In-Flight Aerodynamic Testing Using Interchangeable Wingsets

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Solution Overview

Problem

The conventional method of testing aircraft components and systems, especially those with integrated radar systems, is costly and time-consuming, requiring multiple prototype aircraft and posing engineering challenges due to the need for a common fuselage that can accommodate different wingset configurations and radar systems, which complicates the design and testing process.

Innovation Solution

Utilizing a pre-existing, fully engineered aircraft with a test station and attachment interface to mount and test different aerodynamic structures and wingset planforms, including those with conformal radar arrays, allowing for in-flight data collection without the need for multiple prototype aircraft, by leveraging existing systems like the Boeing E-3 Sentry AWACS aircraft.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If conventional full prototype testing is used, then testing accuracy is improved, but testing time and cost increase significantly

Engineering Contradiction:

Improvetesting accuracyVSAvoidtesting time

Core Design Contradiction:

Measurement precisionVSLoss of time

Solution Approach 1:

The patent segments the testing system into a pre-existing fully-engineered aircraft platform and separate interchangeable aerodynamic structure modules. This allows the complex system to be broken into testable components, where the proven aircraft platform supports various test configurations without requiring full prototype construction for each test case.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The pre-existing aircraft is designed with universal attachment interfaces that can accommodate multiple different aerodynamic structure configurations. This multi-functional capability allows a single aircraft platform to serve as the test bed for various wingset planforms and radar system integrations, eliminating the need for multiple specialized prototypes.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If conventional full prototype testing is used, then testing reliability is improved, but cost increases significantly

Engineering Contradiction:

Improvetesting reliabilityVSAvoidtesting cost

Core Design Contradiction:

ReliabilityVSQuantity of substance

Solution Approach 1:

The aircraft platform is fully engineered and tested in advance before being used as the test bed for aerodynamic structures. This preliminary action ensures the platform's reliability and certification are established beforehand, allowing subsequent aerodynamic structure tests to leverage this pre-validated platform without incurring the full cost of repeated prototype certifications.

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

Instead of constructing multiple full prototypes, the patent uses a single pre-existing aircraft as a reusable copy or surrogate for multiple test configurations. The aircraft serves as a faithful representation of the operational platform, allowing various aerodynamic structures to be tested in their intended environment without duplicating the entire aircraft for each test case.

Inventive Principle:

Principle #26Copying

3Adaptability or versatility

If a common fuselage is designed to accommodate different wingset configurations, then adaptability is improved, but device complexity increases

Engineering Contradiction:

ImproveadaptabilityVSAvoidengineering complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The attachment interface is designed with dynamic adjustability, allowing the aerodynamic structures to be mounted at different angles of incidence and configured in various orientations. This dynamic capability enables the same interface to accommodate multiple wingset planforms with different geometric requirements without redesigning the fuselage structure.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The patent introduces an intermediary attachment interface structure that mediates between the fixed fuselage and the variable aerodynamic configurations. This interface layer absorbs the complexity of adaptation, providing standardized mounting points and adjustment mechanisms that simplify the integration of different wingset and radar system combinations without modifying the core fuselage design.

Inventive Principle:

Principle #24Intermediary (Mediator)

Data Source

PatentUS7966872B2In-flight testing kits and methods for evaluating proposed aerodynamic structures for aircraft

Publication Date: 2011.06.28 THE BOEING CO

AI summary

In-flight testing methods and kits for in-flight testing of proposed aerodynamic structures are disclosed. The methods and kits involve a testing station carried on a pre-existing fully engineered and tested host aircraft. Interchangeable but differently configured aerodynamic structures may be carried upon the host aircraft, and existing systems of the host aircraft may be utilized to conduct the testing, avoiding time and cost associated with constructing fully operational demonstrator aircraft for testing purposes.