光電吊艙隔振系統(tǒng)設計及試驗研究
發(fā)布時間：2018-12-07 20:02
【摘要】：隨著民用無人機技術的發(fā)展,工業(yè)級無人機廣泛的應用于地圖測繪、災害搜救、電力巡線等領域,光電吊艙作為無人機上的主要有效載荷得到越來越多的關注。光電吊艙工作時不可避免的受到發(fā)動機、無人機速度及姿態(tài)變化產生的振動和滑起滑降、彈射傘降的起飛著陸沖擊等一系列復雜的振動影響。為提高光電吊艙的成像質量,必須對振動加以控制。振動控制可分為主動控制和被動控制,在小型無人機上搭載光電吊艙要求隔振系統(tǒng)總體質量低、結構簡單、可實現(xiàn)性強且經濟適用,因此本課題針對機載光電吊艙的實際使用工況,研制一套適用于工業(yè)級無人機光電吊艙的被動隔振系統(tǒng)。首先進行了無人機飛行振動環(huán)境試驗,獲得光電吊艙實際工作階段:無人機在一定的飛行高度和發(fā)動機轉速條件下的振動信號,通過數(shù)據(jù)處理獲得光電吊艙隔振器安裝位置處三個方向的時域特征和頻域特征,為隔振系統(tǒng)設計提供依據(jù)。然后建立了光電吊艙隔振系統(tǒng)多自由度模型,根據(jù)數(shù)學模型和隔振理論指導隔振器的空間布局及相對位置、隔振器的三向剛度及阻尼值和隔振系統(tǒng)框架結構的設計,以合理配置光電吊艙隔振系統(tǒng)的六個自由度固有頻率。最終應用了一種小型干摩擦高阻尼金屬隔振器。在此基礎上建立了光電吊艙隔振系統(tǒng)動力學模型和隔振系統(tǒng)有限元模型,利用Adams/Vibration模塊獲得光電吊艙隔振系統(tǒng)的模態(tài)信息、耦合率、頻率響應曲線和隨機振動響應曲線,結果顯示理論計算和仿真分析計算的固有頻率最大誤差為1.27%;利用Workbench軟件進行了隔振系統(tǒng)框架的模態(tài)分析、強度分析和安裝骨架的動剛度分析,檢驗隔振系統(tǒng)結構的適應性和可靠性。最后進行了光電吊艙隔振系統(tǒng)振動臺試驗包括正弦掃頻試驗和隨機振動試驗,獲得隔振系統(tǒng)的固有頻率、共振點放大倍數(shù)和振動衰減的情況,結果顯示在激振力頻率92.5Hz處的傳遞率豎直方向為0.2,水平方向為0.3;理論計算和振動試驗的固有頻率誤差豎直方向為2.81%,水平方向為10.5%;隔振系統(tǒng)在0-250Hz頻率范圍內的隔振效率豎直方向為63.8%,水平方向為55.5%;無人機飛行實測獲得的高質量圖像也驗證了隔振系統(tǒng)的隔振性能良好。本文研究工作具有實際工程意義同樣可供機載被動隔振系統(tǒng)設計參考。
[Abstract]:With the development of civilian UAV technology, industrial UAV is widely used in map mapping, disaster search and rescue, power survey and other fields. As the main payload of UAV, photoelectric pods have been paid more and more attention. The photoelectric pods are inevitably affected by a series of complex vibration, such as the engine, the vibration caused by the change of the UAV's speed and attitude, the sliding and sliding, the take-off and landing impact of the ejection parachute, and so on. In order to improve the imaging quality of photoelectric pods, vibration must be controlled. Vibration control can be divided into active control and passive control. Carrying photoelectric pods on a small UAV requires low overall quality, simple structure, strong realizability and economic applicability. Therefore, a passive vibration isolation system suitable for the photoelectric pods of industrial UAV is developed in accordance with the actual operating conditions of the airborne optoelectronic pods. Firstly, the vibration environment test of UAV flight is carried out, and the actual working stage of photoelectric pods is obtained: the vibration signals of UAV under certain flight altitude and engine speed are obtained. Through the data processing, the time domain and frequency domain characteristics of the three directions of the installation position of the photoelectric pod isolator are obtained, which provides the basis for the design of the vibration isolation system. Then the multi-degree-of-freedom model of the photoelectric pod vibration isolation system is established. According to the mathematical model and vibration isolation theory, the spatial layout and relative position of the isolator, the three-dimensional stiffness and damping value of the isolator and the design of the frame structure of the isolation system are guided. The natural frequencies of six degrees of freedom of the optoelectronic pod vibration isolation system are reasonably configured. Finally, a small dry friction high damping metal vibration isolator is applied. On this basis, the dynamic model and the finite element model of the photoelectric pod vibration isolation system are established. The modal information, coupling rate, frequency response curve and random vibration response curve of the photoelectric pod vibration isolation system are obtained by using the Adams/Vibration module. The results show that the maximum error of natural frequency between theoretical calculation and simulation analysis is 1.27. The modal analysis, strength analysis and dynamic stiffness analysis of the frame of vibration isolation system are carried out by using Workbench software to verify the adaptability and reliability of the structure of the isolation system. Finally, the vibration table test of the photoelectric pod vibration isolation system including sinusoidal sweep frequency test and random vibration test is carried out. The natural frequency of the isolation system, the magnification of the common vibration point and the vibration attenuation are obtained. The results show that the vertical direction is 0.2 and the horizontal direction is 0.3 at the excitation frequency 92.5Hz. The vertical direction of natural frequency error in theoretical calculation and vibration test is 2.81, the horizontal direction is 10.5, the vertical direction of isolation efficiency in 0-250Hz frequency range is 63.8 and the horizontal direction is 55.5. The high-quality images obtained from UAV flight test also verify the good isolation performance of the vibration isolation system. The research work in this paper is of practical engineering significance and can be used as a reference for the design of airborne passive vibration isolation system.
