Aircraft Control Surface Anti-Flutter Balance Weight Design
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Solution Overview
Problem
Existing anti-flutter balance weight installations for aircraft control surfaces result in significant aerodynamic drag and weight penalties, with limited flexibility in placement and maintenance due to geometrical and ergonomic constraints.
Innovation Solution
A control surface design featuring a balance weight installed ahead of the leading edge, with a portion in contact and a portion not in contact with the leading edge, allowing the balance weight to be fully enclosed within the trailing edge during movement, thus minimizing aerodynamic drag and facilitating easy replacement and interchangeability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If balance weight is installed ahead of the hinge line in a horn-shape housing on the leading edge, then anti-flutter balance is achieved, but aerodynamic drag increases significantly
Solution Approach 1:
The balance weight is nested within the trailing edge of the stabilizer, specifically housed in a recess or cavity formed by the stabilizer's structure. This nesting approach allows the balance weight to be enclosed within the trailing edge during movement, minimizing its exposure to airflow and reducing aerodynamic drag while maintaining its anti-flutter function.
Solution Approach 2:
The balance weight is positioned in a different spatial dimension relative to the control surface - specifically ahead of the leading edge but enclosed within the trailing edge's envelope. This dimensional repositioning allows the balance weight to be out of the direct airflow path while maintaining its moment arm for flutter prevention.
2Reliability
If balance weight is installed in traditional locations, then anti-flutter balance is achieved, but weight and mass impact increase
Solution Approach 1:
The balance weight is designed with optimized parameters including reduced mass compared to traditional solutions, and strategically positioned to achieve the required moment for flutter prevention with minimal weight. The weight is distributed to optimize the center of gravity position while minimizing overall mass impact on the aircraft.
3Reliability
If balance weight is installed in traditional locations, then anti-flutter balance is achieved, but flexibility for maintenance and replacement is reduced
Solution Approach 1:
The balance weight is designed as a separate, modular component that can be independently removed and replaced without affecting the main control surface or stabilizer structure. This segmentation allows for easy maintenance and replacement operations.
Solution Approach 2:
A access pathway or service hole is provided in the stabilizer structure that allows the balance weight to be accessed and removed from the front side without requiring disassembly of the entire control surface assembly. This preliminary preparation of access pathways facilitates easy maintenance operations.
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
This design effectively prevents flutter without increasing aerodynamic drag, reduces weight compared to traditional solutions, and allows for easy maintenance and interchangeability of control surfaces across different aircraft types.
Implementation Method 1
Flutter is a phenomenon caused by aerodynamic forces which can damage elastic structures such as aircraft, bridges or buildings, for example. Flutter in aircraft causes oscillations in stabilizers and wings.
Implementation Method 2
a balance weight completely installed ahead of and adjacent to the most frontal portion of the leading edge
Data Source
AI summary
A leading edge (3) of a control surface (1) for an aircraft includes a balance weight (6) attached to the forward-most region of the leading edge (3). The control surface (1) rotates with respect to the stabilizer (2) around a hinge line (5). The balance weight (6) is ahead of and adjacent to the most frontal portion (7) of the leading edge (3) of the control surface (1) are is inside the trailing edge of the stabilizer (2). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.