JP3371119B2 - Solar cell mounting device - Google Patents
Solar cell mounting deviceInfo
- Publication number
- JP3371119B2 JP3371119B2 JP2000051965A JP2000051965A JP3371119B2 JP 3371119 B2 JP3371119 B2 JP 3371119B2 JP 2000051965 A JP2000051965 A JP 2000051965A JP 2000051965 A JP2000051965 A JP 2000051965A JP 3371119 B2 JP3371119 B2 JP 3371119B2
- Authority
- JP
- Japan
- Prior art keywords
- solar cell
- sheet
- locking
- mounting
- outer peripheral
- 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
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Landscapes
- Photovoltaic Devices (AREA)
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、被取付け体、たと
えば飛行船、気球および飛行艇などのような飛行体およ
び地上の柔軟構造体であるドームなどに搭載される太陽
電池を、その被取付け体の外周面に取付けるための構造
とその装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a mounted body, for example, a solar cell mounted on a flying body such as an airship, a balloon and an airship and a dome which is a flexible structure on the ground. And a device for mounting on the outer peripheral surface of the.
【０００２】[0002]
【従来の技術】太陽電池取付け装置は、たとえば飛行船
の推進機を駆動するために、太陽電池の電力を利用する
構成において、必要になる。従来では、アモルファス半
導体から成る太陽電池を、飛行船の外周面に粘着テープ
で直接に固定し、または太陽電池を接着剤で飛行船の外
周面に接着して固定する。このような構成では、太陽電
池と飛行体外周面との剛性差が大きいため、飛行船は、
内部に充填されたＨｅガスの熱による膨張、収縮などの
変形に起因して、太陽電池が剥離しやすく、また太陽電
池が飛行船の外周面の変形および熱膨張差によって損傷
するおそれがある。2. Description of the Related Art Solar cell mounting devices are needed in configurations that utilize solar cell power, for example, to drive propulsion units in airships. Conventionally, a solar cell made of an amorphous semiconductor is directly fixed to the outer peripheral surface of the airship with an adhesive tape, or the solar cell is fixed to the outer peripheral surface of the airship with an adhesive. In such a configuration, since the difference in rigidity between the solar cell and the outer peripheral surface of the flying body is large, the airship
Due to the deformation such as expansion and contraction of the He gas filled inside due to heat, the solar cell may be easily peeled off, and the solar cell may be damaged due to deformation of the outer peripheral surface of the airship and a difference in thermal expansion.
【０００３】太陽電池は、たとえば約６０００〜７００
０ｍ2である広い面積にわたって太陽電池が設けられ、
したがってこのような広大な太陽電池を、接着剤で飛行
船の外周面に接着すると、太陽電池の交換等のメンテナ
ンスがきわめて困難な状況になる。A solar cell has, for example, about 6000 to 700.
The solar cells are installed over a large area of 0 m 2 .
Therefore, if such a vast solar cell is bonded to the outer peripheral surface of the airship with an adhesive, maintenance such as replacement of the solar cell becomes extremely difficult.
【０００４】従来ではまた、このような飛行船が、高度
約２０ｋｍの成層圏で浮かべられて用いられるとき、約
３０〜５０ｍ／ｓｅｃの高速度の気流に接触しても、飛
行船の外周面から剥離しないようにするための工夫は、
考慮されていない。Conventionally, when such an airship is floated and used in the stratosphere at an altitude of about 20 km, it does not separate from the outer peripheral surface of the airship even if it comes into contact with a high-velocity airflow of about 30 to 50 m / sec. The idea to do so is
Not considered.
【０００５】典型的な先行技術は、特開平６−１６３９
６４である。この先行技術では、飛行船体のほぼ全周を
囲む太陽電池拡張モジュールを構成し、この太陽電池拡
張モジュールは、多数の太陽電池モジュールが連結され
て構成され、各太陽電池モジュールは、平らな細長い弾
性体を井桁状に配置して構成された弾性支持体上に太陽
電池ユニットを接着剤で固定して構成され、各弾性体の
一方端部におす形コネクタを設け、他方の端部にめす形
コネクタを設け、隣接する太陽電池モジュールを連結す
る。太陽電池拡張モジュールは、飛行船体の船首および
船尾付近で飛行船体のエンベロープに固定して連結し、
または連結部分を設けずに、エンベロープに腹巻き状に
太陽電池モジュールをかぶせる。A typical prior art is Japanese Patent Laid-Open No. 6-1639.
64. In this prior art, a solar cell expansion module that surrounds almost the entire circumference of an airship is configured, and this solar cell expansion module is configured by connecting a large number of solar cell modules, and each solar cell module is a flat elongated elastic member. The solar cell unit is fixed on the elastic support body by arranging the body in a cross shape with an adhesive, and a connector is provided at one end of each elastic body and a female connector is provided at the other end. A connector is provided to connect adjacent solar cell modules. The solar cell expansion module is fixedly connected to the envelope of the airship near the bow and stern of the airship,
Alternatively, the solar cell module is covered in a belly with the envelope without providing the connecting portion.
【０００６】この先行技術は、多数の各太陽電池モジュ
ールが個別的に飛行船体に取付けられておらず、したが
って成層圏における高速度の気流に接触するとき、太陽
電池拡張モジュールは、飛行船体の外周面から剥離して
離脱するおそれがあり、実用化は困難である。According to this prior art, a large number of solar cell modules are not individually attached to an airship hull, and therefore, when the solar cell expansion module comes into contact with a high-velocity airflow in the stratosphere, the solar cell expansion module has an outer surface of the airship hull. It is difficult to put it into practical use because there is a risk of peeling from it and coming off.
【０００７】また、飛行船に限らず、地上のドームな
ど、空気が充填された柔軟な膜を有する構造物において
も外周面に太陽電池を粘着する場合に同様の問題を有す
る。Further, not only the airship, but also a structure having a flexible film filled with air, such as a ground dome, has the same problem when the solar cell is adhered to the outer peripheral surface.
【０００８】[0008]
【発明が解決しようとする課題】本発明の目的は、被取
付け体の外周面に取付けられる太陽電池を、被取付け体
の外周面の膨張、収縮などの変形に拘わらず、太陽電池
を損傷しないようにし、軽量化することができ、高速度
の気流によっても被取付け体の外周面から剥離すること
がないようにし、しかも太陽電池の交換可能な太陽電池
取付け装置を提供することである。SUMMARY OF THE INVENTION It is an object of the present invention to prevent a solar cell mounted on the outer peripheral surface of an attached body from damaging the solar cell regardless of deformation such as expansion or contraction of the outer peripheral surface of the attached body. In this way, it is possible to provide a solar cell mounting device which can be made lighter, and which is prevented from being separated from the outer peripheral surface of the mounted body even by a high-speed air flow, and in which the solar cell can be replaced.
【０００９】[0009]
【課題を解決するための手段】本発明は、（ａ）太陽電
池の受光面を覆う透光性第１シートと、太陽電池の背面
を覆い、太陽電池の周縁部の外方で第１シートと気密に
固定される第２シートとを有し、内部空間に、太陽電池
を収納する太陽電池アセンブリと、（ｂ）太陽電池アセ
ンブリの周縁部に設けられる第１係止片と、（ｃ）被取
付け体の外周面に固定され、第１係止片を覆う可撓性を
有する取付け用シートと、（ｄ）被取付け体の外周面で
取付け用シートに設けられ、第１係止片に着脱可能に係
止する第２係止片とを含むことを特徴とする飛行体の太
陽電池取付け装置である。According to the present invention, there is provided (a) a translucent first sheet for covering a light receiving surface of a solar cell and a rear sheet of the solar cell, and the first sheet is provided outside a peripheral portion of the solar cell. And a second sheet that is airtightly fixed, and a solar cell assembly for accommodating a solar cell in an internal space, (b) a first locking piece provided at a peripheral portion of the solar cell assembly, and (c) A flexible mounting sheet that is fixed to the outer peripheral surface of the mounted body and covers the first locking piece; and (d) an outer peripheral surface of the mounted body that is provided on the mounting sheet and is attached to the first locking piece. A solar cell mounting device for an aircraft, comprising: a second locking piece that is detachably locked.
【００１０】本発明に従えば、第１シートと第２シート
との間で太陽電池が介在されてサンドイッチ構造とされ
た太陽電池アセンブリを、被取付け体の外周面に、第１
および第２係止片によって着脱可能に取付けることがで
きる。第１係止片は、第１または第２シートの周縁部に
たとえばほぼ全周囲にわたって設けられ、この第１係止
片が、可撓性を有する取付け用シートにたとえばほぼ全
周囲にわたって設けられた第２係止片に係止するので、
被取付け体の外周面が内部に充填された気体の膨張、収
縮による変形が生じても、そのような変形によって、剛
性の高い太陽電池が損傷または剥離するおそれをなくす
ことができる。According to the present invention, a solar cell assembly having a sandwich structure in which a solar cell is interposed between a first sheet and a second sheet is provided on the outer peripheral surface of a body to be attached.
