JP2579213B2 - Air supply device for aircraft - Google Patents
Air supply device for aircraftInfo
- Publication number
- JP2579213B2 JP2579213B2 JP1087956A JP8795689A JP2579213B2 JP 2579213 B2 JP2579213 B2 JP 2579213B2 JP 1087956 A JP1087956 A JP 1087956A JP 8795689 A JP8795689 A JP 8795689A JP 2579213 B2 JP2579213 B2 JP 2579213B2
- Authority
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- Japan
- Prior art keywords
- duct
- air supply
- aircraft
- air
- diameter
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Description
【発明の詳細な説明】 〔産業上の利用分野〕 本発明は,駐機中の航空機に調和空気を供給するため
の航空機への送気装置に関する。Description: TECHNICAL FIELD The present invention relates to an air supply device for an aircraft for supplying conditioned air to a parked aircraft.
従来より,中央動力室や各スポットのキュピタルに設
置された空調機から駐機している航空機までダクトによ
って調和空気を供給することが行われているが,そのさ
い,該送気ダクトが空港作業の障害となるので駐機位置
の近傍まで地下ダクトを施設する方策が採られていた。
例えば第9図に示すように,空調機101から地下ダクト1
02を介してスポット内のピット103まで調和空気を導
き,このピット103からフレキシブルダクト104を地上に
導いて駐機中の航空機105に該空気を送気していた。Conventionally, ducts have been used to supply conditioned air from air conditioners installed in the central power room and the capital of each spot to the parked aircraft. Therefore, measures have been taken to install an underground duct near the parking position.
For example, as shown in FIG.
The conditioned air was guided to the pit 103 in the spot via 02, and the flexible duct 104 was guided to the ground from the pit 103 to supply the air to the aircraft 105 parked.
特公昭46−11737号公報はこの送気方式の具体例を開
示している。Japanese Patent Publication No. 46-11737 discloses a specific example of this air supply system.
従来の地下ダクト施設方式では埋設のための建設費が
嵩むと共に設置後のメンテナンスが容易でないといった
問題があった。また埋設ダクト長さは一定となるので航
空機機種や駐機場所の相違によりピットから駐機航空機
の給気口までの距離が遠くなるとフレキシブルダクトを
長くしなければならず,ために空調空気がこの長いフレ
キシブルダクトを通過する際に保温性及び通気性が悪く
なるといった問題点も生じていた。The conventional underground duct facility method has a problem that construction costs for burying are increased and maintenance after installation is not easy. Also, since the length of the buried duct is constant, the flexible duct must be lengthened if the distance from the pit to the air supply port of the parked aircraft becomes longer due to differences in aircraft models and parking locations, so air conditioning air There has also been a problem that heat retention and air permeability deteriorate when passing through a long flexible duct.
加えて,最近の空港並びに航空機の大型化と離着陸回
数の増大につれて駐機中の航空機に対する各種作業の合
理化が進められ,航空機への送気作業も他の作業と共働
して行なうことがますます要求されるようになり,他の
作業に支障をきたさないことはもとより,例えば乗客移
動用のボーデイングブリッジ接続位置に駐機している時
間帯において短時間に送気接続作業を完了することが要
求されるようになった。このボーデイングブリッジ位置
に駐機している航空機に対して地下ダクトを施設するこ
とは,駐機位置が機種の変更に対応しきれないだけに得
策ではない。また,空調機からフレキシブルダクトを引
き出すと他の作業の支障になるし,大風量の送気を行な
うには適さず,また作業の機械化が困難である。In addition, with the recent increase in the size of airports and aircraft and the increase in the number of takeoffs and landings, the rationalization of various operations on parked aircraft has been promoted, and air supply to aircraft can be performed in cooperation with other operations. Complete the air supply connection work in a short period of time, for example, while parked at the boarding bridge connection position for passenger movement, as well as being more required and not hindering other work. Came to be required. It is not advisable to install an underground duct for an aircraft parked at this boarding bridge location, because the parking location cannot fully accommodate the model change. In addition, drawing out the flexible duct from the air conditioner hinders other operations, is not suitable for supplying a large amount of air, and is difficult to mechanize.
本発明は,以上のような従来の問題点を解決し,駐機
中の航空機に対する調和空気の送気作業を一層合理化す
ることを目的としてなされたものである。An object of the present invention is to solve the above-described conventional problems and to further streamline the work of supplying conditioned air to a parked aircraft.
前記の目的を達成せんとする本発明の要旨とするとこ
ろは,その設置位置が固定された空調機と,この空調機
の給気口に一端が接続され,他端が航空機の機内送気口
に接続される送気ダクトと,からなる駐機中の航空機へ
の送気装置において,前記送気ダクトの全長のうち少な
くとも駐機航空機に至る屋外部分において地表より上に
水平方向に空中架設される剛性ダクト部分を有し,この
剛性ダクト部分は,径の異なる2本以上のダクト管が,
それらの接合部で重ね合わせ部をもって軸方向に連設さ
れた構造を有し,該ダクト管の重ね合わせ部にシール手
段が介装されると共に,この重ね合わせ部が滑動部材を
介して滑動自在に構成されており,該ダクト管が最大に
伸長したときにも該ダクト管の外側表面が露出しないよ
うに径大ダクトと径小ダクトの外側に保温材を充填した
保温外筒が取付けられ,前記の滑動部材が管端より突出
して設けられたローラーまたは管端近傍のダクト管に取
付けられたスプリング付ローラーからなることを特徴と
する。The gist of the present invention to achieve the above object is to provide an air conditioner having a fixed installation position, one end connected to the air supply port of the air conditioner, and the other end connected to the air supply port of the aircraft. An air supply duct connected to the aircraft, and an air supply device for an aircraft parked in the air, wherein at least an outdoor portion of the total length of the air supply duct that reaches the aircraft parked, is installed in the air in a horizontal direction above the ground surface. A rigid duct section, which is formed by two or more duct pipes having different diameters.
