Adaptive Trim Tab Control for Reverse Slip in Flight
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Solution Overview
Problem
Existing automatic rudder trim systems require manual adjustments by pilots due to torque and propeller effects, leading to negative training and potential slip issues in air vehicles.
Innovation Solution
An automatic trim tab control system that adjusts trim commands based on airspeed, engine torque, and lateral acceleration data using a flight control computer and controller gains, preventing reverse slip through adaptive gain coefficients.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If manual trim adjustments are required to compensate for torque and propeller effects, then the air vehicle can be controlled, but pilot workload increases and negative training occurs
Solution Approach 1:
The automatic trim system enables the air vehicle to self-adjust trim commands based on measured flight conditions (airspeed, engine torque, lateral acceleration) without continuous pilot intervention. The flight control computer automatically generates trim commands to compensate for torque and propeller effects, freeing the pilot from manual adjustments while maintaining flight control stability
Solution Approach 2:
The system continuously measures flight conditions including airspeed, engine torque, and lateral acceleration, then uses this feedback to automatically adjust trim commands. The controller gain coefficient is determined based on measured lateral acceleration data and airspeed, creating a closed-loop control system that maintains stability without pilot intervention
2Ease of operation
If fixed trim commands are used based on airspeed and torque data, then the trim system is simple to operate, but reverse slip occurs during maneuvering and aerobatics
Solution Approach 1:
The system transitions from fixed trim commands to dynamic trim adjustment by adapting the controller gain coefficient based on measured lateral acceleration and airspeed. During maneuvering and aerobatics, the gain coefficient changes to prevent reverse slip, while maintaining simple operation through automatic adaptation without pilot input
Solution Approach 2:
The controller gain coefficient is dynamically changed based on flight conditions. The system measures lateral acceleration and airspeed to determine appropriate gain values, allowing the trim system to adapt to different maneuvering conditions and prevent reverse slip while keeping the operation simple and automatic
3Reliability
If adaptive gain coefficients are implemented to prevent reverse slip, then flight control reliability improves, but device complexity increases
Solution Approach 1:
The flight control computer performs multiple functions: measuring flight conditions, determining controller gain coefficients, generating trim commands, and preventing reverse slip. By consolidating these functions in a single control system rather than separate devices, the patent reduces overall system complexity while maintaining high reliability through adaptive gain coefficients
Data Source
AI summary
A sensor unit located on an air vehicle enables the measurement of air speed, engine torque and lateral acceleration of the air vehicle. A flight control computer enables a first adjustment command to be generated using the air speed and engine torque data measured by the sensor unit. A controller run in the flight control computer enables a second adjustment command to be generated using the lateral acceleration data. A gain coefficient of the controller is determined by the flight control computer based on the air speed measured by the sensor unit. The flight control computer collects the first adjustment command and the second adjustment command is generated by the controller so that it generates a final adjustment command.