Flight Control Algorithm Reducing Fatigue Loads
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Solution Overview
Problem
Rotary-wing aircraft components suffer damage due to high peak loads during aggressive maneuvers, particularly in combat situations, as existing control algorithms are limited in their applicability and focus on specific components rather than overall system design.
Innovation Solution
The Life Improving Control (LIC) algorithm, integrated within a fly-by-wire flight control system, uses a Virtual Load Sensor model to estimate and reduce fatigue loads by modifying flight control system parameters, thereby extending component life without compromising aircraft agility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional physics-based modeling is used for damage classification, then time-frequency damage classification is achieved, but applicability to rotary-wing aircraft flight control system design is limited
Solution Approach 1:
The patent transforms the damage classification approach by changing the modeling parameters from physics-based models to virtual sensor models that directly estimate component loads. This parameter change enables broader applicability to rotary-wing aircraft while maintaining damage classification capability through load estimation rather than physics-based analysis
2Duration of action of stationary object
If control algorithms focus on specific components, then component life is increased, but overall system design applicability is limited
Solution Approach 1:
The patent creates a universal flight control system that can protect multiple components simultaneously. The virtual sensor model estimates loads on various components (main rotor gearbox, tail rotor drive shaft, etc.) and the control algorithm optimizes maneuvers to reduce peak loads across the entire system, making it applicable to overall system design rather than individual components
3Duration of action of stationary object
If flight control parameters are modified to reduce loads, then component life is extended, but aircraft agility may be compromised
Solution Approach 1:
The patent implements a dynamic control algorithm that continuously monitors virtual sensor load estimates and adapts control parameters in real-time. The system modifies flight control parameters dynamically during maneuvers to reduce peak loads on components while maintaining aircraft agility through adaptive rather than static parameter changes
Solution Approach 2:
The control algorithm uses feedback from virtual sensor load estimates to continuously adjust flight control parameters. By monitoring estimated component loads and responding with appropriate control adjustments, the system extends component life while preserving aircraft performance through closed-loop control rather than open-loop parameter modification
Data Source
Figure 1
Figure 2A
Figure 2B~3A
AI summary
A flight control system includes a command model modified in response to a Life Improving Control (LIC) algorithm. An inverse aircraft model is in communication with the command model to generate a flight control system command to command an aircraft state. A feedback path from the command model and the aircraft state is also modified in response to the Life Improving Control (LIC) algorithm.