These ducts have a structure in which the overlapping portions are connected in the axial direction with the overlapping portions. Sealing means is interposed at the overlapping portions of the duct pipes, and the overlapping portions are slidable via sliding members. A large-diameter duct and a small-diameter duct filled with a heat insulating material are attached to the outside of the large-diameter duct and the small-diameter duct so that the outer surface of the duct pipe is not exposed even when the duct pipe extends to the maximum. The sliding member may comprise a roller provided to protrude from the pipe end or a roller with a spring attached to a duct pipe near the pipe end.
すなわち本発明は,従来の地上部分でのフレキシブル
ダクトの使用に代えて,実質的長さ部分を剛性ダクトと
し,これを,滑動部材(ローラー)を介して伸縮自在に
複数本のダクト管を接続して構成すると共に、途中に支
柱を設けなくとも空中に懸架できる構造としたものであ
り,特に伸縮可能なボーデイングブリッジに沿わせて空
中懸架するのに適する大風量送気可能な航空機への気密
送気装置を提供するものである。In other words, the present invention replaces the conventional use of flexible ducts on the ground, and replaces the substantial length with a rigid duct, which is connected to a plurality of duct pipes via a sliding member (roller) so as to be able to expand and contract. It is designed to be able to be suspended in the air without the need for supporting columns in the middle, and it is particularly suitable for aircraft that can supply large air volumes and is suitable for being suspended in the air along a stretchable boarding bridge. An airtight air supply device is provided.
以下に,本発明を図示の実施例にもとづいて説明す
る。Hereinafter, the present invention will be described based on the illustrated embodiment.
第1図は,ボーデイングブリッジ1に接続している航
空機2に対して,本発明装置によって送気している状態
を示す全体図である。図示のように本発明装置は,空港
ビル3側に固設された空調機4と,この空調機4から航
空機2の機内送気口5に接続される送気ダクトからな
り,この送気ダクトは,ボーデイングブリッジ1に沿っ
て空中懸架される剛性ダクト部分Aと,この剛性ダクト
部分Aの両端に接続される,空調機側のフレキシブルダ
クト部分Bおよび機内送気口側に接続されるフレキシブ
ルダクト部分Cとからなっている。FIG. 1 is an overall view showing a state in which air is supplied to an aircraft 2 connected to a boarding bridge 1 by the apparatus of the present invention. As shown in the drawing, the apparatus of the present invention comprises an air conditioner 4 fixed to the airport building 3 side and an air supply duct connected from the air conditioner 4 to an air supply port 5 of the aircraft 2. Is a rigid duct portion A suspended in the air along the boarding bridge 1, a flexible duct portion B connected to both ends of the rigid duct portion A, and a flexible duct portion B on the air conditioner side and a flexible duct portion connected to the air supply port side in the machine. And a duct portion C.
剛性ダクト部分Aは,その架設下に各種の作業車等が
自由に走行できるに十分な高さをもって地面GLから離れ
て水平方向に空中架設され,この剛性ダクト部分Aの長
さは全送気行程の殆んどを占めている。図示の例に見ら
れるように,この剛性ダクト部分Aは,中間に支点を設
けずに,両端の二点支持で空中架設されている。空調機
4の側の支点はその位置が固定された支柱6であり,機
内送気口5の側の支点は可動支柱7である。この可動支
柱7はボーデイングブリッジ1の移動用支柱に共用す
る。空調機4の側の固定支柱6に対する剛性ダクト部分
Aの支持は,第2図に示すように上下左右に回動するユ
ニバーサル支持装置8を介して行われており,これによ
って,剛性ダクト部分Aは支柱7の動きに従って,上下
方向,前後方向並びに左右方向にその剛性を維持したま
ま(直線を維持したまま)若干の傾斜(首振り)できる
ようになっている。この剛性ダクト部分Aの上下左右の
首振り移動が行われた場合に,空調機4の側でのダクト
の変形を吸収するために,フレキシブルダクト部分Bを
設けてある。他方,可動支柱7は航空機2の駐機位置に
応じて移動できるように走行車9に装架されている。
尚,可動支柱7は剛性ダクト部分A単独用のものとし
て,ボーデイングブリッジ1の移動用支柱と別個に設置
することもできる。The rigid duct portion A is suspended from the ground GL in the horizontal direction at a height high enough to allow various work vehicles to travel freely under the erection, and the length of the rigid duct portion A is equal to the total air supply. Most of the journey. As can be seen from the example shown in the figure, the rigid duct portion A is suspended in the air with two supports at both ends without providing a fulcrum in the middle. The fulcrum on the side of the air conditioner 4 is a column 6 whose position is fixed, and the fulcrum on the side of the air supply port 5 is a movable column 7. The movable support 7 is used commonly as a support support for the boarding bridge 1. The support of the rigid duct portion A with respect to the fixed column 6 on the side of the air conditioner 4 is performed via a universal support device 8 which rotates up, down, left and right as shown in FIG. In accordance with the movement of the column 7, a slight inclination (swinging) can be performed while maintaining its rigidity (while maintaining a straight line) in the up-down direction, the front-rear direction, and the left-right direction. A flexible duct portion B is provided to absorb the deformation of the duct on the air conditioner 4 side when the rigid duct portion A swings up, down, left and right. On the other hand, the movable column 7 is mounted on a traveling vehicle 9 so as to be movable in accordance with the parking position of the aircraft 2.
