To provide a heat input suppression structure and a heat input suppression system for an aircraft capable of sufficiently protecting a structural member from heat even when a heat source must be arranged close to the structural member forming a non-pressurized section due to restrictions of a large number of pipes including piping of a bleed pipe and a hydraulic system and a fitting space :or the like of an accessory.SOLUTION: A heat input suppression structure for an aircraft includes: a structural member forming a non-pressurized section of the aircraft; and heat insulating material disposed between a heat source and an object region opposed to the heat source located in the non-pressurized section in the structural member, and shielding heat radiated from the heat source to the object region.SELECTED DRAWING: Figure 3

    【課題】抽気配管や油圧系統の配管を含む多数の配管や装備品の艤装スペース等の制約から、非与圧区画を形成する構造部材に熱源を近接して配置せざるを得ない場合であっても、構造部材を熱から十分に保護することが可能な航空機の入熱抑制構造および入熱抑制システムを提供すること。【解決手段】航空機の入熱抑制構造は、航空機の非与圧区画を形成する構造部材と、構造部材において非与圧区画に位置する熱源に対向する対象領域と熱源との間に配置され、熱源から放射された熱を対象領域に対して遮蔽する遮熱材と、を備える。【選択図】図3


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    Title :

    HEAT INPUT SUPPRESSION STRUCTURE AND HEAT INPUT SUPPRESSION SYSTEM OF AIRCRAFT


    Additional title:

    航空機の入熱抑制構造および入熱抑制システム


    Contributors:

    Publication date :

    2022-05-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16L PIPES , Rohre



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