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Heat removal structure of aircraft main landing gear bay

机译:飞机主起落架舱的散热结构

摘要

An aircraft includes: a fairing which covers a lower part of a fuselage having a main landing gear bay (MLG bay), and defines a ventilation cavity communicating with the MLG bay between the fairing and the fuselage; and a heat removal system which removes heat generated from the MLG inside the MLG bay to the outside of the MLG bay by suctioning/discharging air through an inlet port and an outlet port leading from the ventilation cavity or the MLG bay to external air. The fairing defines a wheel opening through which a wheel of the MLG enters and exits, and defines a ventilation port, which functions as one of the inlet and outlet ports, between the fairing and an outer peripheral part of the wheel exposed from the wheel opening to the lower side of the MLG bay when the MLG is retracted.
机译:一种飞机,包括:整流罩,该整流罩覆盖具有主起落架舱(MLG舱)的机身下部,并限定了在整流罩和机身之间与MLG舱连通的通风腔。以及排热系统,其通过经由从通风腔或MLG舱室通向外部空气的入口和出口抽吸/排出空气来将在MLG舱室内部的MLG产生的热量排到MLG舱室的外部。整流罩限定了轮孔,MLG的车轮通过该轮孔进入和离开,并且在整流罩和从轮孔暴露的轮的外周部分之间限定了通风口,该通风口用作入口和出口之一。缩回MLG时,将其移至MLG托架的下侧。

著录项

  • 公开/公告号JP6549849B2

    专利类型

  • 公开/公告日2019-07-24

    原文格式PDF

  • 申请/专利权人 三菱航空機株式会社;

    申请/专利号JP20150012564

  • 发明设计人 原 伸英;鈴田 忠彦;

    申请日2015-01-26

  • 分类号B64C25/04;B64C25/12;B64C1/40;B64C25/42;B64C25/36;

  • 国家 JP

  • 入库时间 2022-08-21 12:20:27

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