method 1
A transformer in a transformer rectifier unit on an aircraft may be configured to transform a multiple-phase AC input signal provided by an AC power source to a multiple-phase AC output signal
Data Source
AI summary
A method and apparatus for providing regulated direct current power for a direct current load on an aircraft. A regulated transformer rectifier unit on an aircraft comprises a plurality of converter modules connected in parallel between an input and an output. Each converter module in the plurality of converter modules comprises a transformer rectifier unit. The plurality of converter modules are controlled by a controller to provide regulated direct current power at the output from alternating current power provided at the input from an alternating current power source on the aircraft.