JPH06321193A - Solar battery aircraft - Google Patents
Solar battery aircraftInfo
- Publication number
- JPH06321193A JPH06321193A JP5109302A JP10930293A JPH06321193A JP H06321193 A JPH06321193 A JP H06321193A JP 5109302 A JP5109302 A JP 5109302A JP 10930293 A JP10930293 A JP 10930293A JP H06321193 A JPH06321193 A JP H06321193A
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- secondary battery
- solar cell
- structural member
- outer plate
- 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.)
- Withdrawn
Links
- 239000003792 electrolyte Substances 0.000 abstract description 9
- 239000000463 material Substances 0.000 abstract 1
- 239000012212 insulator Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 229910052725 zinc Inorganic materials 0.000 description 1
- 239000011701 zinc Substances 0.000 description 1
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
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Photovoltaic Devices (AREA)
Abstract
(57)【要約】
【目的】 太陽エネルギーをもとに飛行する太陽電池航
空機の二次電池を構造部材と兼用させて構造部材の重量
を減転するようにし、航空機のペイロードを増すように
した太陽電池航空機。
【構成】 太陽電池１は機体外板２に装備されており、
発生した電力は二次電池に充電される。この二次電池は
複数の陰極３が外板２に接合されており陽極５との間に
は電解質４がつめられて電池を構成しているので、陰極
５が外板２と共に構造材を兼ねるので構造部材の重量を
その分だけ軽減できる。
(57) [Summary] [Purpose] The secondary battery of a solar-powered aircraft that flies based on solar energy is also used as a structural member to reduce the weight of the structural member and increase the payload of the aircraft. Solar powered aircraft. [Structure] The solar cell 1 is mounted on the outer skin 2 of the fuselage,
The generated power is charged in the secondary battery. In this secondary battery, a plurality of cathodes 3 are bonded to the outer plate 2 and an electrolyte 4 is packed between the positive electrode 5 and the anode 5 to form a battery. Therefore, the cathode 5 also serves as a structural material together with the outer plate 2. Therefore, the weight of the structural member can be reduced accordingly.
Description
【０００１】[0001]
【産業上の利用分野】本発明は太陽エネルギーをもとに
飛行する電池を内蔵した太陽電池航空機に関するもので
ある。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a solar-powered aircraft having a battery for flying based on solar energy.
【０００２】[0002]
【従来の技術】現在、各所で太陽エネルギーで飛行する
航空機が研究されているが、長時間、特に夜間も飛行し
ようとすると、二次電池を搭載し、昼間に太陽電池で発
生した余剰電力を二次電池に蓄えておき、夜間にこの電
力を放出して飛行することになる。図５は航空機の主翼
の内部、即ち、外板２２の内部に二次電池２０を搭載し
た例、図６は胴体の内部、即ち、外板２４の内部に二次
電池２３を搭載した例であり、このような二次電池２
０，２３に昼間発生した電力を充電しておき、夜間にこ
れを放出して利用している。2. Description of the Related Art Currently, aircraft that fly with solar energy are being researched in various places. However, when trying to fly for a long time, especially at night, a secondary battery is installed and surplus power generated by the solar cell during the day is removed. It will be stored in a secondary battery, and this power will be discharged at night to fly. 5 shows an example in which the secondary battery 20 is mounted inside the main wing of the aircraft, that is, inside the outer plate 22, and FIG. 6 shows an example in which the secondary battery 23 is mounted inside the fuselage, that is, inside the outer plate 24. Yes, such a secondary battery 2
The electric power generated in the daytime is charged to 0 and 23, and the electric power is discharged and used at night.
【０００３】[0003]
【発明が解決しようとする課題】前述のような二次電池
を搭載した航空機の構造においては、二次電池の重量は
非常に重いため、胴体構造あるいは主翼構造に、二次電
池重量を加えると航空機のペイロードはほとんどなくな
り、太陽電池航空機自体の実現性、成立性もあやぶまれ
ているのが現状である。従って、太陽電池航空機を実現
するためには二次電池を出来るだけ軽くして航空機全体
の軽量化を図る必要がある。In the structure of the aircraft equipped with the secondary battery as described above, the weight of the secondary battery is very heavy. Therefore, if the weight of the secondary battery is added to the fuselage structure or the wing structure, The payload of the aircraft is almost gone, and the feasibility and feasibility of the solar-powered aircraft itself is currently under consideration. Therefore, in order to realize a solar cell aircraft, it is necessary to make the secondary battery as light as possible to reduce the weight of the entire aircraft.
