Movable Wing Longitudinal Shift for Aircraft Balance
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Solution Overview
Problem
Existing aircraft designs face challenges in maintaining precise longitudinal balance due to variable center of gravity and aerodynamic focus positions, which complicates fuel system management and limits the reduction of fin dimensions, leading to increased aerodynamic drag and reduced performance.
Innovation Solution
The aircraft features a movable wing structure that slides longitudinally along the fuselage, allowing precise adjustment of the center of gravity relative to the aerodynamic lift forces without tail assemblies, using a central wing box and parallel beams for structural strength and guidance, reducing the need for large horizontal stabilizers and minimizing aerodynamic drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If fuel transfer systems are used to displace the center of gravity, then longitudinal balance control is improved, but device complexity and fuel system requirements increase
Solution Approach 1:
The wing is made movable relative to the fuselage along the longitudinal axis, allowing dynamic adjustment of the aircraft's center of gravity position. This dynamic configuration enables precise control of longitudinal balance without requiring complex fuel transfer systems, as the wing position can be adjusted directly to compensate for varying center of gravity locations.
2Stability of the object's composition
If horizontal stabilizers are made larger to ensure longitudinal stability, then stability is improved, but aerodynamic drag increases
Solution Approach 1:
By making the wing movable along the longitudinal axis, the system can dynamically adjust the position of aerodynamic forces relative to the center of gravity. This eliminates the need for large horizontal stabilizers to provide longitudinal stability, as the wing position can be optimized to maintain balance, thereby reducing aerodynamic drag from larger stabilizer surfaces.
Solution Approach 2:
The invention changes the position parameter of the wing along the longitudinal axis to optimize the relationship between the center of gravity and aerodynamic foci. By adjusting this positional parameter, the system achieves longitudinal stability with smaller horizontal stabilizers, reducing the harmful aerodynamic drag that would otherwise require larger stabilizer surfaces.
3Device complexity
If the wing position is fixed relative to the fuselage, then structural simplicity is maintained, but precise control of center of gravity and aerodynamic balance is limited
Solution Approach 1:
The wing is equipped with movable mounting that allows it to be repositioned along the longitudinal axis of the fuselage. This dynamic capability enables precise control and positioning of the center of gravity relative to aerodynamic foci, while the overall structure remains relatively simple by utilizing the existing wing box and fuselage structure for the movable connection.
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 solution enables precise control of the center of gravity and lift forces, reducing the size of horizontal stabilizers, minimizing aerodynamic drag, and enhancing flight stability and performance by allowing optimal positioning of the wing relative to the fuselage, thereby improving dynamic stability and reducing fuel consumption.
Implementation Method 1
The wing (3) is mounted to be movable in translation relative to the fuselage (2) along a longitudinal X direction of the aircraft essentially parallel to an axis of said fuselage
Data Source
AI summary
An aircraft has a fuselage a wing integral with the fuselage at a point on a rigid central wing box. Sections of the wing are located on sides of the central wing box and integral and fixed relative to the wing box to form a rigid wing. The wing is mounted movably in translation relative to the fuselage along a longitudinal direction of the aircraft parallel to an axis of the fuselage between an extreme forward position and an extreme rear position of a point of reference of the wing. The central wing box is determined in the front by a wing box front spar, in the rear by a wing box rear spar, and laterally by root ribs. Sections of the wing include external front and external rear spars integral with and fixed relative to the wing box front spars and wing box rear spars to form the rigid wing.