eVTOL Tilt Joint Latch for Actuator Disconnect Fail-Safe
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Solution Overview
Problem
VTOL aircraft face catastrophic failure risks due to uncontrolled movement of tiltable components like proprotors and control surfaces when actuator shafts break, necessitating redundant or overdesigned components that increase weight and cost.
Innovation Solution
Joint assemblies with fail-safe latches that automatically latch to prevent uncontrolled rotation of tiltable components in case of actuator disconnection, eliminating the need for redundancy and overdesign.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant components are introduced to prevent catastrophic failure, then reliability is improved, but weight increases
Solution Approach 1:
The fail-safe latch is pre-configured in a normal position during operation, allowing free movement of the tiltable component. Upon actuator disconnection, the latch automatically transitions to a latched position, preventing uncontrolled movement. This preliminary configuration eliminates the need for redundant components while maintaining safety.
Solution Approach 2:
The fail-safe latch mechanism automatically detects actuator disconnection and activates without external intervention. The latch uses spring biasing to self-engage when the actuator connecting portion separates, preventing catastrophic failure without requiring additional redundant systems.
2Reliability
If overdesigned components are used to prevent catastrophic failure, then reliability is improved, but manufacturing cost increases
Solution Approach 1:
The latch mechanism is designed with a normal operating position where it does not interfere with component movement, and a failure position where it automatically engages to prevent catastrophic failure. This preliminary design approach provides safety without requiring overdesign of the main actuator components.
Solution Approach 2:
The fail-safe latch acts as an intermediary safety device between the actuator and the tiltable component. It provides failure prevention through a separate, simpler mechanism rather than requiring the main actuator components to be overdesigned for failure scenarios.
3Device complexity
If simple latch mechanisms are used, then device complexity is reduced, but reliability may be compromised
Solution Approach 1:
The latch mechanism automatically detects actuator disconnection through the separation of the connecting portion and self-activates to prevent catastrophic failure. The spring-biased design ensures automatic engagement without requiring external sensors, control systems, or complex monitoring mechanisms.
Solution Approach 2:
The fail-safe function is extracted as a separate, dedicated latch mechanism rather than being integrated into the main actuator system. This separation allows the latch to be a simple, reliable component that focuses solely on failure prevention without adding complexity to the primary actuation system.
Data Source
AI summary
A joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.