JP2018016132A - Opening cover and aircraft - Google Patents

Opening cover and aircraft Download PDF

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JP2018016132A
JP2018016132A JP2016146361A JP2016146361A JP2018016132A JP 2018016132 A JP2018016132 A JP 2018016132A JP 2016146361 A JP2016146361 A JP 2016146361A JP 2016146361 A JP2016146361 A JP 2016146361A JP 2018016132 A JP2018016132 A JP 2018016132A
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opening
cover
aircraft
outside air
holes
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JP6768391B2 (en
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修作 梶山
Shusaku Kajiyama
修作 梶山
宏樹 小池
Hiroki Koike
宏樹 小池
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Abstract

PROBLEM TO BE SOLVED: To provide an opening cover and the like that can reduce pressure loss in an opening part of an aircraft.SOLUTION: An opening cover 10 provided in an outside air intake port 5 through which outside air circulates toward an inside from an outside of an aircraft 1 includes: a cover body 11; and a plurality of through-holes 12 formed by penetrating the cover body 11. The cover body 11 is inclined relative to an orthogonal surface orthogonal to an inflow direction of the outside air flowing toward the cover body 11. The through-holes 12 have a penetration direction that is same as the inflow direction of the outside air.SELECTED DRAWING: Figure 3

Description

本発明は、航空機の開口部に設けられる開口カバー及び航空機に関するものである。   The present invention relates to an opening cover provided in an opening of an aircraft and an aircraft.

従来、超音速の空気流を取り入れる取入口を備える航空機が知られている（例えば、特許文献１参照）。   2. Description of the Related Art Conventionally, an aircraft including an intake port that takes in a supersonic airflow is known (see, for example, Patent Document 1).

特開平５−２１３２８１号公報Japanese Patent Laid-Open No. 5-213281

航空機の取入口等の開口部には、この開口部を被覆する開口カバーを設ける場合がある。開口部に開口カバーを設ける場合、開口カバーは、空気を流通させるための貫通孔が形成されたものが用いられており、例えば、パンチングメタルが用いられる。パンチングメタルは、鋼板に貫通孔を形成したものであり、貫通孔の貫通方向と、鋼板の板厚方向とが同じ方向となっている。   An opening cover that covers the opening may be provided at an opening of an aircraft inlet or the like. In the case where an opening cover is provided in the opening, the opening cover is formed with a through-hole for circulating air, and for example, punching metal is used. The punching metal is a steel plate in which a through hole is formed, and the through direction of the through hole and the thickness direction of the steel plate are the same direction.

ところで、開口カバーを開口部に設ける場合、開口カバーは、空気の流入方向に対して、斜めに設けられることがある。この場合、開口カバーの板面は、空気の流入方向に直交する直交面に対して傾斜することから、上記のパンチングメタルを用いると、空気の流入方向に対して、貫通孔の貫通方向が斜めとなってしまう。このため、開口部において圧力損失が生じることから、空気を効率よく取り込むことが困難となり、航空機の性能が低下する可能性がある。   By the way, when providing an opening cover in an opening part, an opening cover may be provided diagonally with respect to the inflow direction of air. In this case, since the plate surface of the opening cover is inclined with respect to the orthogonal plane orthogonal to the air inflow direction, when the punching metal is used, the through direction of the through hole is oblique with respect to the air inflow direction. End up. For this reason, since pressure loss occurs in the opening, it is difficult to efficiently take in air, and the performance of the aircraft may be reduced.

そこで、本発明は、航空機の開口部における圧力損失を低減することができる開口カバー及び航空機を提供することを課題とする。   Then, this invention makes it a subject to provide the opening cover and aircraft which can reduce the pressure loss in the opening part of an aircraft.

本発明の開口カバーは、航空機の内部と外部との間で流体が流通する開口部に設けられる開口カバーであって、カバー本体と、前記カバー本体に貫通形成される複数の貫通孔と、を備え、前記カバー本体は、前記カバー本体へ向かって流入する前記流体の流入方向に直交する直交面に対して傾斜して設けられ、前記貫通孔の貫通方向は、前記流体の流入方向と、同じ方向となっていることを特徴とする。   The opening cover of the present invention is an opening cover provided in an opening through which fluid flows between the inside and the outside of an aircraft, and includes a cover body and a plurality of through holes formed through the cover body. The cover body is provided to be inclined with respect to an orthogonal plane orthogonal to the inflow direction of the fluid flowing into the cover body, and the through direction of the through hole is the same as the inflow direction of the fluid It is characterized by the direction.

