Aircraft Hatch Locking Device with Eccentric Adjustment Bush
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Solution Overview
Problem
Aircraft and spacecraft hatches face challenges in securely locking and aligning under varying loads, particularly due to high tensile forces and load differences that can cause deformations and misalignment of locking elements.
Innovation Solution
A hatch locking device featuring a drivable spindle drive and adjustment bush assemblies with eccentric bushes, providing a positive-locking connection in multiple directions and allowing for self-centering and torque transmission, thereby compensating for manufacturing tolerances and load-induced misalignments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a multiple of hooks swivel mounted on a shaft are used to transfer loads, then the hatch can transfer peripheral loads to the fuselage cell structure, but high tensile forces and load differences cause deformations and deflections that impair the correct orientation of the hatch locking elements
Solution Approach 1:
The invention employs adjustable locking elements that can dynamically adapt their position to compensate for deformations and deflections. The locking elements are designed to be adjustable in at least one degree of freedom, allowing them to self-align with the fuselage cell structure even when manufacturing tolerances or load-induced deformations occur. This dynamic adjustment capability resolves the contradiction by maintaining orientation precision despite varying load conditions.
Solution Approach 2:
The locking elements incorporate adjustable parameters such as position, orientation, or shape that can be modified to compensate for deformations. By changing these parameters in response to detected misalignment or deformation, the system maintains correct locking element orientation while continuing to transfer peripheral loads effectively.
2Reliability
If a positive-locking connection is provided in multiple directions, then the hatch locking device can transmit forces and torques under flight loads, but the device complexity increases with multiple adjustment bush assemblies and eccentric bushes
Solution Approach 1:
The locking elements are designed to perform multiple functions simultaneously: they provide positive-locking connection in multiple directions, transmit forces and torques, and compensate for misalignments. By making each locking element multi-functional, the system achieves high reliability under varying loads without proportionally increasing the number of separate components.
Solution Approach 2:
The invention combines multiple functions into integrated components. The adjustment bush assembly with eccentric bushes merges the functions of position adjustment, orientation correction, and load transmission into a single integrated mechanism. This consolidation achieves reliable multi-directional locking while minimizing the overall number of separate components.
3Manufacturing precision
If adjustable bush assemblies with eccentric bushes are used to compensate for manufacturing tolerances, then self-centering of the hatch and locking bolt is possible, but the device complexity and manufacturing difficulty increase
Solution Approach 1:
The eccentric bush mechanism is designed to automatically self-center the hatch and locking bolt during the closing and locking sequence without requiring external adjustment or complex control systems. The geometric properties of the eccentric bush inherently provide the self-centering action, simplifying both the control system and the manufacturing process compared to actively controlled adjustment 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 solution ensures reliable locking and alignment of aircraft and spacecraft hatches under different load conditions, maintaining a secure connection and withstanding high forces and torques, while also accommodating manufacturing tolerances.
Implementation Method 1
a drivable spindle drive (101) which extends in a longitudinal axis (X) and is fixed in relation to a hatch frame (11) of the aircraft or spacecraft hatch (10) along the longitudinal axis (X)... at least one locking bolt (102) which is driven by the drivable spindle drive (101) and is guided along the longitudinal axis (X)
Implementation Method 2
at least one adjustment bush assembly (110) being mounted on a fuselage frame (1)... a first eccentric bush (111) having a bolt receptacle (112) which is oriented centrally along the longitudinal axis (X) for receiving the at least one locking bolt (102)
Data Source
Figure 1
Figure 2~3
Figure 4A~4B
AI summary
The present invention provides a hatch locking device (100) for an aircraft or spacecraft hatch (10), comprising: a drivable spindle drive (101) which extends in a longitudinal axis (X) and is fixed in relation to a hatch frame (11) of the aircraft or spacecraft hatch (10) along the longitudinal axis (X); at least one locking bolt (102) which is driven by the drivable spindle drive (101) and is guided along the longitudinal axis (X); and at least one adjustment bush assembly (110) being mounted on a fuselage frame (1) and comprising a first eccentric bush (111) having a bolt receptacle (112) which is oriented centrally along the longitudinal axis (X) for receiving the at least one locking bolt (102) such that the hatch locking device (100) is positive-locking connectable in two axles (Y, Z) both being perpendicular to the longitudinal axis (X). Further the present invention provides an aircraft or spacecraft hatch (10) comprising such hatch locking device (100) as well as an aircraft (A) comprising such aircraft or spacecraft hatch (10).