UAV Distributed Propulsion Blown Control Surfaces

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Solution Overview

Problem

Current VTOL UAVs face limitations in range due to high energy consumption and propulsion system weight, making them less suitable for carrying heavier payloads over longer distances, while conventional STOL aircraft require significant infrastructure and increased structural weight for short takeoffs and landings.

Innovation Solution

The implementation of distributed electric propulsion and blown wing and control surfaces in a fixed-wing UAV design, which increases lift and reduces structural weight, allowing for shorter takeoffs and landings with improved cruise efficiency and payload capacity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If VTOL capability is implemented in UAVs, then the ability to takeoff and land vertically is improved, but the range and payload capacity deteriorate due to high energy consumption and propulsion system weight

Engineering Contradiction:

ImproveVTOL capabilityVSAvoidenergy consumption

Core Design Contradiction:

Ease of operationVSUse of energy by moving object

Solution Approach 1:

The propulsion system is divided into multiple distributed electric propulsion units (DEP) along the wingspan, with each unit independently controllable. This segmentation allows selective activation of propulsion units during different flight phases, reducing overall energy consumption compared to a single VTOL propulsion system.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The control surfaces are designed to be dynamically adjusted using blown control surfaces, where high-speed airflow from propulsion units deflects over the control surfaces to provide aerodynamic control forces. This dynamic control mechanism reduces the need for heavy mechanical control systems while maintaining maneuverability.

Inventive Principle:

Principle #15Dynamics

2Ease of operation

If VTOL capability is implemented in UAVs, then vertical takeoff and landing is enabled, but the payload capacity deteriorates due to significant fraction of aircraft mass dedicated to hover propulsion system

Engineering Contradiction:

Improvevertical takeoff and landingVSAvoidpropulsion system weight

Core Design Contradiction:

Ease of operationVSWeight of moving object

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The control surfaces utilize blown control surfaces where high-speed airflow from propulsion units is deflected over the control surfaces to generate aerodynamic control forces. This parameter change in control methodology reduces the mechanical weight of the control system while maintaining effectiveness.

Inventive Principle:

Principle #35Parameter changes

3Speed

If conventional STOL aircraft design is used, then short takeoff and landing capability is achieved, but structural weight increases and ground support infrastructure requirements increase

Engineering Contradiction:

Improvetakeoff and landing speedVSAvoidstructural weight

Core Design Contradiction:

SpeedVSWeight of moving object

Solution Approach 1:

The patent replaces conventional mechanical high-lift devices and structural reinforcements with distributed electric propulsion units that generate thrust directly. This substitution eliminates the need for heavy mechanical STOL modifications while achieving short takeoff and landing capability through aerodynamic thrust vectoring.

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

This configuration enables UAVs to carry 1.9 to 2.2 times the payload of VTOL aircraft for the same range and speed, while being lighter and smaller, and reduces the need for extensive ground support infrastructure, facilitating more efficient package delivery missions.

Implementation Method 1

The fixed-wing aircraft includes a plurality of distributed electric propulsion units extend below the fixed- wings

Methodology Applied

Scientific EffectPropeller thrust: Jet

Implementation Method 2

blown wing and control surfaces in a fixed-wing UAV design, which increases lift

Methodology Applied

Scientific EffectBernoulli effect: Bernoulli Effect

Data Source

PatentUS12091173B2UAV with distributed propulsion and blown control surfaces

Publication Date: 2024.09.17 WING AVIATION LLC

AI summary

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of fixed wings attached to the fuselage, a tail assembly attached to an aft portion of the fuselage and including a pair of stabilizers, a plurality of distributed propulsion units having first propellers that rotate about first rotational axes positioned below the fixed wings, and a plurality of tail propulsion units having second propellers that rotate about second rotational axes each positioned inline with one of the stabilizers. The first propellers are mounted fore of the fixed wings and the second propellers are mounted fore of a corresponding one of the stabilizers. Three or more of the distributed propulsion units are mounted to each of the fixed wings.