Incidentally, the movable column 7 can be used separately for the rigid duct portion A, and can be installed separately from the moving column of the boarding bridge 1.
このようにして空中架設される剛性ダクト部分Aは,
駐機位置の変動に応じて伸縮可能で且つそのスパン下に
おいて作業車等の走行自由性を確保のために中間支柱無
しでも十分な強度を維持する必要があり,しかも,その
伸縮動作は軽快に安全且つ確実に行われねばならない。
このために,本発明においては,該剛性ダクト部分Aを
径の異なる複数本のダクト管を重ね合わせ部で軸方向に
摺動可能に接合する構成とし(第1図では三本の径の異
なるダクト管10a,10b,10cを軸方向に接合した例を示し
ている),この重ね合わせ部において以下に説明するよ
うな特殊なシール構造と滑動構造を採用する。The rigid duct portion A thus installed in the air is
It must be able to expand and contract in response to changes in the parking position and maintain sufficient strength without an intermediate support to ensure the freedom of travel of the work vehicle, etc., under its span. It must be done safely and reliably.
For this purpose, in the present invention, the rigid duct portion A is configured so that a plurality of duct pipes having different diameters are slidably joined in the axial direction at the overlapped portion (in FIG. 1, three ducts having different diameters). An example in which the duct pipes 10a, 10b, and 10c are joined in the axial direction is shown), and a special sealing structure and a sliding structure as described below are employed in the overlapping portion.
第3図と第4図は,第1図のダクト管の接合部の拡大
断面図であり,第3図は最大伸長時の状態を,第4図は
減縮時の状態を示している。これらの図は第1図のダク
ト管10aと10bの接合部を例として示してあるが,他のダ
クト管接合部でも同様に現れる。したがって,以下にお
いて径小側のダクト管10aを径小ダクトSと呼び,径大
側のダクト管10bを径大ダクトLと呼ぶことにする。図
示のように,径大ダクトLの開口端11に径小ダクトSの
開口端12が同軸的に挿入され,この挿入状態における両
者の開口端11と12の間の距離が重ね合わせ部を構成す
る。この重ね合わせ距離がダクトの最大伸長時にも所定
の距離だけ確保できるようにストッパー部材13と14が,
重ね合わせ部における径大ダクトLの内面と径小ダクト
Sの外面に固設されている。このストッパー部材13と14
の位置するところよりもダクト中央部(開口端11と12と
は反対側の胴部)のダクト表面には保温外筒15をダクト
と所定の間隙を保持してダクトと同軸的に設置するとと
もに,この保温外筒15とダクトとの間隙に保温材15′を
充填してダクト表面からの放熱を防止している。3 and 4 are enlarged cross-sectional views of the junction of the duct pipes in FIG. 1. FIG. 3 shows a state at the time of maximum extension, and FIG. 4 shows a state at the time of contraction. These figures show the joint of the duct pipes 10a and 10b in FIG. 1 as an example, but the same applies to other duct pipe joints. Therefore, in the following, the small-diameter duct pipe 10a is referred to as a small-diameter duct S, and the large-diameter duct pipe 10b is referred to as a large-diameter duct L. As shown, the open end 12 of the small-diameter duct S is coaxially inserted into the open end 11 of the large-diameter duct L, and the distance between the two open ends 11 and 12 in this inserted state constitutes an overlapping portion. I do. The stopper members 13 and 14 are provided so that the overlapping distance can be secured by a predetermined distance even when the duct is fully extended.
It is fixed to the inner surface of the large-diameter duct L and the outer surface of the small-diameter duct S in the overlapping portion. These stopper members 13 and 14
At the center of the duct (the body opposite to the open ends 11 and 12) from the position of the duct, the heat insulation outer cylinder 15 is installed coaxially with the duct while maintaining a predetermined gap with the duct. The gap between the heat insulating outer cylinder 15 and the duct is filled with a heat insulating material 15 'to prevent heat radiation from the duct surface.
