Aircraft Power Bus Segmentation for Critical Load Backup
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Solution Overview
Problem
Current hybrid aerospace propulsion systems face limitations in efficiently managing power distribution and backup operations, particularly in ensuring continuous power supply to critical systems during generator failures.
Innovation Solution
An energy storage system for aircraft comprising a main battery, propulsion power bus, non-critical bus, critical bus, and engine starter bus, along with isolated DC-DC converters and backup batteries, which supply power to electric propulsion machines, hotel loads, and critical systems, enabling seamless transition and backup power in case of main battery failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single main battery is used to power all systems, then the system structure is simple, but the reliability of power supply to critical systems during battery failure is poor
Solution Approach 1:
The power distribution system is segmented into separate critical and non-critical buses. The critical bus is dedicated exclusively to powering essential systems, while the non-critical bus handles non-essential loads. This segmentation ensures that failures in non-critical systems or their associated converters cannot affect the reliability of critical system power supply, directly resolving the contradiction between reliability and complexity.
Solution Approach 2:
Isolated DC-DC converters are introduced as intermediary devices between the main battery and different power buses. These converters provide galvanic isolation and fault containment, allowing the system to maintain reliability by preventing fault propagation while managing the complexity through standardized intermediate components.
2Reliability
If independent isolated converters are used for each high voltage network, then the fault isolation capability is improved, but the device complexity increases
Solution Approach 1:
The converter system is segmented into dedicated converters for different power buses (critical bus converter, non-critical bus converter). Each converter is independently isolated and dedicated to a specific bus, enabling fault isolation while maintaining manageable complexity through functional specialization rather than requiring multiple converters for every possible fault scenario.
Solution Approach 2:
The isolated DC-DC converters are designed with multi-functionality, serving as both power conversion devices and fault isolation barriers. They can operate in normal power delivery mode and automatically switch to fault containment mode, reducing the need for additional dedicated fault isolation equipment and thereby managing complexity.
3Reliability
If the main battery directly powers all loads, then the power distribution is simple, but the ability to provide backup power during main battery failure is insufficient
Solution Approach 1:
The power distribution architecture is segmented into critical and non-critical pathways with dedicated converters for each. This segmentation enables independent control and protection strategies for different load categories, allowing the system to provide targeted backup power to critical systems while managing overall system complexity through modular design.
Solution Approach 2:
Isolated DC-DC converters serve as intermediary devices that enable sophisticated power management and backup capabilities without requiring direct complex wiring between the battery and all loads. These converters provide intelligent power delivery, fault isolation, and backup functionality through standardized intermediate components.
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
Ensures reliable power delivery to propulsion, critical, and non-critical systems, including starting the gas turbine engine, by isolating faults and providing backup power through dedicated buses and converters, thereby enhancing operational safety and efficiency.
Implementation Method 1
a main battery, a propulsion power bus configured to convey electricity, which is supplied by the main battery, to an electric propulsion machine
Implementation Method 2
several converters to transfer energy from one of the high voltage direct current networks to one of the low voltage direct current networks, the different converters being independent and isolated from each other
Data Source
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AI summary
Energy storage systems (100) for aircraft and methods of operating the same are provided. The energy storage system (100) may include a main battery (104), a propulsion power bus (106), a non-critical bus (108), a critical bus (110), and an engine starter bus (112). The propulsion power bus (106) may be configured to convey electricity, which is supplied by the main battery (104), to an electric propulsion machine (114) configured to provide propulsion for the aircraft. The non-critical bus (108) may be configured to convey electricity to a hotel load (116) on the aircraft. The critical bus may be configured to convey electricity, which is supplied by the main battery (104), to a critical load (118) on the aircraft. The engine starter bus (112) may be configured to convey electricity, which is supplied by the main battery (104), to an electric starter (120) for a gas turbine engine (122), where the gas turbine engine (122) is configured to power the electric propulsion machine (114).