Rotating Thrust Array for VTOL to Wing-Borne Transition

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Solution Overview

Problem

Military organizations require small, lightweight unmanned aircraft systems that can transition between thrust-borne lift for vertical takeoff and landing and wing-borne lift for forward flight, capable of continuous operation in adverse conditions, providing real-time situational awareness and easy deployment without burdening soldiers.

Innovation Solution

An unmanned aircraft system with a flying wing design featuring a two-dimensional distributed thrust array, comprising motor mounts with propulsion assemblies and an electric power system, allowing for independent control of thrust and flight configurations, enabling transition between VTOL and flying wing orientations, and a compact storage configuration for ease of transport.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Use of energy by moving object

If a conventional fixed-wing aircraft design is used, then wing-borne lift efficiency is improved, but the aircraft cannot perform vertical takeoff and landing

Engineering Contradiction:

Improvewing-borne lift efficiencyVSAvoidVTOL capability

Core Design Contradiction:

Use of energy by moving objectVSAdaptability or versatility

Solution Approach 1:

The motor mounts are designed to be rotatable relative to the airframe, allowing the propulsion assemblies to dynamically change orientation between a configuration perpendicular to the leading edge (for VTOL) and a configuration aligned with the longitudinal axis (for forward flight). This dynamic reconfiguration enables the aircraft to adapt between thrust-borne and wing-borne lift modes.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The propulsion assemblies serve multiple functions: they provide thrust for vertical takeoff and landing when positioned perpendicular to the leading edge, and they provide pull thrust for forward flight when rotated to align with the longitudinal axis. The same hardware configuration enables both VTOL and conventional forward flight operations.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Ease of operation

If a distributed thrust array with multiple propulsion assemblies is implemented, then flight control authority is improved, but device complexity increases

Engineering Contradiction:

Improveflight control authorityVSAvoidnumber of propulsion assemblies

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The thrust array is segmented into multiple independently controllable propulsion assemblies distributed across the airframe. Each assembly can be controlled individually to provide differential thrust for precise pitch, roll, and yaw control, while the segmented design allows the system to achieve complex flight maneuvers through coordinated operation of simpler individual components.

Inventive Principle:

Principle #1Segmentation

3Power

If the motor mounts are positioned to extend perpendicular to the leading edge for optimal VTOL performance, then thrust-borne lift capability is improved, but the aircraft width increases

Engineering Contradiction:

Improvethrust-borne lift capabilityVSAvoidaircraft width

Core Design Contradiction:

PowerVSArea of moving object

Solution Approach 1:

Inventive Principle:

Principle #15Dynamics

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

The system provides efficient airspeed control, pitch, roll, and yaw authority in both flight modes, enabling prolonged operation and real-time data delivery, while being compact and lightweight for soldier-borne deployment.

Implementation Method 1

A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge, respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof.

Methodology Applied

Scientific EffectThrust generation: Jet

Implementation Method 2

An unmanned aircraft system operable for wing-borne lift in a flying wing orientation

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Data Source

PatentUS11866205B2Flying wing aircraft having a two-dimensional thrust array

Publication Date: 2024.01.09 TEXTRON INNOVATIONS INC

AI summary

An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.