本発明に従う剛性ダクト部分の一つの特徴的な構造
は,重ね合わせ部を滑動自在とすると共に最大伸長時の
重ね合わせ部の距離を滑動部材によって延長し,伸長し
て空中架設されたさいの重ね合わせ部の強度を確保した
点にある。すなわち,径小ダクトSの開口端12の側に一
端が固定されかつ開口端12よりも外方に突出するアーム
16の先端に,ローラー17を,径大ダクトLの内周面上を
滑動できるように取付け,さらに,径大ダクトLの開口
端11の側に一端が固定されかつ開口端11よりも外方に突
出するアーム18の先端に,ローラー19を,径小ダクトS
の外周面上を滑動できるように取付ける。ローラー17と
19はそれぞれの開口端からの距離がほぼ等しい位置に複
数個(例えば3〜6個)並設される。これによって,両
ダクトの重ね合わせ部における荷重の支持はローラー17
と19を介して滑動自在に行われることになり,且つこの
ローラー17と19の相互の距離は開口端11と12よりもアー
ム16および18の部分だけ延長される結果,第3図のよう
にストッパー13と14が係合する最大伸長時においても接
合部における撓み抵抗が増強されることになる。また,
開口端11および12の外に突出するアーム16および18の弾
性力によりローラー17と19が常にダクトに強く圧着する
ように調整されるので,ダクト製作時の直径寸法および
真円度の精度誤差を補うことができる。また,航空機の
駐機時期に合わせた剛性ダクト部分Aのたたみ込み操作
(径大ダクトL内の径小ダクトSの長さの殆んどの部分
を収める操作),並びに伸長操作はローラー17と19の滑
動によって極めて小さな動力でスムースに行なうことが
できる。One characteristic structure of the rigid duct portion according to the present invention is that the overlapping portion is slidable and the distance of the overlapping portion at the time of maximum extension is extended by a sliding member. The point is that the strength of the joint is ensured. That is, an arm having one end fixed to the open end 12 of the small-diameter duct S and protruding outward from the open end 12.
A roller 17 is attached to the end of the large-diameter duct L so that it can slide on the inner peripheral surface thereof. Further, one end is fixed to the open end 11 of the large-diameter duct L and is located outside the open end 11. Roller 19 is attached to the tip of arm 18 that projects
So that it can slide on the outer peripheral surface of. With roller 17
A plurality (e.g., three to six) 19 are arranged side by side at positions substantially equal in distance from the respective opening ends. This allows the load to be supported by the roller 17 at the overlap of the two ducts.
3 and 19, and the distance between the rollers 17 and 19 is longer than the open ends 11 and 12 by the parts of the arms 16 and 18, as shown in FIG. Even at the maximum extension when the stoppers 13 and 14 are engaged, the bending resistance at the joint is enhanced. Also,
Due to the elastic force of the arms 16 and 18 protruding out of the open ends 11 and 12, the rollers 17 and 19 are adjusted so that they are always firmly pressed against the duct. I can make up for it. In addition, the folding operation of the rigid duct portion A (operation for storing most of the length of the small-diameter duct S in the large-diameter duct L) and the extending operation in accordance with the parking time of the aircraft and the rollers 17 and 19 are performed. Can smoothly be performed with extremely small power.
本発明に従う剛性ダクト部分のいま一つの特徴的構造
は,送気時にシールが働き,伸縮動作時にはシールが解
かれて摺動自在となるダクト重ね合わせ部のシール構造
にある。Another characteristic structure of the rigid duct portion according to the present invention is a seal structure of a duct overlapping portion in which a seal works at the time of air supply and is released and slidable at the time of expansion and contraction operation.
第5図は,第3〜4図の例で使用したシール部分の拡
大図である。本例のシールは,軟質材からなる所定の幅
をもった帯状リング20とスプリング部材21とからなり,
帯状リングの一方の縁部20aが重ね合わせ部の一方のダ
クト管の周面(図例では径小ダクトSの外周面)に固着
され,他方の縁部20bが他方のダクト管の周面(図例で
は径大ダクトLの内周面)に対して,スプリング部材21
によって付勢された遊接状態にある。そして,この遊接
部を構成する他方の縁部20bの表面には,ダクトの内面
との間で滑りを良くするスリップリング22が貼付けてあ
る。スプリング部材21は該遊接部に押圧を与える方向に
付勢されており,このために,図例ではスプリング部材
21の一方の端が径小ダクトSの外表面に固定されてい
る。このスプリング部材21は必ずしもダクトの全周面を
廻るリング状でなくてもよく,図例では帯状リング20に
対して所々に互いに間隔をあけて取付けられた複数個の
バネからなっている。また,図例では帯状リング20の一
方の縁部20aが径小ダクトSに固定され,他方の縁部20b
が径大ダクトLに遊接状態とした例が示されているが,
これとは逆に前者に遊接,後者に固定することもでき
る。いずれにしても,固定側より遊接側の縁部の方が径
小ダクトSの開口端12に近くなるように配置する。これ
によって,ダクトの内圧が高まると,帯状リング20の遊
接側がダクト内面にその圧を受けて押し付けられるので
遊接部での気密が確保される。航空機への送気操作は機
内の空調用ダクトに調和空気を送入するものであるが,
一般に航空機内の空調用ダクトは限られた空間に設置さ
れるため送気量に比較してダクト断面が小さいので通気
抵抗が大きくなり,従って送気ダクト内の内圧を高くす
る必要があるが,この内圧が高くなればなるほど遊接部
の気密が維持されるので,重ね合わせ部でのリーク量を
最少に抑えることができる。一方,ダクトの伸縮操作は
送気停止時に行われるので,遊接部での背圧が無くな
り,スリップリング22を介して抵抗なく帯状リング20は
ダクト面上を摺動する。なお本例において帯状リング20
を弾性材料で構成した場合には,スプリング部材21を用
いないでも前記の作用を果たすことができる。FIG. 5 is an enlarged view of the seal portion used in the example of FIGS. The seal of the present embodiment comprises a band-shaped ring 20 made of a soft material and having a predetermined width and a spring member 21.
