Pilot Control Soft Stops for Real-Time Load Factor Limiting
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft pilots face challenges in preventing excessive load factors caused by excessive bank, pitch, and yaw angles, which can lead to structural damage and reduced aircraft lifespan, as existing systems lack effective means to dynamically adjust soft stops to limit these angles in real-time.
Innovation Solution
A method and system that calculate a soft stop position by subtracting actual aircraft variables (such as bank angle, load factor, or net lateral acceleration) from predefined limits, applying a gain factor and optional saturation, to dynamically adjust the pilot control's force-feel characteristic, thereby preventing excessive aircraft orientation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If fixed soft stops are used in pilot control, then the structure is simple and easy to manufacture, but the system cannot dynamically adapt to prevent excessive load factors in real-time
Solution Approach 1:
The patent applies the Dynamics principle by transitioning from fixed soft stops to dynamically adjustable soft stops. The control system continuously calculates the difference between actual aircraft variables (bank angle, pitch angle, load factor) and their respective limits, then adjusts the soft stop position in real-time based on this difference multiplied by a gain factor. This allows the system to adapt to changing flight conditions and prevent excessive load factors dynamically.
Solution Approach 2:
The patent implements parameter changes by modifying the soft stop position parameter based on aircraft state. The soft stop position is calculated as a function of the difference between actual and limit values of aircraft parameters (bank angle, pitch angle, load factor). This dynamic parameter adjustment enables the control system to prevent excessive load factors while maintaining ease of operation.
2Reliability
If no soft stop adjustment is provided, then the pilot control is easy to operate, but the pilot may apply excessive bank, pitch, and yaw angles leading to excessive load factors
Solution Approach 1:
The patent applies the Feedback principle by continuously monitoring aircraft variables (bank angle, pitch angle, load factor) and using this information to adjust the soft stop position. The control system calculates the difference between actual and limit values, then feeds this information back to modify the force feedback characteristic of the pilot control. This creates a closed-loop system that reliably prevents excessive load factors while providing intuitive feedback to the pilot.
Solution Approach 2:
The patent implements preliminary anti-action by proactively adjusting the soft stop position before the pilot can apply excessive control inputs. The system continuously calculates the appropriate soft stop position based on current aircraft state and limit values, creating a preventive barrier that stops excessive bank, pitch, and yaw angles before they can occur, rather than reacting after the fact.
3Reliability
If dynamic soft stop adjustment is implemented, then aircraft safety is improved by preventing excessive load factors, but the control system becomes more complex
Solution Approach 1:
The patent applies the Universality principle by creating a multi-functional control system that simultaneously performs multiple tasks: monitoring aircraft variables, calculating soft stop positions, adjusting force feedback characteristics, and preventing excessive load factors. The same control system handles bank angle, pitch angle, and load factor protection through a unified approach, reducing overall system complexity despite the advanced functionality.
Data Source
Figure 1~2
Figure 3~4
Figure 5~6
AI summary
A method (10) for adjusting a soft stop position on a force-feel characteristic of a pilot control to move an aircraft, the method comprising: step (a): subtracting an actual aircraft variable (1) from an aircraft limit parameter (2) to find a difference (3); step (b): multiplying the difference (3) by a gain factor (6) to generate a soft stop position (7); step (c): outputting the soft stop position for adjustment on the pilot control.