| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
制動圓筒の着陸滑走時に於ける温度上昇に就て |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
departmental bulletin paper |
| その他のタイトル（英） |
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その他のタイトル |
Temperature Rise of the Brake-Drum During the Landing Run |
| 著者 |
小川, 太一郎
宮田, 輝彦
OGAWA, Taitiro
MIYATA, Teruhiko
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| 出版者 |
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出版者 |
東京帝國大學航空研究所 |
| 出版者（英） |
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出版者 |
Aeronautical Research Institute, Tokyo Imperial University |
| 書誌情報 |
東京帝國大學航空研究所報告
en : Report of Aeronautical Research Institute, Tokyo Imperial University
巻 17,
号 224,
p. 353-376,
発行日 1942-04
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
The horizontal kinetic energy of an aeroplane at the instant of landing is dissipated before the end of the run mainly in three kinds of work; i. e., air resistance, rolling friction of wheels, and friction between brake-drum and shoes. In this paper, the authors established a method of calculation for the temperature rise of the brake-drum caused by the friction of brake shoes, and gave suggestions for the design of the brake, deduced from the result of calculation for two numerical examples. The variation of dissipated energy per second by the brake shoes during the run was first rigorously calculated and found that the variation can be approximately expressed by a sine-curve. For the calculation of the temperature rise, following assumptions were made: (1) the brake drum is an infinite parallel plate, (2) one side of this plate is an insulator of heat, and (3) the other side is exposed to air and there exists Newton's radiation. The conclusions are: (1) the cooling effect of air is negligibly small, (2) the temperature gradient between the two sides of the brake drum is considerably great during the run, but finally becomes small, (3) the temperature rise is inversely proportional to the thickness of the brake drum for moderate thicknesses, hence lightening holes for these effective thicknesses are to be avoided, and (4) excessive thicknesses are not effective since the temperature gradient is very small in this case. That the temperature rise as calculated in this paper was rather high is due to the fact that the axial heat flow in the drum, and the dissipated energy in several other forms were not taken into consideration. The authors intend to carry out flight experiment to ascertain the effect of these factors. |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
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収録物識別子 |
AA00387631 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: SA4148645000 |
SA4148645.pdf (826.6 kB)
