Asymmetric Compound Helicopter Propellers for Multi-State Thrust Control
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Solution Overview
Problem
Conventional compound helicopters face inefficiencies in thrust generation and control during various flight states due to similar specifications of propellers, leading to suboptimal performance and stability issues.
Innovation Solution
The compound helicopter design incorporates two propellers with different specifications, including varying pitch angles, washout angles, and sectional shapes, allowing for adjustable thrust direction and magnitude to suit different flight conditions, and a controller to manage these components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If propellers with similar specifications are used in conventional compound helicopters, then device complexity is reduced, but flight efficiency and performance are compromised
Solution Approach 1:
The patent applies local quality by configuring the left and right propellers with different specifications tailored to their respective positions and flight conditions. The first propeller (right side) has different pitch angles, washout angles, and blade section shapes compared to the second propeller (left side), allowing each propeller to be optimized for its specific operational role and location on the aircraft.
Solution Approach 2:
The patent implements asymmetry by deliberately designing asymmetric propeller configurations where the left and right propellers have non-identical specifications. This asymmetric design allows the aircraft to achieve superior flight performance across different flight states by having each propeller contribute differently to thrust generation, rather than using symmetric identical propellers.
2Productivity
If propellers with different specifications are used, then thrust generation is optimized for various flight states, but control complexity increases
Solution Approach 1:
The patent incorporates a control system that monitors flight conditions and adjusts propeller parameters in real-time based on feedback from sensors. This feedback mechanism allows the asymmetric propeller configuration to adapt to different flight states automatically, maintaining optimal thrust generation while simplifying pilot operation through automated control adjustments.
Solution Approach 2:
The patent applies dynamics by making the propeller characteristics variable rather than fixed. The pitch angles, washout angles, and blade sections are designed to be adjustable during flight, allowing the propellers to dynamically adapt their performance characteristics to match current flight conditions, thereby optimizing thrust generation across hovering, low-speed, and high-speed regimes.
3Productivity
If propellers are designed for specific flight conditions, then performance in those conditions improves, but adaptability to other conditions decreases
Solution Approach 1:
The patent achieves universality by designing the asymmetric propeller system to perform multiple functions across different flight states. The first propeller is optimized for certain conditions while the second propeller complements it for other conditions, and together they provide versatile performance throughout the entire flight envelope, from hovering to high-speed flight, making the system adaptable to all operational requirements.
Solution Approach 2:
The patent implements parameter changes by varying key propeller parameters including pitch angles, washout angles, and blade section shapes between the two propellers. These parameter variations allow each propeller to be tuned for specific flight conditions while the combined system maintains adaptability across all flight states through coordinated operation and control system adjustments.
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
Enhances flight efficiency and stability by optimizing thrust generation and control across hovering, low-speed, and high-speed flight states, improving overall performance.
Implementation Method 1
a first propeller that is disposed at the first main wing and generates positive thrust when the proceeding direction is regarded as positive
Implementation Method 2
a second propeller that is disposed at the second main wing and generates positive thrust and negative thrust
Implementation Method 3
a main rotor disposed at an upper side of the body
Data Source
AI summary
A compound helicopter includes: a body; a first main wing extending from the body toward a right side in a proceeding direction of the body; a second main wing extending from the body toward a left side in the proceeding direction of the body; a main rotor disposed at an upper side of the body; a first propeller that is disposed at the first main wing and generates positive thrust when the proceeding direction is regarded as positive; and a second propeller that is disposed at the second main wing and generates positive thrust and negative thrust. Specifications of the first propeller are different from specifications of the second propeller.