Segmented Rotor Blades With Variable Airfoils for Stable High-Speed Flight
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Solution Overview
Problem
Rotary-wing vehicles face limitations in stability, speed, efficiency, and fuel consumption due to their rotary-wing kinematics, and existing technologies do not effectively utilize the thrust generated by variable asymmetric wing profiles for propulsion and direction control.
Innovation Solution
A rotary-wing vehicle with rotor blades subdivided into longitudinal sections, each equipped with actuators, allowing for adjustable asymmetric airfoils that change orientation during rotation, enabling thrust and lift generation in various directions, and incorporating a motor-generator system for efficient energy conversion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If traditional rotary-wing kinematics with fixed or simple adjustable rotor blades are used, then the vehicle can achieve vertical takeoff and hovering capability, but the maximum speed is limited to around 200-300 km/h due to aerodynamic imbalance between leading and trailing blades
Solution Approach 1:
The rotor blade is divided into multiple independent longitudinal sections (at least three sections per blade) that can be adjusted individually. This segmentation allows each section to be optimized for different phases of rotation, enabling the blade to maintain optimal aerodynamic characteristics throughout the entire rotation cycle, thereby increasing maximum speed while managing complexity through modular control
Solution Approach 2:
The rotor blade configuration is made dynamically adjustable during rotation, with each longitudinal section capable of independent pitch and roll adjustments. This dynamic adaptability allows the blade to compensate for aerodynamic imbalances between leading and trailing edges in real-time, enabling higher speeds without sacrificing stability
2Speed
If the swashplate and rotor plane are tilted to achieve straight and level flight, then forward speed can be maintained, but very strong vibrations are caused by the swashplate
Solution Approach 1:
The invention extracts and eliminates the swashplate component from the rotor control system. Instead of using a tilted swashplate to achieve forward flight, the system uses independent adjustment of rotor blade longitudinal sections to generate thrust in the desired direction, thereby removing the source of strong vibrations while maintaining forward speed capability
Solution Approach 2:
The complex mechanical swashplate linkage system is replaced with a more direct control mechanism where actuators adjust the pitch and roll of individual blade sections. This substitution eliminates the mechanical vibrations inherent in swashplate systems while achieving the same flight control objectives
3Speed
If the rotor blade speed is increased to exceed the speed of sound at the blade tips, then higher forward speed can be achieved, but aerodynamic disadvantages and unpleasant noise levels occur
Solution Approach 1:
The rotor blade operates with dynamic adjustment of each longitudinal section during rotation, allowing the blade to maintain optimal angle of attack and aerodynamic efficiency at lower rotational speeds. This dynamic control enables the blade to generate sufficient thrust without needing to rotate at speeds that would cause supersonic tip conditions, thereby reducing noise and aerodynamic penalties
4Adaptability or versatility
If variable asymmetric airfoil profiles are used for rotor blades, then thrust and lift can be generated in various directions, but the device complexity increases due to multiple actuators and control systems
Solution Approach 1:
The rotor blade is segmented into multiple longitudinal sections, each with its own actuators for pitch and roll control. This segmentation enables independent adjustment of each section to create variable asymmetric airfoil profiles, providing versatile thrust direction control while managing complexity through a modular, scalable architecture where each section can be controlled independently or in coordination with others
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 flight, high agility, reduced vibrations, and efficient energy conversion, allowing for vehicles that can switch between road and air travel, with improved speed and reduced fuel consumption.
Implementation Method 1
the variable, asymmetric airfoil of the rotor blade temporarily has a symmetric airfoil in a transition position and generates a lift force
Implementation Method 2
A rotary-wing vehicle with rotor blades subdivided into longitudinal sections, each equipped with actuators, allowing for adjustable asymmetric airfoils that change orientation during rotation, enabling thrust and lift generation in various directions, and incorporating a motor-generator system for efficient energy conversion
Data Source
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AI summary
The invention relates to an apparatus (11, 12) which is designed as a rotary-wing vehicle (11) or as a rotary-wing turbine (12). The apparatus (11, 12) has a rotor module (2) comprising a motor generator (13), rotor blades (1), and a rotary-wing kinematic system (10) for the rotor blades (1) connected to the motor generator. The rotor module (2) is designed to make it possible to rotate the rotor blades (1) in the same direction or in opposite directions with the directions of rotation (T, T) on a circular path (U) about an axis of rotation (t). The rotor blades (1) are each divided into a plurality of longitudinal sections (A1- An), each for receiving at least one actuator (20) integrated in a longitudinal member (21) or transverse member (22) of the rotor blade (1), and have a variable, asymmetrical aerofoil (201) which, in one revolution of the rotor blade (1) on a diameter of the circular path (U), said diameter being freely orientable within an adjustment range (ö) and having turning points (P, P'), can be adjusted in at least one longitudinal section (A1-An) of the rotor blade (1) with a length (g) in such a way that the suction surface (-) and the pressure surface (+) of the asymmetrical aerofoil (201) change at the turning points (P, P') from the outside to the inside of the circular path (U), or vice versa, by means of the rotary-wing kinematic system (10), and the variable, asymmetrical aerofoil (201) of the rotor blade (1), in a transition position, temporarily has a symmetrical aerofoil (200), the chord (p) of which is oriented tangentially to the circular path (U).