Aircraft Airflow Vortex Sensing for Close Formation Flight

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Solution Overview

Problem

Current flight control systems for close formation flight are inadequate due to inaccuracies in estimating wingtip vortex positions, failure to account for wind effects, and sluggish response to changing conditions, making it difficult to maintain stable and safe close formation flight.

Innovation Solution

Implement a method involving airflow sensing and computer modeling to accurately track and predict wingtip vortex positions, using sensors and processors to collect and analyze data, and adjust aircraft positions accordingly, while accounting for wind influences and vortex dynamics.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional autopilot systems are used to avoid wake turbulence, then aircraft safety is improved, but close formation flight capability is lost

Engineering Contradiction:

Improveaircraft safetyVSAvoidclose formation flight capability

Core Design Contradiction:

ReliabilityVSAdaptability or versatility

Solution Approach 1:

The patent replaces conventional autopilot systems with an advanced adaptive flight control system that uses airflow sensors (hot-wire anemometers) to directly detect vortex positions and structures. This substitution enables the system to perceive wake turbulence rather than merely avoid it, allowing close formation flight while maintaining safety through real-time vortex tracking and adaptive control algorithms.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent introduces airflow sensors as intermediaries between the aircraft and wake turbulence. These sensors act as mediators that convert vortex structures into measurable airflow data, enabling the flight control system to understand and adapt to wake turbulence conditions rather than treating them as undetectable hazards.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Use of energy by moving object

If aircraft fly in close formation to reduce drag and fuel consumption, then energy efficiency is improved, but flight control difficulty increases

Engineering Contradiction:

Improvefuel consumptionVSAvoidflight control difficulty

Core Design Contradiction:

Use of energy by moving objectVSEase of operation

Solution Approach 1:

The patent implements a feedback mechanism where airflow sensors continuously measure vortex positions and structures, and this information is fed back to the adaptive flight control algorithm. The algorithm processes this feedback and adjusts control surfaces in real-time to maintain optimal formation positions, reducing flight control difficulty through closed-loop control while preserving energy efficiency benefits.

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The patent employs dynamic control algorithms that continuously adapt to changing vortex conditions and aircraft states. The flight control system is not static but dynamically adjusts control parameters based on real-time airflow measurements, making close formation flight easier to maintain while preserving the aerodynamic benefits of drag reduction.

Inventive Principle:

Principle #15Dynamics

3Use of energy by moving object

If gradient peak-seeking approach is used to maximize formation benefits, then fuel efficiency is improved, but response time increases

Engineering Contradiction:

Improvefuel efficiencyVSAvoidresponse time

Core Design Contradiction:

Use of energy by moving objectVSSpeed

Solution Approach 1:

The patent uses preliminary action by pre-computing optimal formation positions and vortex avoidance paths based on predicted vortex trajectories. The adaptive control algorithm anticipates future vortex positions and prepares control commands in advance, enabling faster response times while maintaining the fuel efficiency benefits of optimized formation flight.

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

Enables reliable and accurate maintenance of close formation flight, reducing aerodynamic disruptions and enhancing fuel efficiency and aircraft endurance by precise control of relative positions between aircraft.

Implementation Method 1

an airflow sensor, such as a hot-wire anemometer, is used to sense the vortex structure

Methodology Applied

Scientific EffectHot-wire anemometry:

Implementation Method 2

lift being generated by the wings and air rotating around the wingtips from the high pressure regions at the bottom of the wing to the low pressure regions at the top of the wing

Methodology Applied

Scientific EffectPressure differential lift:

Implementation Method 3

The pair of vortices generated by each aircraft is the result of lift being generated by the wings and air rotating around the wingtips

Methodology Applied

Scientific EffectVortex flow: Vortex Ring

Data Source

PatentUS10450083B2Methods of airflow vortex sensing and tracking

Publication Date: 2019.10.22 SUNLIGHT AEROSPACE INC

AI summary

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of sensing three dimensional (3D) airflow by an aircraft includes: collecting measurements characterizing airflow near the aircraft; analyzing the collected measurements; creating, by a processor, a computer model predicting one or more 3D airflow patterns parameter values based on the analyzing; obtaining one or more additional measurements characterizing airflow near an aircraft of the plurality of aircraft, and evaluating an error between an airflow parameter value predicted by the computer model and the one or more additional measurement.