この構成によれば、カバー本体が流入方向に対して傾斜して設けられる場合であっても、複数の貫通孔が、流体の流入方向と同じ方向となっているため、流体の流通を阻害し難いものとすることができ、これにより、航空機の開口部における圧力損失を低減することができる。   According to this configuration, even if the cover main body is provided to be inclined with respect to the inflow direction, the plurality of through holes are in the same direction as the inflow direction of the fluid, and thus the fluid circulation is hindered. Can be difficult, thereby reducing pressure loss at the opening of the aircraft.

また、前記開口部は、前記流体としての外気を取り込む外気取入口、及び前記流体としての排気を排出する排気口の少なくとも一方であることが好ましい。   Moreover, it is preferable that the said opening part is at least one of the external air intake which takes in the external air as said fluid, and the exhaust port which discharges | emits exhaust as said fluid.

この構成によれば、外気取入口における外気の圧力損失を低減することができるため、外気を効率よく取り込むことができる。また、排気口における排気の圧力損失を低減することができるため、排気を効率よく排出することができる。   According to this configuration, the pressure loss of the outside air at the outside air inlet can be reduced, so that the outside air can be taken in efficiently. Moreover, since the pressure loss of the exhaust at the exhaust port can be reduced, the exhaust can be efficiently discharged.

また、複数の前記貫通孔は、千鳥配置となっていることが好ましい。   The plurality of through holes are preferably arranged in a staggered manner.

この構成によれば、複数の貫通孔を千鳥配置とすることで、カバー本体に対する複数の貫通孔の開口率を大きくし易いものとすることができる。このため、複数の貫通孔の開口率が低くなることを抑制できることから、圧力損失の増大を抑制することができる。なお、複数の貫通孔は、カバー本体に対して均等配置することがより好ましく、また、千鳥配置としては、６０°千鳥配置が好ましい。   According to this configuration, by arranging the plurality of through holes in a staggered arrangement, it is possible to easily increase the aperture ratio of the plurality of through holes with respect to the cover body. For this reason, since it can suppress that the aperture ratio of a some through-hole becomes low, the increase in pressure loss can be suppressed. In addition, it is more preferable that the plurality of through holes are arranged uniformly with respect to the cover body, and the staggered arrangement is preferably a 60 ° staggered arrangement.

また、複数の前記貫通孔は、所定の内径となる中空円柱形状となっており、前記内径は、前記貫通方向に亘って同径となっていることが好ましい。   Moreover, it is preferable that the said several through-hole becomes a hollow cylinder shape used as a predetermined | prescribed internal diameter, and the said internal diameter is the same diameter over the said penetration direction.

この構成によれば、ドリル等の穿孔工具を用いて、カバー本体に対し各貫通孔を容易に加工することができる。   According to this structure, each through-hole can be easily processed with respect to a cover main body using drilling tools, such as a drill.

また、前記貫通孔の前記内径は、前記カバー本体の板厚よりも小さくなっていることが好ましい。   Moreover, it is preferable that the said internal diameter of the said through-hole is smaller than the plate | board thickness of the said cover main body.

この構成によれば、カバー本体の板厚を貫通孔の内径よりも厚くできるため、カバー本体の剛性を高くすることができる。このため、流体の流速が速く、流体からカバー本体に力が与えられても、カバー本体が変形することを抑制することができる。   According to this structure, since the plate | board thickness of a cover main body can be made thicker than the internal diameter of a through-hole, the rigidity of a cover main body can be made high. For this reason, even if the flow rate of the fluid is fast and a force is applied from the fluid to the cover body, the cover body can be prevented from being deformed.

本発明の航空機は、上記の開口カバーを備えることを特徴とする。   An aircraft according to the present invention includes the opening cover described above.

この構成によれば、開口部に開口カバーを設ける場合であっても、開口部における圧力損失を低減することができるため、圧力損失による航空機の性能低下を抑制することができる。   According to this configuration, even when the opening cover is provided in the opening, the pressure loss in the opening can be reduced, so that the performance degradation of the aircraft due to the pressure loss can be suppressed.

