| タイトル | Speed benefits of tilt-rotor designs for LHX |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850007408 |
| 著者（英） | Mcdaniel, R. L.; Balberde, A.; Dereska, S. P.; Shaw, D. E.; Adams, J. V.; Gearin, C. J. |
| 著者所属（英） | System Planning Corp. |
| 発行日 | 1983-01-01 |
| 言語 | eng |
| 内容記述 | The merits of an advanced helicopter and a tilt rotor aircraft for light utility, scout, and attack roles in combat missions envisioned for the year 2000 and beyond were compared. It is demonstrated that speed has increasing value for 11 different mission classes broadly encompassing the intended LHX roles. Helicopter speeds beyond 250 knots are judged to have lower military worth. Since the tilt rotor concept offers a different cost speed relationship than that of helicopters, assessment of a tilt rotor LHX variant was warranted. The technical parameters of an advanced tilt rotor are stablished. Parameters of representative missions are identified, computed relative value of the tilt rotor LHX are compared to the baseline helicopter, a first-order life cycle estimate for the tilt rotor LHX is established, military worth of the alternative design is computed and the results are evaluated. It is suggested that the tilt rotor is the solution with the greatest capability for meeting the uncertainties of future needs. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 85N15717
SPC-789
AD-A213125
NAS 1.26:166437
NASA-CR-166437 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/157559 |
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