本文選題：傾轉(zhuǎn)旋翼機(jī) + 多旋翼飛行器��； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：本文設(shè)計(jì)的新構(gòu)型傾轉(zhuǎn)四旋翼飛行器結(jié)合了多旋翼飛行器和固定翼飛機(jī),是一種具有創(chuàng)新性的飛行器。其充分利用成熟穩(wěn)定的多旋翼控制技術(shù),兼?zhèn)浯怪逼鸾?懸停和快速前飛的特點(diǎn),能夠在軍民用領(lǐng)域完成一系列較為復(fù)雜的任務(wù)。首先,通過(guò)對(duì)多旋翼飛行器以及傳統(tǒng)傾轉(zhuǎn)旋翼機(jī)的發(fā)展與研究總結(jié)這兩種飛行器的各自優(yōu)缺點(diǎn),針對(duì)設(shè)計(jì)要求提出該飛行器的不同構(gòu)型方案,并進(jìn)行分析比較,以確定合適的飛行器方案。其次,對(duì)確定的新構(gòu)型傾轉(zhuǎn)四旋翼飛行器進(jìn)行總體參數(shù)設(shè)計(jì),以選定合適的動(dòng)力系統(tǒng)。接著進(jìn)行氣動(dòng)布局設(shè)計(jì),包括四旋翼模式、固定翼模式以及傾轉(zhuǎn)過(guò)渡過(guò)程的氣動(dòng)布局設(shè)計(jì),對(duì)各主要部件的參數(shù)進(jìn)行設(shè)計(jì),并確定飛行器焦點(diǎn)及重心參考位置,繪制三面圖。然后,對(duì)各部件進(jìn)行詳細(xì)的結(jié)構(gòu)設(shè)計(jì),利用Patran/Nastran對(duì)機(jī)翼進(jìn)行結(jié)構(gòu)分析和強(qiáng)度校核,并對(duì)整機(jī)在不同狀態(tài)下利用Fluent進(jìn)行螺旋槳/機(jī)翼/機(jī)身的氣動(dòng)干擾分析,以及根據(jù)理論推導(dǎo)結(jié)合實(shí)際數(shù)據(jù)進(jìn)行性能計(jì)算。最后,制作原理樣機(jī),調(diào)試后進(jìn)行試飛驗(yàn)證,證明了本文設(shè)計(jì)的新構(gòu)型傾轉(zhuǎn)四旋翼飛行器飛行原理合理可行,為后期研制可用于軍民用領(lǐng)域的飛行器打下了基礎(chǔ)。
[Abstract]:The new type tilting four-rotor aircraft designed in this paper is a kind of innovative aircraft which combines multi-rotor aircraft and fixed-wing aircraft. It makes full use of mature and stable multi-rotor control technology and has the characteristics of vertical takeoff / hover and fast forward flight. It can accomplish a series of complex tasks in the field of military and civilian use. First of all, through the development and research of the multi-rotor aircraft and the traditional tilting rotor aircraft, the advantages and disadvantages of the two kinds of aircraft are summarized, and the different configuration schemes of the aircraft are put forward according to the design requirements, and the analysis and comparison are carried out. To determine the appropriate aircraft plan. Secondly, the overall parameters of the new configuration tilting four rotor aircraft are designed to select the appropriate power system. Then the aerodynamic layout design is carried out including four rotor mode fixed wing mode and tilting transition process. The parameters of the main components are designed and the focus and reference position of the center of gravity of the aircraft are determined and the three-sided diagram is drawn. Then, the detailed structural design of each component is carried out, the structure analysis and strength check of the wing are carried out by using Patran/Nastran, and the aerodynamic interference analysis of the propeller / wing / fuselage is carried out by using Fluent in different states. And according to the theoretical derivation combined with the actual data to calculate the performance. Finally, the principle prototype is made and flight test is carried out after debugging, which proves that the flight principle of the new configuration tilting four-rotor aircraft designed in this paper is reasonable and feasible, which lays the foundation for the later development of the aircraft which can be used in the field of military and civilian use.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類(lèi)號(hào)】：V275.1

【相似文獻(xiàn)】

相關(guān)期刊論文 前10條

1 周城鎬;;錐筒形傾轉(zhuǎn)包設(shè)計(jì)計(jì)算中的三個(gè)理論問(wèn)題[J];鑄造設(shè)備研究;1988年01期

2 櫖爾 J.普雷斯，

本文編號(hào)：1893688