And it can be detachably attached by the second locking piece. The first locking piece is provided on, for example, substantially the entire circumference on the peripheral portion of the first or second sheet, and the first locking piece is provided on, for example, the substantially entire circumference on the flexible mounting sheet. Since it is locked to the second locking piece,
Even if deformation occurs due to expansion and contraction of the gas with which the outer peripheral surface of the mounted body is filled, it is possible to eliminate the risk of damage or peeling of the highly rigid solar cell due to such deformation.
【００１１】さらに第１および第２係止片の係止によっ
て、太陽電池アセンブリが被取付け体の外周面に装着さ
れるので、前述の接着剤を用いて太陽電池を被取付け体
の外周面に接着する先行技術に比べて、大幅な軽量化を
図ることができる。Further, since the solar cell assembly is mounted on the outer peripheral surface of the mounted body by the locking of the first and second locking pieces, the solar cell is mounted on the outer peripheral surface of the mounted body using the above-mentioned adhesive. The weight can be significantly reduced as compared with the prior art of bonding.
【００１２】さらに本発明に従えば、第１および第２係
止片は、着脱可能であり、したがって被取付け体である
飛行体をたとえば地上におろした状態で、太陽電池アセ
ンブリを交換することができ、メンテナンスが優れてい
る。Further in accordance with the present invention, the first and second locking pieces are detachable, so that the solar cell assembly can be replaced while the flying body, which is the mounted body, is placed on the ground, for example. Yes, it has good maintenance.
【００１３】さらに本発明に従えば、太陽電池アセンブ
リの周縁部に設けられる第１係止片は、飛行体の外周面
に固定された取付け用シートによって覆われるので、た
とえば成層圏において高速度の気流が、第１および第２
係止片に直接に作用することはなく、太陽電池アセンブ
リが飛行体の外周面から剥離して離脱するおそれはな
い。被取付け体が地上のドームなどの構造物であっても
同様に、気流などによって太陽電池アセンブリが外周面
から剥離して離脱することが防がれる。Further, according to the present invention, since the first locking piece provided on the peripheral portion of the solar cell assembly is covered with the mounting sheet fixed to the outer peripheral surface of the flying body, for example, high-speed air flow in the stratosphere. But the first and second
It does not act directly on the locking piece, and there is no risk of the solar cell assembly peeling off from the outer peripheral surface of the aircraft. Even if the mounted body is a structure such as a dome on the ground, the solar cell assembly can be prevented from being peeled off from the outer peripheral surface and separated from the outer peripheral surface due to airflow or the like.
【００１４】また本発明は、（ａ）太陽電池の受光面を
覆う透光性第１シートと、太陽電池の背面を覆い、太陽
電池の周縁部の外方で第１シートと気密に固定される第
２シートとを有し、内部空間に、太陽電池を収納する太
陽電池アセンブリと、（ｂ）太陽電池アセンブリの周縁
部、被取付け体の外周面とは反対側に設けられ、太陽電
池アセンブリの前記周縁部から内方に延び、可撓性を有
する係止用シートと、（ｃ）係止用シートに設けられる
第１係止片と、（ｄ）被取付け体の外周面に固定され、
第１係止片を覆う可撓性を有する取付け用シートと、
（ｅ）被取付け体の外周面で取付け用シートに設けら
れ、第１係止片に着脱可能に係止する第２係止片とを含
むことを特徴とする太陽電池取付け装置である。Further, according to the present invention, (a) a translucent first sheet that covers the light receiving surface of the solar cell and a back surface of the solar cell, and is hermetically fixed to the first sheet outside the peripheral portion of the solar cell. A second sheet that has a second sheet that accommodates a solar cell in the internal space, and (b) is provided on the opposite side of the peripheral edge of the solar cell assembly and the outer peripheral surface of the mounted body. A locking sheet that extends inwardly from the peripheral edge portion and has flexibility, (c) a first locking piece provided on the locking sheet, and (d) is fixed to the outer peripheral surface of the mounted body. ,
A flexible mounting sheet covering the first locking piece;
(E) A solar cell mounting device including a second locking piece that is provided on the mounting sheet on the outer peripheral surface of the mounted body and that is detachably locked to the first locking piece.
【００１５】本発明に従えば、剛性の高い太陽電池が、
被取付け体の外周面の変形によって、損傷または剥離を
なくすことができ、また接着剤を用いないのでメンテナ
ンスが良好である。また被取付け体として飛行体を用い
た場合、成層圏において高速度の気流によって太陽電池
アセンブリが飛行体の外周面から剥離して脱落するおそ
れはない。According to the present invention, a highly rigid solar cell is
Deformation of the outer peripheral surface of the attached body can eliminate damage or peeling, and since no adhesive is used, maintenance is good. Further, when a flying body is used as the mounted body, there is no possibility that the solar cell assembly will peel off from the outer peripheral surface of the flying body and fall off due to the high-speed air flow in the stratosphere.
【００１６】しかも本発明に従えば、可撓性を有する係
止用シートに設けられる第１係止片と、可撓性を有する
取付け用シートに設けられる第２係止片とを着脱可能に
係止するようにしたので、第１および第２係止片の相互
の着脱操作が容易になる。Further, according to the present invention, the first locking piece provided on the flexible locking sheet and the second locking piece provided on the flexible mounting sheet can be attached and detached. Since they are locked, it is easy to attach and detach the first and second locking pieces to and from each other.
【００１７】また本発明は、係止用シートと取付け用シ
ートとを各開放端側から挟み、第１および第２係止片の
長手方向に沿って移動操作することによって、第１およ
び第２係止片を係止／離脱する係止部材を、さらに含む
ことを特徴とする。Further, according to the present invention, the locking seat and the mounting seat are sandwiched from the respective open end sides, and the first and second locking pieces are moved along the longitudinal direction of the first and second locking pieces. It is characterized by further including a locking member for locking / releasing the locking piece.
【００１８】本発明に従えば、操作部材を、第１および
第２係止片の長手方向に沿って移動操作することによっ
て、第１および第２係止片の係止および離脱を行うこと
ができ、操作性が向上される。このことは特に被取付け
体が大形であることに鑑み、操作性が良好であることは
重要である。According to the invention, the first and second locking pieces can be locked and released by moving the operating member along the longitudinal direction of the first and second locking pieces. And the operability is improved. This is especially important in that the operability is good, considering that the mounted body is large.
【００１９】また本発明は、第１および第２係止片のい
ずれか一方は、頂部が膨出した突条であり、いずれか他
方は、前記頂部が弾発的に嵌合して係止する係止溝を有
し、操作部材には、移動操作方向の一方端に、第１およ
び第２係止片をそれぞれ案内する一対の第１案内用切欠
きが形成され、他方端に、係止した第１および第２係止
片を案内する前記一対の第１案内用切欠きが合流して単
一の第２案内用切欠きが形成されることを特徴とする。Further, according to the present invention, one of the first and second locking pieces is a ridge having a bulged top portion, and the other of the first and second locking pieces is elastically fitted and locked at the top portion. The operating member has a pair of first guiding notches for guiding the first and second locking pieces, respectively, at one end in the movement operating direction, and the engaging member has an engaging groove at the other end. The pair of first guide notches for guiding the stopped first and second locking pieces merge to form a single second guide notch.
【００２０】本発明に従えば、突条の膨出した頂部が係
止溝に弾発的に嵌合して係止し、着脱が容易であるとと
もに、係止用シートと取付け用シートとを、操作部材の
一対の第１案内用切欠きに案内し、この操作部材を、第
１案内用切欠きが移動操作方向下流側に移動することに
よって、突条と係止溝とが嵌合して係止することがで自
動的に可能になる。これとは逆に、第１案内用切欠きが
移動操作方向上流側になるように操作部材を移動操作す
ることによって、相互に嵌合して係止している突条と係
止溝とを、離脱することが自動的に可能になる。According to the present invention, the bulged top portion of the ridge is elastically fitted and locked in the locking groove so that it can be easily attached and detached, and the locking seat and the mounting seat are separated. , The pair of first guiding notches of the operating member are guided, and the first guiding notch is moved to the downstream side in the moving operation direction so that the projection and the locking groove are fitted to each other. It becomes possible automatically by locking it. On the contrary, by operating the operating member so that the first guide notch is located on the upstream side in the moving operation direction, the projection and the locking groove that are fitted and locked to each other are secured. , It is possible to leave automatically.
【００２１】また本発明は、取付け用シートの少なくと
も被取付け体の外周面に固定されるシート部分は、伸縮
しやすく、かつ撓んで変形しやすい材料から成ることを
特徴とする。Further, the present invention is characterized in that at least the seat portion fixed to the outer peripheral surface of the body to be attached of the attachment sheet is made of a material which easily expands and contracts and is easily bent and deformed.