【０００４】[0004]
【課題を解決するための手段】本発明は前述のような課
題を解決するために二次電池の電極を航空機の翼桁や外
板と構造的に一体となるような構成にして電気的にはこ
の電極が太陽電池の電極の機能を有すると共に構造部材
の機能もはたすような構成としたものである。In order to solve the above-mentioned problems, the present invention has a structure in which an electrode of a secondary battery is structurally integrated with a wing spar or outer plate of an aircraft. This electrode is configured to have the function of the electrode of the solar cell and the function of the structural member.
【０００５】即ち、本発明は、航空機に太陽電池を装備
し、昼間は該太陽電池で発生した電力を二次電池に充電
しておき夜間にこの電力を活用する太陽電池航空機にお
いて、前記二次電池の電極を構造部材として構成し、電
極と構造部材とを兼用させたことを特徴とする太陽電池
航空機を提供するものである。That is, the present invention is a solar cell aircraft in which a solar cell is installed in an aircraft, and a secondary battery is charged with electric power generated by the solar cell in the daytime and the electric power is utilized at night. It is intended to provide a solar cell aircraft characterized in that an electrode of a battery is configured as a structural member and the electrode and the structural member are used in common.
【０００６】[0006]
【作用】本発明は前述のような手段により、二次電池の
電極が電気的には太陽電池と接続されているので二次電
池の電極としての機能を有すると共に航空機の構造部材
と一体となり構造部材の一部を兼ねているのでその分だ
け構造部材の重量が軽減されることになる。従って太陽
電池航空機の機体重量が軽減され、ペイロードの増加が
図れるものである。According to the present invention, since the electrode of the secondary battery is electrically connected to the solar cell by the means as described above, it has a function as an electrode of the secondary battery and is integrated with the structural member of the aircraft. Since it also serves as a part of the member, the weight of the structural member is reduced accordingly. Therefore, the weight of the solar cell aircraft can be reduced, and the payload can be increased.
【０００７】[0007]
【実施例】以下、本発明を図面に示す実施例に基づいて
具体的に説明する。図１は本発明の第一実施例で太陽電
池を航空機の翼に適用した場合の翼の断面図である。翼
上面には太陽電池１を表面に配し、翼内部に二次電池を
配したものである。その二次電池の構造は、銅又は亜鉛
等でできた陰極３と黒鉛でできた陽極５を交互に複数個
必要に応じ翼の全部又は部分的に配し、その間には電解
質４がつめられている。陽極５は、翼根あるいは翼端で
１ケ所に接続してまとめられ、太陽電池１と電気的に接
続され、陰極３は、外板２に接合した後外板２を通して
電気的に太陽電池１に接続されている。従って、この場
合、陰極３は翼の外板２に接合されているので翼の構造
部材としての機能も有する。DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be specifically described below based on the embodiments shown in the drawings. FIG. 1 is a sectional view of a wing when a solar cell is applied to the wing of an aircraft in the first embodiment of the present invention. The solar cell 1 is arranged on the upper surface of the wing, and the secondary battery is arranged inside the wing. The structure of the secondary battery is such that a plurality of cathodes 3 made of copper or zinc or the like and anodes 5 made of graphite are alternately arranged in whole or in part of the blades as necessary, and an electrolyte 4 is packed between them. ing. The anode 5 is connected to the solar cell 1 at one location by a blade root or a blade tip and electrically connected to the solar cell 1, and the cathode 3 is electrically connected to the solar cell 1 through the outer cell 2 after being joined to the outer cell 2. It is connected to the. Therefore, in this case, since the cathode 3 is joined to the outer plate 2 of the blade, it also functions as a structural member of the blade.
【０００８】なお、陽極５は、かならずしも翼根、ある
いは翼端で太陽電池に接続させる必要はなく、翼の途中
で、外板２を絶縁して貫通し、太陽電池１に接続しても
良く、その他の場所でも可能である。まとめる個所につ
いては構造的に支障のない場所を選び適切な個所でまと
めれば良い。The anode 5 does not always have to be connected to the solar cell at the blade root or the blade tip, and may be connected to the solar cell 1 by insulating and penetrating the outer plate 2 in the middle of the blade. , Other locations are possible. Concerning the places to put together, it is sufficient to select a place that does not cause any structural problems and put together at an appropriate place.
