摘要
为了最大限度地逼近真实杆力和脚蹬力,提高某型军用飞行模拟器的操纵性能,建立一种升降舵操纵系统数学模型和电动力伺服系统模型。分析真实飞机操纵负荷系统的结构及工作原理,将飞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等效线性模型,以升降舵系统为例建立了杆力-位移模型、舵偏角-位移数学模型,并对其操纵结构进行具体分析。该模型现已成功应用于某型飞行模拟器操纵负荷系统。Matlab/simulink环境下的仿真结果表明:建立的系统模型与实际系统静动态响应相吻合,证明了等效低阶模型的有效性。
In order to approach the real pole-force and pedaling-force extremely, improve the control performance of a certain type of military flight simulator. Mathematical model of elevator control system and electric power servo system model were built. Analysis the structure and work theory of real helicopter. The centralized processing sub-system distribution parameters and getting the equivalent linear model by the least square parameter estimation. Take elevator system and elevator angle model an example, pole-force shift model and rudder angle shift mathematical model was built up and analysis the control mechanism. The model is successfully applied to a certain type of flight simulator control loading system. In the Matlab/simulink environment, the simulation results show that the established system model and the actual system are consistent on static and dynamic response, and prove the validity of the equivalent low-level model.
出处
《兵工自动化》
2012年第8期24-28,共5页
Ordnance Industry Automation
基金
空军科研基金项目(KJZ06139)
关键词
操纵负荷系统
仿真
最小二乘参数估计
control loading system
simulation
the least square parameter estimation
