Real-time Rotor Wake Simulation Using Vortex Rings
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Solution Overview
Problem
Current flight simulation systems for hover-capable aircraft struggle to accurately and efficiently simulate the effects of rotor-wake generated aerodynamic loads in real-time, with existing methods being either too expensive due to extensive flight testing or using simplified models that lack precision.
Innovation Solution
A real-time simulation system that uses a processing unit to simulate the aerodynamic loads by modeling the rotor wake as a series of vortex rings, allowing for accurate computation of induced velocities and aerodynamic loads on the aircraft, enabling precise and cost-effective simulation of flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If experimental flight testing is used to measure aerodynamic loads, then measurement precision is improved, but loss of time and cost increase significantly
Solution Approach 1:
The patent creates a computational copy of the aerodynamic loads through mathematical modeling. Instead of physically measuring loads during flight tests, the system computes equivalent aerodynamic loads using mathematical models that replicate the physical phenomena, thereby eliminating the need for extensive flight testing while maintaining measurement precision
Solution Approach 2:
The patent replaces the mechanical measurement system (sensors, instruments, flight tests) with a computational mathematical model. The physical measurement process is substituted by mathematical calculations that compute aerodynamic loads based on flight conditions, significantly reducing time and cost while preserving accuracy
2Productivity
If simple prescribed wake models are used, then productivity is improved through real-time computation, but measurement precision deteriorates
Solution Approach 1:
The patent transitions from static, simplified wake models to a dynamic mathematical model that adapts to changing flight conditions. The model dynamically computes aerodynamic loads based on current rotor wake configuration, aircraft attitude, and flight parameters, maintaining both real-time performance and high precision across varying operational states
Solution Approach 2:
The patent changes the parameters and complexity of the mathematical model to achieve optimal balance between computation speed and precision. By adjusting model parameters such as wake discretization, integration steps, and computational algorithms, the system achieves real-time performance without sacrificing aerodynamic load prediction accuracy
3Measurement precision
If complex computational fluid dynamics models are used, then measurement precision is improved, but device complexity and processing time increase
Solution Approach 1:
The patent segments the complex computational fluid dynamics problem into manageable mathematical components. Instead of solving the full CFD equations, the system divides the aerodynamic load computation into separate mathematical models for different aspects ( rotor wake, fuselage interference, control surface effects), computing each segment independently and combining results to achieve high precision with reduced complexity
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 system achieves high-accuracy simulation of aerodynamic loads generated by the rotor wake, allowing for realistic and efficient training of pilots without the need for extensive flight testing, while maintaining compatibility with real-time frame rates.
Implementation Method 1
modeling the rotor wake as a series of vortex rings, allowing for accurate computation of induced velocities and aerodynamic loads on the aircraft
Data Source
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AI summary
A real-time simulation system of the aerodynamic loads generated by the wake of a rotor of a hover-capable aircraft on the aircraft itself is described, said system comprising: a cockpit seat; a simulated control device able to receive a simulated command to simulate a flight condition of the aircraft; a plurality of simulation devices able to generate a simulated representation of the flight condition; and a processing unit configured to receive a first signal associated with the command given via the control device and to generate a second control signal for the plurality of simulation devices associated with the simulated aerodynamic loads. The processing unit cyclically generates a vortex ring, associates one or more control points with the vortex ring, computes the velocity induced on the control points, moves and updates the vortex ring, and generates the second signal on the basis of the velocities induced on the control points.