Aircraft Fuel Valve Failure Detection Using Torque and Encoder Feedback

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Solution Overview

Problem

Current methods for monitoring aircraft fuel valves are inadequate as they fail to accurately detect failures in the drive shaft and motor, leading to hidden failures that can affect operational availability and require frequent maintenance, and introducing additional sensors poses risks of short circuits.

Innovation Solution

The implementation of torque generation and position detection means in the fuel valve, which increase torque as the ball approaches stable positions, allowing for precise detection of the valve's position and generating signals to diagnose failures, integrated with a control system to analyze current drawn and generate warning messages.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If additional position sensors are added to the spherical ball to detect valve position accurately, then measurement precision is improved, but device complexity increases and risk of short circuits increases due to cables in fuel tank

Engineering Contradiction:
Improvevalve position detection accuracyVSAvoidnumber of sensors and cables
Core Design Contradiction:
Measurement precisionVSDevice complexity

Solution Approach 1:

The invention extracts the position detection function from separate sensors on the spherical ball and integrates it into the actuator's existing encoder. The encoder, which already tracks drive shaft position, is used to infer ball position through the known mechanical relationship between drive shaft rotation and ball orientation, eliminating the need for additional sensors in the fuel tank.

Inventive Principle:
Principle #2Taking out (Extraction)

Solution Approach 2:

The existing encoder in the actuator, originally designed for motor control, is made multi-functional by using it also for position detection. The same rotational position data from the encoder serves both motor control purposes and valve position monitoring, eliminating the need for dedicated position sensors.

Inventive Principle:
Principle #6Universality (Multi-functionality)

2Device complexity

If switches are used to monitor valve position, then device complexity is kept low, but reliability decreases due to electrical contact problems and undetected hidden failures

Engineering Contradiction:
Improvemonitoring system structureVSAvoidfailure detection accuracy
Core Design Contradiction:
Device complexityVSReliability

Solution Approach 1:

The invention implements continuous feedback by using the encoder to constantly monitor drive shaft position and comparing it with the expected position based on valve state. This feedback mechanism enables real-time detection of discrepancies indicating drive shaft failures, providing reliable failure detection without complex additional hardware.

Inventive Principle:
Principle #23Feedback

Solution Approach 2:

The invention replaces mechanical switches with electrical sensing using the encoder. Instead of mechanical contact switches that prone to failure, the electronic encoder provides contactless position detection, significantly improving reliability while maintaining simplicity.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

3Reliability

If maintenance operations are performed at regular intervals to detect hidden failures, then reliability is improved, but productivity decreases due to aircraft taking out of service

Engineering Contradiction:
Improvevalve operational statusVSAvoidaircraft availability
Core Design Contradiction:
ReliabilityVSProductivity

Solution Approach 1:

The invention performs preliminary detection of potential failures during normal operation by continuously monitoring drive shaft position through the encoder. By detecting anomalies before they cause actual valve failure, the system enables proactive maintenance scheduling that minimizes aircraft downtime and prevents catastrophic failures.

Inventive Principle:
Principle #10Preliminary action

Solution Approach 2:

The monitoring system uses the actuator's own encoder and control electronics to perform self-diagnosis of drive shaft integrity. The system monitors itself during normal operation without requiring external inspection equipment or taking the aircraft out of service, enabling continuous operational monitoring.

Inventive Principle:
Principle #25Self-service

Data Source

PatentUS8807161B2Device and method for detecting a failure in a powered valve
Publication Date: 2014.08.19 AIRBUS (SAS)
  • US8807161B2 patent drawing
  • US8807161B2 patent drawing
  • US8807161B2 patent drawing

AI summary

The disclosed embodiments relate to a fuel line valve for an aircraft, that includes a shell capable of rotation inside the valve body and connected to a driving shaft driven by an electric actuator. The valve further includes a torque generation means and position detection means. The torque generation means are connected to the shell and generate a torque that varies based on the position of said shell in the valve body on the driving shaft. The position detection means provide electric signals characterizing the positions of said driving shaft. The disclosed embodiments also relate to a method for diagnosing the operation of such a valve in order to detect a failure during the operation thereof, and to a device for implementing said method.