Aircraft Control Surface Actuator Receptacle for Compact Integration
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Solution Overview
Problem
Existing aircraft control surfaces and actuators are not compact enough and require improvements for more efficient integration with aircraft structures, particularly in terms of size and weight reduction.
Innovation Solution
The assembly integrates linear actuators within the aircraft control surface, using actuator receptacles and mounts that are offset from the pivot axes, allowing for a more compact and lightweight design by embedding the actuation apparatuses within the control surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If linear actuators are integrated within the aircraft control surface, then the overall size and weight of the control surface assembly is reduced, but the structural complexity within the control surface increases
Solution Approach 1:
The linear actuator is nested within the control surface structure itself, with the actuator receptacle integrated into the control surface skin and support structure. This nesting arrangement eliminates the need for separate external actuator mounts and reduces overall assembly weight while containing the increased structural complexity within the existing control surface boundaries.
Solution Approach 2:
The actuator mount is merged with the control surface structure through the actuator receptacle and support structure integration. The receptacle extends between skin panels and connects to internal support ribs, combining what were previously separate components (actuator, mount, and control surface) into a unified integrated assembly that reduces total weight.
2Volume of moving object
If actuators are embedded within the control surface, then the control surface becomes more compact, but the manufacturing complexity increases
Solution Approach 1:
The control surface is segmented into distinct functional zones: the skin panels forming the external surface, the actuator receptacle providing a dedicated cavity for the linear actuator, and the support structure with internal ribs providing structural reinforcement. This segmentation allows each component to be manufactured and assembled separately before final integration, reducing overall manufacturing complexity despite the compact integrated design.
3Device complexity
If the actuator receptacle extends laterally between skin panels, then the actuator integration is simplified, but the control surface width increases
Solution Approach 1:
The actuator receptacle extends laterally between skin panels rather than only longitudinally, utilizing the width dimension of the control surface to accommodate the actuator. This dimensional approach allows the actuator to be integrated without significantly increasing the overall longitudinal length of the control surface, simplifying actuator mounting while maintaining a compact profile.
Data Source
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AI summary
An aircraft assembly (20) includes an aircraft control surface (24) having a first skin (50), a second skin (52) and a support structure laterally between and connected to the first skin (50) and the second skin (52). The support structure includes a spar (60C), a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface (24). The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface (24) to the spar (60C). An actuator receptacle projects longitudinally into the aircraft control surface (24) from a base (42) of the aircraft control surface (24) to the spar. The actuator receptacle extends spanwise within the aircraft control surface (24) between the first stiffener and the second stiffener.