Split-Leg Landing Gear Venting for Compact VTOL Aircraft

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Solution Overview

Problem

Fixed-wing aircraft require runways for takeoff, limiting deployment locations and necessitating laborious assembly by trained operators, with a large footprint when landed, restricting rapid deployment and space efficiency.

Innovation Solution

Aircraft designed for vertical take-off and landing with a split-leg landing gear system at the aft, allowing disassembly into a compact stowed state for transport and rapid assembly using a cart system with actuation and control systems for efficient deployment.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Area of stationary object

If fixed-wing aircraft use conventional landing gear, then the aircraft can be landed, but the footprint is large and deployment locations are restricted

Engineering Contradiction:

Improvefootprint when landedVSAvoiddeployment location flexibility

Core Design Contradiction:

Area of stationary objectVSAdaptability or versatility

Solution Approach 1:

The landing gear is divided into two separate legs instead of a conventional single-strut design. Each leg can be independently positioned and configured, allowing the aircraft to land in restricted spaces while maintaining stability. The split-leg configuration reduces the overall footprint when landed compared to traditional gear arrangements.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The landing gear legs are configured to extend in different spatial dimensions rather than parallel to each other. This three-dimensional arrangement allows the aircraft to achieve a compact landed footprint while still providing adequate support and stability, enabling deployment in locations with space constraints.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Adaptability or versatility

If fixed-wing aircraft require assembly on site, then the aircraft can be deployed to remote locations, but the assembly process is laborious and requires trained operators

Engineering Contradiction:

Improvedeployment location flexibilityVSAvoidassembly speed

Core Design Contradiction:

Adaptability or versatilityVSProductivity

Solution Approach 1:

The aircraft is divided into modular components that can be transported separately and quickly assembled. The split-leg landing gear design itself is a modular component that can be attached to the airframe in a straightforward manner, reducing assembly complexity and time compared to integrated conventional gear systems.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The landing gear design incorporates features that facilitate self-assembly or minimal-assistance assembly. The modular construction allows operators with basic training to assemble the aircraft and its landing gear components using simple tools and procedures, reducing the need for highly trained technicians and speeding up the deployment process.

Inventive Principle:

Principle #25Self-service

3Adaptability or versatility

If fixed-wing aircraft are transported on larger vessels, then the aircraft can reach distant locations, but the aircraft size is restricted by vessel dimensional requirements

Engineering Contradiction:

Improvetransport capabilityVSAvoidaircraft size

Core Design Contradiction:

Adaptability or versatilityVSLength of moving object

Solution Approach 1:

The aircraft components, including the split-leg landing gear, are designed as separate modules that can be packed efficiently for transport. This segmentation allows the aircraft to be broken down into smaller pieces that fit within the dimensional constraints of cargo vessels, while still maintaining the capability to assemble a functional aircraft at the destination.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The landing gear and aircraft structure incorporate movable and adjustable components that can be configured for compact transport and expanded for operational use. This dynamic design allows the same structure to serve dual purposes: space-efficient packaging for transport and full functional configuration for flight operations.

Inventive Principle:

Principle #15Dynamics

4Device complexity

If conventional landing gear is used, then the structure is simple, but the footprint when landed is large

Engineering Contradiction:

Improvelanding gear structure complexityVSAvoidfootprint when landed

Core Design Contradiction:

Device complexityVSArea of stationary object

Solution Approach 1:

While the split-leg design adds some complexity compared to conventional gear, it achieves a significantly smaller landed footprint. The two separate legs can be positioned closer together and at different angles, creating a compact ground envelope that reduces the aircraft's footprint while maintaining structural integrity and load-bearing capacity.

Inventive Principle:

Principle #1Segmentation

Data Source

PatentUS12570400B1Landing gear structure and venting for vertical take-off dual-engine aircraft

Publication Date: 2026.03.10 ANDURIL IND INC

AI summary

The present application discloses an aircraft. The aircraft comprises (i) a first wing and a second wing, (ii) a fuselage disposed between the first wing and the second wing, and (iii) a first landing gear system disposed at an aft of the aircraft. The first landing gear system comprises a first leg and a second leg that are configured to at least partially rotate around an axis defined by a length of the first wing when the first leg and the second leg are transitioned to a deployed state or a stowed state. The first landing gear system comprises a first actuation system comprising at least a first actuator and a first shock absorber.