One edge 20a of the band-shaped ring is fixed to the peripheral surface of one duct pipe (the outer peripheral surface of the small-diameter duct S in the illustrated example) of the overlapping portion, and the other edge 20b is the peripheral surface of the other duct pipe ( In the illustrated example, the spring member 21 is disposed on the inner peripheral surface of the large-diameter duct L).
Is in a play state biased by. A slip ring 22 is attached to the surface of the other edge portion 20b constituting the play portion so as to improve the slip with the inner surface of the duct. The spring member 21 is urged in a direction for applying pressure to the free contact portion.
One end of 21 is fixed to the outer surface of the small-diameter duct S. The spring member 21 does not necessarily have to be a ring shape that goes around the entire peripheral surface of the duct. In the illustrated example, the spring member 21 is composed of a plurality of springs that are attached to the belt-shaped ring 20 at certain intervals. In the illustrated example, one edge 20a of the belt-shaped ring 20 is fixed to the small-diameter duct S, and the other edge 20b is fixed.
In this example, the free duct is in contact with the large-diameter duct L.
Conversely, it is possible to play with the former and fix it to the latter. In any case, the edge on the free contact side is arranged closer to the open end 12 of the small diameter duct S than on the fixed side. Thus, when the internal pressure of the duct increases, the free contact side of the belt-shaped ring 20 receives the pressure and is pressed against the inner surface of the duct, so that airtightness at the free contact portion is ensured. The air supply operation to the aircraft is to supply conditioned air to the air conditioning duct inside the aircraft,
Generally, air-conditioning ducts in aircraft are installed in a limited space, so the cross-section of the duct is smaller than the amount of air supply, so the ventilation resistance increases. Therefore, it is necessary to increase the internal pressure in the air supply duct. As the internal pressure increases, the airtightness of the free contact portion is maintained, so that the amount of leakage at the overlapping portion can be minimized. On the other hand, since the expansion and contraction operation of the duct is performed when the air supply is stopped, the back pressure at the free contact portion is eliminated, and the belt-like ring 20 slides on the duct surface without resistance via the slip ring 22. In this example, the belt-like ring 20
Is formed of an elastic material, the above-mentioned action can be achieved without using the spring member 21.
第6図は,本発明に従う他のシール構造例を第5図と
同様の関係をもって示したものである。本例では,シー
ル材料として弾性材料からなるリング状の中空チューブ
24を使用し,これを,重ね合わせ部に固定した(図例で
径小ダクトSの外周面に固定した)台座25内に収めたも
のである。この中空チューブ24には圧縮空気をパイプ26
を経て適宜導入する。すなわち航空機への送気時にはホ
ース26から圧縮空気を中空チューブ24内に圧入してチュ
ーブ24を膨脹させ,これによって重ね合わせ部の隙間を
閉塞する。一方,伸縮動作時にはホース26内を常圧また
は減圧にすることによってチューブ24を収縮させ,伸縮
動作の抵抗を無くする。図示の例ではホース26をダクト
内に配置する例を示したがダクトの外側に配置すること
もできる。いずれにしても,ホース26はダクトの伸縮動
作に合わせて巻き取り巻き戻し操作を行なうようにする
のがよい。なお,中空チューブ24内には圧縮空気に代え
て液体を導入するようにしてもよい。なお,図示しない
が,ダクト管10bの開口端11の反対側の開口端にはダク
ト管10aの開口端12と同一の構造にてローラーおよびシ
ール部が形成されており,ダクト管10cの開口端に同軸
的に挿入されている。FIG. 6 shows another example of the seal structure according to the present invention in the same relationship as FIG. In this example, a ring-shaped hollow tube made of an elastic material is used as the seal material.
24, which is housed in a pedestal 25 fixed to the overlapping portion (fixed to the outer peripheral surface of the small-diameter duct S in the illustrated example). Compressed air is piped into this hollow tube 24
It is introduced as appropriate through. That is, when air is supplied to the aircraft, compressed air is pressed into the hollow tube 24 from the hose 26 to expand the tube 24, thereby closing the gap between the overlapping portions. On the other hand, at the time of expansion and contraction operation, the tube 24 is contracted by reducing the pressure inside the hose 26 to normal pressure or reduced pressure, thereby eliminating the resistance of the expansion and contraction operation. In the illustrated example, the hose 26 is arranged inside the duct. However, the hose 26 can be arranged outside the duct. In any case, it is preferable that the hose 26 performs a winding and rewinding operation in accordance with the expansion and contraction operation of the duct. Note that a liquid may be introduced into the hollow tube 24 instead of the compressed air. Although not shown, a roller and a seal are formed at the open end opposite to the open end 11 of the duct pipe 10b with the same structure as the open end 12 of the duct pipe 10a, and the open end of the duct pipe 10c is formed. Is inserted coaxially.