図１は、本実施形態に係る開口カバーが取り付けられた航空機を模式的に示す斜視図である。FIG. 1 is a perspective view schematically showing an aircraft to which an opening cover according to the present embodiment is attached. 図２は、開口カバーを模式的に示す平面図である。FIG. 2 is a plan view schematically showing the opening cover. 図３は、航空機の外気取入口周りを模式的に示す断面図である。FIG. 3 is a cross-sectional view schematically showing the periphery of the outside air intake port of the aircraft. 図４は、開口カバーの一部を示す平面図である。FIG. 4 is a plan view showing a part of the opening cover. 図５は、開口カバーを模式的に示す断面図である。FIG. 5 is a cross-sectional view schematically showing the opening cover.

以下に、本発明に係る実施形態を図面に基づいて詳細に説明する。なお、この実施形態によりこの発明が限定されるものではない。また、下記実施形態における構成要素には、当業者が置換可能かつ容易なもの、あるいは実質的に同一のものが含まれる。さらに、以下に記載した構成要素は適宜組み合わせることが可能であり、また、実施形態が複数ある場合には、各実施形態を組み合わせることも可能である。   Embodiments according to the present invention will be described below in detail with reference to the drawings. In addition, this invention is not limited by this embodiment. In addition, constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art or those that are substantially the same. Furthermore, the constituent elements described below can be appropriately combined, and when there are a plurality of embodiments, the embodiments can be combined.

［実施形態］
図１は、本実施形態に係る開口カバーが取り付けられた航空機を模式的に示す斜視図である。図２は、開口カバーを模式的に示す平面図である。図３は、航空機の外気取入口周りを模式的に示す断面図である。図４は、開口カバーの一部を示す平面図である。図５は、開口カバーを模式的に示す断面図である。 [Embodiment]
FIG. 1 is a perspective view schematically showing an aircraft to which an opening cover according to the present embodiment is attached. FIG. 2 is a plan view schematically showing the opening cover. FIG. 3 is a cross-sectional view schematically showing the periphery of the outside air intake port of the aircraft. FIG. 4 is a plan view showing a part of the opening cover. FIG. 5 is a cross-sectional view schematically showing the opening cover.

本実施形態の開口カバー１０は、航空機１に設けられる開口部を覆うように配置されている。航空機１の開口部としては、例えば、航空機１の空気調和装置に外気を取り込むための外気取入口、及び、航空機１の空気調和装置からの排気を排出するための排気口がある。本実施形態において、開口カバー１０は、航空機１に設けられる外気取入口５を覆うように配置されている。なお、本実施形態では、航空機１の開口部として、外気取入口５に適用して説明するが、排気口に適用してもよく、特に限定されない。   The opening cover 10 of the present embodiment is arranged so as to cover an opening provided in the aircraft 1. Examples of the opening of the aircraft 1 include an outside air intake for taking outside air into the air conditioner of the aircraft 1 and an exhaust port for discharging exhaust from the air conditioner of the aircraft 1. In the present embodiment, the opening cover 10 is disposed so as to cover the outside air intake 5 provided in the aircraft 1. In the present embodiment, the opening of the aircraft 1 is described as being applied to the outside air intake 5, but it may be applied to an exhaust and is not particularly limited.

図１に示すように、開口カバー１０は、板状に形成されており、航空機１の機首から機尾を結ぶ前後方向、つまり、ロール軸の軸方向に対して傾斜して配置されている。つまり、開口カバー１０の板面（表面及び裏面）は、前後方向に直交する直交面に対して傾斜する傾斜面となっている。なお、開口カバー１０は、航空機１の左右を結ぶ左右方向、つまり、ロール軸の軸方向に直交するピッチ軸の軸方向に直交する直交面に対して傾斜して配置されてもよい。そして、外気取入口５に取り込まれる外気は、前後方向に沿って流通すると共に、航空機１の外部から、開口カバー１０が取り付けられた外気取入口５を介して、航空機１の内部へ向かって流通する。なお、ロール軸の軸方向となる前後方向に直交するヨー軸の軸方向を、高さ方向とする。   As shown in FIG. 1, the opening cover 10 is formed in a plate shape, and is arranged to be inclined with respect to the front-rear direction connecting the nose to the aft of the aircraft 1, that is, the axial direction of the roll axis. . That is, the plate surface (front surface and back surface) of the opening cover 10 is an inclined surface that is inclined with respect to an orthogonal surface orthogonal to the front-rear direction. Note that the opening cover 10 may be disposed to be inclined with respect to a left-right direction connecting the left and right sides of the aircraft 1, that is, an orthogonal plane orthogonal to the axial direction of the pitch axis orthogonal to the axial direction of the roll axis. The outside air taken into the outside air intake 5 circulates in the front-rear direction, and circulates from the outside of the aircraft 1 to the inside of the aircraft 1 through the outside air intake 5 to which the opening cover 10 is attached. To do. In addition, let the axial direction of the yaw axis orthogonal to the front-back direction used as the axial direction of a roll axis be a height direction.

