Autonomous Electric Aircraft Layout for Low-Drag Regional Flight

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Solution Overview

Problem

Existing unmanned aircraft systems lack efficient designs that integrate advanced aerodynamics, autonomous control systems, and passenger or cargo capacity while minimizing drag and weight, and often require human pilots, increasing operational costs.

Innovation Solution

The design of an electric autonomous aircraft with a composite semi-monocoque fuselage, low-drag wing planform, and pusher propellers, integrated avionics, and autonomous control systems, eliminating the need for onboard pilots and enabling remote operation.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If human pilots are required for operation, then control and decision-making capability is improved, but operational costs and device complexity increase

Engineering Contradiction:

Improvecontrol capabilityVSAvoidoperational complexity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The aircraft implements autonomous control systems that enable the vehicle to pilot itself without human intervention. Sensors, processors, and actuators work together to automatically control flight parameters, eliminating the need for onboard pilots and reducing operational complexity while maintaining full control capability

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The patent replaces the mechanical system of human pilots with an automated control system comprising sensors, processors, and actuators. This substitution eliminates human operational requirements while maintaining or enhancing control precision and decision-making capability through electronic and software-based systems

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Strength

If traditional aircraft design is used, then structural integrity is improved, but drag and weight increase

Engineering Contradiction:

Improvestructural integrityVSAvoidaircraft weight

Core Design Contradiction:

StrengthVSWeight of moving object

Solution Approach 1:

The aircraft employs composite materials in its airframe construction, combining materials with different properties to achieve optimal strength-to-weight ratios. This allows the structure to maintain integrity while significantly reducing overall weight compared to traditional metallic constructions

Inventive Principle:

Principle #40Composite materials

Solution Approach 2:

The patent implements a blended wing body design with curved, aerodynamic surfaces that eliminate traditional sharp edges and corners. This streamlined geometry reduces drag while maintaining structural strength through distributed stress paths in the curved surfaces

Inventive Principle:

Principle #14Spheroidality (Curvature)

3Strength

If traditional aircraft design is used, then structural integrity is improved, but drag increases

Engineering Contradiction:

Improvestructural integrityVSAvoiddrag

Core Design Contradiction:

StrengthVSObject-affected harmful factors

Solution Approach 1:

The aircraft features a blended wing body design with smooth, curved surfaces that eliminate traditional sharp edges and corners. This streamlined geometry reduces aerodynamic drag by promoting laminar flow and minimizing turbulence, while the curved surfaces maintain structural integrity through distributed stress paths

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The blended wing body structure serves multiple functions simultaneously: it provides structural support, generates lift, and optimizes aerodynamic performance. This multi-functionality eliminates the need for separate structural and aerodynamic components, reducing overall drag while maintaining strength

Inventive Principle:

Principle #6Universality (Multi-functionality)

4Use of energy by moving object

If battery assembly is placed in fuselage, then power supply is improved, but weight distribution and drag may worsen

Engineering Contradiction:

Improvepower supply capacityVSAvoidweight distribution

Core Design Contradiction:

Use of energy by moving objectVSWeight of moving object

Solution Approach 1:

The battery assembly is relocated from the fuselage to the wing structure, utilizing the three-dimensional space within the wings. This dimensional relocation optimizes weight distribution by positioning mass closer to the center of gravity and improves aerodynamics by streamlining the fuselage contours

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

Data Source

PatentUS12492020B2Electric autonomous aircraft

Publication Date: 2025.12.09 JOBY AERO INC

AI summary

An aircraft includes a fuselage that includes a nose portion, a cabin portion, an underwing portion, and an aft portion. The nose portion includes sensors that generate sensor data. The cabin portion is aft of the nose portion and includes a passenger cabin. The underwing portion is aft of the cabin portion and includes a wing attachment region and a battery bay. The aft portion is aft of the underwing portion. A wing assembly including motor mounts and control surfaces is attached to the wing attachment region such that the underwing portion of the fuselage is located under the wing assembly. A tail assembly is attached to the aft portion. The electric motors are attached to motor mounts such that the propellers are in a pusher configuration facing rearward. An autonomous control system controls the electric motors and control surfaces based on the sensor data.