北京航空航天大学学报 ›› 1998, Vol. 24 ›› Issue (3): 283-286.

• 论文 • 上一篇    下一篇

起飞模态的综合飞行矢量喷管控制系统设计

彭可茂, 申功璋, 文传源   

  1. 北京航空航天大学 自动控制系
  • 收稿日期:1997-01-23 出版日期:1998-03-31 发布日期:2010-09-29
  • 作者简介:男 33岁 博士生 100083 北京
  • 基金资助:

    航空科学研究基金(94E51056)资助项目

Design of Integrated Flight/Vectored Nozzle Control System at Take-Off

Peng Kemao, Shen Gongzhang, Wen Chuanyuan   

  1. Beijing University of Aeronautics and Astronautics,Dept of Automatic Control
  • Received:1997-01-23 Online:1998-03-31 Published:2010-09-29

摘要: 通过对背景机加装鸭翼或矢量喷管,采用四种控制方案,研究了矢量喷管控制对飞机起飞性能的改善作用.根据飞机起飞过程,建立了各运动阶段的飞机纵向运动模型.分别设计了各控制方案的综合飞行/矢量喷管控制的综合系统控制律.在已建立的运动模型和非线性推进系统模型上,进行了起飞过程的数学仿真.仿真结果表明,所设计的综合系统控制律较好地完成了起飞任务.主要性能数据表明,矢量喷管与相应舵面协调控制明显改善了飞机的起飞性能.

Abstract: Four kind of configurations are adopted to analyze the improvement of the vectored nozzle control on the flight performances at take-off,where the baseline aircraft is modified to add the horizontal canard or/and vectored nozzle The models of the aircraft longitudinal motion at the different progresses of the take-off are established The system controllers of the integrated flight/vectored nozzle control system at take-off are respectively designed according to the configurations The simulations of the aircraft at take-off are made on the established models and nonlinear propulsion system model The results prove that the designed system controllers are available to implement the take-off mission The major specifications prove that the vectored nozzle control can significantly improve the flight performances at take-off when appropriately coordinated with the aerodynamic control effectors

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