Aircraft Guidance Control System Using Bounded Track Correction
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Solution Overview
Problem
Conventional aircraft guidance systems are complex and require separate modes for intercept, capture, and tracking, leading to computational inefficiencies and instability in transitioning between these modes.
Innovation Solution
A simplified control system that uses a single mode to achieve intercept, capture, and tracking functionality by employing a path tracking controller, correction bounds computer, and track angle correction limiter, which sets track corrections within upper and lower bounds to ensure seamless transitions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate control modes are used for intercept, capture, and tracking phases, then each phase can be optimized independently, but the overall system complexity increases and transitions between modes become unstable
Solution Approach 1:
The patent combines intercept, capture, and tracking functions into a single integrated control mode. The controller continuously calculates track angle errors and applies correction within defined bounds throughout the entire process, eliminating the need for separate control modes and their associated transition complexities.
Solution Approach 2:
The single control mode is designed to perform multiple functions: it handles intercept when the aircraft is far from the track, capture as the aircraft approaches, and tracking when on the track. This universal controller replaces multiple specialized controllers, reducing system complexity while maintaining all necessary functionalities.
2Device complexity
If a single control system is used for all phases, then system complexity is reduced, but computational load increases
Solution Approach 1:
The control algorithm segments the correction process by applying different correction bounds at different stages. When the aircraft is far from the track, larger corrections are permitted; as the aircraft approaches the track, correction bounds are tightened. This segmentation allows a simple controller to handle different operational phases efficiently without requiring complex computational resources.
Solution Approach 2:
The controller dynamically adjusts the correction bounds parameter based on the aircraft's position relative to the track. This parameter change allows the system to maintain simplicity while adapting to different phases of the approach, avoiding the need for complex computational models by using straightforward parameter adjustments.
3Speed
If aggressive track corrections are applied, then convergence to the planned track is faster, but the risk of divergence and instability increases
Solution Approach 1:
The control system dynamically adjusts the correction amount based on the current track angle error and the aircraft's position. The correction bounds are not fixed but vary throughout the process, allowing aggressive corrections when far from the track and gentler corrections near the track, thus maintaining both speed and stability.
Solution Approach 2:
The controller continuously monitors the track angle error and adjusts corrections accordingly. The feedback mechanism ensures that corrections remain within safe bounds while still achieving convergence, preventing divergence by constantly adapting the control output based on the current state of the system.
Data Source
AI summary
A system and method for steering aircraft along a predetermined track is disclosed herein. The system and method relate to steering an aircraft along a lateral path (e.g. a track described by reference to latitude and longitude) by a method comprising: calculating a nominal track correction; providing an upper limit and a lower limit for the nominal track correction; setting a desired track correction as: (i) the nominal track correction if the nominal track is between the upper limit and the lower limit; (ii) the upper limit if the nominal track correction is greater than or equal to the upper limit; or (iii) the lower limit if the nominal track correction is less than or equal to the lower limit; and steering the aircraft using the desired track correction.