Redundant Hydraulic Latching Bolt for Foldable Aircraft Wing
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Solution Overview
Problem
Existing aircraft wing designs face challenges in efficiently increasing wingspan for improved fuel efficiency without requiring infrastructure adaptations or incurring higher airport fees, necessitating a reliable and simple foldable wing latching mechanism.
Innovation Solution
A latching device with a support structure, hydraulic actuators, and a biasing arrangement that allows the wing tip section to pivot between deployed and stowed positions, using a latching bolt that can be extended or retracted to secure the wing in place, with redundancy provided by separate hydraulic systems and locking mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If a foldable wing construction is provided to increase wingspan without infrastructure adaptation, then wingspan is increased and fuel efficiency is improved, but the complexity of the latching device increases to ensure safe retention in deployed and stowed positions
Solution Approach 1:
The patent employs hydraulic actuators to provide the force necessary for extending and retracting the latch pin, enabling reliable engagement and disengagement of the foldable wing section. The hydraulic system provides controlled, high-force actuation required for safely securing the wing in deployed position or allowing it to fold to stowed position, resolving the complexity issue by using aĉç, reliable actuation mechanism.
2Reliability
If a hydraulic actuator system is used to move the latch pin between extended and retracted positions, then the latching device becomes more reliable in operation, but the device complexity and number of components increase
Solution Approach 1:
The hydraulic actuator serves multiple functions: it provides the force to extend the latch pin for secure engagement, retract the latch pin for disengagement, and can be controlled to maintain latch pin position. This multi-functionality reduces the need for separate mechanisms for each operation, thereby improving reliability while limiting the increase in overall system complexity.
3Reliability
If separate hydraulic systems with redundancy are provided for the latching device, then safety and reliability are improved, but the device complexity and weight increase
Solution Approach 1:
The patent implements redundancy locally within the hydraulic actuator system rather than throughout the entire latching device. The hydraulic actuator is designed with internal redundancy or dual hydraulic circuits that provide backup capability specifically for the critical latching function, while other parts of the latching device maintain minimal weight design. This localized approach to redundancy improves safety without proportionally increasing overall weight.
Data Source
Figure 1a
Figure 1b
Figure 2a~2b
AI summary
The present invention relates to a latching device for a wing arrangement (3) for an aircraft (1), which wing arrangement (3) includes a wing (9) comprising a base section (11) and an outboard tip section (13) connected base section (11) to be pivotable between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position. The latching device (27) comprises a support structure (29), a latching bolt (35) having a longitudinal axis (36) and being slidably supported by the support structure (29) such that the latching bolt (35) is movable between a retracted position and an extended position. In the extended position the latching bolt (35) extends further from the support structure (29) than in the retracted position. The latching device (27) further comprises at least one first hydraulic actuator (47a) and at least one first connector assembly (38a) adapted to be connected to a first hydraulic system of an aircraft (1) and to supply the at least one first hydraulic actuator (47a) with pressurized hydraulic fluid, and at least one second hydraulic actuator (47b) and at least one second connector assembly (38b) adapted to be connected to a second hydraulic system of an aircraft (1) and to supply the at least one second hydraulic actuator (47b) with pressurized hydraulic fluid. The at least one first connector assembly (38a) is separated from the at least one second connector assembly (38b). The at least one first hydraulic actuator (47a) and the at least one second hydraulic actuator (47b) are adapted to effect movement of the latching bolt (35) from the extended position into the retracted position independent of the other one of the at least one first hydraulic actuator (47a) and the at least one second hydraulic actuator (47b).