Adjustable Asymmetrical Wing Profile for Smoother Rotor Loads
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Solution Overview
Problem
Existing rotor blades in rotary-wing vehicles and wind/water turbines experience abrupt load changes and dynamic stresses due to symmetrical or asymmetrical wing profiles, leading to inefficiencies and structural instability, particularly in helicopters and vertical-axis wind turbines.
Innovation Solution
An asymmetrical wing profile with a three-part design and an adjusting device using electric or electromechanical mechanisms allows simultaneous turning of front and rear wing segments, enabling a variable suction side and controlled angle of attack, reducing abrupt load changes and enhancing lift and thrust generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a symmetrical or asymmetrical wing profile is used in rotor blades, then the rotor blades can generate lift and thrust, but they experience abrupt load changes and dynamic stresses during rotation
Solution Approach 1:
The patent applies the dynamics principle by making the wing profile adjustable during rotation. The rotor blade transitions from a fixed symmetric profile to a variable asymmetric profile through an adjusting mechanism that changes the angle of attack and camber dynamically. This allows the blade to adapt its aerodynamic characteristics continuously during rotation, smoothing out load variations and reducing dynamic stresses while maintaining effective lift and thrust generation.
Solution Approach 2:
The patent implements parameter changes by varying the geometric parameters of the wing profile (angle of attack, camber, and asymmetry ratio) during rotation. The adjusting mechanism modifies these parameters based on the rotational position and operational conditions, enabling the rotor blade to optimize its aerodynamic performance at different phases of rotation and reduce abrupt load changes.
2Speed
If a fixed-wing aircraft design is used, then the aircraft achieves higher speeds and better fuel efficiency, but it requires a landing and take-off runway and lacks vertical flight capability
Solution Approach 1:
The patent applies the universality principle by designing a rotor blade that can function in multiple flight modes. The adjustable asymmetric wing profile enables the rotor blade to generate both vertical lift for hover and forward thrust for high-speed flight. The same blade structure adapts its aerodynamic characteristics to perform different functions, combining the vertical flight capability of helicopters with the speed potential of fixed-wing aircraft.
Solution Approach 2:
The patent uses dynamics by enabling the rotor blade to transition between different aerodynamic regimes. Through continuous adjustment of the wing profile parameters during rotation, the blade can optimize for vertical lift generation during hover or for forward thrust during high-speed flight, providing versatility across different flight conditions without requiring separate systems.
3Adaptability or versatility
If a helicopter with swashplate control is used, then vertical flight and hover capability are achieved, but the aircraft experiences strong vibrations and limited forward speed
Solution Approach 1:
The patent applies dynamics by replacing the discrete swashplate adjustment mechanism with a continuous dynamic adjustment system. The asymmetric wing profile adjusts continuously during rotation, allowing for smoother control and reduced vibrations. This dynamic adaptation enables the helicopter to maintain vertical flight and hover capability while achieving higher forward speeds by optimizing the blade aerodynamics throughout the rotation cycle.
Solution Approach 2:
The patent substitutes the traditional mechanical swashplate control system with an aerodynamic adjustment mechanism. Instead of using complex mechanical linkages to change blade angle, the system uses aerodynamic forces and adjustable wing profile geometry to achieve control, reducing mechanical vibrations and enabling higher speeds.
4Ease of operation
If a vertical axis wind turbine with symmetrical wing profile is used, then the turbine does not require alignment with wind direction, but it achieves lower energy capture efficiency
Solution Approach 1:
The patent applies dynamics by enabling the vertical axis turbine blades to dynamically adjust their asymmetric profile during rotation. The blades transition from a fixed symmetric profile to a variable asymmetric profile that optimizes energy capture at different rotational positions. This dynamic adjustment allows the turbine to maintain ease of operation without wind alignment while significantly improving energy capture efficiency through optimized aerodynamics.
Solution Approach 2:
The patent implements parameter changes by varying the wing profile parameters (asymmetry ratio, angle of attack, camber) during rotation. The adjusting mechanism modifies these parameters based on the rotational position to maximize the aerodynamic efficiency at each point in the rotation cycle, thereby increasing overall energy capture while maintaining the advantage of not requiring wind direction alignment.
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
The solution provides stable and efficient lift and thrust generation, reduces dynamic stresses, and increases energy capture efficiency in rotary-wing vehicles and turbines by optimizing wing profile alignment with incident flow direction.
Implementation Method 1
The adjusting device is designed to enable simultaneous turning in or out of the front and rear wing segments in opposite directions of rotation with the aid of the at least one electric motor
Implementation Method 2
Device with an asymmetrical wing profile and with an adjusting device influencing the lift on the device as a result of the incident flow of the asymmetrical wing profile
Data Source
AI summary
The invention relates to a device comprising an asymmetrical wing profile (2) and an adjusting device (15), which asymmetrical wing profile (2) has a profile thickness (q) and a profile chord (p) extending between a wing leading edge (n) and a wing trailing edge (e), which asymmetrical wing profile (2) has, in at least one longitudinal portion (L1-Ln), a three-part variable wing profile (21) in which a front and a rear wing segment (211, 213) are joined to a central wing segment (212) in an articulated manner by means of two hinges (214) having axes of rotation (z) and are designed to permit a rotational movement about the associated axis of rotation (z) with respect to the central wing segment (212).