【００２２】本発明に従えば、取付け用シートの被取付
け体の外周面に固定されるシート部分は、被取付け体の
機体を構成するシートと同様に伸縮しやすく、かつ撓ん
で変形しやすい材料、たとえば合成樹脂材料などから成
る。したがって取付け用シートが、被取付け体の外周面
から剥離するおそれをなくすことができる。上述のよう
に伸縮しやすく撓んで変形しやすい材料は、取付け用シ
ートの被取付け体外周面に固定されるシート部分だけで
あってもよいけれども、取付け用シートの全体を構成し
てもよい。According to the present invention, the seat portion of the mounting sheet, which is fixed to the outer peripheral surface of the body to be attached, is easily stretchable, and is likely to be bent and deformed similarly to the sheet constituting the body of the body to be attached. , A synthetic resin material, for example. Therefore, the attachment sheet can be prevented from peeling off from the outer peripheral surface of the attached body. As described above, the material that easily expands and contracts and is easily deformed may be only the sheet portion fixed to the outer peripheral surface of the mounting sheet, but may be the entire mounting sheet.
【００２３】また本発明は、取付け用シートの外周面
と、太陽電池アセンブリの第１シートの取付け用シート
付近で取付け用シートから露出した表面とにわたって、
粘着テープが貼着されることを特徴とする。The present invention also relates to the outer peripheral surface of the mounting sheet and the surface exposed from the mounting sheet near the mounting sheet of the first sheet of the solar cell assembly.
It is characterized in that an adhesive tape is attached.
【００２４】本発明に従えば、粘着テープによって、取
付け用シートと第１シートとを、外方から貼着し、これ
によって高速度の気流が生じているたとえば成層圏など
においても、第１および第２係止片の係止状態が確実に
保たれる。これによって太陽電池アセンブリの被取付け
体外周面からの剥離を確実に防ぐことができる。According to the present invention, the attaching sheet and the first sheet are adhered from the outside by the adhesive tape, and the first and the second sheets are also attached in the stratosphere where a high-speed airflow is generated. (2) The locking state of the locking pieces is reliably maintained. This can surely prevent the solar cell assembly from being peeled off from the outer peripheral surface of the mounted body.
【００２５】また本発明は、被取付け体は飛行体であ
り、第１および第２係止片は、飛行体の船尾側で周方向
に分断された部分を有し、この分断部分には、太陽電池
に接続されるリード線が配置され、飛行体には、太陽電
池の電力によって駆動される推進機が設けられ、飛行体
の機首が空気の流れの上流に向かうように操舵手段が設
けられることを特徴とする。According to the present invention, the attached body is a flying body, and the first and second locking pieces have a circumferentially divided portion on the stern side of the flying body. The lead wire connected to the solar cell is arranged, the aircraft is provided with a propulsion device driven by the electric power of the solar cell, and the steering means is provided so that the nose of the aircraft is directed upstream of the air flow. It is characterized by being.
【００２６】本発明に従えば、飛行体に設けられた推進
機は、太陽電池の電力によって駆動され、推進機および
操舵手段の働きによって、飛行体の機首が空気の流れの
上流に向かうように操舵され、これによって空力抵抗を
できるだけ小さくすることができる。According to the present invention, the propulsion unit provided in the aircraft is driven by the electric power of the solar cell so that the nose of the aircraft is directed upstream of the air flow by the action of the propulsion unit and the steering means. The aerodynamic drag can be minimized as a result.
【００２７】太陽電池のリード線は、第１および第２係
止片の周方向に分断された部分を経て、外部に取り出さ
れ、太陽電池からの電力がリード線を介して外部に供給
される。さらに本発明に従えば、第１および第２係止片
は周方向に分断されており、この分断された部分は飛行
体の船尾側であるので、船首が気流の上流に向かう姿勢
では、前記分断部分が高速度の気流に接触することを、
できるだけ回避することができ、太陽電池アセンブリが
飛行体から剥離することを抑制することができる。The lead wire of the solar cell is taken out to the outside through the circumferentially divided portions of the first and second locking pieces, and the electric power from the solar cell is supplied to the outside through the lead wire. . Further, according to the invention, the first and second locking pieces are divided in the circumferential direction, and the divided portion is on the stern side of the aircraft, so that in the posture in which the bow heads upstream of the air flow, That the divided part comes into contact with the high-speed air flow,
This can be avoided as much as possible, and the solar cell assembly can be prevented from peeling off from the flying body.
【００２８】[0028]
【発明の実施の形態】図１は本発明の実施の一形態の飛
行船２８（後述の図７参照）の太陽電池取付け装置１の
一部の断面図であり、図２は飛行船２８の太陽電池取付
け装置１の平面図である。太陽電池アセンブリ２は、飛
行船２８の機体２９の外周面３に、着脱可能な取付け手
段４によって取付けられる。1 is a partial sectional view of a solar cell mounting device 1 of an airship 28 (see FIG. 7 described later) according to an embodiment of the present invention, and FIG. 2 is a solar cell of the airship 28. FIG. 3 is a plan view of the mounting device 1. The solar cell assembly 2 is attached to the outer peripheral surface 3 of the body 29 of the airship 28 by the detachable attachment means 4.
【００２９】図３は、図１および図２に示される飛行船
２８の太陽電池取付け装置１の分解した状態を示す断面
図である。太陽電池アセンブリ２は、偏平な矩形の太陽
電池５を、第１シート６と第２シート７とで挟んでサン
ドイッチした構成を有する。太陽電池５は、図１および
図３の上方に臨む受光面８を有し、この受光面８を覆う
第１シート６は、透光性材料から成り、たとえば透明で
ある。第２シート７は、第１シート６よりも小さい面積
を有し、太陽電池５の下方で、第１シート６の太陽電池
５側の表面（図１の下面）で、接続部９で気密に接続さ
れる。第１および第２シート６，７は、たとえば熱可塑
性合成樹脂性であり、可撓性を有し、接続部９で熱溶着
される。第２シート７は、第１シート６と同一材料から
成ってもよいけれども、異なる材料から成ってもよく、
太陽電池５の背面を覆う。こうして第１および第２シー
ト６，７によって形成された気密の内部空間に、太陽電
池５が収納される。FIG. 3 is a sectional view showing the solar cell mounting device 1 of the airship 28 shown in FIGS. 1 and 2 in a disassembled state. The solar cell assembly 2 has a configuration in which a flat rectangular solar cell 5 is sandwiched between a first sheet 6 and a second sheet 7. The solar cell 5 has a light receiving surface 8 facing upward in FIGS. 1 and 3, and the first sheet 6 covering the light receiving surface 8 is made of a light transmissive material and is, for example, transparent. The second sheet 7 has an area smaller than that of the first sheet 6, and is airtight at the connecting portion 9 on the surface of the first sheet 6 on the solar cell 5 side (the lower surface in FIG. 1) below the solar cell 5. Connected. The first and second sheets 6 and 7 are made of, for example, thermoplastic synthetic resin, have flexibility, and are heat-welded at the connecting portion 9. The second sheet 7 may be made of the same material as the first sheet 6, but may be made of a different material,
The back surface of the solar cell 5 is covered. In this way, the solar cell 5 is housed in the airtight internal space formed by the first and second sheets 6 and 7.
【００３０】太陽電池アセンブリ２の第１シート６の周
縁部１１は、取付け手段４によって、飛行船の機体２９
の外周面３に着脱可能に取付けられる。取付け手段４に
おいて、前記周縁部１１には、飛行船２８の外周面３と
は反対側に臨んで外方に突出した突起である第１係止片
１３が一体的に形成される。第１係止片１３は、その頂
部１３ａが図１の左右に膨出し、連結部１３ｂに連なる
構成を有する。頂部１３ａの軸線に直角な断面は、たと
えばほぼ円形であってもよい。取付け用シート１４に
は、第１係止片１３が弾発的に嵌合して係止する係止溝
１５を有する第２係止片１６が設けられる。取付け用シ
ート１４は、飛行船の外周面３に一端部１７ａが固定部
分３９で固定された固定部１７と、この固定部１７に参
照符１８で示される接続部で溶着によって、または接着
剤によって一体的に固定された被覆部１９とを有する。
固定部７と被覆部１９とは、いずれも偏平に構成され
る。固定部７は、飛行船２８の外周面３を構成する機体
２９である可撓性を有する膜と同様な材料から成っても
よく、伸縮しやすくかつ撓んで変形しやすい材料から成
る。固定部１７は、飛行船の外周面３に、前記固定部分
３９で、溶着によって、または接着剤を用いて固定され
る。被覆部１９は、固定部１７と同一材料から成っても
よいけれども、第２係止片１６が第１係止片１３に確実
に嵌合するために充分な強度を有する材料、たとえば合
成樹脂材料などから成ってもよい。第１および第２シー
ト６，７は、可撓性を有し、たとえば０．１〜０．５ｍ
ｍの厚みを有する。取付け用シート１４の厚みは、たと
えば０．１〜０．５ｍｍである。The peripheral portion 11 of the first sheet 6 of the solar cell assembly 2 is attached to the airframe 29 of the airship by the attachment means 4.
