Spanwise Slat Actuation Using a Bell-Crank in Thin Wings
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Solution Overview
Problem
As aircraft wings become thinner to reduce drag, it becomes challenging to accommodate linear hydraulic slat actuators, leading to limited actuator displacement and the need for penetrations in the front spar web.
Innovation Solution
A spanwise-oriented linear hydraulic slat actuator utilizing a bell-crank mechanism to achieve variable output displacement, allowing the actuator to be oriented along the aircraft wing while bypassing the need for front spar web penetration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If the aircraft wing is made thinner to reduce drag, then drag is decreased, but it becomes difficult to accommodate linear hydraulic slat actuators and their displacement is limited
Solution Approach 1:
The patent reorients the linear hydraulic slat actuator from a chordwise orientation to a spanwise orientation along the aircraft wing. This dimensional change allows the actuator to utilize the spanwise space within the thinner wing structure, achieving sufficient displacement without requiring chordwise penetration of the front spar web.
2Length of moving object
If the linear hydraulic slat actuator is oriented spanwise along the aircraft wing, then greater displacement is achieved within the wing architecture, but the actuator mechanism becomes more complex
Solution Approach 1:
The patent introduces a bell-crank mechanism as an intermediary between the spanwise-oriented linear hydraulic slat actuator and the slat. The bell-crank converts the spanwise movement of the actuator into chordwise movement of the slat, enabling the actuator to achieve greater displacement while maintaining a relatively simple hydraulic actuator design.
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 enables greater displacement of the slat within the aircraft wing architecture while occupying less space, allowing for more efficient packaging and operation of the slat actuator.
Implementation Method 1
linear hydraulic slat actuator
Implementation Method 2
bell-crank is coupled to the linear hydraulic slat actuator and to the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell-crank is configured to move the actuator output link in a different direction
Data Source
Figure 1
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Figure 3
AI summary
An aircraft wing (700) includes a fixed structure (102) and a linear hydraulic slat actuator (104) attached to the fixed structure (102). The linear hydraulic slat actuator (104) is oriented spanwise along the aircraft wing (700). The aircraft wing (700) also includes an actuator output link (108) and a slat (710) attached to the actuator output link (108). The aircraft wing (700) also includes a bell-crank (106) coupled to the linear hydraulic slat actuator (104) and to the actuator output link (108). In response to spanwise movement of the linear hydraulic slat actuator (104), the bell-crank (106) is configured to move the actuator output link (108) in a different direction that enables the slat (710) to move between a retracted position and an extended position.