High Aspect Ratio Rotor Wing Flight Vehicle Design
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Solution Overview
Problem
Conventional aircraft designs for High Altitude Long Endurance (HALE) missions prioritize lift capacity over endurance, resulting in suboptimal cruise efficiency and limited operational range due to inadequate rotor and wing configurations.
Innovation Solution
A flight vehicle with a high aspect ratio wing and rotors that transition between vertical and horizontal planes of rotation, featuring a rotor diameter-to-wingspan ratio of at least 0.25, optimized for maximum rotor efficiency and glide ratio, enabling efficient hover and cruise modes with high static thrust and low drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If conventional aircraft designs prioritize lift capacity, then carrying capacity is improved, but cruise endurance and efficiency deteriorate
Solution Approach 1:
The rotor is designed to rotate between vertical and horizontal planes dynamically. In vertical plane during hover/takeoff, providing high lift capacity. In horizontal plane during cruise, optimizing for endurance and efficiency. This dynamic reconfiguration resolves the contradiction between lift capacity and cruise endurance.
Solution Approach 2:
The rotor diameter-to-wingspan ratio is optimized to be at least 0.25, and the rotor aspect ratio is at least 0.55. These parameter optimizations allow the rotor to efficiently operate in both vertical and horizontal modes, achieving high lift capacity when needed while maintaining excellent cruise endurance through optimized aerodynamic parameters.
2Quantity of substance
If rotor diameter is increased to improve lift capacity, then carrying capacity is improved, but device complexity increases
Solution Approach 1:
The rotor system serves multiple functions: it provides lift during hover (vertical rotation), generates thrust during cruise (horizontal rotation), and enables takeoff and landing. This multi-functionality eliminates the need for separate systems for different operations, reducing overall device complexity while maintaining high carrying capacity.
Solution Approach 2:
The rotor dynamically changes its plane of rotation based on operational requirements. This dynamic adaptability allows a single rotor system to handle various flight phases efficiently, avoiding the complexity of multiple dedicated systems for different functions.
3Loss of energy
If wing aspect ratio is increased to improve glide ratio, then cruise efficiency is improved, but device complexity increases
Solution Approach 1:
The wing aspect ratio is optimized to be at least 10:1, and the rotor aspect ratio is at least 0.55. These parameter optimizations maximize the glide ratio and cruise efficiency while maintaining manageable structural complexity through standardized design approaches.
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 design achieves extended cruise endurance and efficiency by maximizing rotor efficiency over a wide range of airspeeds, with a high static thrust parameter and low drag, suitable for high-altitude, long-duration operations.
Implementation Method 1
first and second rotors connected to the wing, wherein the first and second rotors have a high aspect ratio... a first motor to drive the first rotor and a second motor to drive the second rotor
Implementation Method 2
a wing having a high aspect ratio... optimized for maximum rotor efficiency and glide ratio, enabling efficient hover and cruise modes
Data Source
AI summary
Method and apparatus for a flight vehicle including a wing having a high aspect ratio and first and second rotors having a high aspect ratio, with a ratio of the rotor diameter to wing length ratio is equal to or greater than about 0.25. In embodiments, the flight vehicle can include a first and second motor, each less than about one thousand HP, to drive a respective rotor and a second motor. The flight vehicle can include a cruise mode and a VTOL mode.