本文選題：無(wú)人機(jī)　切入點(diǎn)：撞擊過(guò)載　出處：《中北大學(xué)》2017年碩士論文　論文類型：學(xué)位論文

【摘要】：本課題來(lái)源于無(wú)人機(jī)撞擊混凝土靶試驗(yàn)項(xiàng)目,試驗(yàn)旨在收集撞擊時(shí)刻靶體的應(yīng)力和飛機(jī)的過(guò)載數(shù)據(jù),為核電站防護(hù)殼和國(guó)家重要建筑物的設(shè)計(jì)提供理論依據(jù)。在碰撞時(shí)刻,飛機(jī)實(shí)時(shí)狀態(tài)下的過(guò)載作為試驗(yàn)數(shù)據(jù)的重要組成部分,需要一套專業(yè)的測(cè)試系統(tǒng)來(lái)收集,因測(cè)試時(shí)飛機(jī)的動(dòng)態(tài)性和環(huán)境惡劣性決定了測(cè)試有一定的難度。本文基于FPGA控制器利用大容量固態(tài)存儲(chǔ)介質(zhì)研制了一套適用于動(dòng)態(tài)、惡劣環(huán)境的過(guò)載測(cè)試系統(tǒng),旨在收集無(wú)人機(jī)撞擊混凝土靶過(guò)程中飛機(jī)的過(guò)載數(shù)據(jù),根據(jù)試驗(yàn)環(huán)境和數(shù)據(jù)精度的要求確定了系統(tǒng)設(shè)計(jì)指標(biāo),定位了系統(tǒng)設(shè)計(jì)的主要研究?jī)?nèi)容:試驗(yàn)的仿真、軟硬件功能的實(shí)現(xiàn)、項(xiàng)目中的應(yīng)用、實(shí)測(cè)數(shù)據(jù)的分析。(1)在試驗(yàn)的仿真部分,使用ANSYS/LS-DYNA軟件完成仿真,提取了無(wú)人機(jī)尾部的撞擊加速度數(shù)據(jù),并以此確定了所選傳感器的量程;然后,分析了飛機(jī)前端破損區(qū)和后端未破損區(qū)碰撞混凝土靶時(shí)的過(guò)載數(shù)據(jù),為后續(xù)實(shí)測(cè)數(shù)據(jù)的驗(yàn)證提供參考的依據(jù)。(2)在軟硬件功能實(shí)現(xiàn)部分,針對(duì)測(cè)試時(shí)飛機(jī)動(dòng)態(tài)的特點(diǎn)和數(shù)據(jù)高精度要求的難點(diǎn),在硬件部分對(duì)主控制器和Flash存儲(chǔ)電路做了重點(diǎn)說(shuō)明;在軟件部分對(duì)觸發(fā)信號(hào)的消抖、數(shù)據(jù)緩存FIFO、FLASH的讀、寫、擦除控制及壞塊檢測(cè)進(jìn)行了詳細(xì)的說(shuō)明,完成了高速大容量測(cè)試系統(tǒng)功能的實(shí)現(xiàn)。(3)在實(shí)際項(xiàng)目的應(yīng)用部分,介紹了設(shè)備在模型機(jī)試驗(yàn)中出現(xiàn)的電路被燒、電池?fù)p壞、外部傳感器干擾嚴(yán)重的問(wèn)題,并設(shè)計(jì)了相應(yīng)的解決方案,在改進(jìn)后應(yīng)用于第二次模型機(jī)試驗(yàn),驗(yàn)證了解決方案的有效性;最后,將設(shè)備應(yīng)用于無(wú)人機(jī)試驗(yàn)中,對(duì)比試驗(yàn)前后設(shè)備的工作狀態(tài),驗(yàn)證了過(guò)載測(cè)試設(shè)備在應(yīng)用中的可靠性。(4)在數(shù)據(jù)分析部分,一方面,對(duì)設(shè)備內(nèi)部和外部的傳感器所測(cè)數(shù)據(jù)做了對(duì)比,證實(shí)了設(shè)備在試驗(yàn)中工作正常;另一方面,對(duì)比了實(shí)測(cè)數(shù)據(jù)與仿真數(shù)據(jù),分析了飛機(jī)破損區(qū)和發(fā)動(dòng)機(jī)區(qū)的撞擊過(guò)載,驗(yàn)證了所測(cè)數(shù)據(jù)的合理性和正確性。
[Abstract]:This subject comes from the test project of UAV hitting concrete target. The purpose of the experiment is to collect the stress of target and the overload data of aircraft at impact time, and to provide the theoretical basis for the design of nuclear power plant protective shell and important national building. As an important part of the test data, aircraft overload in real time requires a professional test system to collect, It is difficult to test the aircraft because of its dynamic and bad environment. Based on FPGA controller, a set of overload test system is developed based on FPGA controller, which is suitable for dynamic and bad environment. In order to collect the overload data of aircraft in the course of UAV impact on concrete target, the system design index is determined according to the requirements of test environment and data precision, and the main research content of system design is located: simulation of test. The realization of software and hardware function, the application of the project and the analysis of the measured data. In the simulation part of the experiment, the ANSYS/LS-DYNA software is used to complete the simulation, and the acceleration data of the tail of the UAV are extracted, and the range of the selected sensor is determined. Then, the overload data of the damaged area and the undamaged zone of the front end of the plane are analyzed, which provides a reference for the verification of the measured data in the software and hardware. Aiming at the characteristics of aircraft dynamics and the difficulty of high precision data, the main controller and Flash storage circuit are described in the hardware part, and in the software part, the trigger signal is removed and the data cache is read and written. The erasure control and bad block detection are described in detail, and the function of high-speed and large-capacity test system is realized. The application part of the system is introduced. The circuit of the equipment in the model machine test is burned and the battery is damaged. The external sensor interferes seriously, and designs the corresponding solution, after the improvement applies to the second model machine test, the validity of the solution is verified. Finally, the equipment is applied in the UAV test. Comparing the working status of the equipment before and after the test, the reliability of the overload test equipment in application. 4) in the data analysis part. On the one hand, the data measured by the sensors inside and outside the equipment are compared. On the other hand, comparing the measured data with the simulation data, the impact overload in the damaged area and the engine area of the aircraft is analyzed, and the rationality and correctness of the measured data are verified.
【學(xué)位授予單位】：中北大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：V217;TU761.1

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