Close Formation Flight Control Using Laser Vortex Sensing

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Solution Overview

Problem

Close formation flight is challenging due to difficulties in maintaining accurate relative positions between aircraft, as existing flight control systems struggle to account for wind effects on wingtip vortices, leading to unpredictable vortex positions and increased collision risks.

Innovation Solution

An advanced flight control system equipped with sensors for 3D airflow measurement and a processor to analyze data, create computer models of airflow patterns, and adjust aircraft positions based on real-time vortex sensing, allowing for precise alignment and maintenance of close formation flight.

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 flight control system that uses optical sensing (laser-based vortex detection) to detect and track wingtip vortices. This substitution enables the system to achieve both safety by avoiding vortices and close formation flight capability by precisely controlling aircraft positioning in the upwash region.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent introduces an intermediary vortex detection and tracking system that acts as a mediator between the aircraft and the wake turbulence. This system uses laser-based sensors to detect vortex positions and provides real-time feedback to the flight control system, enabling safe close formation flight by maintaining awareness of vortex locations while positioning the aircraft in beneficial upwash regions.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Loss of energy

If aircraft are positioned close together to maximize aerodynamic benefits, then fuel consumption is reduced, but collision risk increases

Engineering Contradiction:

Improvefuel consumptionVSAvoidcollision risk

Core Design Contradiction:

Loss of energyVSReliability

Solution Approach 1:

The patent implements a feedback-based flight control system that continuously monitors the position of wingtip vortices relative to the aircraft and automatically adjusts the aircraft's position to maintain safe separation while remaining in the upwash region. This real-time feedback mechanism enables the system to maximize aerodynamic benefits by keeping aircraft close together while preventing collisions through automated vortex avoidance.

Inventive Principle:

Principle #23Feedback

3Productivity

If gradient peak-seeking approach is used to optimize formation position, then aerodynamic performance is improved, but response time becomes too slow for fast-changing conditions

Engineering Contradiction:

Improveaerodynamic performanceVSAvoidresponse time

Core Design Contradiction:

ProductivityVSSpeed

Solution Approach 1:

The patent uses preliminary action by pre-calculating optimal formation positions based on predicted vortex locations and wind conditions. The flight control system proactively adjusts aircraft positioning before the aircraft actually enter suboptimal regions, enabling faster response to changing conditions while maintaining aerodynamic performance. This predictive approach eliminates the need for slow gradient-based optimization during flight.

Inventive Principle:

Principle #10Preliminary action

4Productivity

If wingtip vortices are allowed to trail behind leading aircraft, then aerodynamic benefits are achieved, but position uncertainty due to wind effects increases

Engineering Contradiction:

Improveaerodynamic benefitsVSAvoidvortex position accuracy

Core Design Contradiction:

ProductivityVSMeasurement precision

Solution Approach 1:

The patent replaces conventional estimation methods for vortex positioning with direct optical sensing using laser-based detectors. This substitution enables precise measurement of vortex positions and wind-induced displacements in real-time, eliminating the uncertainty that plagues estimation-based systems while maintaining the aerodynamic benefits of close formation flight.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

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 close formation flight by directly sensing vortex positions, reducing collision risks and enhancing aerodynamic benefits such as reduced drag and increased lift, thereby improving aircraft endurance and range.

Implementation Method 1

a first plurality of sensors coupled to the first aircraft for collecting measurements characterizing airflow near the first aircraft during close formation flight

Methodology Applied

Scientific EffectPitot tube measurement: Pitot Tube

Data Source

PatentUS9870005B2Apparatus for close formation flight

Publication Date: 2018.01.16 SUNLIGHT AEROSPACE INC

AI summary

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, an apparatus for close formation flight, comprises a plurality of sensors for collecting measurements characterizing airflow near an aircraft. The plurality of sensors are attachable to at least one of a wing, fuselage, or tail of the aircraft, and the measurements provide information about airflow velocity in a direction transverse to a direction of the aircraft flight.