It is detachably attached to the outer peripheral surface 3. In the attachment means 4, the peripheral edge portion 11 is integrally formed with a first locking piece 13 which is a protrusion protruding outwardly facing the outer peripheral surface 3 of the airship 28. The first locking piece 13 has a configuration in which the top portion 13a thereof bulges to the left and right in FIG. 1 and is continuous with the connecting portion 13b. The cross section of the top portion 13a perpendicular to the axis may be, for example, substantially circular. The mounting sheet 14 is provided with a second locking piece 16 having a locking groove 15 into which the first locking piece 13 is elastically fitted and locked. The mounting sheet 14 is integrally formed with a fixing portion 17 whose one end portion 17a is fixed to a fixing portion 39 on the outer peripheral surface 3 of the airship and a welding portion or a bonding agent at a connecting portion indicated by reference numeral 18 to the fixing portion 17. And a covering portion 19 that is fixed in place.
The fixing portion 7 and the covering portion 19 are both flat. The fixing portion 7 may be made of the same material as the flexible film that is the machine body 29 that constitutes the outer peripheral surface 3 of the airship 28, and is made of a material that easily expands and contracts and is easily deformed by bending. The fixing portion 17 is fixed to the outer peripheral surface 3 of the airship at the fixing portion 39 by welding or using an adhesive. The covering portion 19 may be made of the same material as that of the fixing portion 17, but a material having sufficient strength so that the second locking piece 16 can be securely fitted to the first locking piece 13, for example, a synthetic resin material. It may consist of The first and second sheets 6 and 7 have flexibility and are, for example, 0.1 to 0.5 m.
It has a thickness of m. The thickness of the mounting sheet 14 is, for example, 0.1 to 0.5 mm.
【００３１】第１および第２シート６，７および取付け
用シート１４の固定部１７および被覆部１９は、たとえ
ばテドラー（デュポン社製商品名）などのポリふっ化ビ
ニル（略称ＰＶＦ）などによって実現されてもよく、ま
たはポリエチレン、塩化ビニル、ポリアミド系樹脂など
によって実現されてもよく、前述のように固定部１７と
被覆部１９とは、相互に異なる材料から成ってもよく、
さらに繊維によって強化された合成樹脂材料から成って
もよい。The fixing portions 17 and the covering portions 19 of the first and second sheets 6 and 7 and the attachment sheet 14 are realized by polyvinyl fluoride (abbreviation PVF) such as Tedlar (trade name of DuPont). Or may be realized by polyethylene, vinyl chloride, polyamide-based resin or the like, and as described above, the fixing portion 17 and the covering portion 19 may be made of materials different from each other,
Further, it may be made of a fiber-reinforced synthetic resin material.
【００３２】飛行船の機体２９を構成する膜の厚みは、
たとえば３ｍｍである。第１および第２シート６，７な
らびに取付け用シート１４の熱膨張率は、飛行船の機体
２９を構成する膜の熱膨張率と同様に、太陽電池５の熱
膨張率に比べて充分大きいけれども、太陽電池５は、第
１および第２シート６，７によって形成された収納空間
内に、これらの第１および第２シート６，７と相互に変
位可能に設けられているので、熱変形によって太陽電池
５に応力が作用することが防がれる。したがって太陽電
池５の破損を防ぐことができる。The thickness of the film forming the airframe body 29 is
For example, it is 3 mm. Although the thermal expansion coefficients of the first and second sheets 6 and 7 and the mounting sheet 14 are sufficiently larger than the thermal expansion coefficient of the solar cell 5, like the thermal expansion coefficient of the film forming the airframe body 29 of the airship, Since the solar cell 5 is provided in the storage space formed by the first and second sheets 6 and 7 so as to be displaceable with respect to the first and second sheets 6 and 7, the solar cell 5 may be deformed by thermal deformation. It is possible to prevent stress from acting on the battery 5. Therefore, damage to the solar cell 5 can be prevented.
【００３３】取付け用シート１４の外周面と、太陽電池
アセンブリ２の第１シート６の取付け用シート１４から
露出した表面とにわたって、粘着テープ２１が貼着され
る。粘着テープ２１は、可撓性を有する合成樹脂製フィ
ルムの図１における下面に、粘着性を有する接着剤が塗
布されて構成される。粘着テープ２１は、太陽電池５の
受光面８を覆わないように配置され、したがってその受
光面８全体に、太陽光が確実に照射される。取付け用シ
ート１４は、太陽電池アセンブリ２の全周にわたって設
けられる。取付け手段４は、太陽電池アセンブリ２のほ
ぼ全周にわたって設けられる。太陽電池アセンブリ２
は、飛行船２８の外周面３に、前述の先行技術に関連し
て述べた接着剤を用いて接着されることはなく、太陽電
池アセンブリ２は着脱交換可能であり、メンテナンスが
容易である。The adhesive tape 21 is attached to the outer peripheral surface of the mounting sheet 14 and the surface of the first sheet 6 of the solar cell assembly 2 exposed from the mounting sheet 14. The adhesive tape 21 is configured by applying an adhesive having adhesiveness to the lower surface of the flexible synthetic resin film in FIG. The adhesive tape 21 is arranged so as not to cover the light receiving surface 8 of the solar cell 5, so that the entire light receiving surface 8 is reliably irradiated with sunlight. The mounting sheet 14 is provided over the entire circumference of the solar cell assembly 2. The mounting means 4 is provided over substantially the entire circumference of the solar cell assembly 2. Solar cell assembly 2
Is not adhered to the outer peripheral surface 3 of the airship 28 using the adhesive described in connection with the above-mentioned prior art, and the solar cell assembly 2 is removable and replaceable, and maintenance is easy.
【００３４】図４は図２のセクションＡ４付近の一部の
断面図であり、図５はセクションＡ４の平面図である。
第１シート６の周縁部１１には、１カ所に切欠き２３が
形成され、これによって第１係止片１３が周方向に分断
されている。また取付け用シート１４の少なくとも被覆
部１９には、切欠き２４が形成される。これらの切欠き
２３，２４によって第１および第２係止片１３，１６の
分断部分２５が形成される。分断部分２５には、可撓性
を有するリード線２６が配置される。リード線２６の端
部は、太陽電池５に接続される。FIG. 4 is a sectional view of a part near the section A4 in FIG. 2, and FIG. 5 is a plan view of the section A4.
A notch 23 is formed at one location on the peripheral portion 11 of the first sheet 6, and the first locking piece 13 is circumferentially divided by this. Further, a cutout 24 is formed in at least the covering portion 19 of the mounting sheet 14. The cutouts 23 and 24 form the dividing portions 25 of the first and second locking pieces 13 and 16. A flexible lead wire 26 is arranged in the divided portion 25. The ends of the lead wires 26 are connected to the solar cell 5.
【００３５】図６は、分断部分２５で周方向に分断され
た取付け手段４を示す簡略化した平面図である。分断部
分２５から、上述のように、リード線２６が取り出され
る。FIG. 6 is a simplified plan view showing the mounting means 4 which is divided in the circumferential direction at the dividing portion 25. The lead wire 26 is extracted from the divided portion 25 as described above.
【００３６】これらの分断部分２５によって、太陽電池
アセンブリ２と飛行船の外周面３との間の空間２７が外
部と連通する。したがってこの空間２７内に空気が封入
されることはなく、太陽電池アセンブリ２は、前記外周
面３に密着して配置されることができる。したがって太
陽電池アセンブリ２が高速度の気流によって振動するこ
となどが防がれ、太陽電池アセンブリ２が、前記表面３
から離脱することを防ぐことができる。By these divided portions 25, the space 27 between the solar cell assembly 2 and the outer peripheral surface 3 of the airship communicates with the outside. Therefore, air is not enclosed in the space 27, and the solar cell assembly 2 can be placed in close contact with the outer peripheral surface 3. Therefore, it is possible to prevent the solar cell assembly 2 from vibrating due to a high-speed air flow, and the solar cell assembly 2 may be attached to the surface 3
Can be prevented from leaving.
