Aircraft Pressure Sensor Heater Assembly for Freezing Prevention
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Solution Overview
Problem
Aircraft engine pressure sensing systems are prone to failures due to freezing during flight, as existing methods like drainage weep holes and refrigerant-based vacuum pumps are ineffective in maintaining the system's temperature above the freezing point during flight.
Innovation Solution
A pressure sensing system incorporating a heater assembly that maintains the temperature of the pressure transducer and manifold above a predetermined level, using a temperature sensor and control circuit to manage heating elements, and employing thermal insulators to minimize heat loss, ensuring the system operates effectively despite ambient temperature drops.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of substance
If drainage weep holes are formed in the pressure lines to remove accumulated water, then water removal is improved, but the system cannot prevent freezing during flight
Solution Approach 1:
The heater assembly is activated before the aircraft enters cold environments or during flight to preemptively heat the pressure sensing system, preventing water accumulation from freezing before it can cause failures
Solution Approach 2:
A thermal insulator is introduced between the pressure sensing components and the external cold environment, acting as a mediator to reduce heat transfer and maintain internal temperatures above freezing point
2Loss of substance
If a refrigerant-based vacuum pump is employed to extract water, then water extraction is improved, but it cannot prevent freezing during flight as it only operates on the ground
Solution Approach 1:
The pressure sensing system performs its own heating and temperature maintenance through the integrated heater assembly, eliminating dependence on ground-based refrigerant vacuum pumps and enabling autonomous operation during flight
Solution Approach 2:
The thermal insulator serves as a mediator that traps heat within the pressure sensing system, working synergistically with the heater assembly to maintain temperatures above freezing throughout all operational phases
3Reliability
If the pressure sensing system is heated to maintain temperature above freezing, then freezing prevention is improved, but power consumption increases
Solution Approach 1:
The heater assembly operates periodically rather than continuously, activating when temperature sensors detect approaching freezing conditions and deactivating when temperature thresholds are met, reducing overall power consumption while maintaining freezing prevention
Solution Approach 2:
Temperature sensors provide feedback to the control system, which adjusts heater assembly operation based on real-time temperature measurements, optimizing power usage by heating only when necessary to maintain temperatures above freezing
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 prevents freezing of the pressure sensing system during flight, ensuring reliable engine pressure monitoring and minimizing power usage and control logic impact on the engine control system.
Implementation Method 1
a plurality of heating elements configured to provide heat to the pressure transducer
Implementation Method 2
a thermal insulator disposed between the heated pressure subsystem and the non-heated subsystem
Data Source
AI summary
A pressure sensing system includes a pressure transducer, a pressure manifold, and a heater assembly. The pressure transducer is configured to measure pressures at one or more locations of a vehicle engine. The pressure manifold is configured to cover a face of the pressure transducer and provide an interface for transferring air or gas generated at the one or more locations of the vehicle engine. The heater assembly is configured to heat one or more portions of the pressure transducer and one or more portions of the pressure manifold and maintain a temperature of each of the pressure transducer and the pressure manifold above a predetermined temperature level.