發(fā)布時(shí)間：2018-01-07 08:42

  本文關(guān)鍵詞：帶可傾轉(zhuǎn)升力風(fēng)扇飛翼布局的氣動(dòng)特性研究及優(yōu)化　出處：《南昌航空大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 開口機(jī)翼 升力風(fēng)扇 飛翼布局 氣動(dòng)特性 優(yōu)化

【摘要】：鑒于帶升力風(fēng)扇飛翼布局飛機(jī)兼具垂直/短距起降和飛翼布局飛機(jī)的優(yōu)點(diǎn)之外,還具有推重比較大、凈升效率較高、無熱噴流等優(yōu)點(diǎn)。帶升力風(fēng)扇以實(shí)現(xiàn)飛機(jī)的短距/垂直起降將會(huì)是在以后很長時(shí)間內(nèi)的一個(gè)重要研究課題。但由于帶可傾轉(zhuǎn)升力風(fēng)扇飛翼布局飛機(jī)的升力風(fēng)扇設(shè)置在機(jī)翼中央,在平飛時(shí)機(jī)翼上的風(fēng)扇開口將對(duì)飛機(jī)的氣動(dòng)特性產(chǎn)生重要影響,因此,研究其氣動(dòng)特性與開口形狀的關(guān)系顯得尤為重要。本文采用CFD數(shù)值方法對(duì)在平飛狀態(tài)下帶可傾轉(zhuǎn)升力風(fēng)扇飛翼布局無人機(jī)為安裝升力風(fēng)扇而開口的機(jī)翼氣動(dòng)特性進(jìn)行了研究,分析開口機(jī)翼在平飛狀態(tài)不同來流速度下以及不同迎角下開口機(jī)翼的氣動(dòng)特性。主要研究內(nèi)容為:1建立開口機(jī)翼開口處最大縱向剖面二維模型,通過ICEM進(jìn)行幾何模型的結(jié)構(gòu)網(wǎng)格化分,并將結(jié)構(gòu)網(wǎng)格導(dǎo)入到FLUENT進(jìn)行數(shù)值仿真。結(jié)果表明,在相同條件下,開口機(jī)翼的氣動(dòng)特性明顯變差,但俯仰的操控性較好。且開口機(jī)翼的開口處產(chǎn)生了渦,損失了部分的能量,從而進(jìn)一步降低了的開口機(jī)翼的氣動(dòng)特性。2通過對(duì)九組優(yōu)化二維模型氣動(dòng)特性進(jìn)行了對(duì)比,對(duì)機(jī)翼開口機(jī)翼截面進(jìn)行了不同的修形,結(jié)果表明:開口機(jī)翼開口處完全圓弧優(yōu)化且開口前段截面前傾適當(dāng)角度得到的氣動(dòng)特性最佳。優(yōu)化后開口機(jī)翼的氣動(dòng)特性得到了顯著的提升。3建立開口機(jī)翼三維幾何模型,通過ICEM進(jìn)行幾何模型的結(jié)構(gòu)網(wǎng)格化分,并將結(jié)構(gòu)網(wǎng)格導(dǎo)入到FLUENT進(jìn)行數(shù)值仿真。結(jié)果表明,三維仿真結(jié)果和二維仿真結(jié)果類似。開口機(jī)翼同樣是由于損失了部分機(jī)翼,且在開口處產(chǎn)生了渦,損耗了部分能量是導(dǎo)致開口機(jī)翼氣動(dòng)特性變差的重要原因。4根據(jù)二維模型的優(yōu)化方向,選定了十六個(gè)優(yōu)化方向,并進(jìn)行三維數(shù)值仿真。結(jié)果表明,開口機(jī)翼開口處前段進(jìn)行內(nèi)切圓弧化處理得到的氣動(dòng)特性最佳。從流線圖看,其產(chǎn)生的渦極小,相對(duì)于未優(yōu)化開口機(jī)翼來說可以忽略不計(jì),而優(yōu)化后開口機(jī)翼開口處后段產(chǎn)生的渦從渦的范圍以及強(qiáng)度來說也變小了很多,這些都是改善開口機(jī)翼氣動(dòng)特性的重要方法。綜上所述,帶升力風(fēng)扇飛翼布局飛機(jī)由于機(jī)翼中間開口,造成氣動(dòng)特性降低,但通過對(duì)開口的合理設(shè)計(jì),可有效改善其氣動(dòng)特性;二維優(yōu)化一定程度上可以代表優(yōu)化的方向,但經(jīng)三維優(yōu)化的結(jié)果更加明顯。
[Abstract]:In view of the fact that with the lift fan flying wing aircraft has both advantages of V / STOL and flying wing aircraft, has given rise is relatively large, the net efficiency is high, the advantages of no hot jet. With the lift fan aircraft to achieve short takeoff / vertical landing will be an important research topic in the future for a long time. The lift fan with tilting lift fan flying wing set in the central wing, flying wing in the fan opening on the aircraft aerodynamic characteristics have an important impact, therefore, to study the relationship between the dynamic characteristics of gas and the shape of the opening is particularly important. This paper uses the CFD numerical method of wings to fly in the state flat with tilting lift fan flying wing UAV and the opening for the installation of lift fan aerodynamic characteristics of the wing in the flat state analysis of opening different flow velocity and different The opening angle of the aerodynamic characteristics of the wing. The main contents are as follows: 1 the establishment of the opening at the opening of the maximum longitudinal profile of the wing structure of two-dimensional model, grid geometry model by ICEM, and the structure of the grid into FLUENT numerical simulation. The results show that under the same conditions, opening the aerodynamic characteristics of the wing worse, but control of the pitch better. The opening and the opening of the wing vortex, the loss of some energy, thus further reducing the opening wing aerodynamic characteristics of the.2 based on nine dimensional model optimization of aerodynamic characteristics were compared by different modification of wing wing opening the results show that the opening section of wing opening and opening the front section completely optimum arc forward proper angle of aerodynamic characteristics was optimized. The best opening of the aerodynamic characteristics of the wing can significantly improve the establishment of open.3 The three-dimensional geometric model of grid structure, the geometric model by ICEM, and the structure of the grid into FLUENT numerical simulation. The results show that the 3D simulation results similar to two-dimensional simulation results. The wing is also due to the loss of the opening part of the wing, and produced a vortex in the opening, a part of the energy loss is the result of.4 an important reason for opening the wing's aerodynamic characteristics of variation according to the direction of optimization of two dimensional model, selected sixteen optimization direction, and three-dimensional numerical simulation. The results show that the opening of the opening of the front wing inscribed circle arc processing of aerodynamic characteristics was the best. From the flow chart, the minimum vortex, compared with optimization of wing is negligible opening, and the optimized wing opening period after opening the vortex generated by the vortex from the range and strength is also a lot smaller, these are the improvement of opening An important method of aerodynamic characteristics of wings. To sum up, with the flying wing aircraft wing lift fan as an opening in the middle, resulting in reduced aerodynamic characteristics, but by the reasonable design of the opening, can effectively improve its aerodynamic characteristics; two-dimensional optimization to a certain extent can represent the direction of optimization, but the three-dimensional optimization results more obvious.