第7図は,剛性ダクトの重ね合わせ部を滑動自在とす
る他の実施例を示したものである。本例の場合には,前
記第3図の例に比べて,径大ダクトL(10b)および径
小ダクトS(10a)の開口端11および12を保温外筒15の
端よりも比較的長い距離l1およびl2だけ延長して突出さ
せ,この保温外筒を持たない露出管部分28と29の先端部
に,スプリングで付勢されたローラー17,19が取付けら
れている。径小ダクトS側に取付けられたローラー17は
径大ダクトLの内面に滑動するように,そして径大ダク
トL側に取付けたローラー19は径小ダクトSの外面(保
温外筒の外面)に滑動するようにしてある。FIG. 7 shows another embodiment in which the overlapping portion of the rigid duct is slidable. In the case of this embodiment, the open ends 11 and 12 of the large-diameter duct L (10b) and the small-diameter duct S (10a) are relatively longer than the end of the heat-insulating outer cylinder 15 as compared with the example of FIG. distance l 1 and l 2 is protruded by extending the tip portion of the exposed tube portions 28 and 29 without this heat insulating outer cylinder, the rollers 17 and 19 is attached, which is urged by a spring. The roller 17 attached to the small-diameter duct S is slid on the inner surface of the large-diameter duct L, and the roller 19 attached to the large-diameter duct L is attached to the outer surface of the small-diameter duct S (the outer surface of the heat-insulating outer cylinder). It is made to slide.
第8図は径小ダクトS側に取付けられたローラー17の
詳細を拡大して示したものである(径大ダクトL側のロ
ーラー19も向きは逆となるが同じ構造を有する)が,図
示のように,ダクト10aの開口端12の近くに孔30を開
け,この孔30にローラー保持装置31をネジ32によって装
着する。ローラー保持装置31は,該孔30に装着させる円
筒状シリンダー33内と,その中に収容されるロッド34,
スプリング35およびスペーサ36からなっている。ロッド
34の一端にはシリンダー33の内面に摺接するスピンドル
部37が取付けられ,このスピンドル部37にローラー17が
取付けられる。また,ロッド34の他端はシリンダー33の
突き当り面38に設けた開口39を貫通している。開口39は
方形を有し,この開口39を貫通する部分のロッド34もそ
の断面が方形である。これによって,ロッド34が軸回り
に回動するのが防止される。そして,シリンダー33内に
おいてシリンダーの突き当り面38とスピンドル部37との
間に介装されたコイルスプリング35によって,ローラー
17はその滑動面の方向に弾性的に押圧される。また,所
定の長さをもつ両端開口の筒からなるスペーサ36がロッ
ド34の外側に同軸的に遊嵌させてある。このスペーサ36
の長さのスプリングが必要以上に圧縮されないような長
さに設計することにより,ローラー17が必要以上にロー
ラー保持装置31側に押え込まれ径小ダクトSの保温外筒
15が径大ダクトLの内径側に接触することが阻止され
る。以上のように構成されたスプリング付きローラー17
の複数個(第7図の例では3個)がダクト管10aの同一
円周上に等間隔で設置され,他方,ダクト管10bにも,
その向きは逆であるが同様にして複数個のローラー19が
設置されることによって,ダクト管10aと10bはこれらロ
ーラーを支持点として常時同心的に滑動自在に保持され
る。なお,第7図にはシール手段が描かれてはいない
が,先に説明した例えば第5図や第6図のものが使用さ
れ,またストッパー部材も適宜設置される。ただし,第
7図の例では径小ダクトS(10a)に突出して設けられ
るローラー19の保持装置自身が一方のストッパーを兼ね
ることができる。FIG. 8 is an enlarged view showing the details of the roller 17 attached to the small-diameter duct S (the roller 19 on the large-diameter duct L also has the same structure, although the direction is reversed). A hole 30 is opened near the open end 12 of the duct 10a as shown in FIG. The roller holding device 31 includes a cylindrical cylinder 33 mounted in the hole 30 and a rod 34 contained therein.
It consists of a spring 35 and a spacer 36. rod
At one end of 34, a spindle portion 37 that is in sliding contact with the inner surface of the cylinder 33 is attached, and the roller 17 is attached to the spindle portion 37. The other end of the rod 34 penetrates an opening 39 provided in the abutting surface 38 of the cylinder 33. The opening 39 has a square shape, and the cross section of the rod 34 passing through the opening 39 is also square. This prevents the rod 34 from rotating around the axis. Then, a roller is provided by a coil spring 35 interposed between the abutting surface 38 of the cylinder and the spindle portion 37 in the cylinder 33.
17 is elastically pressed in the direction of its sliding surface. In addition, a spacer 36 having a predetermined length and having a tube having both ends open is coaxially loosely fitted to the outside of the rod 34. This spacer 36
The length of the spring is designed not to be compressed more than necessary, so that the roller 17 is pressed more than necessary to the roller holding device 31 side and the outer cylinder of the small diameter duct S is kept warm.