【００３７】図７は、本発明の太陽電池取付け装置１が
実施される飛行船２８の全体の構成を示す斜視図であ
る。飛行船２８の機体２９は、テドラー（デュポン社製
商品名）などの合成樹脂材料製膜から成り、その機体２
９のほぼ上半分の外周面３には、前述のように本発明に
従う太陽電池アセンブリ２が多数個、配置される。各太
陽電池アセンブリ２は、たとえば横１ｍ×縦１ｍの大き
さであってもよい。機体２９の長さは約２３０ｍであ
り、外径は約５３ｍφであってもよい。機体２９を構成
する膜内には、Ｈｅガスなどの気体が充填され、浮力が
発生される。FIG. 7 is a perspective view showing the overall structure of an airship 28 in which the solar cell mounting apparatus 1 of the present invention is implemented. The body 29 of the airship 28 is made of a synthetic resin material film such as Tedlar (trade name manufactured by DuPont), and the body 2
A large number of solar cell assemblies 2 according to the present invention are arranged on the outer peripheral surface 3 of the substantially upper half of 9, as described above. Each solar cell assembly 2 may be, for example, 1 m wide × 1 m long. Airframe 29 may have a length of about 230 m and an outer diameter of about 53 mφ. A gas such as He gas is filled in the film forming the machine body 29 to generate buoyancy.
【００３８】機体２９の下部には、推進機３０，３１が
取付けられる。この推進機３０，３１は、モータを有
し、太陽電池５からの電力によって駆動され、推進機３
０，３１のプロペラが回転される。機体２９にはまた、
操舵手段３２が設けられ、機体２９の姿勢が制御され
る。操舵手段３２は、たとえば前後バロネットの空気の
移動および昇降舵を含むとともに、操縦のための翼が含
まれる。この飛行船２８は、機体２９の機首３３が空気
の流れの上流に向かうように、したがって船尾３４が下
流に向かうように、操舵手段３２が動作される。On the lower part of the machine body 29, propulsion machines 30 and 31 are attached. Each of the propulsion units 30 and 31 has a motor and is driven by the electric power from the solar cell 5,
The 0, 31 propeller is rotated. Aircraft 29 also has
Steering means 32 is provided to control the attitude of the airframe 29. The steering means 32 includes, for example, movement of air in the front and rear baronets and elevators, and also includes wings for steering. In this airship 28, the steering means 32 is operated so that the nose 33 of the airframe 29 is directed upstream of the air flow, and thus the stern 34 is directed downstream.
【００３９】再び図２を参照して、太陽電池取付け装置
１において、分断部分２５が、船尾３４側になるよう
に、飛行船８の外周面３に配置される。参照符３６は、
機首３３の方向を示し、参照符３７は、機体２９の上部
である天頂方向を示す。分断部分２５が船尾３４側に配
置され、これによって高速度の太陽電池アセンブリ２
が、飛行船２８の外周面３から剥離することができる。Referring again to FIG. 2, in the solar cell mounting device 1, the dividing portion 25 is arranged on the outer peripheral surface 3 of the airship 8 so as to be on the stern 34 side. Reference numeral 36 is
The direction of the nose 33 is shown, and the reference numeral 37 shows the zenith direction, which is the upper part of the machine body 29. The divided portion 25 is arranged on the stern 34 side, which allows the high-speed solar cell assembly 2
However, it can be separated from the outer peripheral surface 3 of the airship 28.
【００４０】取付け手段４は、前述の実施例では、第１
および第２係止片１３，１６を含む構成であったけれど
も、本発明の実施の他の形態では、そのほかの相互に係
合／離脱が可能な構成であってもよく、また操作性を向
上するために、操作片を、太陽電池アセンブリ２の周方
向に移動することによって、相互に係合離脱が可能な構
成を有していてもよく、さらにファスナなどの構成であ
ってもよい。The mounting means 4 is the first in the above embodiment.
Although the second locking pieces 13 and 16 are included, in another embodiment of the present invention, other mutually engageable / disengageable structures may be used, and the operability is improved. In order to do so, the operation piece may have a configuration in which it can be engaged and disengaged from each other by moving the operation piece in the circumferential direction of the solar cell assembly 2, and may have a configuration such as a fastener.
【００４１】本発明の実施の他の形態では、飛行体の太
陽電池に太陽光が照射されない時間帯では、飛行体に搭
載された燃料電池からの電力を用いて、推進機を駆動す
ることができ、このようにして太陽電池と燃料電池との
出力を切換える手段を介して、推進機に電力を供給する
ように構成してもよい。In another embodiment of the present invention, the propulsion unit can be driven by using the electric power from the fuel cell mounted on the flight vehicle in a time period when the solar cell of the flight vehicle is not irradiated with sunlight. Alternatively, the electric power may be supplied to the propulsion unit via the means for switching the output of the solar cell and the fuel cell in this manner.
【００４２】図８は、本発明の実施の他の形態の一部の
断面図である。この実施の形態は、前述の図１〜図７の
実施の形態に類似し、対応する部分には同一の参照符を
付す。注目すべきはこの実施の形態では、係止用シート
４１が用いられる。この係止用シート４１は、可撓性を
有する材料から成り、たとえば前述の第１および第２シ
ート６，７などと同様な材料から成ってもよい。係止用
シート４１は、太陽電池アセンブリ２の第１シート６の
周縁部１１で、飛行船２８の機体２９の外周面３とは反
対側（図８の上方）に、固定部分４２で固定されて設け
られる。この係止用シート４１は、太陽電池アセンブリ
２の前記周縁部１１から内方に、すなわち図８において
固定部分４２から左方に、延びる。本発明の実施の他の
形態では、第１シート６が上述の固定部分４２で屈曲さ
れて、係止用シート４１が形成されてもよい。係止用シ
ート４１には、第１係止片１３が設けられる。FIG. 8 is a partial sectional view of another embodiment of the present invention. This embodiment is similar to the embodiment of FIGS. 1 to 7 described above, and corresponding parts are designated by the same reference numerals. It should be noted that the locking sheet 41 is used in this embodiment. The locking sheet 41 is made of a flexible material, and may be made of the same material as the above-mentioned first and second sheets 6 and 7, for example. The locking sheet 41 is fixed to the peripheral portion 11 of the first sheet 6 of the solar cell assembly 2 on the side opposite to the outer peripheral surface 3 of the airframe 28 of the airship 28 (upper side in FIG. 8) by the fixing portion 42. It is provided. The locking sheet 41 extends inward from the peripheral portion 11 of the solar cell assembly 2, that is, from the fixed portion 42 in FIG. 8 to the left. In another embodiment of the present invention, the first sheet 6 may be bent at the above-mentioned fixing portion 42 to form the locking sheet 41. The locking sheet 41 is provided with the first locking piece 13.
【００４３】図９は、図８に示される本発明の実施の他
の形態の一部の斜視図である。操作部材４３は、第１お
よび第２係止片１３，１５を相互に係止および離脱する
ために用いられる。この係止部材４３を、第１移動操作
方向４４に移動操作することによって、第１および第２
係止片１３，１５を相互に係止することができる。操作
部材４３を、第１移動操作方向４４とは逆方向の第２移
動操作方向４５に移動操作することによって、第１およ
び第２係止片１３，１５を離脱することができる。FIG. 9 is a perspective view of a part of another embodiment of the present invention shown in FIG. The operation member 43 is used to mutually lock and release the first and second locking pieces 13 and 15. By operating the locking member 43 in the first moving operation direction 44, the first and second
The locking pieces 13 and 15 can be locked to each other. The first and second locking pieces 13 and 15 can be disengaged by operating the operating member 43 in the second moving operating direction 45, which is opposite to the first moving operating direction 44.
【００４４】図１０は操作部材４３の斜視図であり、図
１１は操作部材４３の前記一方端４６側から見た斜視図
である。操作部材４３は、たとえば合成樹脂などの材料
から成り、立方体または直方体状の形状に構成されても
よい。操作部材４３には、第１移動操作方向４４の下流
側（図９の右方、図１０の左方）の一方端４６に、一対
の第１案内用切欠き４８，４９が形成される。一方の第
１案内用切欠き４８には、第１および第２係止片１３，
１５が相互に離脱した状態における第１係止片１３と、
係止用シート４１の第１係止片１３よりも第１シート６
の内方側の部分５１とが嵌まり込む。FIG. 10 is a perspective view of the operating member 43, and FIG. 11 is a perspective view of the operating member 43 as seen from the one end 46 side. The operating member 43 is made of a material such as synthetic resin, and may be formed into a cubic or rectangular parallelepiped shape. The operation member 43 has a pair of first guiding notches 48 and 49 formed at one end 46 on the downstream side in the first movement operation direction 44 (right side in FIG. 9, left side in FIG. 10). One of the first guiding notches 48 has the first and second locking pieces 13,
A first locking piece 13 in a state where 15 are separated from each other;
The first sheet 6 rather than the first locking piece 13 of the locking sheet 41
The portion 51 on the inner side of is fitted.
