Lightning HIRF Protection Component Evaluation System
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Solution Overview
Problem
Current aircraft design methodologies do not effectively integrate the long-term durability and maintenance of lightning and high-intensity radiated field (HIRF) protection components, leading to increased product support expenses, redesign needs, and extensive maintenance, particularly in carbon fiber reinforced plastic (CFRP) aircraft which lack inherent shielding capabilities.
Innovation Solution
A computer-based system and method for evaluating the effectiveness of lightning/HIRF protection components by storing design service life goals, critical characteristics, and potential degradation in a database, allowing for continuous functionality assessment and early identification of maintenance needs, thereby reducing maintenance and redesign requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If carbon fiber reinforced plastic (CFRP) is used for aircraft construction, then weight is reduced and manufacturing costs are reduced, but shielding capabilities against HIRF and lightning effects are lost
Solution Approach 1:
The patent applies composite materials by integrating lightning protection components directly into the CFRP structure during manufacturing. The protection components are embedded within the composite material layers, creating a multi-functional composite structure that maintains both the weight benefits of CFRP and the shielding capabilities against lightning and HIRF effects.
Solution Approach 2:
The patent implements multi-functionality by designing protection components that serve dual purposes: they provide structural support as part of the CFRP airframe while simultaneously providing electromagnetic shielding and lightning protection. This eliminates the need for separate shielding systems, maintaining weight efficiency while ensuring reliability.
2Productivity
If initial aircraft design practices do not account for long-term health of HIRF and lightning effects protection components, then product support expenses increase and risk of rework/redesign increases
Solution Approach 1:
The patent applies preliminary action by incorporating durability testing and long-term performance evaluation into the initial design and manufacturing phases. Protection components are tested under simulated aging conditions and environmental stress before final assembly, ensuring they will maintain reliability throughout the aircraft's service life without requiring later rework.
Solution Approach 2:
The patent implements feedback mechanisms by establishing monitoring systems that track the performance and condition of protection components throughout the aircraft's operational life. This continuous feedback allows for proactive maintenance and verification of continued airworthiness, preventing expensive rework by identifying issues before they compromise safety.
3Reliability
If extensive scheduled maintenance is performed to determine continued effectiveness of protection components, then maintenance costs and engineering labor hours increase
Solution Approach 1:
The patent applies self-service by designing protection components with built-in health monitoring capabilities and self-diagnosis features. The components automatically track their own condition, performance degradation, and effectiveness, eliminating the need for extensive manual inspections and maintenance interventions while ensuring continued reliability.
Solution Approach 2:
The patent replaces manual mechanical inspection systems with automated electronic monitoring and diagnostic systems. Sensors and embedded diagnostics continuously assess the condition of protection components, substituting time-consuming physical examinations with rapid electronic evaluations that maintain reliability verification while minimizing maintenance time and labor requirements.
Data Source
AI summary
A method for evaluating a lightning/HIRF protection effectiveness of a vehicle design is provided. The method is performed using a computer system coupled to a database. The method includes storing in the database design service life goals and critical characteristics for at least one lightning/HIRF protection component. The method also includes storing in the database a potential for degradation of the at least one component. The potential for degradation is based at least partially on a position where the component is to be installed. The method also includes determining continued functionality of the at least one component using the computer system to compare the vehicle design to the stored design service life goals.