15 is prevented from contacting the inner diameter side of the large-diameter duct L. Roller 17 with spring configured as above
(Three in the example of FIG. 7) are installed at equal intervals on the same circumference of the duct pipe 10a, and on the other hand,
The direction is reversed, but by installing a plurality of rollers 19 in the same manner, the duct tubes 10a and 10b are always slidably held concentrically with these rollers as supporting points. Although the sealing means is not shown in FIG. 7, for example, those described above with reference to FIGS. 5 and 6 are used, and a stopper member is appropriately provided. However, in the example of FIG. 7, the holding device itself of the roller 19 provided to protrude from the small-diameter duct S (10a) can also serve as one stopper.
以上のように,本発明の航空機への送気装置は従来の
地下埋設ダクトを空中架設の剛性ダクトとしたものであ
り,したがって設置費用が低廉化すると共に保温材を充
填した保温外筒をダクトの外側に備えるので保温性が向
上し且つ通気抵抗も少なくなり,取扱も格段に向上し
た。そして,剛性ダクト部分は空中架設されるのでその
下に作業車や作業員が自由に出入でき,航空機への送気
動作中においても他の作業に支障を来すことがなくなっ
た。そして剛性ダクトは複数本のダクト管の接合によっ
て行い且つその重ね合わせ部において特殊なシール構造
と支持構造を採用したので,長いスパンをもって空中架
設されても中間支柱なしで自重や風力に十分に耐える強
度をもち且つ完全気密が達成され,伸縮操作も抵抗なく
簡単に行なうことができる。As described above, the air supply device for an aircraft according to the present invention uses a conventional underground duct as an aerial rigid duct, thus reducing installation costs and using a heat insulating outer tube filled with a heat insulating material. Because it is provided outside the, the heat retention was improved, the ventilation resistance was reduced, and the handling was significantly improved. Since the rigid duct portion is installed in the air, a work vehicle and workers can freely enter and exit under the rigid duct portion, so that other operations are not hindered even during the air supply operation to the aircraft. The rigid duct is constructed by joining multiple duct pipes and adopts a special seal structure and support structure at the overlapping part, so that even if it is installed in the air with a long span, it can sufficiently withstand its own weight and wind force without intermediate supports It has high strength and complete hermeticity, and can be easily expanded and contracted without any resistance.
特に本発明装置ではボーデイングブリッジの伸縮動作
(伸長時の長さ約40〜50m,短縮時の長さ約20m)に合わ
せて剛性ダクトを伸縮動作させることができ,駐機中の
航空機にボーデイングブリッジを接続すると同時に送気
口にもフレキシブルダクトが接続可能となるので一層そ
の使用が便宜となるものである。しかも,そのさいにボ
ーデイングブリッジに剛性ダクトの荷重を預けることな
く従来設計のままのボーデイングブリッジに沿わせて設
置することができ,したがって,ボーデイングブリッジ
の新設既設を問わず本発明装置の並設が可能である。ま
た転じて,ボーディングブリッジに剛性、アクトの荷重
をかけて並設或いは一体化して内蔵する場合にも,本発
明によるダクト管のシール手段および滑動部材はボーデ
イングブリッジの伸縮動作に十分に対応することができ
る。このようなことから,本発明装置は,特に大型空港
施設の合理化に大きく貢献することができる。In particular, in the device of the present invention, the rigid duct can be extended and retracted in accordance with the extension and contraction movement of the boarding bridge (length of about 40 to 50 m when extended, about 20 m when shortened). Since the flexible duct can be connected to the air supply port at the same time as the connection of the inking bridge, the use thereof is further facilitated. Moreover, at this time, the rigid bridge can be installed along the boarding bridge of the conventional design without entrusting the load of the rigid duct to the boarding bridge. Side by side is possible. In addition, the sealing means and the sliding member of the duct pipe according to the present invention can sufficiently cope with the expansion and contraction operation of the boarding bridge even when the boarding bridge is installed side by side or integrated by applying rigidity and act load to the boarding bridge. be able to. For this reason, the apparatus of the present invention can greatly contribute to rationalization of large airport facilities.
第1図は本発明に従う装置例の使用状態を示す全体図,
第2図はユニバーサル支持装置の拡大図,第3図と第4
図は本発明に従う剛性ダクトの重ね合わせ部の最大伸長
時とやや短縮時の状態を示す断面図,第5図は第3〜4
図のシール構造部分の拡大断面図,第6図は本発明に従
う他のシール構造を示す第5図同様の拡大断面図,第7
図は剛性ダクトの重ね合わせ部を滑動自在とする他の実
施例を示す断面図,第8図は第7図のローラー支持装置
部分の拡大断面図,第9図は従来の航空機への送気装置
の例を示す配置図である。 1……ボーデイングブリッジ,2……航空機,4……空調
機,5……機内送気口,6……固定支柱,7……移動支柱,8…
…ユニバーサル支持装置,13,14……ストッパー部材,15
……保温外筒,16,18……ローラー支持アーム,17,19……
ローラー,20……帯状リング,21……スプリング部材,22
……スリップリング,24……中空チューブ,26……圧縮空
気送気用ホース,31……ローラー支持装置,35……スプリ
ング,36……スペーサ。 A……剛性ダクト部分,B,C……フレキシブルダクト部
分,L……径大ダクト,S……径小ダクト。FIG. 1 is an overall view showing a use state of an example of an apparatus according to the present invention,
FIG. 2 is an enlarged view of the universal support device, FIG. 3 and FIG.
