Adaptive UAV Flight Control for Smooth Speed Transitions

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Solution Overview

Problem

Existing unmanned aerial vehicle (UAV) control systems face challenges in smoothly transitioning between low and high speeds, leading to abrupt changes in altitude and control difficulties for pilots.

Innovation Solution

The implementation of an adaptive speed control method using a virtual gear shifting mechanism and Proportional, Integral, and Derivative (PID) controls, which adjusts rotor power based on initial velocity and control trigger position, allowing seamless transitions and maintaining smooth flight by dynamically adjusting acceleration, roll, and pitch angles.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If traditional fixed-gear control is used, then the control system is simple, but the UAV cannot smoothly transition between low and high speeds

Engineering Contradiction:

Improvespeed transition capabilityVSAvoidcontrol system complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent implements a virtual gear shifting mechanism that dynamically adjusts the relationship between control trigger input and rotor power output based on current velocity. The control system continuously adapts the effective gear ratio, allowing smooth transitions between low and high speeds by modifying how control inputs are translated into rotor commands, rather than using fixed mechanical gears

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system changes the control parameters (acceleration gains, power distribution ratios) based on the current operating state and velocity. By dynamically adjusting these parameters, the system achieves smooth speed transitions without requiring complex mechanical gear changes, resolving the contradiction between adaptability and complexity

Inventive Principle:

Principle #35Parameter changes

2Productivity

If high acceleration is applied during speed transitions, then the UAV reaches target speed faster, but altitude instability and overshoot occur

Engineering Contradiction:

Improvespeed transition speedVSAvoidaltitude stability

Core Design Contradiction:

ProductivityVSStability of the object's composition

Solution Approach 1:

The patent employs PID (Proportional-Integral-Derivative) control that continuously monitors altitude, velocity, and control input, then adjusts rotor power commands in real-time. This feedback mechanism detects altitude deviations during acceleration and automatically compensates, allowing rapid speed transitions while maintaining altitude stability and preventing overshoot

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The control system anticipates potential altitude instability by applying damping factors and adjusting acceleration profiles before overshoot occurs. The PID controller's derivative term specifically predicts future error trends and applies counteracting force in advance, cushioning against altitude instability during rapid speed transitions

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

3Loss of time

If proportional control only is used, then the control system is simple, but convergence time to target point is excessive

Engineering Contradiction:

Improveconvergence timeVSAvoidcontrol algorithm complexity

Core Design Contradiction:

Loss of timeVSDevice complexity

Solution Approach 1:

The system performs preliminary calculations to determine optimal acceleration profiles and power distribution before executing speed transitions. By pre-computing the ideal control commands based on current state and desired target, the system achieves rapid convergence without requiring complex real-time adjustments, reducing both time loss and control complexity

Inventive Principle:

Principle #10Preliminary action

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

This solution enables UAVs to maintain smooth flight across a wide range of speeds, minimizing convergence time and overshoot, and ensuring stable control by continuously adapting to changes in velocity and throttle input, enhancing pilot experience and operational safety.

Implementation Method 1

the detecting a change in position of a control trigger may be carried out by a hall effect sensor that may be configured to translate a control trigger pressure value into an acceleration value

Methodology Applied

Scientific EffectHall effect: Hall Effect

Data Source

PatentUS20240085927A1Methods and systems for adaptive UAV flight controls for smooth transitions between various speeds and accelerations

Publication Date: 2024.03.14 XTEND REALITY EXPANSION LTD

AI summary

Embodiments of the present disclosure may include a method for providing adaptive speed control of an unmanned aerial vehicle (UAV) in transitions between velocities, and between accelerations, the method includes determining an initial velocity of a UAV. Embodiments may also include detecting a change in position of a control trigger. In some embodiments, the control trigger may be operable to control acceleration of the UAV. In some embodiments, the change in position of the control trigger signals a desired positive acceleration or a desired negative acceleration of the UAV. Embodiments may also include increasing or decreasing power to one or more rotors of the UAV based on the initial velocity and the detected change in position of the trigger.