Inflatable Aircraft Recovery System for Confined Space Capture

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Solution Overview

Problem

Existing unmanned aircraft recovery systems are difficult to install and operate in cramped spaces, such as small boats or vehicles, and require improvements in effectiveness for capturing aircraft with vertically oriented flexible recovery lines.

Innovation Solution

An inflatable aircraft recovery system with a vertically oriented landing pocket and guidance system, comprising first and second inflatable portions that guide and capture the aircraft, absorbing landing forces and allowing for quick deployment and recovery in various environments.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If a vertically oriented flexible recovery line is used to capture the aircraft, then the system can operate in cramped spaces, but the effectiveness of aircraft recovery is insufficient

Engineering Contradiction:

Improveoperation in cramped spacesVSAvoideffectiveness of aircraft recovery

Core Design Contradiction:

Ease of operationVSReliability

Solution Approach 1:

The patent employs flexible inflatable portions that can be deployed vertically in confined spaces. These inflatable structures provide a compliant yet effective capture mechanism that adapts to the aircraft's impact, combining the space efficiency of flexible deployment with the reliability of controlled inflation for reliable aircraft recovery.

Inventive Principle:

Principle #30Flexible shells and thin films

2Productivity

If an inflatable recovery system is used, then quick deployment and recovery are enabled, but the system complexity increases

Engineering Contradiction:

Improvedeployment speedVSAvoidsystem complexity

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The recovery system is divided into multiple separate inflatable portions that can be independently deployed and inflated. This segmentation allows each component to be simple in design while the collective system achieves rapid deployment capability, reducing overall complexity compared to a single complex inflatable structure.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The inflatable portions are pre-positioned and can be rapidly inflated upon aircraft approach. This preliminary positioning combined with on-demand inflation enables quick deployment without requiring complex real-time adjustment mechanisms, thereby reducing system complexity while maintaining high productivity.

Inventive Principle:

Principle #10Preliminary action

3Force

If the recovery system captures the aircraft with high force, then the capture is effective, but damage to delicate components increases

Engineering Contradiction:

Improvecapture forceVSAvoiddamage to delicate components

Core Design Contradiction:

ForceVSObject-affected harmful factors

Solution Approach 1:

The inflatable portions are designed to inflate progressively upon aircraft contact, providing initial cushioning that absorbs impact energy. This beforehand cushioning effect protects delicate aircraft components by gradually decelerating the aircraft rather than applying sudden high force, thus reducing damage while maintaining effective capture.

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

Solution Approach 2:

The system controls the inflation pressure and rate of the inflatable portions to optimize the capture force profile. By dynamically adjusting these parameters, the system achieves effective capture with controlled force application that minimizes damage to delicate components while ensuring reliable aircraft recovery.

Inventive Principle:

Principle #35Parameter changes

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 enables efficient and effective recovery of unmanned aircraft in confined spaces, minimizing damage to delicate components and allowing for rapid deployment and reuse across different aircraft configurations without requiring extensive modifications.

Implementation Method 1

The first and second inflatable portions actively deform as the aircraft's landing forces are absorbed

Methodology Applied

Scientific EffectDeformation: Deformation

Implementation Method 2

at least a portion of the gas is discharged via one-way valves as the aircraft recovery system absorbs the aircraft's landing forces

Methodology Applied

Scientific EffectGas discharge: Depressurisation

Data Source

PatentUS7798445B2Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft

Publication Date: 2010.09.21 INSITU INC

AI summary

Systems and methods for recovering unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft recovery system for recovering an unmanned aircraft in flight in accordance with one embodiment of the disclosure, for example, can include an inflatable aircraft recovery system having an inflatable portion with a generally vertical orientation. The inflatable portion can also include a landing pocket extending at least partially therethrough. The landing pocket is sized to receive at least a portion of a fuselage of the aircraft. The aircraft recovery system can also include a guidance system at least proximate to the landing pocket and positioned to guide the aircraft toward the landing pocket.