Hydraulic Sync Shaft Lock for Lightweight Thrust Reversers
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Solution Overview
Problem
Existing aircraft thrust reverser locking systems are heavy, mechanically complex, and require additional hydraulic control lines, making them unsuitable for newer aircraft designs and posing risks of accidental deployment during flight or ground maintenance.
Innovation Solution
A thrust reverser synchronization shaft lock system using a rotatable shaft with radial prongs, a hydraulic lock assembly, and an electric lock assembly, which replaces traditional two-piece jaw mechanisms with a simpler rotary design, eliminating the need for dedicated hydraulic lines and reducing weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional rotating jaw locking mechanisms are used, then reliable locking function is achieved, but device complexity and weight increase
Solution Approach 1:
The patent replaces the traditional mechanical rotating jaw locking mechanism with a hydraulic actuation system. The hydraulic lock assembly uses hydraulic pressure to move a piston rod that engages with or disengages from the radial prong, substituting complex mechanical rotation with simpler hydraulic linear motion. This reduces mechanical complexity while maintaining the locking function.
Solution Approach 2:
The patent extracts and eliminates unnecessary mechanical components from the traditional locking system. By removing the rotating jaw mechanism and its associated mechanical linkages, the design achieves weight reduction and simplified structure while the hydraulic system provides the essential locking and unlocking functions.
2Reliability
If traditional hydraulic lock designs with dedicated hydraulic control lines are used, then locking function is achieved, but adaptability to newer aircraft designs is reduced
Solution Approach 1:
The patent makes the hydraulic lock assembly compatible with existing aircraft hydraulic systems by using standard hydraulic pressure sources already present on the aircraft. The lock assembly can be actuated by the same hydraulic system used for thrust reverser operation, eliminating the need for dedicated control lines and enabling installation on newer aircraft designs that lack additional hydraulic infrastructure.
Solution Approach 2:
The patent designs the hydraulic lock assembly to dynamically respond to hydraulic pressure changes from existing aircraft systems. The piston rod moves in response to hydraulic pressure applied through existing lines, allowing the locking mechanism to adapt to the dynamic operational states of modern aircraft hydraulic systems without requiring dedicated control infrastructure.
3Reliability
If traditional locking mechanisms are used, then safety against accidental deployment is achieved, but weight increases
Solution Approach 1:
The patent replaces heavy mechanical locking components with a lighter hydraulic actuation system. The hydraulic lock assembly uses fluid pressure to actuate the piston rod, eliminating the need for heavy mechanical springs, levers, and rotating components while maintaining the safety function of preventing accidental deployment.
Solution Approach 2:
The patent changes the operating parameter from mechanical force to hydraulic pressure. By using hydraulic pressure to actuate the locking mechanism, the system achieves the same safety function with reduced weight, as hydraulic systems can generate high forces with compact, lightweight components compared to traditional mechanical spring-loaded or lever-based mechanisms.
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 reliable locking and unlocking mechanisms, preventing unintentional thrust reverser activation, while being lighter and more reliable than existing designs, and compatible with aircraft lacking hydraulic control lines.
Implementation Method 1
a hydraulic lock assembly that includes a housing having a tubular inner wall defining a chamber, a piston head configured to contact the tubular inner wall... The first fluid chamber can be configured to be in fluid communication with a thrust reverser stowage fluid pressure source
Implementation Method 2
a bias member configured to urge the first piston rod end into engagement with the radial prong to selectably prohibit rotation of the shaft
Implementation Method 3
an electric actuator configured to controllably extend and retract the lock pin in and out of engagement with the lock recess
Data Source
AI summary
The subject matter of this specification can be embodied in, among other things, a thrust reverser synchronization shaft lock system includes a rotatable shaft comprising at least one radial prong extending radially from the shaft, a hydraulic lock assembly that includes a housing, a piston head having a lock recess, a piston rod extending radially away from the shaft and configured to be urged by the piston head to move the first piston rod end out of engagement with the radial prong to selectably permit rotation of the shaft, and a bias member configured to urge the first piston rod end into engagement with the radial prong, and an electric lock assembly that includes a lock pin and an electric actuator configured to controllably extend and retract the lock pin in and out of engagement with the lock recess.