【０００９】図２は本発明の第二実施例を示すもので、
翼の断面部の部分的な拡大図である。図１の第一実施例
では二次電池が陽極５と陰極３の複数を外板２を介して
並列に多数接続しているので二次電池の電圧が充分にと
れない場合があるが、この場合には複数の電極を直列に
接続することができる構造である。図２はこの場合の１
部分のみ図示したものであり、陰極７を必要に応じて翼
の全部又は部分的に何重にも折り曲げ外板９に接合し、
その間に陽極８を配し、電解質６がつめられている。こ
の例において、電極配列が折り曲げ部を数個絶縁して直
列になるよう接続すれば電気的に直列接続とすることが
できる。この場合の外板９は、絶縁体で構成するか、又
は金属の外板上に絶縁物をはさんでも良く、外板９と陰
極７は接着で接合する。この第二実施例の陰極７は第一
実施例のものよりも更に確実に構造部材としての役割を
兼用することが可能となる。FIG. 2 shows a second embodiment of the present invention.
It is a partially expanded view of the cross-sectional part of a wing. In the first embodiment of FIG. 1, since the secondary battery has a plurality of anodes 5 and cathodes 3 connected in parallel via the outer plate 2, the voltage of the secondary battery may not be sufficient. In some cases, it has a structure in which a plurality of electrodes can be connected in series. Fig. 2 shows 1 of this case
Only a part is shown in the drawing, and the cathode 7 is joined to the outer plate 9 by bending the whole or a part of the blade in multiple layers if necessary.
An anode 8 is arranged between them, and an electrolyte 6 is packed therein. In this example, the electrode arrangement can be electrically connected in series by connecting several bent portions so as to be insulated and connected in series. In this case, the outer plate 9 may be made of an insulator, or an insulator may be sandwiched between metal outer plates, and the outer plate 9 and the cathode 7 are bonded to each other by adhesion. The cathode 7 of the second embodiment can serve as a structural member more reliably than that of the first embodiment.
【００１０】これら第一、第二実施例では陰極３又は７
を翼の外板２又は９に接合又は接着する例で説明したが
陰極は外板のみではなく、例えば翼の桁に適用して構造
的に兼ねるような構成としても良く、電気的に電池の電
極としての要求を満せば翼のどのような構造部材と兼用
させても良いものである。又、本実施例の翼は主翼でも
尾翼でもいずれの場合にも適用されるものである。In these first and second embodiments, the cathode 3 or 7 is used.
Although the above description has been made on the example of bonding or adhering to the outer plate 2 or 9 of the blade, the cathode may be applied not only to the outer plate but also to the structure of the blade girder so as to serve as a structural member. It may be used as any structural member of the blade as long as it satisfies the requirement as an electrode. Further, the blade of this embodiment is applicable to both the main blade and the tail blade.
【００１１】図３は本発明の第三実施例を示すもので、
胴体構造に二次電池を配したものである。胴体構造部の
曲面に合わせて陰極１２を必要に応じ機体胴体の全面又
は一部として構成し、陽極１０との間に電解質１１をは
さんで、陽極１０も同様に一定間隔をもって曲面に合わ
せて二次電池を構成したものである。従って、この場合
は電極そのものが胴体構造部となるものである。FIG. 3 shows a third embodiment of the present invention.
A secondary battery is arranged in the body structure. If necessary, the cathode 12 may be configured as the whole or a part of the fuselage body according to the curved surface of the body structure, and the electrolyte 11 may be sandwiched between the anode 10 and the anode 10. This is a secondary battery. Therefore, in this case, the electrode itself becomes the body structure portion.
【００１２】図４は本発明の第四実施例で、図３に示し
たような胴体構造に二次電池を配する場合に電極が一重
では構造的に強度が不足する恐れがときに適用するもの
である。図示のように陽極１３と陰極１４を何重にも重
ねる配置として強度を増し、その間に電解質１４をはさ
み、陽極１３と陰極１４が１対となるようにセパレータ
１４で分離、絶縁した構成である。このようにすること
により図３に示す第三実施例よりも更に強度を増すこと
ができる。FIG. 4 is a fourth embodiment of the present invention, which is applied when the secondary battery is arranged in the body structure as shown in FIG. It is a thing. As shown in the drawing, the anode 13 and the cathode 14 are stacked in multiple layers to increase the strength, and the electrolyte 14 is sandwiched therebetween, and the anode 13 and the cathode 14 are separated and insulated by the separator 14 so as to form a pair. . By doing so, the strength can be further increased as compared with the third embodiment shown in FIG.
