Airplane Suspension Fairing with Curved Vertical Section
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing airplane suspension fairing structures with wing-mounted arrangements face challenges in maintaining aerodynamic performance when mounting engines close to the wing, as they either increase landing gear length, reduce flight performance, or obstruct engine flow, leading to disturbances on the wing's upper surface and reduced lift force.
Innovation Solution
The fairing structure features an S-shaped vertical section line that rises to a maximum height above the wing, then descends and extends below the leading edge, ensuring necessary inner space without increasing landing gear length or width, thus avoiding disturbances to the wing's upper surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the suspension extends to the position above the wing to ensure inner space, then the inner space requirement is met, but the flight performance is reduced due to flow separation and disturbance to the wing's upper surface
Solution Approach 1:
The fairing structure transitions from a straight extension to a curved path that moves in multiple dimensions - rising above the wing at the leading edge, then curving downward to end below the wing at the trailing edge. This dimensional change allows the suspension to maintain adequate inner space while avoiding continuous contact with the wing's upper surface, thereby preserving flight performance.
Solution Approach 2:
The fairing structure employs curved surfaces and smooth transitions instead of straight lines and sharp angles. The vertical section line follows a curved path that rises and then descends gracefully, creating an aerodynamically fair surface that reduces flow separation and disturbance to the wing while maintaining the necessary inner space for suspension components.
2Volume of moving object
If the distance between the engine and the leading edge of the wing is increased to ensure inner space, then the inner space is increased, but the landing gear length is increased, which increases weight and fuel consumption
Solution Approach 1:
Instead of increasing the longitudinal distance between the engine and wing leading edge, the fairing structure utilizes the vertical dimension by extending above and then curving below the wing. This allows adequate inner space to be achieved without increasing the horizontal span, thereby avoiding the need for longer and heavier landing gear.
3Volume of moving object
If the width of the suspension is increased to ensure inner space, then the inner space is increased, but the area of the cross section of the flow-out channel of the engine is reduced, which blocks engine flow and reduces thrust
Solution Approach 1:
The fairing structure achieves adequate inner space by utilizing the vertical dimension rather than increasing the lateral width. The curved fairing extends above and then below the wing in the vertical direction, providing necessary space for suspension components without encroaching on the engine's lateral flow channels, thereby preserving engine thrust.
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 maintains aerodynamic performance by reducing disturbances to the wing, avoiding the need for additional weight or devices, and ensuring efficient engine thrust while providing sufficient space for suspension components.
Implementation Method 1
the suspension will cause a flow separation on the upper surface of the wing in the case of small angle of attack so that the drag force is increased
Data Source
Figure 1~2
Figure 3~5
AI summary
Provided is an airplane suspension (20) fairing structure with a wing-mounted arrangement, the fairing structure comprising a front fairing located in front of the leading edge (31) of a wing and a rear fairing located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front fairing is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front fairing of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the fairing aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.