Helicopter Rotor Simulation via Sector-Based Disc Partitioning
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Solution Overview
Problem
Current helicopter rotor simulation methods are slow and costly, making real-time simulations inconsistent with precision, particularly in training pilots, due to the complexity of calculating forces and moments on flapping and drag articulations.
Innovation Solution
A real-time simulation procedure that partitions the rotor disc instead of individual blades, using Fourier series to express flapping and drag as functions of azimuth, minimizing dynamic balance errors with Lagrange multipliers, and accounting for induced velocity and ground effect, allowing for faster and more accurate calculations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional blade element partition methods are used for helicopter rotor simulation, then calculation precision is improved, but simulation time increases and real-time performance is lost
Solution Approach 1:
The patent applies segmentation by dividing the rotor disc into multiple sectors rather than partitioning each individual blade into numerous elements. This sector-based segmentation reduces the total number of calculation units while maintaining adequate spatial resolution for capturing rotor aerodynamics, thereby achieving real-time simulation speeds without completely sacrificing precision.
Solution Approach 2:
The patent merges the treatment of multiple blades by applying a single set of sector partitions to the entire rotor disc, effectively combining the computational domains of all blades. This approach reduces redundancy in the computational model and accelerates simulation execution while preserving the essential physics of blade-element theory through appropriate mathematical formulations.
2Measurement precision
If traditional blade element partition methods are used for helicopter rotor simulation, then calculation precision is improved, but computational cost increases
Solution Approach 1:
The sector-based segmentation approach reduces the computational domain complexity by treating the rotor disc as a whole rather than as multiple independent blades. This segmentation strategy decreases the total number of discrete elements requiring computational processing, thereby lowering computational costs and improving productivity while maintaining sufficient precision for real-time applications.
Solution Approach 2:
The patent creates a universal computational framework where a single set of sector partitions serves all blades simultaneously. This multi-functional approach allows the same mathematical model and computational procedures to be applied across the entire rotor system, eliminating redundant calculations and significantly improving computational efficiency compared to blade-specific partitioning methods.
3Speed
If rotor disc partitioning is used instead of blade partitioning, then simulation speed is improved, but calculation complexity in determining forces and moments may increase
Solution Approach 1:
The patent inverts the traditional approach by partitioning the rotor disc into sectors rather than partitioning individual blades. This inversion of the computational perspective simplifies the overall system complexity by treating all blades uniformly within each sector, reducing the number of discrete computational entities while maintaining the necessary physical fidelity for calculating forces and moments on flapping and drag articulations.
Data Source
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AI summary
This procedure proposes the appropriate equations that determine the rotor movement in order to obtain the aerodynamic actions for each blade in each iteration (the forces that are transmitted to the helicopter and the moments with respect to the articulations), and they are resolved by discretizations made in the rotor disc, such that that the blade elements of the partition are connected to the disc, which does not rotate, instead of to each blade. The blades pass through an azimuth range in each iteration, making a division of each blade longitudinally into ne elements, and the rotor disc into na sectors, corresponding to divisions of the range of azimuth angles. Therefore, partitions are made on ne·na blade elements, identifying each blade element by means of its distance to the rotor axis and its azimuth angle.