【００１３】以上、説明の第一実施例乃至第四実施例に
おいては、二次電池の陰極を航空機の翼の外板又は翼の
桁に、あるいは電極そのものを胴体の構造部材としての
機能を兼ねた構成として、かつ二次電池の電極としての
機能を満足するようにしたため太陽電池航空機の構造重
量を大幅に低減することが可能となり、太陽電池航空機
のペイロードを増すことができるものである。In the above-described first to fourth embodiments, the cathode of the secondary battery serves as the outer plate of the wing of the aircraft or the girder of the wing, or the electrode itself serves as the structural member of the fuselage. With such a configuration, and since the function as the electrode of the secondary battery is satisfied, the structural weight of the solar cell aircraft can be significantly reduced, and the payload of the solar cell aircraft can be increased.
【００１４】[0014]
【発明の効果】以上、具体的に説明したように本発明に
おいては、二次電池の電極を航空機の構造体と一体的に
配設して、電池の電極としての機能をはたすと共に電極
が構造体を兼ねるようにしたので構造重量を大幅に低減
することが可能になり、太陽電池航空機のペイロードを
増すことができるようになったものである。As described above in detail, according to the present invention, the electrode of the secondary battery is integrally arranged with the structure of the aircraft so as to function as the electrode of the battery and the electrode is structured. Since it also serves as a body, the structural weight can be significantly reduced, and the payload of the solar cell aircraft can be increased.
【図１】本発明の第一実施例で、航空機の翼に二次電池
を適用した太陽電池航空機の翼断面図である。FIG. 1 is a wing cross-sectional view of a solar cell aircraft in which a secondary battery is applied to the wing of the aircraft according to the first embodiment of the present invention.
【図２】本発明の第二実施例で、航空機の翼に二次電池
を適用した太陽電池航空機の翼の部分的な断面図であ
る。FIG. 2 is a partial cross-sectional view of a wing of a solar cell aircraft in which a secondary battery is applied to the wing of the aircraft according to the second embodiment of the present invention.
【図３】本発明の第三実施例で、胴体を電極で構成した
太陽電池航空機の断面図である。FIG. 3 is a cross-sectional view of a solar cell aircraft having a fuselage formed of electrodes according to a third embodiment of the present invention.
【図４】本発明の第四実施例で、胴体を電極で構成し、
電極の強度を増した場合の胴体断面図である。FIG. 4 is a fourth embodiment of the present invention, in which the body is composed of electrodes,
It is a fuselage sectional view when the intensity of an electrode is increased.
【図５】従来の主翼に二次電池を配した場合の断面図で
ある。FIG. 5 is a cross-sectional view when a secondary battery is arranged on a conventional main wing.
【図６】従来の胴体に二次電池を配した場合の断面図で
ある。FIG. 6 is a cross-sectional view when a secondary battery is arranged on a conventional body.
１ 太陽電池 ２ 外板 ３ 陰極 ４ 電解質 ５ 陽極 ６ 電解質 ７ 陰極 ８ 陽極 ９ 外板 １０ 陽極 １１ 電解質 １２ 陰極 １３ 陽極 １４ 電解質 １５ 陰極 １６ セパレータ 1 Solar Cell 2 Outer Plate 3 Cathode 4 Electrolyte 5 Anode 6 Electrolyte 7 Cathode 8 Anode 9 Outer Plate 10 Anode 11 Electrolyte 12 Cathode 13 Anode 14 Electrolyte 15 Cathode 16 Separator
Claims (1)
陽電池で発生した電力を二次電池に充電しておき夜間に
この電力を活用する太陽電池航空機において、前記二次
電池の電極を構造部材として構成し、電極と構造部材と
を兼用させたことを特徴とする太陽電池航空機。1. In a solar cell aircraft in which an aircraft is equipped with a solar cell, and the secondary cell is charged with electric power generated by the solar cell in the daytime and the electric power is utilized at night, the electrode of the secondary cell is A solar cell aircraft, which is configured as a structural member and is used as both an electrode and a structural member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5109302A JPH06321193A (en) | 1993-05-11 | 1993-05-11 | Solar battery aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5109302A JPH06321193A (en) | 1993-05-11 | 1993-05-11 | Solar battery aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH06321193A true JPH06321193A (en) | 1994-11-22 |
Family
ID=14506751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5109302A Withdrawn JPH06321193A (en) | 1993-05-11 | 1993-05-11 | Solar battery aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH06321193A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013181722A3 (en) * | 2012-06-07 | 2014-02-20 | Krastev Ivan | Road-and-air transport vehicle |
-
1993
- 1993-05-11 JP JP5109302A patent/JPH06321193A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013181722A3 (en) * | 2012-06-07 | 2014-02-20 | Krastev Ivan | Road-and-air transport vehicle |
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