【００４５】図１２は、操作部材４３の他方端４７から
見た斜視図である。操作部材４３には、他方端４７に、
単一の第２案内用切欠き５４が形成される。他方の第１
案内用切欠き４９には、第２係止片１５と、取付け用シ
ート１４の第２係止片４５よりも太陽電池アセンブリ２
の内方（図９の左方）の部分５２とが嵌まり込む。操作
部材４３の第１および第２案内用切欠き４８，４９；５
４は、係止用シート４１と取付け用シート１４とを、そ
れらの各開放端５６，５７側から挟む。一対の第２案内
用切欠き４８，４９は、合流点５５で合流し、単一の第
２案内用切欠き５４に連なる。操作部材４３の前記一方
端４６は、移動操作方向４４の下流側の端部であり、前
記他方端４７は移動操作方向４５の下流側の端部であ
る。FIG. 12 is a perspective view seen from the other end 47 of the operating member 43. On the other end 47 of the operating member 43,
A single second guiding notch 54 is formed. First of the other
In the guide notch 49, the second locking piece 15 and the second locking piece 45 of the mounting sheet 14 are provided more than the solar cell assembly 2.
The inner part 52 (the left part of FIG. 9) is fitted. First and second guiding notches 48, 49; 5 of the operating member 43
4 sandwiches the locking seat 41 and the mounting seat 14 from the respective open ends 56, 57 side thereof. The pair of second guiding notches 48 and 49 meet at a meeting point 55 and are connected to a single second guiding notch 54. The one end 46 of the operating member 43 is an end portion on the downstream side in the moving operation direction 44, and the other end 47 is an end portion on the downstream side in the moving operation direction 45.
【００４６】操作部材４３を、図９における第１移動操
作方向４４に移動操作することによって、一対の各第１
案内用切欠き４８，４９に案内される第１および第２係
止片１３，１５が、操作部材４３の合流点５５付近で嵌
合して係止し、第２案内用切欠き５４から、第１および
第２係止片１３，１５が係止した状態となる。操作部材
４３を、第１移動操作方向４４とは逆方向の第２移動操
作方向４５に移動することによって、係止状態にある第
１および第２係止片１３，１５が嵌合状態を脱し、離脱
される。こうして操作部材４３を、太陽電池アセンブリ
２の周縁部１１に沿って移動操作することによって、第
１および第２係止片１３，１５を自動的に係止および離
脱することができ、操作性が向上される。操作部材４３
は、図５に関連して前述した分断部分２５において、係
止用シート４１および取付け用シート１４から図５の左
方に取外すことができる。したがって第１および第２係
止片１３，１６の係止状態とした後、分断部分２５から
操作部材４３を取外すことができる。したがって操作部
材４３が設けられたままになることによって、高速度の
気流の悪影響を受けることが確実に防がれる。By moving the operating member 43 in the first moving operating direction 44 in FIG.
The first and second locking pieces 13 and 15 guided by the guide notches 48 and 49 are fitted and locked in the vicinity of the confluence point 55 of the operation member 43, and from the second guide notch 54, The first and second locking pieces 13 and 15 are locked. By moving the operating member 43 in the second moving operating direction 45 opposite to the first moving operating direction 44, the first and second locking pieces 13 and 15 in the locked state are released from the fitted state. Will be withdrawn. By moving the operating member 43 along the peripheral portion 11 of the solar cell assembly 2 in this manner, the first and second locking pieces 13 and 15 can be automatically locked and released, and the operability is improved. Be improved. Operating member 43
Can be removed from the locking seat 41 and the mounting seat 14 to the left in FIG. 5 at the dividing portion 25 described above with reference to FIG. Therefore, after the first and second locking pieces 13 and 16 are brought into the locked state, the operating member 43 can be detached from the dividing portion 25. Therefore, by keeping the operation member 43 provided, the adverse effect of the high-speed airflow can be reliably prevented.
【００４７】本発明の実施の他の形態では、第１および
第２係止片１３，１５の取付け場所が相互に逆であって
もよく、すなわち第２係止片１５が第１シート６または
係止用シート４１に形成され、第１係止片１３が取付け
用シート１４に形成されてもよい。第１および第２係止
片１３，１５は、そのほかの構成を有していてもよい。In another embodiment of the present invention, the mounting positions of the first and second locking pieces 13 and 15 may be opposite to each other, that is, the second locking piece 15 may be the first sheet 6 or The first locking piece 13 may be formed on the locking sheet 41 and the first locking piece 13 may be formed on the mounting sheet 14. The first and second locking pieces 13 and 15 may have other configurations.
【００４８】本発明は、飛行船だけでなく、気球、飛行
艇およびそのほかの飛行体に関連して広範囲に実施する
ことができる。The present invention may be implemented in a wide variety of ways not only in airships, but also in the context of balloons, airships and other air vehicles.
【００４９】上述した実施形態では、飛行船に太陽電池
を取付ける場合の太陽電池取付け装置として説明したけ
れども、本発明はこのような形態に限らず、たとえば可
撓性を有する柔軟な膜によって覆われ、空気が充填され
る地上のドーム構造物などの外周面に太陽電池を取付け
る場合にも適用可能である。In the above-described embodiment, the solar cell mounting device for mounting a solar cell on an airship is described, but the present invention is not limited to such a configuration, and is covered with a flexible film having flexibility, for example. It can also be applied to a case where a solar cell is mounted on the outer peripheral surface of a ground dome structure or the like filled with air.
【００５０】[0050]
【発明の効果】請求項１の本発明によれば、太陽電池を
第１および第２シートによってサンドイッチした太陽電
池アセンブリを、第１および第２係止片によって着脱可
能にして取付け用シートによって被取付け体の外周面に
着脱可能に取付けることができるようになる。本発明に
よれば、前述の先行技術における大面積にわたって多量
の接着剤を用いることはなく、またはメンテナンスの容
易化を図ることができる。According to the present invention of claim 1, the solar cell assembly in which the solar cell is sandwiched by the first and second sheets is made detachable by the first and second locking pieces and is covered by the mounting sheet. It becomes possible to removably attach to the outer peripheral surface of the attachment body. According to the present invention, it is possible to facilitate the maintenance without using a large amount of adhesive over a large area in the above-mentioned prior art.
【００５１】さらに本発明によれば、取付け用シート
は、太陽電池アセンブリの第１係止片が設けられた周縁
部付近を覆うので、被取付け体の外周面に沿って流れる
気流によって、太陽電池アセンブリが剥離してしまうお
それをなくし、太陽電池アセンブリを、被取付け体に確
実に取付けることができるようになる。Further, according to the present invention, since the mounting sheet covers the vicinity of the peripheral edge portion of the solar cell assembly where the first locking piece is provided, the solar cell is generated by the air flow flowing along the outer peripheral surface of the mounted body. It is possible to securely attach the solar cell assembly to the mounted body without the risk of the assembly peeling off.
【００５２】また本発明によれば、第１および第２係止
片は着脱可能であり、太陽電池アセンブリの交換が容易
であり、メンテナンスが容易になる。Further, according to the present invention, the first and second locking pieces can be attached and detached, the solar cell assembly can be easily replaced, and the maintenance becomes easy.
【００５３】請求項２の本発明によれば、第１係止片が
可撓性係止用シートに設けられ、第２係止片が取付け用
シートに設けられ、これによって第１および第２係止片
の相互の係止および離脱を容易に行うことができる。According to the present invention of claim 2, the first locking piece is provided on the flexible locking sheet, and the second locking piece is provided on the mounting sheet, whereby the first and second locking pieces are provided. The locking pieces can be easily locked and released from each other.
【００５４】請求項３の本発明によれば、操作部材を、
第１および第２係止片の長手方向に沿って移動操作する
ことによって、第１および第２係止片の係止および離脱
を自動的に行うことができ、操作性が良好であり、この
ことは特に被取付け体が大形である場合も重要である。According to the present invention of claim 3, the operating member is
By moving and operating the first and second locking pieces in the longitudinal direction, the first and second locking pieces can be automatically locked and released, and the operability is excellent. This is especially important when the mounted object is large.
【００５５】請求項４の本発明によれば、突条の膨出し
た頂部が係止溝に弾発的に嵌合して係止し、操作部材を
移動操作方向に前後に移動することによって、係止およ
び離脱をすることが容易に可能であり、構成が簡単であ
るとともに操作性が良好である。According to the present invention of claim 4, the bulged top portion of the ridge is elastically fitted and locked in the locking groove, and the operating member is moved back and forth in the moving operation direction. It is possible to easily engage and disengage, and the configuration is simple and the operability is good.
