Volume 13 Issue 2
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Article Navigation >  Journal of Traffic and Transportation Engineering  > 2013  >  13(2): 66-72
CAI Liang-cai, WANG Hai-fu, ZHU Zhan-qing, ZHONG Xiao-lei. Calculation method of running distance for aircraft takeoff on plateau airport[J]. Journal of Traffic and Transportation Engineering, 2013, 13(2): 66-72. doi: 10.19818/j.cnki.1671-1637.2013.02.010
Citation: CAI Liang-cai, WANG Hai-fu, ZHU Zhan-qing, ZHONG Xiao-lei. Calculation method of running distance for aircraft takeoff on plateau airport[J]. Journal of Traffic and Transportation Engineering, 2013, 13(2): 66-72. doi: 10.19818/j.cnki.1671-1637.2013.02.010
shu

Calculation method of running distance for aircraft takeoff on plateau airport

doi: 10.19818/j.cnki.1671-1637.2013.02.010

  • Department of Airport and Architecture Engineering, Air Force Engineering University, Xi'an 710038, Shaanxi, China

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  • Author Bio:

    CAI Liang-cai(1960-), male, professor, PhD, +86-29-84787008, liangcai07@126.com

  • Received Date: 2012-09-18
  • Publish Date: 2013-04-25
    Abstract
  • Aiming at the complicated environment of plateau airport and the characteristic of significant decline for aircraft engine performance, the running process of aircraft takeoff on plateau airport was analyzed. The practical pressure of airport was transformed into standard atmosphere pressure, the running distances under different times were calculated by using the correctional instantaneous thrust of aircraft engine, and the calculation method of running distance for aircraft takeoff on plateau airport was put out. The influences of altitude, takeoff mass, temperature and wind speed on the running distances of aircraft takeoff were analyzed, the simplification formula of running distance was put forward, and example verification was carried out. Analysis result shows that when altitude is 3 569.5 m, temperature is 16.4 ℃ and upwind speed is 2.1 m·s-1, the maximum absolute error between the running distance calculated by the proposed method and test running distance for aircraft Ⅰ is no more than 48 m, and the maximum relative error is no more than 2.7%. The maximum absolute error between the running distance calculated by the proposed method and test running distance for aircraft Ⅱ is no more than 100 m, and the maximum relative error is no more than 4.2%, The maximum relative errors between the running distances calculated by simplification formula and test running distances for aircraft Ⅰ and aircraft Ⅱ are 3.9% and 2.8% respectively, which meet the engineering requirement.

     

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