本文選題：雙量程傳感器 + MATLAB分析軟件�。� 參考：《內(nèi)蒙古工業(yè)大學(xué)》2017年碩士論文

【摘要】：隨著世界各航天大國對大推力火箭技術(shù)應(yīng)用需求的提高,火箭發(fā)動機作為航天事業(yè)的“心臟”也獲得了極大地投入。推力測試技術(shù)作為火箭發(fā)動機實驗中一項最為關(guān)鍵的內(nèi)容,為發(fā)動機的研發(fā)與優(yōu)化提供了必要的數(shù)據(jù)支撐,也是判斷固體火箭發(fā)動機是否運行良好的關(guān)鍵指標(biāo)。固體火箭發(fā)動機實際工作時,有推力大、時間短、推力持續(xù)變化等特點,對于固體火箭發(fā)動機一系列復(fù)雜的運行過程,如何準(zhǔn)確測量其推力,滿足精度高、推力比大、推力動態(tài)變化等測量要求成為研究固體火箭發(fā)動機的重中之重。針對這個復(fù)雜的情況,本文結(jié)合前人的經(jīng)驗總結(jié),設(shè)計出一款雙量程傳感器,有效的滿足了這些要求,使得火箭發(fā)動機在推力較小時可以精確測量發(fā)動機推力,而在推力較大的階段時又可以滿足大量程測量,并保護小量程傳感器,為火箭發(fā)動機的動態(tài)性能研究,提供了必要保障。本文主要以前人的理論研究為基礎(chǔ),介紹了雙量程傳感器的工作原理,并且進行了危險構(gòu)件的沖擊力驗算,保證了安全要求。通過建模,建立理論的數(shù)學(xué)模型,進行了理論計算,獲得結(jié)構(gòu)的固有頻率、振型。并利用MATLAB分析軟件,對雙量程傳感器進行了運動狀態(tài)仿真,以及輸出力仿真,再通過沖擊試驗與仿真結(jié)果的比較,判斷仿真結(jié)果誤差,數(shù)學(xué)模型是否可以滿足實際要求。通過錘擊實驗測量得到大、小量程傳感器的輸入輸出數(shù)據(jù),利用MATLAB分析軟件,通過信號處理獲得大、小量程傳感器的傳遞函數(shù)以及BODE圖、實頻與虛頻等相關(guān)結(jié)果。通過實驗與理論分析結(jié)合,為雙量程傳感器的優(yōu)化改進提供了理論支持。本文對雙量傳感器進行了動力學(xué)建模與仿真,利用MATLAN軟件得出大小量程傳感器的傳遞函數(shù),很好的對該型傳感器進行了理論補充,為雙量程傳感器的發(fā)展起到了一定作用。
[Abstract]:With the increasing demand of the large thrust rocket technology in the world, the rocket engine as the heart of the aerospace industry has been greatly invested. As one of the most important contents in the rocket engine experiment, thrust test technology provides the necessary data support for the research and development and optimization of the engine, and is also the key index to judge whether the solid rocket motor is running well or not. The solid rocket motor has the characteristics of large thrust, short time, continuous change of thrust and so on. For a series of complicated operation process of solid rocket motor, how to accurately measure its thrust force to meet the high precision and high thrust ratio, The measurement of dynamic change of thrust has become the most important task in the study of solid rocket motor (SRM). In view of this complex situation, combined with the previous experience, this paper designs a dual-range sensor, which can effectively meet these requirements, so that the rocket engine can accurately measure the thrust of the engine at a relatively small thrust. At the stage of high thrust, a large number of range measurements can be satisfied and small range sensors can be protected, which provides a necessary guarantee for the study of the dynamic performance of rocket engines. In this paper, the working principle of double range sensor is introduced, and the impact force of dangerous component is checked to ensure the safety requirement. Through modeling, the mathematical model of the theory is established, and the theoretical calculation is carried out, and the natural frequency and mode shape of the structure are obtained. The simulation of the motion state and the output force of the dual-range sensor is carried out by using the MATLAB analysis software. Through the comparison of the results of the impact test and the simulation, the error of the simulation results and whether the mathematical model can meet the practical requirements are judged. The input and output data of large and small range sensors are obtained by hammering experiment. By using MATLAB analysis software, the transfer function of large and small range sensors, BODE diagram, real frequency and virtual frequency are obtained by signal processing. Through the combination of experiment and theoretical analysis, it provides theoretical support for the optimization and improvement of dual range sensor. In this paper, the dynamic modeling and simulation of the dual sensor is carried out, and the transfer function of the size range sensor is obtained by using MATLAN software, which is a good theoretical supplement to this type of sensor, and plays a certain role in the development of the dual range sensor.
【學(xué)位授予單位】：內(nèi)蒙古工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：V433.9;TP212

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