【００５６】請求項５の本発明によれば、取付け用シー
トは、少なくとも被取付け体の外周面に固定されるシー
ト部分が、被取付け体を構成する膜であるシートと同様
に伸縮しやすく、かつ撓んで変形しやすい材料から成る
ので、被取付け体の外周面から剥離するおそれをなくす
ことができ、取付け用シートを、被取付け体の外周面に
確実に固定しておくことができる。According to the fifth aspect of the present invention, in the mounting sheet, at least the seat portion fixed to the outer peripheral surface of the mounted body easily expands and contracts similarly to the sheet which is a film constituting the mounted body, Further, since it is made of a material that is easily bent and deformed, it is possible to eliminate the risk of peeling from the outer peripheral surface of the mounted body, and it is possible to securely fix the mounting sheet to the outer peripheral surface of the mounted body.
【００５７】請求項６の本発明によれば、粘着テープを
用いて、取付け用シートの外周面と、第１シートとにわ
たって、粘着テープを貼着し、これによって高速度の気
流による第１および第２係止片の係止が外れてしまうお
それがなくなり、太陽電池アセンブリが被取付け体の外
周面から剥離することを防ぐことができる。According to the sixth aspect of the present invention, the adhesive tape is attached to the outer peripheral surface of the attachment sheet and the first sheet by using the adhesive tape, whereby the first and the second sheets are formed by the high-speed air flow. There is no risk that the second locking piece will be unlocked, and the solar cell assembly can be prevented from peeling from the outer peripheral surface of the mounted body.
【００５８】請求項７の本発明によれば、飛行体の推進
機は、太陽電池の電力によって駆動され、操舵手段によ
って飛行体の機首を、空気の流れの上流に向かうように
し、これによって空力抵抗をできるだけ少なくして、飛
行体をたとえば地球の上空の予め定める地点に、定点滞
留することができ、この太陽電池に接続されるリード線
は、第１および第２係止片の分断された部分から外部に
取り出される。このような分断部分は、飛行体の船尾側
に配置されるので、高速度の気流によって第１および第
２係止片が離脱するおそれをできるだけなくすことがで
きる。さらにこのような分断された部分の働きによっ
て、太陽電池と飛行体の外周面との間の空間２７の不所
望な空気を外部に排出し、太陽電池アセンブリを飛行体
の外周面にぴったりと沿わせて、取付けることができる
ようになる。According to the present invention of claim 7, the propulsion device of the flying body is driven by the electric power of the solar cell, and the nose of the flying body is directed to the upstream of the air flow by the steering means. The aerodynamic drag can be kept as low as possible to allow the air vehicle to stay at a fixed point, for example at a predetermined point above the earth, and the lead wire connected to this solar cell is separated from the first and second locking pieces. It is taken out from the open part. Since such a divided portion is arranged on the stern side of the aircraft, it is possible to eliminate the possibility that the first and second locking pieces are separated due to the high-speed airflow. Further, due to the function of such a divided portion, undesired air in the space 27 between the solar cell and the outer peripheral surface of the flying body is discharged to the outside, and the solar cell assembly is closely aligned with the outer peripheral surface of the flying body. It will be possible to install it.
【図１】本発明の実施の一形態の飛行船の太陽電池取付
け装置１の一部の断面図である。FIG. 1 is a partial cross-sectional view of a solar cell mounting device 1 for an airship according to an embodiment of the present invention.
【図２】飛行船の太陽電池取付け装置１の平面図であるFIG. 2 is a plan view of a solar cell mounting device 1 for an airship.
【図３】図１および図２に示される飛行船の太陽電池取
付け装置１の分解した状態を示す断面図である。FIG. 3 is a cross-sectional view showing an exploded state of the solar cell mounting device 1 for the airship shown in FIGS. 1 and 2.
【図４】図２のセクションＡ４付近の一部の断面図であ
る。FIG. 4 is a partial cross-sectional view in the vicinity of section A4 in FIG.
【図５】図２のセクションＡ４付近の平面図である。5 is a plan view near section A4 in FIG. 2. FIG.
【図６】分断部分２５で周方向に分断された取付け手段
４を示す簡略化した平面図である。FIG. 6 is a simplified plan view showing the attachment means 4 divided in the circumferential direction at a dividing portion 25.
【図７】本発明の太陽電池取付け装置１が実施される飛
行船２８の全体の構成を示す斜視図である。FIG. 7 is a perspective view showing the overall configuration of an airship 28 in which the solar cell mounting apparatus 1 of the present invention is implemented.
【図８】本発明の実施の他の形態の一部の断面図であ
る。FIG. 8 is a partial cross-sectional view of another embodiment of the present invention.
【図９】図８に示される本発明の実施の他の形態の一部
の斜視図である。9 is a partial perspective view of another embodiment of the present invention shown in FIG.
【図１０】操作部材４３の斜視図である。FIG. 10 is a perspective view of an operation member 43.
【図１１】操作部材４３の前記一方端４６側から見た斜
視図である。FIG. 11 is a perspective view of the operating member 43 as viewed from the one end 46 side.
【図１２】操作部材４３の他方端４７から見た斜視図で
ある。FIG. 12 is a perspective view of the operating member 43 as viewed from the other end 47 thereof.
１ 飛行船の太陽電池取付け装置 ２ 太陽電池アセンブリ ４ 取付け手段 ５ 太陽電池 ６ 第１シート ７ 第２シート １１ 周縁部 １３ 第１係止片 １４ 取付け用シート １６ 第２係止片 ２１ 粘着テープ ２３，２４ 切欠き ２５ 分断部分 ２６ リード線 ２８ 飛行船 ２９ 機体 ３０，３１ 推進機 ３２ 操舵手段 ３３ 機首 ３４ 船尾 ４１ 係止用シート ４３ 操作部材 ４４ 第１移動操作方向 ４５ 第２移動操作方向 ４６ 一方端 ４７ 他方端 ４８，４９ 第１案内用切欠き ５４ 第２案内用切欠き ５６，５７ 開放端 1 Solar cell mounting device for airships 2 Solar cell assembly 4 Mounting means 5 solar cells 6 First sheet 7 Second sheet 11 Perimeter 13 First locking piece 14 Mounting sheet 16 Second locking piece 21 Adhesive tape 23, 24 notches 25 part 26 Lead wire 28 Airship 29 aircraft 30,31 propulsion machine 32 Steering means 33 nose 34 Stern 41 Locking sheet 43 Operation member 44 First movement operation direction 45 Second movement operation direction 46 one end 47 the other end 48,49 First guide notch 54 Second guide notch 56,57 open end
フロントページの続き (56)参考文献 特開 平６−163964（ＪＰ，Ａ) 特開 平５−193573（ＪＰ，Ａ) 特開2001−199397（ＪＰ，Ａ) 特開 平４−5198（ＪＰ，Ａ) 実開 平５−19099（ＪＰ，Ｕ) 実開 昭58−180799（ＪＰ，Ｕ) (58)調査した分野(Int.Cl.7，ＤＢ名) B64B 1/14 H01L 31/042 Continuation of the front page (56) Reference JP-A-6-163964 (JP, A) JP-A-5-193573 (JP, A) JP-A-2001-199397 (JP, A) JP-A-4-5198 (JP, A) Actual development Hei 5-19099 (JP, U) Actual development Sho 58-180799 (JP, U) (58) Fields investigated (Int.Cl. 7 , DB name) B64B 1/14 H01L 31/042
Claims (7)
１シートと、 太陽電池の背面を覆い、太陽電池の周縁部の外方で第１
シートと気密に固定される第２シートとを有し、 内部空間に、太陽電池を収納する太陽電池アセンブリ
と、 （ｂ）太陽電池アセンブリの周縁部に設けられる第１係
止片と、 （ｃ）被取付け体の外周面に固定され、第１係止片を覆
う可撓性を有する取付け用シートと、 （ｄ）被取付け体の外周面で取付け用シートに設けら
れ、第１係止片に着脱可能に係止する第２係止片とを含
むことを特徴とする飛行体の太陽電池取付け装置。1. A transparent first sheet for covering a light receiving surface of a solar cell; and a first sheet outside a peripheral portion of the solar cell for covering a rear surface of the solar cell.
A solar cell assembly that has a seat and a second sheet that is airtightly fixed, and that houses a solar cell in the internal space; (b) a first locking piece that is provided at a peripheral portion of the solar cell assembly; ) A flexible mounting sheet that is fixed to the outer peripheral surface of the mounted body and covers the first locking piece, and (d) an outer peripheral surface of the mounted body that is provided on the mounting sheet and has a first locking piece. A second locking piece that is detachably locked to the solar cell.