図２に示すように、開口カバー１０は、カバー本体１１と、複数の貫通孔１２と、複数の締結孔１３とを備えており、例えば、パンチングメタルが用いられている。   As shown in FIG. 2, the opening cover 10 includes a cover body 11, a plurality of through holes 12, and a plurality of fastening holes 13. For example, punching metal is used.

カバー本体１１は、例えば、鋼板を用いて構成されており、外気取入口５の全面を被覆可能な形状に形成されている。カバー本体１１は、航空機１に対して外側の面が表面側となり、外気がカバー本体１１へ向かって流入する流入側の面となっている。また、カバー本体１１は、航空機１に対して内側の面が裏面側となり、外気がカバー本体１１から流出する流出側の面となっている。そして、カバー本体１１は、その表面及び裏面が平行となっており、また、表面及び裏面を含む板面が、流入方向に直交する直交面に対して、非平行となる傾斜面となっている。また、カバー本体１１は、その外側の周縁部が、外気取入口５に取り付けられる枠状の外枠部位１１ａとなっている。   The cover body 11 is made of, for example, a steel plate, and is formed in a shape that can cover the entire outside air intake 5. The cover body 11 has a surface on the outer side with respect to the aircraft 1 and a surface on the inflow side where outside air flows into the cover body 11. In addition, the cover body 11 has an inner surface with respect to the aircraft 1 on the back surface side and an outflow surface from which outside air flows out from the cover body 11. The front surface and the back surface of the cover body 11 are parallel, and the plate surface including the front surface and the back surface is an inclined surface that is not parallel to the orthogonal surface orthogonal to the inflow direction. . Further, the outer peripheral edge of the cover main body 11 is a frame-shaped outer frame portion 11 a attached to the outside air inlet 5.

複数の貫通孔１２は、カバー本体１１に形成されており、カバー本体１１の外枠部位１１ａの内側となる内側部位１１ｂに形成されている。複数の貫通孔１２は、カバー本体１１に貫通形成されている。各貫通孔１２は、カバー本体１１が外気取入口５に取り付けられた状態において、貫通孔１２の貫通方向が、外気の流入方向と同じ方向となるように形成されている。具体的に、貫通孔１２の貫通方向は、前後方向となっている。このため、図５に示すように、各貫通孔１２は、カバー本体１１の板面に対する垂線方向に対して、斜めに貫通形成されている。   The plurality of through holes 12 are formed in the cover main body 11 and are formed in the inner part 11 b which is the inner side of the outer frame part 11 a of the cover main body 11. The plurality of through holes 12 are formed through the cover body 11. Each through hole 12 is formed so that the through direction of the through hole 12 is the same as the inflow direction of the outside air in a state where the cover body 11 is attached to the outside air inlet 5. Specifically, the penetration direction of the through hole 12 is the front-rear direction. For this reason, as shown in FIG. 5, each through-hole 12 is formed so as to penetrate obliquely with respect to the direction perpendicular to the plate surface of the cover body 11.

複数の貫通孔１２は、図４に示すように、千鳥配置となっている。つまり、複数の貫通孔１２は、所定の方向に並べて配置された一列の貫通孔を複数列並べて設け、隣接する一方の列の貫通孔１２同士の間に、隣接する他方の列の貫通孔１２が位置するように配置されている。このため、複数の貫通孔１２は、６０°千鳥配置なっている。また、複数の貫通孔１２は、カバー本体１１に対して均等となるように配置されている。つまり、複数の貫通孔１２は、その粗密の度合いがカバー本体１１に対して一定となっている。   The plurality of through holes 12 are arranged in a staggered manner as shown in FIG. That is, the plurality of through-holes 12 are provided by arranging a plurality of rows of through-holes arranged side by side in a predetermined direction, and the through-holes 12 in the other adjacent row are disposed between the through-holes 12 in one adjacent row. Is arranged to be located. For this reason, the plurality of through holes 12 are arranged in a 60 ° staggered manner. Further, the plurality of through holes 12 are arranged to be equal to the cover body 11. That is, the degree of density of the plurality of through holes 12 is constant with respect to the cover body 11.

