Aircraft Propulsion Bus Voltage Control for High-Altitude Insulation
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Solution Overview
Problem
Aircraft electric propulsion systems face challenges with partial discharge at high altitudes, leading to premature insulation failure and increased weight due to the need for thicker insulation or higher voltages, which are not efficiently managed by existing technologies.
Innovation Solution
A voltage-controlled aircraft electric propulsion system dynamically adjusts the voltage on the power supply bus based on altitude, maintaining constant current and reducing electrical stress, thereby minimizing insulation thickness and weight while preventing partial discharge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If higher voltage is used to reduce current and minimize I²R losses, then energy efficiency improves, but insulation thickness must increase to prevent partial discharge at high altitudes, leading to increased weight
Solution Approach 1:
The system dynamically adjusts voltage based on altitude using a controller that receives altitude signals and modifies voltage output accordingly. This dynamic adaptation allows the system to maintain optimal voltage levels for energy efficiency at low altitudes while preventing partial discharge at high altitudes, eliminating the need for excessive insulation thickness throughout the entire operational range.
Solution Approach 2:
The system changes the voltage parameter in response to altitude changes. By monitoring altitude and adjusting voltage levels, the system optimizes the balance between energy efficiency (requiring higher voltage) and partial discharge prevention (requiring lower voltage), thereby reducing insulation weight requirements while maintaining both efficiency and reliability across different flight conditions.
2Reliability
If thicker insulation is used to prevent partial discharge at high altitudes, then reliability improves, but device weight increases
Solution Approach 1:
The voltage control system dynamically adapts to altitude changes, maintaining voltage below the partial discharge inception voltage threshold at high altitudes. This dynamic protection mechanism ensures insulation reliability without requiring excessive insulation thickness, thereby reducing overall system weight while maintaining reliability across the full altitude range.
Solution Approach 2:
The system takes preliminary action by reducing voltage before partial discharge can occur at high altitudes. The controller proactively adjusts voltage levels based on altitude signals, preventing the harmful effect of partial discharge before it can degrade the insulation, thus maintaining reliability without excessive insulation weight.
3Power
If constant high voltage is maintained to ensure power delivery, then power availability improves, but partial discharge occurs at high altitudes leading to premature insulation failure
Solution Approach 1:
The system dynamically adjusts voltage based on real-time altitude information, maintaining high voltage for optimal power delivery at low altitudes while automatically reducing voltage at high altitudes to prevent partial discharge. This dynamic control ensures both power availability and insulation lifetime are optimized across the entire operational altitude range.
Solution Approach 2:
The controller receives feedback about altitude and uses this information to adjust voltage levels accordingly. This feedback mechanism ensures that voltage is maintained at levels that provide adequate power delivery while staying below the partial discharge inception voltage threshold at high altitudes, thereby preventing insulation failure and extending system lifetime.
Data Source
AI summary
A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.