Helicopter Wing Dihedral Anhedral Profile Segmentation
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Solution Overview
Problem
Attack helicopters face challenges in maintaining aerodynamic efficiency and stability while carrying ammunition and payloads, particularly due to the drag caused by ammunition-loaded wings, which affects their forward flight speed and hovering capabilities at high weight densities.
Innovation Solution
The design incorporates wings with a dihedral and anhedral angle configuration, varying hump ratios, and a bent-form profile, along with a horizontal tail for enhanced stability and aerodynamic interaction, allowing for efficient air flow and reduced drag, enabling higher forward flight speeds and fuel efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the wing carries ammunition and payloads, then the helicopter can perform military operations, but the aerodynamic drag increases and forward flight speed decreases
Solution Approach 1:
The wing is divided into three distinct regions (root region, bending region, tip region) with different profile cross-sections optimized for their specific functions. The root region handles structural support and ammunition carriage, the bending region manages aerodynamic flow transitions, and the tip region optimizes payload carriage with reduced drag, collectively resolving the contradiction between carrying loads and maintaining speed.
Solution Approach 2:
Each region of the wing is assigned a specific profile cross-section tailored to its functional requirements. The root region uses a profile suitable for structural strength and ammunition carriage, while the tip region uses a profile optimized for reduced drag and payload carriage. This local optimization allows the wing to simultaneously carry ammunition and maintain forward flight speed.
2Adaptability or versatility
If the wing carries ammunition and payloads, then the helicopter can perform military operations, but the aerodynamic drag increases and hovering performance at high weight deteriorates
Solution Approach 1:
The wing is segmented into three regions with different profile cross-sections that collectively reduce the overall aerodynamic drag on the ammunition-loaded wing. This segmentation allows the helicopter to maintain hovering performance at high weights by minimizing the drag penalty associated with carrying ammunition and payloads.
Solution Approach 2:
The profile cross-section parameters are varied across different wing regions to optimize aerodynamic efficiency. By changing the profile characteristics (such as airfoil shape, camber, and thickness ratio) in each region, the design reduces the aerodynamic drag coefficient, thereby improving hovering performance at high weights while maintaining military operation capability.
3Ease of manufacture
If the wing uses a simple profile, then the manufacturing is easier, but the aerodynamic interaction with the horizontal tail is insufficient
Solution Approach 1:
The wing is segmented into three regions, each with a specifically designed profile cross-section that optimizes aerodynamic interaction with the horizontal tail. This segmentation allows for tailored profile designs in each region that enhance aerodynamic stability while remaining manufacturable, resolving the contradiction between manufacturing simplicity and aerodynamic interaction quality.
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 enhances the helicopter's forward flight speed, improves hovering performance at high weights, and reduces fuel consumption by optimizing aerodynamic interactions between the rotor, wing, and horizontal tail, ensuring safe separation of ammunition and improved stability.
Implementation Method 1
a rotor (R) generating the aerodynamic lift and thrust required for the body (2) to take off
Implementation Method 2
The profile cross-sections of the root region, tip region and bending region on the wing are all different from each other. The helicopter's wing design provides control and enhanced stability in the aerodynamic interaction of ammunition with the horizontal tail by narrowing the low-pressure wake flow region created behind the wing.
Implementation Method 3
a horizontal tail (6) positioned on the tail (4) cone on the body (2), extending outward from the body (2); and providing stability to the flight characteristics of the body (2)
Data Source
AI summary
A helicopter has a body exposed to air flow, at least one wing provided on the body, extending outward from the body and enabling ammunition and similar payloads to be placed thereto, a rotor generating the aerodynamic lift and/or thrust required for the body to take off, a tail provided on the body, extending outward from the body and providing balance during the movement of the body.