各貫通孔１２は、所定の内径となる中空円柱形状となっており、貫通方向に亘って同じ内径となっている。つまり、各貫通孔１２は、ストレート孔となっている。この貫通孔１２は、カバー本体１１に対して、ドリル等の穿孔工具により機械加工されることにより貫通形成される。また、各貫通孔１２は、その内径が、カバー本体１１の板厚よりも小さくなるように形成されている。   Each through hole 12 has a hollow cylindrical shape having a predetermined inner diameter, and has the same inner diameter in the penetration direction. That is, each through hole 12 is a straight hole. The through hole 12 is formed through the cover body 11 by being machined by a drilling tool such as a drill. Further, each through hole 12 is formed such that its inner diameter is smaller than the plate thickness of the cover main body 11.

このような、複数の貫通孔１２は、所定の開口率となるように、カバー本体１１に形成されている。なお、開口率は、カバー本体１１に対する複数の貫通孔１２の開口の割合である。ここで、複数の貫通孔１２は、千鳥配置となっていることから、貫通孔１２が形成されない領域を小さくでき、開口率を大きくし易いものとすることができる。   Such a plurality of through holes 12 are formed in the cover body 11 so as to have a predetermined opening ratio. The aperture ratio is the ratio of the openings of the plurality of through holes 12 to the cover body 11. Here, since the plurality of through holes 12 are arranged in a staggered manner, a region where the through holes 12 are not formed can be reduced, and the aperture ratio can be easily increased.

複数の締結孔１３は、カバー本体１１の外枠部位１１ａに設けられており、ボルト等の締結部材が挿入される貫通孔となっている。締結孔１３は、貫通孔１２よりも大きく形成されている。複数の締結孔１３は、外枠部位１１ａに所定の間隔を空けて並べて形成されている。   The plurality of fastening holes 13 are provided in the outer frame portion 11a of the cover body 11 and are through holes into which fastening members such as bolts are inserted. The fastening hole 13 is formed larger than the through hole 12. The plurality of fastening holes 13 are formed side by side with a predetermined interval in the outer frame part 11a.

上記の開口カバー１０は、航空機１の外気取入口５に、締結孔１３を介してカバー本体１１の外枠部位１１ａが取り付けられる。この状態において、開口カバー１０は、カバー本体１１の内側部位１１ｂに形成される複数の貫通孔１２が、外気の流入方向と同じ方向となる。このため、外気が開口カバー１０を介して航空機１の内部に流入する場合、外気は、流入方向と同じ方向となる貫通孔１２を流通する。   In the opening cover 10, the outer frame portion 11 a of the cover body 11 is attached to the outside air intake 5 of the aircraft 1 through the fastening hole 13. In this state, in the opening cover 10, the plurality of through holes 12 formed in the inner portion 11 b of the cover main body 11 are in the same direction as the inflow direction of the outside air. For this reason, when outside air flows into the interior of the aircraft 1 through the opening cover 10, the outside air flows through the through holes 12 that are in the same direction as the inflow direction.

以上のように、本実施形態によれば、カバー本体１１が流入方向に対して傾斜して設けられる場合であっても、複数の貫通孔１２が、外気の流入方向と同じ方向となっているため、外気の流通を阻害し難いものとすることができる。これにより、航空機１の外気取入口５における圧力損失を低減することができるため、外気を効率よく取り込むことができる。そして、外気を効率よく取り込むことで、空気調和装置の作動効率を向上させることができ、航空機１に搭載されている電子機器等の冷却を好適に行うことができる。   As described above, according to the present embodiment, even when the cover main body 11 is provided to be inclined with respect to the inflow direction, the plurality of through holes 12 are in the same direction as the inflow direction of the outside air. Therefore, it is possible to make it difficult to inhibit the circulation of outside air. Thereby, since the pressure loss in the outside air intake 5 of the aircraft 1 can be reduced, outside air can be taken in efficiently. And by taking in external air efficiently, the operating efficiency of an air conditioning apparatus can be improved and the electronic device etc. which are mounted in the aircraft 1 can be cooled suitably.

