Aircraft Throttle Position Sensor Digital Interface

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Solution Overview

Problem

Existing throttle lever position determination systems in aircraft are heavy due to the use of synchro-trigonometers, complex in technology, and prone to errors, leading to incorrect thrust control, and are costly and complex in architecture.

Innovation Solution

A system with position sensors divided into groups, using simpler sensors like potentiometers and rheostats, connected to primary and engine control computers, with an interface computer to calculate and transmit digital position values, eliminating the need for synchro-trigonometers and reducing wiring, and incorporating redundancy for reliability.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If synchro-trigonometers are used to determine throttle lever position, then measurement precision is improved, but device weight increases significantly

Engineering Contradiction:
Improvethrottle lever position measurement precisionVSAvoiddevice weight
Core Design Contradiction:
Measurement precisionVSWeight of moving object

Solution Approach 1:

The patent replaces the mechanical synchro-trigonometer system with a digital sensor system. Instead of using mechanical coils and magnetic cores, the invention uses optical or magnetic sensors combined with digital signal processing to measure throttle lever position. This substitution eliminates the heavy mechanical components while maintaining measurement precision through electronic detection and calculation methods.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent changes the measurement parameters from analog sinusoidal/cosinusoidal signals to digital position values. By using digital sensors that directly output position data rather than requiring complex trigonometric calculations from analog signals, the system achieves the same measurement precision with significantly reduced hardware weight.

Inventive Principle:
Principle #35Parameter changes

2Measurement precision

If synchro-trigonometers are used, then measurement capability is improved, but device complexity increases

Engineering Contradiction:
Improveposition measurement capabilityVSAvoidsensor technology complexity
Core Design Contradiction:
Measurement precisionVSDevice complexity

Solution Approach 1:

The patent replaces the complex mechanical synchro-trigonometer system with simpler digital sensors. Instead of requiring six-wire connections, sinusoidal voltage supply, and arctangent calculations, the invention uses digital sensors that directly provide position values through standard digital communication interfaces, dramatically simplifying the overall system architecture.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent extracts the essential measurement function from the complex synchro-trigonometer system and implements it separately using simple digital sensors. By separating the measurement function from the complex signal processing requirements, the system achieves the same capability with much simpler components and interfaces.

Inventive Principle:
Principle #2Taking out (Extraction)

3Measurement precision

If synchro-trigonometers are used, then position determination is achieved, but system reliability decreases

Engineering Contradiction:
Improveposition determination accuracyVSAvoidsystem reliability
Core Design Contradiction:
Measurement precisionVSReliability

Solution Approach 1:

The patent replaces the analog synchro-trigonometer system with a digital sensor system that is inherently more reliable. Digital sensors provide direct position values without requiring complex signal processing, reducing the number of potential failure points. The digital interface eliminates issues with signal degradation, phase errors, and calculation errors that plague analog systems.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent implements a system where multiple independent sensors continuously monitor throttle lever position and cross-validate their readings. Each sensor operates independently and can verify the others, providing built-in redundancy and fault detection without requiring complex external monitoring systems.

Inventive Principle:
Principle #25Self-service

4Measurement precision

If multiple sensors and computers are used, then measurement accuracy is improved, but architecture complexity increases

Engineering Contradiction:
Improveposition determination accuracyVSAvoidarchitecture complexity
Core Design Contradiction:
Measurement precisionVSDevice complexity

Solution Approach 1:

The patent merges the functions of multiple sensors and computers into a unified digital architecture. Instead of having separate analog signal processing paths for each sensor, the invention integrates all sensor inputs into a single digital processing unit that handles multiple sensor readings, calculations, and output generation, significantly simplifying the overall architecture.

Inventive Principle:
Principle #5Merging (Combining)

Solution Approach 2:

The patent creates a universal digital interface that can accommodate multiple types of sensors and multiple computer systems. The digital architecture provides a common communication protocol and data format that allows different sensors to be interconnected and processed by various computing devices, reducing architectural complexity through standardization.

Inventive Principle:
Principle #6Universality (Multi-functionality)

Data Source

PatentEP2296971B1Device and method for determining the position of a throttle lever in an aircraft
Publication Date: 2012.05.09 AIRBUS OPERATIONS (SAS)
  • EP2296971B1 patent drawingFigure 1~2
  • EP2296971B1 patent drawingFigure 3
  • EP2296971B1 patent drawingFigure 4

AI summary

The device for determining the position of a throttle lever according to the invention comprises position sensors each connected to a primary flight control computer, position sensors each connected to an engine management computer, the said position sensors being split into at least three groups of sensors with no common simple failure mode, and at least one computer, known as the interface computer, that has at least one input to receive measurement information emitted by the computers connected to the position sensors and outputs leading to the engine management computer.