Heat exchanger assembly for an aircraft control

Abstract

A heat exchanger assembly for an aircraft control has an aircraft control for controlling an operation of an aircraft. The aircraft control is in thermal communication with a first fluid. A first thermoelectric device is configured to transfer heat between the first fluid and the second fluid against a temperature gradient of the first fluid and the second fluid. A temperature sensor is provided for sensing a temperature of the first fluid. A temperature control is also configured to control the first thermoelectric device based on an input from the temperature sensor.

Description

BACKGROUND OF THE INVENTION[0001]This invention relates to a heat exchanger for an aircraft control. An aircraft has a number of electronic controls used to control an operation of the aircraft. One such control manages the function of the aircraft engines and is commonly known as a Full Authority Digital Engine Control or FADEC. The FADEC is generally installed in an environment of the aircraft susceptible to both very high temperatures and very low temperatures. For example, the FADEC may be installed in the engine bay where large amounts of heat are generated during flight conditions. In these conditions, the FADEC requires a substantial amount of cooling to limit its operating temperature. When the aircraft is not in flight, however, the engine bay may be extremely cold when ambient air temperature is low. At these conditions, the FADEC requires very little, if any, cooling.[0002]The FADEC, like many aircraft controls, is composed of electronic components that require moderate a...

AI Technical Summary

Benefits of technology

[0004]A heat exchanger assembly includes an aircraft control. The aircraft control is in thermal communication with a first fluid. A first thermoelectric device is configured to transfer heat between the first fluid and a second fluid against a temperature gradient of the first fluid and the second fluid. A temperature sensor is provided for sensing a temperature of the first fluid. A temperature control is also configured to control the first thermoelectric device based on an input from the temperature sensor.

Problems solved by technology

In these conditions, the FADEC requires a substantial amount of cooling to limit its operating temperature.

When the aircraft is not in flight, however, the engine bay may be extremely cold when ambient air temperature is low.

The large temperature swings experienced by the FADEC is not conducive to the best performance of these temperature sensitive components.

While there are electronic components that are capable of performing at the extreme temperature conditions of the aircraft, these components are generally very expensive and have relatively low performance (memory, process, or speed) compared to most modern electronics.

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