また、本実施形態によれば、複数の貫通孔１２を千鳥配置とすることで、カバー本体１１に対する複数の貫通孔１２の開口率を大きくし易いものとすることができる。このため、複数の貫通孔１２の開口率が低くなることを抑制できることから、開口カバー１０における圧力損失の増大を抑制することができる。   Further, according to the present embodiment, the plurality of through holes 12 are arranged in a staggered manner, whereby the opening ratio of the plurality of through holes 12 with respect to the cover body 11 can be easily increased. For this reason, since it can suppress that the opening rate of the several through-hole 12 becomes low, the increase in the pressure loss in the opening cover 10 can be suppressed.

また、本実施形態によれば、貫通孔１２を中空円柱形状としたため、カバー本体１１に対して各貫通孔１２を容易に加工することができる。   Moreover, according to this embodiment, since the through-hole 12 was made into the hollow cylinder shape, each through-hole 12 can be easily processed with respect to the cover main body 11. FIG.

また、本実施形態によれば、カバー本体１１の板厚を貫通孔１２の内径よりも厚くできるため、カバー本体１１の剛性を高くすることができる。このため、外気の流速が速く、外気からカバー本体１１に力が与えられても、カバー本体１１が変形することを抑制することができる。   Moreover, according to this embodiment, since the plate | board thickness of the cover main body 11 can be made thicker than the internal diameter of the through-hole 12, the rigidity of the cover main body 11 can be made high. For this reason, even if the flow rate of outside air is fast and force is given to the cover main body 11 from outside air, it can suppress that the cover main body 11 deform | transforms.

また、本実施形態によれば、外気取入口５に取り付けられた開口カバー１０における圧力損失を低減することができるため、圧力損失による航空機１の性能低下を抑制することができる。   Moreover, according to this embodiment, since the pressure loss in the opening cover 10 attached to the outside air inlet 5 can be reduced, the performance degradation of the aircraft 1 due to the pressure loss can be suppressed.

なお、本実施形態では、開口カバー１０を航空機１の外気取入口５に取り付ける場合について説明したが、本実施形態の開口カバー１０を、航空機１の空気調和装置からの排気を排出する排気口に取り付けてもよい。この場合、航空機１の排気口における排気の圧力損失を低減することができるため、排気を効率よく排出することができることから、圧力損失による航空機１の性能低下を抑制することができる。なお、開口カバー１０は、航空機１に設けられる開口部であれば、いずれに設けてもよい。   In the present embodiment, the case where the opening cover 10 is attached to the outside air intake 5 of the aircraft 1 has been described. However, the opening cover 10 of the present embodiment is used as an exhaust port that discharges exhaust from the air conditioner of the aircraft 1. It may be attached. In this case, since the pressure loss of the exhaust at the exhaust port of the aircraft 1 can be reduced, and the exhaust can be discharged efficiently, the performance degradation of the aircraft 1 due to the pressure loss can be suppressed. The opening cover 10 may be provided at any opening provided in the aircraft 1.

また、本実施形態では、各貫通孔１２をストレート孔に形成したが、これに限定されず、各貫通孔１２の内径を、外気の流入方向に沿って大きくなるように形成してもよい。   In the present embodiment, each through hole 12 is formed as a straight hole. However, the present invention is not limited to this, and the inner diameter of each through hole 12 may be increased along the inflow direction of the outside air.

また、本実施形態では、鋼板のカバー本体１１に複数の貫通孔１２を形成した、いわゆるパンチングメタルを用いたが、この構成に特に限定されず、ハニカム材を用いてもよい。この場合、貫通孔１２は、中空六角柱形状となる。   In the present embodiment, so-called punching metal in which a plurality of through holes 12 are formed in the cover main body 11 of the steel plate is used, but the present invention is not particularly limited, and a honeycomb material may be used. In this case, the through hole 12 has a hollow hexagonal column shape.

