Digital Aircraft Thrust Control to Eliminate Analog Signal Noise
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Solution Overview
Problem
Existing aircraft throttle control systems suffer from significant analog acquisition noise, especially at greater distances from the engine, and are unreliable due to harsh environmental conditions near the engine, leading to latency and loss of thrust control in case of failures.
Innovation Solution
A digital flight control system is introduced, where a flight control unit processes signals from the throttle and sensors, developing redundant digital thrust control vectors that are transmitted to a separate engine computing unit, ensuring robustness against noise and environmental interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If an analog signal is used for throttle control, then the system is simpler, but the noise increases significantly with distance from the engine
Solution Approach 1:
The patent replaces the analog mechanical signal transmission system with a digital communication system. The throttle position is converted to digital data packets that are transmitted via aircraft bus (e.g., ARINC 429, AFDX) to the engine control unit, eliminating analog signal degradation over distance while maintaining system functionality.
Solution Approach 2:
The patent introduces a digital signal intermediary (flight control computer or data bus interface) between the throttle and engine control unit. This intermediary converts analog throttle input to digital format and transmits it through the aircraft's digital communication network, isolating the control signal from analog noise interference.
2Speed
If the engine control unit is located close to the engine, then the control response is faster, but the reliability decreases due to harsh environmental conditions
Solution Approach 1:
The patent segments the control system into distinct functional units: the throttle control unit, the digital communication interface, and the engine control unit. This segmentation allows the ECU to be positioned optimally near the engine for fast response while the digital communication interface handles signal processing in a protected environment, isolating sensitive electronics from harsh conditions.
Solution Approach 2:
The patent protects the digital communication interface and signal processing electronics from harsh engine environment (high temperature, vibration, electromagnetic interference) by locating them in inert, controlled environments such as the flight control computer or protected avionics bays, while still enabling fast control response through digital communication.
3Extent of automation
If a motorized throttle with auto-throttle is used, then the automation is improved, but the latency and delay in thrust control increase
Solution Approach 1:
The patent implements a dynamic throttle control system where the motorized throttle can operate in multiple modes: fully automatic (auto-throttle), manual override, and direct mechanical coupling. The system dynamically adjusts its control loop characteristics and can bypass digital processing paths when immediate response is required, reducing latency while maintaining automation capabilities.
Solution Approach 2:
The patent pre-positions the motorized throttle actuator and control algorithms to enable rapid response. The auto-throttle system maintains ready-state parameters and can execute pre-calculated thrust commands, reducing processing latency while preserving full automation functionality.
4Extent of automation
If the throttle lever is motorized, then the automation capability is enhanced, but the system complexity and potential failure points increase
Solution Approach 1:
The patent designs the motorized throttle system with multi-functionality: the same motorized actuator serves both automatic thrust control and manual pilot input functions. The system can operate in auto-throttle mode, manual mode, or with direct mechanical linkage, providing universal functionality that reduces the need for separate systems and components.
Data Source
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AI summary
An aircraft (12) piloting system (10) comprising a throttle (16), a flight parameter sensor system (18), and an engine control unit (22) controlling thrust parameters of an aircraft (14) engine (12). The piloting system (10) includes a flight control unit (20) connected to the engine control unit (22), the sensors (18), and the throttle (16); the flight control unit (20) generating a thrust control vector from a flight control law and sending a digital signal including the generated thrust control vector to the engine control unit (22); and the engine control unit (22) controlling said thrust parameters of the engine (14) according to the generated thrust control vector received.