本文關鍵詞： PID控制器 數(shù)值虛擬飛行 CFD/RBD/FCS耦合模擬 快速機動 數(shù)值模擬　出處：《航空學報》2016年08期 　論文類型：期刊論文

【摘要】：飛行控制系統(tǒng)(FCS)與計算流體力學(CFD)的耦合求解是一個嶄新的研究領域。傳統(tǒng)的飛行控制系統(tǒng)的工程仿真方法依靠氣動力模型或氣動力數(shù)據(jù)庫得到不同飛行姿態(tài)的氣動力;而當前方法通過耦合求解Navier-Stokes方程和剛體動力學方程(RBD)以獲取飛行器運動過程實時流場和非定常氣動力。由于充分反映了氣動力的非定常、非線性效應,因而從根本上保證了飛行控制系統(tǒng)仿真的精度。以方形截面導彈俯仰姿態(tài)控制為例,首先給出了系統(tǒng)的傳遞函數(shù),并基于系統(tǒng)在單位階躍舵偏操縱下的開環(huán)響應特性,提出了傳遞函數(shù)的修正方法,進而設計了該外形俯仰姿態(tài)控制的PID控制器。數(shù)值模擬了不同控制參數(shù)時,P控制器、PD控制器和PID控制器的控制效果。針對不同的控制指令,根據(jù)建立的控制律,數(shù)值模擬了飛行器在PID控制器作用下的實時響應過程,最終成功實現(xiàn)了對飛行器的俯仰姿態(tài)控制。研究發(fā)現(xiàn),當飛行器作慢速機動時,工程仿真與CFD數(shù)值計算的結果吻合很好,兩種方法可以互相驗證;但快速機動時,兩種方法給出的結果差異明顯,基于CFD的耦合模擬方法由于模擬了飛行器運動和舵面偏轉導致的非定常流動過程,其結果比基于靜態(tài)氣動力的工程方法的可靠性更高。在大攻角和快速機動等非定常效應較強時,采用CFD方法評估和驗證飛行控制系統(tǒng)是很有必要的。
[Abstract]:The coupling solution of flight control system (FCS) and computational fluid dynamics (CFDs) is a new research field. The traditional engineering simulation method of flight control system relies on aerodynamic model or aerodynamic database to obtain aerodynamic force of different flight attitude. However, the current method can obtain the real time flow field and unsteady aerodynamic force in flight vehicle motion process by coupling solving Navier-Stokes equation and rigid body dynamics equation, because it fully reflects the unsteady and nonlinear effect of aerodynamic force. Therefore, the simulation accuracy of flight control system is guaranteed fundamentally. Taking the pitch attitude control of square cross-section missile as an example, the transfer function of the system is first given, and based on the open-loop response characteristics of the system under the control of unit step rudder deviation. A modified method of transfer function is proposed, and then the PID controller for pitch attitude control is designed. The control effects of PD controller and PID controller are numerically simulated under different control parameters. According to the established control law, the real-time response process of the aircraft under the action of the PID controller is numerically simulated, and the pitching attitude control of the aircraft is successfully realized. The results of engineering simulation and CFD numerical calculation are in good agreement, and the two methods can verify each other, but the difference between the two methods is obvious in fast maneuvering. The coupling simulation method based on CFD is used to simulate the unsteady flow process caused by the motion of the aircraft and the deflection of the rudder surface. The result is more reliable than the engineering method based on static aerodynamic force. When the unsteady effects such as large angle of attack and fast maneuvering are strong, it is necessary to use CFD method to evaluate and verify the flight control system.
【作者單位】： 中國空氣動力研究與發(fā)展中心計算空氣動力研究所;
【基金】：國家自然科學基金(11172315,91216203,11372341,11532016)~~
【分類號】：V249.1

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