１ 航空機
５ 外気取入口
１０ 開口カバー
１１ カバー本体
１１ａ 外枠部位
１１ｂ 内側部位
１２ 貫通孔
１３ 締結孔 DESCRIPTION OF SYMBOLS 1 Aircraft 5 Outside air intake 10 Opening cover 11 Cover main body 11a Outer frame part 11b Inner part 12 Through-hole 13 Fastening hole

Claims (6)

航空機の内部と外部との間で流体が流通する開口部に設けられる開口カバーであって、
カバー本体と、
前記カバー本体に貫通形成される複数の貫通孔と、を備え、
前記カバー本体は、前記カバー本体へ向かって流入する前記流体の流入方向に直交する直交面に対して傾斜して設けられ、
前記貫通孔の貫通方向は、前記流体の流入方向と、同じ方向となっていることを特徴とする開口カバー。 An opening cover provided in an opening through which fluid flows between the inside and the outside of the aircraft,
A cover body;
A plurality of through holes formed through the cover body,
The cover body is provided to be inclined with respect to an orthogonal plane orthogonal to the inflow direction of the fluid flowing into the cover body,
The opening cover, wherein a through direction of the through hole is the same as an inflow direction of the fluid. 前記開口部は、前記流体としての外気を取り込む外気取入口、及び前記流体としての排気を排出する排気口の少なくとも一方であることを特徴とする請求項１に記載の開口カバー。   The opening cover according to claim 1, wherein the opening is at least one of an outside air intake port that takes in outside air as the fluid and an exhaust port that discharges exhaust gas as the fluid. 複数の前記貫通孔は、千鳥配置となっていることを特徴とする請求項１または２に記載の開口カバー。   The opening cover according to claim 1, wherein the plurality of through holes are arranged in a staggered manner. 複数の前記貫通孔は、所定の内径となる中空円柱形状となっており、
前記内径は、前記貫通方向に亘って同径となっていることを特徴とする請求項１から３のいずれか１項に記載の開口カバー。 The plurality of through holes have a hollow cylindrical shape with a predetermined inner diameter,
The opening cover according to any one of claims 1 to 3, wherein the inner diameter is the same in the penetrating direction. 前記貫通孔の前記内径は、前記カバー本体の板厚よりも小さくなっていることを特徴とする請求項４に記載の開口カバー。   The opening cover according to claim 4, wherein the inner diameter of the through hole is smaller than a plate thickness of the cover body. 請求項１から５のいずれか１項に記載の開口カバーを備えることを特徴とする航空機。   An aircraft comprising the opening cover according to any one of claims 1 to 5.
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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4252286A (en) * 1979-04-16 1981-02-24 The Boeing Company Simplified core flow thrust control device
JPH01297394A (en) * 1988-05-24 1989-11-30 Mitsubishi Heavy Ind Ltd Air intake for aircraft
JPH05213281A (en) * 1992-02-05 1993-08-24 Kawasaki Heavy Ind Ltd Intake for supersonic air flow
JPH07257492A (en) * 1994-03-22 1995-10-09 Mitsubishi Heavy Ind Ltd Intake dust for aircraft
JPH11301595A (en) * 1998-04-22 1999-11-02 Kazuo Ariyoshi Cover protector of jet engine for airplane
JP2000095195A (en) * 1998-07-24 2000-04-04 Kazuo Ariyoshi Device to prevent bird strike for airplane
US6138950A (en) * 1998-10-06 2000-10-31 Northrop Grumman Corporation Aircraft engine air intake system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4252286A (en) * 1979-04-16 1981-02-24 The Boeing Company Simplified core flow thrust control device
JPH01297394A (en) * 1988-05-24 1989-11-30 Mitsubishi Heavy Ind Ltd Air intake for aircraft
JPH05213281A (en) * 1992-02-05 1993-08-24 Kawasaki Heavy Ind Ltd Intake for supersonic air flow
JPH07257492A (en) * 1994-03-22 1995-10-09 Mitsubishi Heavy Ind Ltd Intake dust for aircraft
JPH11301595A (en) * 1998-04-22 1999-11-02 Kazuo Ariyoshi Cover protector of jet engine for airplane
JP2000095195A (en) * 1998-07-24 2000-04-04 Kazuo Ariyoshi Device to prevent bird strike for airplane
US6138950A (en) * 1998-10-06 2000-10-31 Northrop Grumman Corporation Aircraft engine air intake system

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