１シートと、 太陽電池の背面を覆い、太陽電池の周縁部の外方で第１
シートと気密に固定される第２シートとを有し、 内部空間に、太陽電池を収納する太陽電池アセンブリ
と、 （ｂ）太陽電池アセンブリの周縁部、被取付け体の外周
面とは反対側に設けられ、太陽電池アセンブリの前記周
縁部から内方に延び、可撓性を有する係止用シートと、 （ｃ）係止用シートに設けられる第１係止片と、 （ｄ）被取付け体の外周面に固定され、第１係止片を覆
う可撓性を有する取付け用シートと、 （ｅ）被取付け体の外周面で取付け用シートに設けら
れ、第１係止片に着脱可能に係止する第２係止片とを含
むことを特徴とする太陽電池取付け装置。2. A transparent first sheet for covering a light receiving surface of a solar cell; and a first sheet outside a peripheral portion of the solar cell for covering a rear surface of the solar cell.
A solar cell assembly that has a seat and a second sheet that is airtightly fixed, and that houses a solar cell in the internal space; A flexible locking sheet that is provided and extends inward from the peripheral portion of the solar cell assembly; (c) a first locking piece provided on the locking sheet; and (d) an attached body. A flexible mounting sheet that is fixed to the outer peripheral surface of the mounting member and that covers the first locking piece, and (e) is provided on the mounting sheet on the outer peripheral surface of the mounted body, and is detachably attached to the first locking piece. A solar cell mounting device comprising a second locking piece for locking.
放端側から挟み、第１および第２係止片の長手方向に沿
って移動操作することによって、第１および第２係止片
を係止／離脱する係止部材を、さらに含むことを特徴と
する請求項２記載の太陽電池取付け装置。3. A first and a second locking piece by sandwiching the locking sheet and the mounting sheet from the respective open end sides and moving the locking sheet and the mounting sheet along the longitudinal direction of the first and second locking pieces. The solar cell mounting device according to claim 2, further comprising a locking member for locking / unlocking.
は、頂部が膨出した突条であり、 いずれか他方は、前記頂部が弾発的に嵌合して係止する
係止溝を有し、 操作部材には、移動操作方向の一方端に、第１および第
２係止片をそれぞれ案内する一対の第１案内用切欠きが
形成され、 他方端に、係止した第１および第２係止片を案内する前
記一対の第１案内用切欠きが合流して単一の第２案内用
切欠きが形成されることを特徴とする請求項３記載の太
陽電池取付け装置。4. One of the first and second locking pieces is a ridge having a bulged top portion, and the other is a locking portion for elastically fitting and locking the top portion. The operating member has a pair of first notches for guiding the first and second locking pieces at one end in the moving operation direction, and the locking member has a groove at the other end. 4. The solar cell mounting device according to claim 3, wherein the pair of first guide notches for guiding the first and second locking pieces merge to form a single second guide notch. .
の外周面に固定されるシート部分は、伸縮しやすく、か
つ撓んで変形しやすい材料から成ることを特徴とする請
求項１〜４のうちの１つに記載の太陽電池取付け装置。5. The sheet portion fixed to at least the outer peripheral surface of the body to be attached of the attachment sheet is made of a material which easily expands and contracts and is easily bent and deformed. The solar cell mounting device according to one.
センブリの第１シートの取付け用シート付近で取付け用
シートから露出した表面とにわたって、粘着テープが貼
着されることを特徴とする請求項１〜５のうちの１つに
記載の太陽電池取付け装置。6. The adhesive tape is attached to the outer peripheral surface of the mounting sheet and the surface exposed from the mounting sheet near the mounting sheet of the first sheet of the solar cell assembly. The solar cell mounting device according to any one of 1 to 5.
断された部分を有し、 この分断部分には、太陽電池に接続されるリード線が配
置され、 飛行体には、太陽電池の電力によって駆動される推進機
が設けられ、 飛行体の機首が空気の流れの上流に向かうように操舵手
段が設けられることを特徴とする請求項１〜６のうちの
１つに記載の太陽電池取付け装置。7. The mounted body is a flying body, and the first and second locking pieces have a circumferentially divided portion on the stern side of the flying body, and the divided portion is connected to a solar cell. The lead wires to be connected are arranged, the aircraft is provided with a propulsion device driven by the electric power of the solar cell, and the steering means is provided so that the nose of the aircraft is directed upstream of the air flow. The solar cell mounting device according to claim 1, wherein the solar cell mounting device is a solar cell mounting device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000051965A JP3371119B2 (en) | 2000-02-28 | 2000-02-28 | Solar cell mounting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000051965A JP3371119B2 (en) | 2000-02-28 | 2000-02-28 | Solar cell mounting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2001239996A JP2001239996A (en) | 2001-09-04 |
| JP3371119B2 true JP3371119B2 (en) | 2003-01-27 |
Family
ID=18573549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2000051965A Expired - Lifetime JP3371119B2 (en) | 2000-02-28 | 2000-02-28 | Solar cell mounting device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3371119B2 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101275883B1 (en) * | 2011-12-27 | 2013-06-24 | 한국항공우주연구원 | Flexible solar panel wing structure |
| JP6002442B2 (en) * | 2012-05-22 | 2016-10-05 | 太陽工業株式会社 | Solar cell mounting structure on membrane |
| CN102897330B (en) * | 2012-10-22 | 2015-02-11 | 湖南航天机电设备与特种材料研究所 | Method for reliably connecting flexible thin-film solar cell and airship envelop |
| JP6116894B2 (en) * | 2012-12-26 | 2017-04-19 | 太陽工業株式会社 | Membrane material mounting structure to membrane |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58180799U (en) * | 1982-05-28 | 1983-12-02 | 藤倉ゴム工業株式会社 | Fin attaching/detaching device for soft airships, etc. |
| JPH045198A (en) * | 1990-04-23 | 1992-01-09 | Sanyo Electric Co Ltd | Solar cell type of electric aircraft |
| JPH0519099U (en) * | 1991-02-05 | 1993-03-09 | 三菱重工業株式会社 | Dustproof mechanism for space solar cells |
| JP3101388B2 (en) * | 1992-01-20 | 2000-10-23 | 三洋電機株式会社 | Airship with solar cells |
| JPH06163964A (en) * | 1992-07-21 | 1994-06-10 | Osaka Shosen Mitsui Senpaku Kk | Solar cell installing mechanism for airship |
| JP3903202B2 (en) * | 2000-01-19 | 2007-04-11 | 独立行政法人 宇宙航空研究開発機構 | Stratospheric airship |
-
2000
- 2000-02-28 JP JP2000051965A patent/JP3371119B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JP2001239996A (en) | 2001-09-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| ES2603584T3 (en) | System and method to isolate a frame element | |
| RU2747328C2 (en) | Airship and method of its manufacture | |
| US4933227A (en) | Aircraft windshield | |
| US20080179453A1 (en) | Modular airship system and method | |
| US20090236473A1 (en) | Providing skins for aircraft fuselages | |
| KR102225588B1 (en) | Personal air veihcle | |
| JP3371119B2 (en) | Solar cell mounting device | |
| US20200148327A1 (en) | Method of forming a hollow spar for an aerial vehicle | |
| KR20210071039A (en) | Aircraft wing beams with integrated power cells and related systems and methods | |
| CN101903242A (en) | Fuel cell system module | |
| US10573772B2 (en) | Composite vehicle skin co-cured with solar-cell array | |
| JP3574815B2 (en) | Solar cell mounting structure and its installation method | |
| JP3101388B2 (en) | Airship with solar cells | |
| FR2946616A1 (en) | Aerostat assembly e.g. drone assembly, for transporting person, has set of photovoltaic panels fixed on elongated envelope, where each photovoltaic panel is removably fixed on envelope using self-gripping band and detachable attachment | |
| JP2000280988A (en) | Installing method of solar battery for airship and airship with solar battery | |
| JP3888634B2 (en) | Connecting structure of solar cells | |
| EP4050663B1 (en) | Assembly and mounting of solar cells | |
| CN114604412B (en) | Bulkhead for a beam of an aircraft | |
| US11591061B2 (en) | Watertight bulkhead for a boom of an aircraft | |
| KR102374535B1 (en) | A bulkhead for a boom of an aircraft | |
| CA3096223C (en) | A bulkhead for a boom of an aircraft | |
| EP3805091B1 (en) | A bulkhead for a boom of an aircraft | |
| EP3896845A1 (en) | Solar array attachment | |
| JP2024011381A (en) | Repairing member | |
| JPH10167199A (en) | Adiabatic covering for spacecraft and spacecraft having such covering |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| TRDD | Decision of grant or rejection written | ||
| R150 | Certificate of patent or registration of utility model |
Ref document number: 3371119 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313115 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20081122 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20081122 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20081122 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20091122 Year of fee payment: 7 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20101122 Year of fee payment: 8 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20111122 Year of fee payment: 9 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20111122 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20121122 Year of fee payment: 10 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20121122 Year of fee payment: 10 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20131122 Year of fee payment: 11 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20141122 Year of fee payment: 12 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| S533 | Written request for registration of change of name |
Free format text: JAPANESE INTERMEDIATE CODE: R313533 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| EXPY | Cancellation because of completion of term |