Distributed-Propulsion VTOL Aircraft for Repeatable EDL Trajectories

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Solution Overview

Problem

Existing aircraft platforms are unable to reliably simulate the entry-descent-landing (EDL) flight trajectories required for testing and validating sensors for space missions, particularly at high ground speeds and low altitudes, lacking the necessary versatility and repeatability for effective sensor validation.

Innovation Solution

A multi-mode flight capable aircraft with distributed propulsion, including vertical takeoff and landing (VTOL), hover, rapid descent, forward, and backward flight modes, equipped with an avionics system to transition between these modes and control flight surfaces, using propellers with variable pitch blades and drag flaps for enhanced maneuverability.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If a rocket is used to produce flight trajectories similar to EDL stages, then the required flight trajectories can be achieved, but the cost increases, risk levels increase, and repeatability decreases

Engineering Contradiction:

Improveflight trajectory capabilityVSAvoidrepeatability

Core Design Contradiction:

Adaptability or versatilityVSReliability

Solution Approach 1:

The aircraft is designed with multi-mode flight capabilities including VTOL, forward flight, backward flight, hover, and rapid descent modes, allowing a single platform to replicate multiple EDL trajectory phases repeatedly. This multi-functionality enables consistent reproduction of test conditions without requiring expensive rocket systems.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The aircraft employs a distributed propulsion system with multiple propellers that can be independently controlled to dynamically adjust flight modes and trajectories. This dynamic control capability allows the aircraft to transition between different flight phases (VTOL, forward flight, hover, rapid descent) to simulate various EDL conditions with high repeatability.

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If a rocket is used to produce flight trajectories similar to EDL stages, then the required flight trajectories can be achieved, but the cost increases and risk levels increase

Engineering Contradiction:

Improveflight trajectory capabilityVSAvoidcost

Core Design Contradiction:

Adaptability or versatilityVSEase of manufacture

Solution Approach 1:

The patent employs a conventional aircraft platform with reusable components (propellers, wings, control surfaces) that can be manufactured at lower cost compared to rocket systems. The aircraft's ability to perform multiple flight modes with a single platform eliminates the need for expensive rocket launches while maintaining the capability to simulate EDL trajectories.

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

Solution Approach 2:

By designing an aircraft that can perform VTOL, forward flight, backward flight, hover, and rapid descent modes, the system achieves multi-functionality that replaces the need for multiple separate systems (rockets for EDL simulation, conventional aircraft for other tests). This universal platform reduces overall system cost while maintaining trajectory capability.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Ease of manufacture

If conventional aircraft platforms are used, then costs are reduced, but they cannot meet the demanding flight trajectory and performance requirements for testing EDL stages

Engineering Contradiction:

ImprovecostVSAvoidflight trajectory capability

Core Design Contradiction:

Ease of manufactureVSAdaptability or versatility

Solution Approach 1:

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The aircraft is designed with multi-mode flight capabilities including VTOL, forward flight, backward flight, hover, and rapid descent modes, allowing a single platform to replicate multiple EDL trajectory phases. This multi-functionality enables the conventional aircraft to meet the demanding flight trajectory requirements for EDL testing.

Inventive Principle:

Principle #6Universality (Multi-functionality)

4Productivity

If limited data availability is accepted during EDL sensor validation, then testing can proceed with existing platforms, but sensor validation and verification are compromised

Engineering Contradiction:

Improvedata availabilityVSAvoidsensor validation quality

Core Design Contradiction:

ProductivityVSReliability

Solution Approach 1:

The aircraft enables continuous and repeatable execution of EDL trajectory tests through its multi-mode flight capabilities. By able to perform VTOL, forward flight, backward flight, hover, and rapid descent modes on demand, the system provides continuous data collection opportunities without the limitations of rocket-based systems, thereby improving both data availability and sensor validation quality.

Inventive Principle:

Principle #20Continuity of useful 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 precise simulation of EDL trajectories, allowing frequent testing of sensors under challenging conditions, improving data availability and reducing operational costs by duplicating the flight profiles needed for lunar and planetary landings.

Implementation Method 1

a distributed propulsion system having a first pair of propellers connected to the horizontal main wing and a second pair of propellers connected to the vertical cross-wing

Methodology Applied

Scientific EffectThrust generation: Jet

Implementation Method 2

a horizontal main wing connected to the fuselage, and a vertical cross-wing arranged orthogonally with respect to the horizontal main wing

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Implementation Method 3

the flight control surfaces may be arranged on the vertical cross-wing include drag flaps

Methodology Applied

Scientific EffectAerodynamic drag: Drag

Implementation Method 4

An empennage assembly is also connected to the fuselage. Flight control surfaces are arranged on the empennage assembly, the vertical cross-wing, and the horizontal main wing

Methodology Applied

Scientific EffectMoment generation: Fin

Implementation Method 5

an unpowered rapid descent mode

Methodology Applied

Scientific EffectGravity: Gravitation

Data Source

PatentUS12612191B2VTOL aircraft capable of flying forward and backward

Publication Date: 2026.04.28 UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR NAT AERONAUTICS & SPACE ADMINISTRATION

AI summary

An aircraft includes an onboard power supply, an empennage assembly, and a horizontal main wing each connected to a fuselage, and a vertical cross-wing arranged orthogonally with respect to the main wing. Flight control surfaces are arranged on the empennage assembly, vertical cross-wing, and horizontal main wing. A distributed propulsion system includes a first pair of propellers connected to the horizontal main wing and a second pair of propellers connected to the vertical cross-wing. Each of the propellers is connected to and powered by the power supply. Each propeller forms an acute canting angle with respect to an axis of the particular horizontal main wing or the vertical cross-wing to which the propeller is connected. The flight modes may include vertical takeoff and landing (VTOL), hover mode, rapid descent, and forward and backward flight modes. The propellers are unpowered during the rapid descent mode.