電動復(fù)合力矩加載系統(tǒng)的設(shè)計
發(fā)布時間：2019-04-29 12:51
【摘要】：電動加載系統(tǒng)是在實驗室條件下模擬飛行器在空中飛行時舵面所承受的氣動載荷，是飛行器舵系統(tǒng)進行半實物仿真試驗的重要設(shè)備。針對飛行器舵面在空中所承受的多種載荷，，復(fù)合力矩加載系統(tǒng)通過在原有扭矩加載系統(tǒng)的基礎(chǔ)上加入了彎矩加載系統(tǒng)，更加真實的模擬和復(fù)現(xiàn)飛行器舵面在空中所受的各種氣動載荷，實現(xiàn)舵系統(tǒng)快速、有效的實驗驗證。因此，設(shè)計一種復(fù)合力矩加載系統(tǒng)，并對其進行相關(guān)研究有著重要的理論意義和實際工程應(yīng)用價值。 論文對國內(nèi)外加載系統(tǒng)的研究成果和發(fā)展現(xiàn)狀進行了研究和分析，通過分析飛行器舵面的氣動載荷譜，提出了研制復(fù)合力矩加載系統(tǒng)的必要性。文中說明了復(fù)合力矩加載系統(tǒng)的組成，并概述了其工作原理，采用機械最優(yōu)化設(shè)計理念，對復(fù)合力矩加載系統(tǒng)中的機械加工構(gòu)件進行了設(shè)計計算，使系統(tǒng)在滿足實際工作要求的前提下達到最優(yōu)設(shè)計，并在動、靜態(tài)加載方式下對結(jié)構(gòu)軸的機械特性進行了校核。建立了電動加載系統(tǒng)的完整數(shù)學(xué)模型，通過分析和研究加載系統(tǒng)多余力矩的產(chǎn)生機理和影響多余力矩大小的主要因素，提出了有效抑制多余力矩的方法。采用了PID控制與舵機指令直接前饋控制的復(fù)合控制方法和基于參考模型的自適應(yīng)補償法對系統(tǒng)中多余力矩進行消除，實現(xiàn)了電動加載系統(tǒng)的快速、高精度控制，并通過對校正后的系統(tǒng)進行仿真分析驗證了該方法的有效性。 最后，根據(jù)實際測試需求完成了整個復(fù)合力矩加載系統(tǒng)的方案制定，分別對系統(tǒng)的硬件和軟件系統(tǒng)進行了設(shè)計，并依據(jù)實際需求對系統(tǒng)中的主要器件進行了選型，在確定系統(tǒng)操作流程后設(shè)計出了軟件操作界面。通過仿真實驗分析，驗證了電動復(fù)合力矩加載系統(tǒng)的可行性。
[Abstract]:Electric loading system is an important equipment in hardware-in-the-loop simulation test of aircraft rudder system, which is used to simulate the aerodynamic load on the rudder surface of aircraft in the air under laboratory conditions. The composite moment loading system adds a bending moment loading system based on the original torque loading system, aiming at the multiple loads on the rudder surface of the aircraft in the air. More real simulation and reproduction of all kinds of aerodynamic loads on the rudder surface of the vehicle in the air to realize the rapid and effective experimental verification of the rudder system. Therefore, the design of a composite moment loading system and its related research has important theoretical significance and practical engineering application value. In this paper, the research achievements and development status of loading system at home and abroad are studied and analyzed. By analyzing the aerodynamic load spectrum of the rudder surface of aircraft, the necessity of developing composite moment loading system is put forward. In this paper, the composition of the composite moment loading system is described, and its working principle is summarized. The mechanical machining components in the composite moment loading system are designed and calculated by using the idea of mechanical optimum design. The optimal design of the system is achieved on the premise of satisfying the practical work requirements, and the mechanical characteristics of the structural shaft are checked under the dynamic and static loading mode. The complete mathematical model of the electric loading system is established. By analyzing and studying the generating mechanism of the redundant torque of the loading system and the main factors affecting the magnitude of the redundant torque, an effective method to restrain the redundant torque is put forward. The compound control method of PID control and direct feedforward control of the steering gear and the adaptive compensation method based on reference model are adopted to eliminate the redundant torque in the system, and the fast and high precision control of the electric loading system is realized. The validity of the method is verified by simulation and analysis of the corrected system. Finally, according to the actual testing requirements, the scheme of the whole composite moment loading system is completed, the hardware and software systems are designed, and the main components in the system are selected according to the actual requirements. After determining the operation flow of the system, the interface of software operation is designed. The feasibility of the electric composite moment loading system is verified by the analysis of simulation experiments.
【學(xué)位授予單位】：中北大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V216.8
[Abstract]:Electric loading system is an important equipment in hardware-in-the-loop simulation test of aircraft rudder system, which is used to simulate the aerodynamic load on the rudder surface of aircraft in the air under laboratory conditions. The composite moment loading system adds a bending moment loading system based on the original torque loading system, aiming at the multiple loads on the rudder surface of the aircraft in the air. More real simulation and reproduction of all kinds of aerodynamic loads on the rudder surface of the vehicle in the air to realize the rapid and effective experimental verification of the rudder system. Therefore, the design of a composite moment loading system and its related research has important theoretical significance and practical engineering application value. In this paper, the research achievements and development status of loading system at home and abroad are studied and analyzed. By analyzing the aerodynamic load spectrum of the rudder surface of aircraft, the necessity of developing composite moment loading system is put forward. In this paper, the composition of the composite moment loading system is described, and its working principle is summarized. The mechanical machining components in the composite moment loading system are designed and calculated by using the idea of mechanical optimum design. The optimal design of the system is achieved on the premise of satisfying the practical work requirements, and the mechanical characteristics of the structural shaft are checked under the dynamic and static loading mode. The complete mathematical model of the electric loading system is established. By analyzing and studying the generating mechanism of the redundant torque of the loading system and the main factors affecting the magnitude of the redundant torque, an effective method to restrain the redundant torque is put forward. The compound control method of PID control and direct feedforward control of the steering gear and the adaptive compensation method based on reference model are adopted to eliminate the redundant torque in the system, and the fast and high precision control of the electric loading system is realized. The validity of the method is verified by simulation and analysis of the corrected system. Finally, according to the actual testing requirements, the scheme of the whole composite moment loading system is completed, the hardware and software systems are designed, and the main components in the system are selected according to the actual requirements. After determining the operation flow of the system, the interface of software operation is designed. The feasibility of the electric composite moment loading system is verified by the analysis of simulation experiments.
【學(xué)位授予單位】：中北大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V216.8
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