FIG. 5 is a cross-sectional view showing the superposed portion of the rigid duct according to the present invention at the time of maximum extension and at the time of slightly shortening, and FIG.
FIG. 6 is an enlarged sectional view of the seal structure shown in FIG. 6, and FIG. 6 is an enlarged sectional view similar to FIG. 5, showing another seal structure according to the present invention.
The figure is a sectional view showing another embodiment in which the overlapping portion of the rigid duct is slidable, FIG. 8 is an enlarged sectional view of the roller supporting device portion of FIG. 7, and FIG. 9 is a conventional air supply to an aircraft. FIG. 3 is a layout diagram illustrating an example of a device. 1… Boarding bridge, 2… Aircraft, 4… Air conditioner, 5… In-flight air vent, 6… Fixed prop, 7… Movable prop, 8…
… Universal support device, 13,14 …… Stopper member, 15
…… Insulated outer cylinder, 16,18 …… Roller support arm, 17,19 ……
Roller, 20 ... Band-shaped ring, 21 ... Spring member, 22
… Slip ring, 24… Hollow tube, 26… Compressed air supply hose, 31… Roller support device, 35… Spring, 36… Spacer. A: Rigid duct part, B, C ... Flexible duct part, L ... Large diameter duct, S ... Small diameter duct.
Claims (3)
空調機の給気口に一端が接続され,他端が航空機の機内
送気口に接続される送気ダクトと,からなる駐機中の航
空機への送気装置において, 前記送気ダクトの全長のうち少なくとも駐機航空機に至
る屋外部分において地表より上に水平方向に空中架設さ
れる剛性ダクト部分を有し, この剛性ダクト部分は,径の異なる2本以上のダクト管
をそれらの接合部で重ね合わせ部をもって軸方向に連設
された構造を有し, 該ダクト管の重ね合わせ部にシール手段が介装されると
共に,この重ね合わせ部が滑動部材を介して滑動自在に
構成されており, 該ダクト管が最大に伸長したときにも該ダクト管の外側
表面が露出しないように径大ダクトと径小ダクトの外側
に保温材を充填した保温外筒が取付けられ, 前記の滑動部材が,管端より突出して設けられたローラ
ーまたは管端近傍のダクト管に取付けられたスプリング
付ローラーからなる, ことを特徴とする駐機中の航空機への送気装置。An air conditioner having a fixed installation position and an air supply duct having one end connected to an air supply port of the air conditioner and the other end connected to an air supply port in the aircraft. An air supply device for an in-flight aircraft, comprising: a rigid duct portion that is installed in the air horizontally above the ground surface at least in an outdoor portion of the entire length of the air supply duct and that extends to a parked aircraft; Has a structure in which two or more duct pipes having different diameters are connected in the axial direction with an overlapped portion at their joint, and a sealing means is interposed at the overlapped portion of the duct pipes, The overlapping portion is slidable via a sliding member, and is provided outside the large-diameter duct and the small-diameter duct so that the outer surface of the duct tube is not exposed even when the duct tube extends to its maximum. Heat insulation outer tube filled with heat insulation material The air supply device for a parked aircraft, wherein the sliding member comprises a roller provided protruding from a pipe end or a roller with a spring mounted on a duct pipe near the pipe end. .
グからなり,この帯状リングの一方の縁部が,該重ね合
わせ部の一方のダクト管の周面に固着され,この帯状リ
ングの他方の縁部が他方のダクト管の周面に対して,付
勢手段を介してまたは該帯状リング自身の弾性によっ
て,遊接されている請求項1に記載の送気装置。2. The sealing means comprises a band-like ring having a predetermined width, and one edge of the band-like ring is fixed to the peripheral surface of one of the duct pipes of the overlapping portion. 2. The air supply device according to claim 1, wherein the other edge is loosely connected to the peripheral surface of the other duct pipe via a biasing means or by the elasticity of the band-shaped ring itself.
管で他方のダクト管を自己支持できるに十分な重ね合わ
せ量が確保され,この重ね合わせ量の確保はストッパー
部材によってダクト管の伸長が制限されることによって
行われる請求項1または2に記載の送気装置。3. The overlapping portion of the duct is provided with a sufficient overlapping amount so that one duct tube can support the other duct tube by itself, and the overlapping amount is secured by a stopper member by extending the duct tube. The air supply device according to claim 1, wherein the air supply is performed by restricting.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP1-11174 | 1989-01-20 | ||
JP1117489 | 1989-01-20 |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH02279498A JPH02279498A (en) | 1990-11-15 |
JP2579213B2 true JP2579213B2 (en) | 1997-02-05 |
Family
ID=11770693
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP1087956A Expired - Lifetime JP2579213B2 (en) | 1989-01-20 | 1989-04-10 | Air supply device for aircraft |
Country Status (1)
Country | Link |
---|---|
JP (1) | JP2579213B2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR100924225B1 (en) * | 2007-12-21 | 2009-11-02 | 오티스 엘리베이터 컴파니 | Boarding Bridge with Air Conditiontioner Facility |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS56143687U (en) * | 1980-03-28 | 1981-10-29 |
-
1989
- 1989-04-10 JP JP1087956A patent/JP2579213B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPH02279498A (en) | 1990-11-15 |
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