Aircraft Hatch Locking Mechanism with Conical Bolt
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Solution Overview
Problem
Aircraft or spacecraft hatches face challenges in securely locking and aligning under varying loads, particularly due to high tensile forces and load differences, which can cause deformations and misalignments, impairing the correct operation of hatch locking elements.
Innovation Solution
The implementation of a hatch locking device with a drivable spindle drive, a pull-in device, and a drive unit that assists in closing the hatch, allowing for force transmission in multiple directions and torque, while compensating for manufacturing tolerances and misalignments through eccentric bush assemblies and a conical shape, ensuring secure locking and self-centering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional hatch locking device is used, then the structure is simple, but it cannot compensate for misalignments and deformations under varying loads
Solution Approach 1:
The patent employs a conical locking bolt that can dynamically adjust its orientation and position during the locking process. The conical shape allows the bolt to self-align and compensate for misalignments between the hatch and fuselage frame under varying loads, transforming a static locking mechanism into a dynamic one that adapts to dimensional changes.
Solution Approach 2:
The conical geometry of the locking bolt introduces a parameter change in the form of variable angular orientation. As the bolt is driven into the conical receptacle, its angle of insertion changes, allowing it to accommodate misalignments and deformations caused by load variations, thereby compensating for dimensional tolerances without requiring complex adjustment mechanisms.
2Force
If high tensile forces act on large aircraft doors, then the locking force is sufficient, but deformations occur in the region of the hatch gaps which impair correct orientation of locking elements
Solution Approach 1:
The pull-in device performs a preliminary action by forcing the hatch into correct alignment and closure before the locking bolt is engaged. This preliminary positioning ensures that the locking elements are correctly oriented relative to each other before the high locking forces are applied, preventing deformations that would impair locking accuracy.
Solution Approach 2:
The conical receptacle acts as an intermediary element between the locking bolt and the fuselage frame. It provides a self-aligning interface that accommodates misalignments and maintains correct orientation of the locking elements even under high tensile forces, mediating between the rigid structural components and the variable loading conditions.
3Reliability
If a pull-in device is added to assist closing the hatch, then complete closure is achieved, but the device complexity increases
Solution Approach 1:
The patent merges the pull-in function and the locking function into a single integrated mechanism. The same drivable spindle drive that actuates the locking bolt also operates the pull-in device through a mechanically coupled drive system, combining two functions into one unified system driven by a single motor, thereby reducing overall complexity while ensuring complete closure.
Solution Approach 2:
The drivable spindle drive serves multiple functions: it directly drives the locking bolt for securing the hatch and simultaneously drives the pull-in device for forcing complete closure. This multi-functional design eliminates the need for separate actuators, reducing the number of components while achieving both complete closure and secure locking.
Data Source
Figure 1A~1B
Figure 1C~1D
Figure 2~3
AI summary
The present invention provides an air- or spacecraft hatch (10), comprising: a hatch frame (11); a hatch locking device (100) being mounted to the hatch frame (11) and comprising a drivable spindle drive (101) that drives at least one locking bolt (102) of the hatch locking device (100); a pull-in device (14) for forcing the air- or spacecraft hatch (10) to close being arranged at a lateral side of the air- or spacecraft hatch (10); and a drive unit (12) being mounted to the hatch frame (11) and simultaneously driving the drivable spindle drive (101) and the pull-in device (14). Further, the present invention provides an aircraft (A) comprising such an air- or spacecraft hatch (10).