北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (10): 2222-2230.doi: 10.13700/j.bh.1001-5965.2015.0617

• 论文 • 上一篇    下一篇

民机起飞爬升梯度适航符合性数学仿真评估

孟祥光1, 王立新2, 刘海良2   

  1. 1. 北京航空航天大学 大型飞机高级人才培训班, 北京 100083;
    2. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2015-09-22 出版日期:2016-10-20 发布日期:2016-06-24
  • 通讯作者: 王立新,Tel.:010-82338821,E-mail:wlx_c818@163.com E-mail:wlx_c818@163.com
  • 作者简介:孟祥光,男,硕士研究生。主要研究方向:飞行动力学。Tel.:010-82338821,E-mail:xiangguangmeng@163.com;王立新,男,博士,教授,博士生导师。主要研究方向:飞机设计、飞行动力学与控制及飞行安全等。Tel.:010-82338821,E-mail:wlx_c818@163.com
  • 基金资助:
    国家“863”计划(2014AA110501)

Mathematical simulation and assessment of airworthiness compliance of climb gradient during takeoff of civil aircraft

MENG Xiangguang1, WANG Lixin2, LIU Hailiang2   

  1. 1. Large Aircraft Advanced Training Center, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-09-22 Online:2016-10-20 Published:2016-06-24
  • Supported by:
    National High-tech Research and Development Program of China (2014AA110501)

摘要: 民机起飞过程中沿起飞航迹各点的爬升梯度反映了飞机超越地面障碍达到安全飞行高度的能力。针对适航条款对于起飞程序和爬升性能的要求,提出了一种基于人机闭环数学仿真计算的单发停车起飞爬升梯度适航符合性评估方法。建立了飞机本体动力学模型、起落架运动模型和驾驶员操纵模型,提出了适航符合性评估指标,并设计了飞机单发停车起飞的仿真任务和驾驶员操纵程序。通过闭环数字飞行仿真完成了不同验证状态点的爬升梯度评估。该方法可应用于民机的概念方案设计,计算结果可为飞机起飞重量的确定与单发失效爬升性能的试飞验证等提供理论参考。

关键词: 爬升梯度, 适航, 单发停车, 数字飞行仿真, 驾驶员操纵模型

Abstract: The climb gradient along the takeoff path reflects the civil aircraft's ability of flying over the ground obstacles to reach the safe height. According to the requirements of airworthiness regulations for takeoff procedure and climb performance, an airworthiness compliance assessment method of climb gradient with one engine inoperative was proposed based on the pilot-in-loop flight simulation and calculation. A nonlinear aircraft model, a landing gear model and pilot control models were established and assessment criteria were set up. A simulation task of takeoff with one engine inoperative as well as the control procedure of the pilot was designed. The climb gradient of various states was assessed based on the closed-loop digital flight simulation. This method can be applied to the preliminary design phase of civil aircrafts to provide support for the configuration design and the determination of takeoff weight limit, and offer theoretical references for flight tests of climb performance with one engine inoperative.

Key words: climb gradient, airworthiness, one engine inoperative, digital flight simulation, pilot control model

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