Aircraft pipeline heating control method, pipeline heating system and aircraft

A heating system and heating control technology, applied in the field of aircraft pipelines, can solve problems such as energy waste, achieve the effects of reducing energy consumption, stabilizing the temperature state, and saving on-board energy

Active Publication Date: 2022-02-18
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The embodiment of the present application provides an aircraft pipeline heating control method, a pipeline heating system and an aircraft, which can solve the problem of simultaneous heating of the high temperature section and the low temperature section of the pipeline in the traditional way Cause energy waste, thereby reducing system energy consumption

Method used

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  • Aircraft pipeline heating control method, pipeline heating system and aircraft
  • Aircraft pipeline heating control method, pipeline heating system and aircraft
  • Aircraft pipeline heating control method, pipeline heating system and aircraft

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Embodiment

[0059] The main body of the present embodiment is a aircraft pipe heating system, which is applied to the aircraft, please see figure 1 , figure 1 Structure of the aircraft pipe heating system provided for the invention, in the present embodiment, the aircraft pipe heating system includes:

[0060] Pipe body 1;

[0061] A plurality of heating elements 2, and the plurality of heating elements 2 are sequentially attached to the conduit body 1 along the conduit body 1, so that the conduit body 1 is divided into a plurality of continuous arrangement along its extending direction and is sequentially arranged and the heating element 2 phase. Corresponding heat-conducting zone;

[0062] The acquisition unit 3 is used to acquire the actual temperature of each heat-inspiration section;

[0063] The control unit is configured to obtain the target power of each of the heating elements 2 according to a preset target temperature and the actual temperature of each of the heat-inspiration segmen...

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Abstract

The embodiment of the invention discloses an aircraft pipeline heating control method, a pipeline heating system and an aircraft, and belongs to the technical field of aircraft pipelines. According to the aircraft pipeline heating control method, the pipeline heating system and the aircraft of the invention, a plurality of heating elements which are sequentially arranged in the extending direction of a pipeline body are arranged on the pipeline body, so that the pipeline body is divided into a plurality of heated sections which are sequentially and continuously arranged in the extending direction of the pipeline body and correspond to the heating elements; and in the control method, the actual temperature of each heated section is obtained, the heating elements are differently controlled to operate at target power according to preset target temperature and the actual temperature of each heated section, so that the energy consumption of the heating elements is reduced on the premise of meeting the heating requirements of each heated section, and the energy consumption of the aircraft pipeline heating system is saved.

Description

Technical field [0001] The present invention relates to the technical field of aircraft pipeline, and more particularly to aircraft pipe heating control method, a pipe heating system, and aircraft. Background technique [0002] The aircraft pipe heating system is mainly used for the delivery and heating of the aircraft fluid medium. Currently, there is a certain limit on the conventional aircraft pipe heating system. [0003] In detail, in the prior art, the acquisition unit tends to be installed at a certain end interface of the pipe, measuring the ambient temperature at this end interface, representing the temperature temperature at one end of the pipeline, representing this pipe temperature, for The pipe has a long extended length of the fluid temperature distribution in the conduit is not uniform, for example, under some working condition, some positions in the tube are high temperature sections of 6 ° C to 7 ° C, and some locations are 1 The low temperature segment of ° C to...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16L53/38G05D23/20
CPCF16L53/38G05D23/20
Inventor 张玉莹朱翀张雪苹王重曹灿王彬
Owner COMAC
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