Computer Engineering and Applications ›› 2013, Vol. 49 ›› Issue (17): 258-262.

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Research on modeling and experiments of control loading system of helicopter flight simulator

DUAN Yongsheng1, LU Ying1, GUO Quan1, REN Beibei2   

  1. 1.Military Simulation Technology Research Institute, Aviation University of Air Force, Changchun 130022, China
    2.Northeast Normal University, Changchun 130022, China
  • Online:2013-09-01 Published:2013-09-13


段永胜1,卢  颖1,郭  全1,任贝贝2   

  1. 1.空军航空大学 军事仿真技术研究所,长春 130022
    2.东北师范大学,长春 130022

Abstract: To improve the force-sense fidelity of control loading system for a certain type of helicopter flight simulator, the helicopter distributed system parameters are centralized, and the linear model is built with the Least-Square estimation method (LS). Taking longitudinal channel as an example, the pole force-displacement mathematical model and electro-servo loading system model are built. The model is applied to a type of helicopter and it makes force-sense experimental flight, the results show that force-displacement model meets with the real flight force-sense characteristics and its validity is proved, the model is successfully applied to a type of flight simulator control loading system.

Key words: control loading system, least square parameter estimation, simulation

摘要: 为提高某型直升机飞行模拟器操纵系统操纵力感逼真度,将直升机操纵系统分布参数分段集中化处理,利用最小二乘参数估计法得到其线性模型,并以纵向通道为例建立了杆力-位移模型和电动力伺服加载系统模型。将模型应用于某型直升机飞行模拟器并进行力感试验,试验结果表明,所建立的杆力-位移模型与实装飞机力感特性相吻合,充分证明了杆力-位移模型的有效性,该模型已成功地应用于某型直升机飞行模拟器操纵负荷系统。

关键词: 操纵负荷系统, 最小二乘参数估计, 仿真