Follower Aircraft Speed Control for Stable Formation Spacing
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Solution Overview
Problem
Existing methods for managing the longitudinal position of a follower aircraft in formation flight lead to speed setpoint fluctuations, degrading passenger comfort.
Innovation Solution
A method that involves obtaining the position and speed of both the leader and follower aircraft, determining a target longitudinal position, calculating the difference between the target and real positions, comparing this difference to predefined thresholds, and choosing an appropriate control law to manage the follower aircraft's speed, thereby reducing speed setpoint fluctuations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If continuous speed setpoint calculation with longitudinal position and speed feedback is used to manage the longitudinal position of the follower aircraft, then the longitudinal position control is achieved, but speed setpoint fluctuations occur which degrade passenger comfort
Solution Approach 1:
The patent applies dynamics by making the control system adaptive through multiple control laws that are selected based on real-time conditions. The system transitions between different control strategies (proportional control, derivative control, combined control) depending on the longitudinal position error and speed error, allowing the controller to respond optimally to different flight phases and disturbance conditions while maintaining position precision and reducing unnecessary speed fluctuations.
Solution Approach 2:
The patent changes control parameters dynamically by selecting different control laws based on the current state of the system. The control law selection depends on parameters such as the longitudinal position error magnitude and speed error, allowing the system to adjust its control strategy. This parameter-based selection enables the system to maintain precise position control while minimizing speed setpoint fluctuations that would affect passenger comfort.
2Object-affected harmful factors
If multiple control laws are selected based on threshold comparisons to manage follower aircraft speed, then passenger comfort is improved by reducing speed fluctuations, but control system complexity increases
Solution Approach 1:
The patent segments the control space into multiple regions based on threshold comparisons of position error and speed error. Each region is associated with a specific control law, allowing the system to apply appropriate control strategies for different operating conditions. This segmentation approach divides the complex control problem into manageable segments, where simple threshold comparisons determine which control law to apply, reducing overall system complexity while maintaining comfort.
Solution Approach 2:
The patent introduces an intermediary control law selection mechanism that acts as a mediator between the error signals and the actuator commands. The selection logic based on threshold comparisons serves as an intermediary layer that processes the error information and chooses the most appropriate control strategy, simplifying the control architecture while improving passenger comfort by reducing unnecessary speed fluctuations.
Data Source
AI summary
A method for managing a longitudinal position a follower aircraft following a leader aircraft by: obtaining a position and speed of the leader aircraft and a real longitudinal position and speed of the follower aircraft; determining a target longitudinal position of the follower aircraft with respect to the longitudinal position of the leader aircraft; calculating a difference between the target longitudinal position of the follower aircraft and the real longitudinal position of the follower aircraft; comparing the value of the difference with at least one predefined threshold; choosing a control law for controlling the speed of the follower aircraft, from among at least two separate control laws, on the basis of the comparison; and, applying the chosen control law so as to manage the real longitudinal position of the follower aircraft with respect to the position of the leader aircraft.