Single-Blade Rotor Layout for Hybrid Aircraft Payload Balance
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Solution Overview
Problem
Existing hybrid aircraft designs face a trade-off between maximizing lift and minimizing counterweight weight, which affects payload capacity, particularly in two-bladed rotor systems with single-bladed wings.
Innovation Solution
The aircraft is designed with two single-bladed rotors where the rotor mast axis divides each blade into two parts, with a ratio of r/R approximately equal to 0.2, optimizing the relationship between blade length, counterweight position, and rotor spacing for improved payload and power efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If blade length is increased to maximize lift, then lift capacity is improved, but counterweight mass must increase which reduces payload
Solution Approach 1:
The invention optimizes the r/R ratio parameter (distance from rotor axis to counterweight center of gravity divided by blade length) to a specific range of 0.15-0.25. This parameter optimization allows the system to achieve maximum lift while minimizing counterweight mass, resolving the contradiction between lift capacity and payload by finding the optimal geometric configuration rather than simply increasing or decreasing counterweight size.
2Weight of moving object
If counterweight is moved closer to rotor axis to reduce its mass, then dead weight is reduced, but lift capacity decreases
Solution Approach 1:
By defining and optimizing the r/R ratio within the specific range of 0.15-0.25, the invention determines the precise optimal position of the counterweight relative to blade length. This parameter optimization ensures that the counterweight is positioned to generate sufficient centrifugal force for lift while minimizing its mass, thereby reducing dead weight without sacrificing lift capacity.
3Weight of moving object
If r/R ratio is decreased below 0.2, then counterweight mass is reduced, but payload decreases due to excessive dead weight increase
Solution Approach 1:
The invention establishes the optimal r/R ratio range of 0.15-0.25 through parameter optimization. Within this range, the system achieves the best balance between counterweight mass and payload capacity. The lower bound of 0.15 prevents the counterweight from being too close to the rotor axis (which would reduce lift), while the upper bound of 0.25 prevents the counterweight from being too far out (which would increase dead weight and reduce payload).
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 configuration enhances payload capacity and power efficiency by balancing lift and counterweight weight, achieving optimal performance within a specific r/R ratio range of 0.15 to 0.25.
Implementation Method 1
a two-successive rotating-wing architecture... the rotor axes are spaced along the vehicle's roll axis... capable of vertical or short takeoff
Implementation Method 2
the counterweight in the case of a single-bladed propeller is a dead weight... the ratio between blade length and counterweight length is around 20%
Data Source
Figure 1~3
AI summary
The invention relates to a hybrid aerodyne comprising a fuselage (1), a fixed wing (2, 4) and at least two rotary wings (6, 7), the latter being capable of producing lift by their rotation in the vertical flight phase and of being immobilized and stowed longitudinally in cruising flight phase, and comprising at least one counterweight (6d) mono-blade (6) located at the top of the fuselage (1), each wing comprising a rotor mast (8, 9) which are spaced apart from one another along the roll axis (la) of the aerodyne. The invention is characterized in that the length of the counterweight (6c, 6d) (r) is between 15 and 25 % of the length (R) of the active part (6a, 6b) of the mono-blade (6).