Backup Thrust Reverser Control for Safer Aircraft Landings
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Summary
Problems
Thrust reverser actuation systems in aircraft are prone to failure during landing, leading to potential catastrophic consequences due to uncontrolled acceleration and impact with end stops, necessitating a reliable backup power system to ensure safe and controlled power down.
Innovation solutions
A backup power supply and motor control system architecture that includes a rectifier, DC link capacitor, brake control switch, and inverters to provide a fail-safe mechanism for the electric motor, ensuring controlled power down and reduced weight and cost.
TRIZ Analysis
Specific contradictions:
General conflict description:
Principle concept:
If a backup power supply system is added to ensure safe power down, then system reliability is improved, but device complexity increases
Why choose this principle:
The backup power supply utilizes the existing rectifier and DC link capacitor from the main power system, merging these components into a shared architecture. This allows the backup system to derive power from the rectifier's DC supply without requiring separate power conversion equipment, thereby improving reliability while minimizing additional complexity
Principle concept:
If a backup power supply system is added to ensure safe power down, then system reliability is improved, but device complexity increases
Why choose this principle:
The rectifier and DC link capacitor serve dual functions: they power the main electric motor during normal operation and simultaneously serve as the power source for the backup system when AC power fails. This multi-functionality reduces the need for dedicated backup components, addressing the contradiction between reliability and complexity
Application Domain
Data Source
AI summary:
A backup power supply and motor control system architecture that includes a rectifier, DC link capacitor, brake control switch, and inverters to provide a fail-safe mechanism for the electric motor, ensuring controlled power down and reduced weight and cost.
Abstract
A system architecture for a backup thrust reverser actuation system control is provided. The system architecture includes an AC power supply of an aircraft, a power supply and a motor control adapted to control an electric motor (M) of a thrust reverser actuation system. The system architecture further includes a backup power supply adapted to provide power to the electric motor in the event that the power supply fails.