Propeller Blade Airbag System for Impact Energy Absorption
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Solution Overview
Problem
Propeller blades in aircraft engines pose a hazard when they break or are released, causing damage to the aircraft structure and systems, and existing solutions do not adequately address the risk of blade impact during flight.
Innovation Solution
Integration of an airbag system within the propeller blade, including a gas generator, detecting system, and frangible lines to inflate and deploy bags outside the blade upon detection of a rupture, minimizing impact damage by acting as an energy absorber and aerodynamic brake.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If an airbag system is integrated inside the propeller blade, then the damage caused to the aircraft during blade impact is minimized, but the device complexity increases
Solution Approach 1:
An airbag system is integrated inside the propeller blade that inflates automatically upon blade release to cushion and absorb impact energy. The airbag is positioned to deploy outward from the blade interior, providing a compliant barrier between the blade structure and the aircraft fuselage, thereby minimizing damage during unintended blade release events
Solution Approach 2:
The airbag system is nested within the existing propeller blade structure. The airbag is contained inside the blade's internal volume, utilizing the blade's own structural envelope. This nesting approach allows the safety system to be integrated without adding external components, thus limiting the increase in device complexity while still providing effective impact protection
2Reliability
If a detecting system and trigger are added to activate the airbag, then the reliability of blade release detection is improved, but the device complexity increases
Solution Approach 1:
The blade incorporates a self-monitoring capability through strain gauges or similar sensors that directly detect structural changes indicating blade release. The detection system is integrated into the blade's load path, allowing it to sense release conditions autonomously without requiring external monitoring equipment. This self-service approach improves reliability while minimizing the addition of complex external control systems
Solution Approach 2:
A feedback mechanism is implemented where strain sensors continuously monitor the blade's structural integrity and transmit signals to a trigger system. When the sensors detect patterns consistent with blade release (such as sudden load changes or vibration signatures), they automatically trigger the airbag inflation sequence. This closed-loop feedback system ensures reliable detection and response while maintaining relatively simple system architecture
3Ease of manufacture
If frangible lines are provided in the blade skin, then the ease of manufacture is improved, but the strength of the blade skin is reduced
Solution Approach 1:
Frangible lines are introduced as localized features at specific positions on the blade skin where controlled separation is desired. These lines are not distributed uniformly but are strategically placed in areas where blade skin failure would facilitate airbag deployment or where controlled separation would occur during blade release. By concentrating the frangible features only where needed, the overall strength of the blade skin is minimized only in those specific locations, while the rest of the skin maintains full structural integrity
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 solution effectively reduces damage and risk during blade release by deploying airbags to absorb energy and reduce impact velocity, ensuring continued safe flight and landing while maintaining compatibility with conventional aircraft designs.
Implementation Method 1
The airbag system is contained inside the blade and includes at least one bag and at least one gas generator, wherein the at least one gas generator is in fluid communication with at least one bag for inflating the bag
Implementation Method 2
The disclosure provides an airbag system integrated inside the blade for minimizing the damage caused to the aircraft when the blade is partially or entirely released
Implementation Method 3
the blade of the disclosure is configured for that the bag reaches a fully opened condition outside the blade
Data Source
AI summary
The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.