Auto-Throttle Inner Loop for Flight Path Acceleration Guidance
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Solution Overview
Problem
Current auto-throttle systems lack intuitive throttle rate control that effectively translates flight path acceleration commands into appropriate engine power settings, making it difficult for pilots to achieve desired acceleration targets.
Innovation Solution
A processor-implemented method and system that generates throttle rate commands by converting flight path acceleration errors into equivalent throttle rate commands, using a novel auto-throttle inner loop control algorithm that compensates for flight path changes and engine non-linearities without requiring accurate drag readings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional auto-throttle systems use speed control law or thrust control law to generate engine power commands, then the system can control aircraft speed or thrust, but the system fails to provide intuitive indication of acceleration or deceleration to the pilot
Solution Approach 1:
The patent introduces an acceleration indicator as an intermediary element between the auto-throttle control system and the pilot. This indicator visually represents the aircraft's acceleration or deceleration state, allowing pilots to intuitively understand the thrust axis guidance without directly interpreting complex engine power commands or throttle position data. The acceleration indicator serves as a mediator that translates control system outputs into meaningful flight dynamics information.
2Productivity
If pilots manually use flight path acceleration indicator to regulate aircraft acceleration, then pilots can achieve target speed control, but the auto-throttle function requires complex adjustment to translate acceleration commands into appropriate engine power settings
Solution Approach 1:
The patent replaces the complex mechanical control translation process with an electronic control algorithm. Instead of requiring manual adjustment of auto-throttle mechanisms to convert acceleration commands into engine power settings, the system uses a processor-executed control law that automatically performs this translation. The electronic system calculates the relationship between desired flight path acceleration and required engine power based on aircraft state data, eliminating the need for complex mechanical adjustments.
Solution Approach 2:
The patent changes the control parameter from direct engine power or throttle position control to flight path acceleration control. By using acceleration as the primary control parameter and deriving engine power commands from it, the system simplifies the control logic while improving speed control accuracy. The control algorithm dynamically adjusts engine power settings based on the desired acceleration rate and current aircraft state, providing more precise and intuitive speed management.
3Extent of automation
If auto-throttle systems generate engine power commands in engine control units, then the system can directly control engine power, but pilots cannot intuitively evaluate whether the aircraft is accelerating or decelerating
Solution Approach 1:
The patent implements a feedback mechanism by displaying acceleration information to the pilot while the auto-throttle system automatically controls engine power. The acceleration indicator provides real-time feedback about the aircraft's thrust axis guidance, allowing pilots to evaluate whether the automated system is producing the desired acceleration or deceleration effect. This feedback loop maintains high automation while preventing information loss about flight dynamics.
Data Source
AI summary
Technologically improved vehicle control systems and methods are described. The provided vehicle control systems and methods embody an inner loop auto-throttle control for causing delta-throttle changes, i.e., servo changes, to achieve desired acceleration targets. The system generates an error on a potential flight path angle using a received thrust acceleration command. The error on the potential flight path angle is converted into an equivalent acceleration. A throttle rate command TLA_ratecmd is generated by converting the equivalent acceleration into the throttle rate command TLA_ratecmd.