Aircraft In-Flight Stabilization for Component Failure Response
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Solution Overview
Problem
Electrically propelled aircraft, such as eVTOLs, face challenges in maintaining stability and safety during flights due to potential component failures, which can lead to catastrophic outcomes like loss of control or airframe breakup, with existing mitigation methods like ballistic parachutes and redundancy systems being inadequate.
Innovation Solution
A system comprising flight components mechanically coupled to the aircraft, sensors to detect failures, and a vehicle controller that generates and initiates mitigating responses to ensure safe landing, utilizing a heuristic database and machine-learning algorithms to adapt flight maneuvers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional mitigation methods like ballistic parachutes and redundancy systems are used, then some level of safety is provided, but they are inadequate to prevent catastrophic outcomes from component failures
Solution Approach 1:
The system dynamically adjusts flight control parameters and stabilizer configurations in real-time based on detected component failures. The vehicle controller continuously monitors flight components and modifies control surface positions, thrust distribution, and flight path to maintain stability despite failures, transforming a static safety system into an adaptive one.
Solution Approach 2:
The system implements continuous feedback loops where sensors monitor flight component status and aircraft state, the vehicle controller processes this information to detect failures, and the system automatically adjusts control surfaces and thrust to compensate. This closed-loop feedback enables real-time mitigation of component failures without pilot intervention.
2Adaptability or versatility
If the aircraft operates with multiple flight components, then functionality is maintained, but the risk of component failure increases
Solution Approach 1:
The system performs preliminary actions by pre-configuring multiple flight components and control pathways before failures occur. The vehicle controller is pre-programmed with failure detection algorithms and mitigation strategies, so when a component fails, the system can immediately switch to alternative control modes using remaining functional components, preventing catastrophic outcomes.
Solution Approach 2:
The system changes operational parameters dynamically based on component status. When a flight component fails, the vehicle controller modifies control surface deflections, thrust vectoring angles, and flight path parameters to compensate for the loss, allowing the aircraft to maintain safe operation with reduced functionality.
3Reliability
If real-time failure detection and mitigation is implemented, then safety is improved, but system complexity and computational requirements increase
Solution Approach 1:
The system provides self-service through automated failure detection and mitigation without requiring external intervention or complex pilot procedures. The vehicle controller autonomously monitors flight components, detects failures using pre-programmed algorithms, and executes compensation maneuvers, reducing the need for complex human-machine interfaces and pilot training.
Solution Approach 2:
The vehicle controller serves multiple functions: it monitors flight component status, detects failures, calculates mitigation strategies, and controls multiple flight surfaces and thrust elements. This multi-functionality consolidates what could be separate complex systems into a single integrated controller, reducing overall system complexity.
Data Source
AI summary
A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.