【學(xué)位授予單位】：南昌航空大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V211.4

【相似文獻(xiàn)】

相關(guān)期刊論文 前10條

1 鄭志成;周洲;;垂直起降飛機(jī)設(shè)計(jì)中升力風(fēng)扇估算模型分析[J];飛行力學(xué);2010年03期

2 牛東科;翟普;;垂直起降無人機(jī)用升力風(fēng)扇分析模型初探[J];戰(zhàn)術(shù)導(dǎo)彈技術(shù);2012年02期

3 張冰融;詹浩;張怡哲;張煒;;帶擾流片的升力風(fēng)扇操縱特性數(shù)據(jù)采集系統(tǒng)設(shè)計(jì)[J];航空工程進(jìn)展;2013年03期

4 徐雪;黃愛華;郭捷;;基于關(guān)鍵結(jié)構(gòu)特征的升力風(fēng)扇結(jié)構(gòu)布局方案設(shè)計(jì)[J];航空發(fā)動(dòng)機(jī);2014年04期

5 ;F-35B戰(zhàn)斗機(jī)俯視[J];兵器知識(shí);2014年06期

6 劉峻峰;羅·羅公司完成JSF關(guān)鍵性試驗(yàn)[J];燃?xì)鉁u輪試驗(yàn)與研究;2003年04期

7 郭捷;楊琳;鄭寧;王詠梅;;短距/垂直起落戰(zhàn)斗機(jī)升力風(fēng)扇關(guān)鍵技術(shù)的探討[J];航空科學(xué)技術(shù);2008年02期

8 王平;詹浩;張怡哲;;升力風(fēng)扇無人機(jī)垂直起飛控制系統(tǒng)設(shè)計(jì)與仿真[J];航空計(jì)算技術(shù);2012年04期

9 楊國才;JSF的STOVL型別推進(jìn)系統(tǒng)的設(shè)計(jì)競(jìng)爭(zhēng)[J];飛機(jī)設(shè)計(jì);2003年01期

10 鄭志成;周洲;昌敏;王琛;;升力風(fēng)扇垂直起降飛機(jī)阻力特性分析[J];西北工業(yè)大學(xué)學(xué)報(bào);2012年01期

相關(guān)會(huì)議論文 前1條

1 王華飛;陳勇;陳圓圓;;基于升力風(fēng)扇系統(tǒng)的垂直/短距起降技術(shù)在固定翼無人飛行器上應(yīng)用的可行性分析[A];探索 創(chuàng)新 交流——第五屆中國航空學(xué)會(huì)青年科技論壇文集(第5集)[C];2012年

相關(guān)重要報(bào)紙文章 前2條

1 鐘強(qiáng);“個(gè)人飛行器”有望變成現(xiàn)實(shí)[N];中國航空?qǐng)?bào);2005年

2 本報(bào)專稿 陳言;無人運(yùn)輸機(jī)成特種部隊(duì)新寵[N];世界報(bào);2010年

相關(guān)碩士學(xué)位論文 前1條

1 林玉祥;帶可傾轉(zhuǎn)升力風(fēng)扇飛翼布局的氣動(dòng)特性研究及優(yōu)化[D];南昌航空大學(xué);2016年

，

本文編號(hào)：1391841