本文選題：姿控模擬器 + ZYNQ��； 參考：《哈爾濱工業(yè)大學》2016年碩士論文

【摘要】：衛(wèi)星姿控系統(tǒng)是衛(wèi)星的重要組成部分,起到控制衛(wèi)星姿態(tài)的作用。姿控電模擬器主要用來替代星上的真實部件完成衛(wèi)星姿控系統(tǒng)的地面閉環(huán)仿真測試。傳統(tǒng)的衛(wèi)星姿控模擬器受到處理器性能、系統(tǒng)架構等多方面原因的影響,已經無法滿足在性能指標上更為嚴格的需求。針對上述問題,本文研制了一種通用化程度高、精度高、實時性好的小衛(wèi)星姿控電模擬器。本文首先提出模擬器的總體設計需求,并從接口、模型解算、軟件通用化等四個方面對典型的敏感器類和執(zhí)行機構類模擬器的需求進行了詳細的分析。在此基礎上提出課題的總體方案:在嵌入式開發(fā)平臺ZYNQ上進行小衛(wèi)星姿控電模擬器的設計及驗證。在此平臺PS端(Processing System,PS)實現(xiàn)模擬器中涉及到的模型解算,在PL端(Programmable Logic,PL)實現(xiàn)電氣接口功能。采用軟硬件協(xié)同設計的設計方法,進行小衛(wèi)星模擬器的設計。該方案可以實現(xiàn)模擬器較好的通用性和實時性。PL固件部分設計了7個控制模塊,用來實現(xiàn)模擬器與外部設備的通信;PS軟件部分,設計了13個軟件程序功能模塊,用來實現(xiàn)軟件程序的通用化。除此之外,本課題對模型解算中涉及到的一階微分方程的實現(xiàn)方法進行了分析,最終采用四級龍格-庫塔法實現(xiàn)模型解算。課題最終采用三種代表性的模擬器:飛輪模擬器、太陽敏感器模擬器和控制力矩陀螺(也稱CMG,Control Moment Gyroscope)模擬器,驗證在此平臺上設計的模擬器的功能、優(yōu)勢以及不足。驗證結果表明,本文設計的小衛(wèi)星姿控電模擬器能夠很好的實現(xiàn)與外部設備的數(shù)據(jù)傳輸功能以及模型解算功能;能夠很好的滿足系統(tǒng)性能指標要求:閉環(huán)仿真時間小于10ms,模型解算精度達到32位。模擬器的功能和技術指標滿足設計要求。
[Abstract]:Satellite attitude control system is an important part of satellite and plays a role in controlling satellite attitude. The attitude control simulator is mainly used to replace the real satellite components to complete the ground closed loop simulation test of the satellite attitude control system. The traditional satellite attitude control simulator is affected by processor performance, system architecture and other reasons, and can not meet the more stringent performance requirements. In order to solve the above problems, a small satellite attitude control simulator with high generalization, high precision and good real-time performance is developed in this paper. In this paper, the general design requirements of simulator are put forward, and the requirements of typical sensors and actuator simulator are analyzed in detail from four aspects: interface, model solution and software generalization. On this basis, the overall scheme of the subject is put forward: the design and verification of the small satellite attitude control simulator based on the embedded development platform ZYNQ. The model solution involved in the simulator is realized on the PS platform, and the electrical interface function is realized in the PL terminal programmable logic device (PLL). The software and hardware co-design method is used to design the small satellite simulator. This scheme can realize the better generality and real-time of the simulator. The firmware part of PL has designed 7 control modules, which are used to realize the communication between the simulator and the external equipment in PS software part, and 13 software program function modules have been designed. Used to generalize software programs. In addition, this paper analyzes the realization method of the first order differential equation in the solution of the model, and finally uses the four levels Runge-Kutta method to solve the model. Finally, three typical simulators are adopted: flywheel simulator, sun sensor simulator and control moment gyroscope simulator. The functions, advantages and disadvantages of the simulator designed on this platform are verified. The verification results show that the small satellite attitude control simulator designed in this paper can achieve the function of data transmission with external equipment and the function of model solution. The closed loop simulation time is less than 10msand the precision of the model is 32 bits. The function and technical specifications of the simulator meet the design requirements.
【學位授予單位】：哈爾濱工業(yè)大學
【學位級別】：碩士
【學位授予年份】：2016
【分類號】：V448.22

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