Variable Aerodynamic Propelling System for Rotary Wing Aircraft
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Solution Overview
Problem
Rotary wing aircraft have complex rotor blade pitch control mechanisms that require regular maintenance and are limited in their ability to efficiently control lift and thrust direction, especially at high altitudes, and lack the flexibility to reverse lift or thrust direction without loss of efficiency.
Innovation Solution
A propelling system with variable aerodynamic controls that allows each propelling unit to rotate 360 degrees around a pitch axis, enabling efficient control of lift or thrust direction without mechanical connection to the rotor, using aileron assemblies and an electronically controlled actuation mechanism to adjust pitch and angle of attack, allowing for passive and active lift generation relative to rotor speed and airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional rotor blade pitch control mechanisms are used, then the pitch can be altered over a limited range, but the mechanism becomes highly complex and requires regular maintenance
Solution Approach 1:
The patent extracts the pitch control function from the traditional mechanical connection to the rotor hub. Each blade is given independent pitch control capability through its own actuator and control system, removing the need for complex mechanical linkages to the hub while enabling full 360-degree pitch control range.
Solution Approach 2:
The patent segments the pitch control system into independent units for each blade. Each blade has its own pitch actuator, sensor, and control logic, allowing individual blades to be controlled independently without affecting others, thereby simplifying the overall mechanical structure while maximizing pitch control versatility.
2Stability of the object's composition
If traditional mechanically connected rotor blades are used, then the structure is stable, but the number, weight, and complexity of pitch actuating components increases
Solution Approach 1:
The patent replaces traditional mechanical pitch control linkages with an electronic control system. Each blade has an electronic pitch actuator that directly controls the blade pitch angle through electronic signals rather than mechanical linkages to the hub, significantly reducing the weight and complexity of actuating components while maintaining structural stability through controlled operation.
3Ease of operation
If rotor blades are tied to the rotor with mechanical mechanisms, then pitch can be physically altered, but the mechanism requires regular maintenance to avoid failure
Solution Approach 1:
Each blade is equipped with its own independent pitch actuator and control system that operates autonomously without requiring mechanical connection to the rotor hub. This self-contained design eliminates wear points and failure modes associated with mechanical linkages, reducing maintenance requirements while preserving full pitch actuation capability.
4Productivity
If higher rotor RPM is used to generate greater lift, then lifting efficiency increases, but the complexity of pitch control mechanisms increases
Solution Approach 1:
The patent implements dynamic pitch control where each blade's pitch angle can be independently and rapidly adjusted in response to real-time operating conditions. This dynamic control system allows the rotor to operate efficiently at higher RPM by optimizing blade pitch angles for maximum lift generation, while the electronic control system manages the complexity rather than mechanical linkages.
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 system reduces the complexity and weight of pitch actuating components, enables higher rotor RPM for greater lift, and allows for efficient reversal of lift or thrust direction without loss of efficiency, improving lifting efficiency at high altitudes and reducing maintenance needs.
Implementation Method 1
each of the plurality of propelling units is free to fly into the oncoming airflow through 360 degrees of pitch, thus naturally generating the optimum amount of lift for any rotational speed
Data Source
AI summary
A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.