【學位授予單位】：中國科學院長春光學精密機械與物理研究所
【學位級別】：碩士
【學位授予年份】：2017
【分類號】：TB535.1
本文編號：2367771
[Abstract]:With the development of civilian UAV technology, industrial UAV is widely used in map mapping, disaster search and rescue, power survey and other fields. As the main payload of UAV, photoelectric pods have been paid more and more attention. The photoelectric pods are inevitably affected by a series of complex vibration, such as the engine, the vibration caused by the change of the UAV's speed and attitude, the sliding and sliding, the take-off and landing impact of the ejection parachute, and so on. In order to improve the imaging quality of photoelectric pods, vibration must be controlled. Vibration control can be divided into active control and passive control. Carrying photoelectric pods on a small UAV requires low overall quality, simple structure, strong realizability and economic applicability. Therefore, a passive vibration isolation system suitable for the photoelectric pods of industrial UAV is developed in accordance with the actual operating conditions of the airborne optoelectronic pods. Firstly, the vibration environment test of UAV flight is carried out, and the actual working stage of photoelectric pods is obtained: the vibration signals of UAV under certain flight altitude and engine speed are obtained. Through the data processing, the time domain and frequency domain characteristics of the three directions of the installation position of the photoelectric pod isolator are obtained, which provides the basis for the design of the vibration isolation system. Then the multi-degree-of-freedom model of the photoelectric pod vibration isolation system is established. According to the mathematical model and vibration isolation theory, the spatial layout and relative position of the isolator, the three-dimensional stiffness and damping value of the isolator and the design of the frame structure of the isolation system are guided. The natural frequencies of six degrees of freedom of the optoelectronic pod vibration isolation system are reasonably configured. Finally, a small dry friction high damping metal vibration isolator is applied. On this basis, the dynamic model and the finite element model of the photoelectric pod vibration isolation system are established. The modal information, coupling rate, frequency response curve and random vibration response curve of the photoelectric pod vibration isolation system are obtained by using the Adams/Vibration module. The results show that the maximum error of natural frequency between theoretical calculation and simulation analysis is 1.27. The modal analysis, strength analysis and dynamic stiffness analysis of the frame of vibration isolation system are carried out by using Workbench software to verify the adaptability and reliability of the structure of the isolation system. Finally, the vibration table test of the photoelectric pod vibration isolation system including sinusoidal sweep frequency test and random vibration test is carried out. The natural frequency of the isolation system, the magnification of the common vibration point and the vibration attenuation are obtained. The results show that the vertical direction is 0.2 and the horizontal direction is 0.3 at the excitation frequency 92.5Hz. The vertical direction of natural frequency error in theoretical calculation and vibration test is 2.81, the horizontal direction is 10.5, the vertical direction of isolation efficiency in 0-250Hz frequency range is 63.8 and the horizontal direction is 55.5. The high-quality images obtained from UAV flight test also verify the good isolation performance of the vibration isolation system. The research work in this paper is of practical engineering significance and can be used as a reference for the design of airborne passive vibration isolation system.
【學位授予單位】：中國科學院長春光學精密機械與物理研究所
【學位級別】：碩士
【學位授予年份】：2017
【分類號】：TB535.1
【參考文獻】
相關期刊論文 前10條
1 杜言魯;丁亞林;許永森;聶品;;機載光電平臺隔振系統(tǒng)振動耦合分析[J];中國機械工程;2015年21期
2 楊劍鋒;徐振邦;吳清文;李義;陳立恒;顧營迎;;空間光學載荷六維隔振系統(tǒng)的設計[J];光學精密工程;2015年05期
3 閆勇;姚勁松;;光學小衛(wèi)星振動夾具設計及動特性分析[J];紅外與激光工程;2014年S1期
4 李創(chuàng);郗小鵬;孫穎;鄧東東;;機載高精度光電吊艙無轉角隔振設計[J];機電技術;2014年04期
5 王平;張國玉;高玉軍;丁金偉;郎小龍;;金屬橡膠減振器在機載光電吊艙復合減振系統(tǒng)中的應用[J];振動與沖擊;2014年05期
6 王平;張國玉;劉家燕;高玉軍;黃猛;;機載光電吊艙無角位移隔振設計[J];紅外與激光工程;2012年10期
7 劉蘊華;;光電吊艙測角精度分析[J];現(xiàn)代電子技術;2012年17期
8 李玉龍;何忠波;白鴻柏;郝慧榮;李冬偉;;光電吊艙無角位移被動減振系統(tǒng)研究[J];振動與沖擊;2012年16期
9 程來;宋言明;楊洋;;機載裝置的振動試驗夾具設計[J];機械科學與技術;2012年06期
10 王平;王偉;丁金偉;程志峰;劉家燕;;機載光電偵察平臺復合減振設計[J];光學精密工程;2011年01期
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