Aircraft Inceptor Force Compensation Without Counterweights
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Solution Overview
Problem
Existing aircraft control systems using counterweights to compensate for acceleration forces result in bulky and expensive setups, complicating the control system.
Innovation Solution
A control system for aircraft that includes an inceptor, an actuator, and sensors to measure acceleration and total force, with a control unit that modifies the actuator force based on these measurements to counteract unwanted acceleration forces, thereby improving pilot control and reducing system complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If counterweights are used to compensate for acceleration forces on inceptors, then the pilot control comfort is improved, but the system becomes bulky and expensive
Solution Approach 1:
The patent replaces the mechanical counterweight system with an electronic control system that uses sensors to detect acceleration forces and actuators to generate compensating forces on the inceptor. This substitution eliminates the need for bulky mechanical counterweights while maintaining the same compensation function, thereby improving pilot control comfort without increasing device complexity
Solution Approach 2:
The patent changes the physical state of the compensation mechanism from a static mechanical counterweight to a dynamic electronic control system that adjusts forces in real-time based on measured acceleration parameters. This allows the system to adapt to varying flight conditions without requiring a fixed, bulky mechanical structure
2Ease of operation
If counterweights are used to compensate for acceleration forces on inceptors, then the pilot control comfort is improved, but the system cost increases
Solution Approach 1:
The patent replaces expensive mechanical counterweight assemblies with more cost-effective electronic components including accelerometers, control units, and actuators. This substitution significantly reduces manufacturing costs while maintaining the same level of pilot control comfort through electronic force compensation
3Device complexity
If traditional control systems are used without acceleration compensation, then the system remains simple, but the pilot experiences inconvenience and erroneous inceptor movement during acceleration
Solution Approach 1:
The patent implements a feedback control system where sensors continuously monitor acceleration forces acting on the inceptor, and the control unit uses this information to dynamically adjust actuator forces. This closed-loop feedback mechanism maintains pilot control comfort without requiring complex mechanical pre-compensation structures
Solution Approach 2:
The patent introduces an electronic control unit as an intermediary between the sensor detection and actuator response. This intermediary processes acceleration data and generates appropriate compensating forces, providing a simple yet effective bridge that maintains system simplicity while improving pilot control comfort
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 effectively compensates for acceleration forces, enhancing pilot control comfort and reducing system bulk and cost by dynamically adjusting actuator forces, thus improving operational efficiency and reducing complexity.
Implementation Method 1
a first sensor configured to measure an acceleration of the control system
Data Source
Figure 1a~1d
Figure 2a~2c
Figure 3~4
AI summary
A control system for an aircraft, the control system comprising: an inceptor operable by a pilot; an actuator configured to generate a force on the inceptor; a first sensor configured to measure an acceleration of the control system; and a control unit configured to: determine an acceleration force on the inceptor based on the measured acceleration; and modify the force generated by the actuator based on the acceleration force.