【摘要】：武器內(nèi)埋式裝載是新一代戰(zhàn)斗機(jī)實(shí)現(xiàn)超聲速巡航和雷達(dá)隱身的重要技術(shù),武器內(nèi)埋技術(shù)涉及很多關(guān)鍵的氣動性問題。在軍事作戰(zhàn)中,武器艙門需快速開啟,導(dǎo)彈迅速地完成與彈艙的分離,強(qiáng)耦合流動會對外部流場產(chǎn)生強(qiáng)烈干擾,加劇艙內(nèi)流場的非定常效應(yīng),出現(xiàn)一系列復(fù)雜的物理現(xiàn)象：如流動分離與再附著、旋渦的產(chǎn)生／發(fā)展／脫落、旋渦／剪切層相互干擾；特別在超聲速條件下,還存在波系干擾、激波／剪切層及激波／邊界層的相互作用。同時(shí),強(qiáng)耦合流動會增加艙門及導(dǎo)彈表面的氣動載荷,出現(xiàn)流致振動,引發(fā)結(jié)構(gòu)疲勞及損傷,嚴(yán)重危及飛行安全。因此,有必要開展艙門開啟和導(dǎo)彈分離所引發(fā)的耦合流場動態(tài)特性研究。 本研究采用數(shù)值計(jì)算的方法來模擬艙門開啟和導(dǎo)彈分離的動態(tài)過程。通過有限體積法求解三維、非定常、可壓縮N-S方程,運(yùn)用非結(jié)構(gòu)網(wǎng)格和基于局部重構(gòu)的動態(tài)網(wǎng)格技術(shù),分別對亞、跨、超聲速下的艙門開啟過程進(jìn)行數(shù)值模擬研究。根據(jù)不同來流馬赫數(shù)時(shí)的動態(tài)計(jì)算結(jié)果來分析流場中旋渦、剪切層、邊界層、波系等物理現(xiàn)象的產(chǎn)生和發(fā)展機(jī)理,以及相互之間復(fù)雜干擾作用。并在此基礎(chǔ)上進(jìn)一步探究來流攻角和內(nèi)埋導(dǎo)彈干擾分別對艙內(nèi)／外流場非定�，F(xiàn)象和艙門氣動荷載產(chǎn)生的影響。 采用同樣的數(shù)值方法,通過耦合求解控制方程和剛體六自由度(6DOF)方程,對超聲速下(來流馬赫數(shù)分別為1.5和2.0)的導(dǎo)彈分離動態(tài)過程進(jìn)行數(shù)值模擬研究。依據(jù)瞬態(tài)流線圖和流場云圖,對超聲速下的物理現(xiàn)象進(jìn)行詳細(xì)的分析；同時(shí),對不同來流馬赫數(shù)下艙底壓力分布、導(dǎo)彈氣動載荷作出對比分析,分別給出以上數(shù)據(jù)隨導(dǎo)彈分離過程的變化趨勢,揭示了飛行馬赫數(shù)對流場動態(tài)特性及導(dǎo)彈姿態(tài)的影響。 模擬結(jié)果顯示：艙門開啟和導(dǎo)彈分離的動態(tài)過程,會引發(fā)艙內(nèi)旋渦的非定常發(fā)展和旋渦／剪切層的相互干擾,在彈艙前緣、導(dǎo)彈上表面產(chǎn)生分離流動；跨、超聲速流場中出現(xiàn)了激波相交、激波／膨脹波相交、激波／剪切層干擾和激波／邊界層干擾等復(fù)雜物理現(xiàn)象；同時(shí),艙門開啟和導(dǎo)彈分離運(yùn)動誘使艙內(nèi)流動形態(tài)發(fā)生改變,引起艙底壓力分布的變化,艙門和導(dǎo)彈的氣動載荷也產(chǎn)生非定常效應(yīng)。 本研究的數(shù)值模擬結(jié)果在一定程度上豐富了內(nèi)埋武器技術(shù)的研究,為內(nèi)埋武器艙的結(jié)構(gòu)設(shè)計(jì)、導(dǎo)彈安全分離等工程實(shí)際問題提供了參考和依據(jù)。
[Abstract]:Weapon embedded loading is an important technology for the new generation fighter to realize supersonic cruise and radar stealth. The embedded weapon technology involves many key aerodynamic problems. In military operations, the weapon hatch needs to be opened quickly, and the missile is quickly separated from the projectile. The strong coupling flow will cause strong interference to the external flow field and aggravate the unsteady effect of the flow field in the cabin. A series of complex physical phenomena appear, such as separation and reattachment of flow, generation / development / shedding of vortex, interaction of vortex / shear layer, and interference of wave system, especially in supersonic condition. The interaction of shock wave / shear layer and shock wave / boundary layer. At the same time, the strong coupling flow will increase the aerodynamic load on the door and missile surface, cause fluid-induced vibration, cause structural fatigue and damage, and seriously endanger flight safety. Therefore, it is necessary to study the dynamic characteristics of coupled flow field caused by door opening and missile separation. In this study, a numerical method is used to simulate the dynamic process of door opening and missile separation. The three-dimensional, unsteady and compressible N-S equations are solved by finite volume method. The unstructured meshes and the dynamic meshes based on local reconstruction are used to simulate the opening process of the hatch at sub-, transonic and supersonic velocities, respectively. According to the dynamic calculation results of different incoming Mach numbers, the generation and development mechanism of vortex, shear layer, boundary layer and wave system in the flow field are analyzed, as well as the complex interaction between them. On this basis, the influences of angle of attack and missile interference on the unsteady phenomena and aerodynamic loads on the cabin / outflow field are further investigated. Using the same numerical method, the dynamic process of missile separation with supersonic velocity (Mach number 1.5 and Mach number 2.0) is numerically simulated by coupling solving control equation and 6-DOF equation of rigid body. According to the transient streamline diagram and the flow field cloud diagram, the physical phenomena under supersonic velocity are analyzed in detail, at the same time, the distribution of bilge pressure and the aerodynamic load of missile under different flow Mach numbers are compared and analyzed. The variation trend of the above data with the missile separation process is given, and the dynamic characteristics of the flight Mach number flow field and the influence of the missile attitude are revealed. The simulation results show that the dynamic process of hatch opening and missile separation will lead to unsteady development of vortex in cabin and mutual interference of vortex / shear layer, and separate flow on the upper surface of missile at the front edge of missile. Complex physical phenomena such as shock wave intersection, shock / expansion wave intersection, shock / shear layer interference and shock / boundary layer interference occur in supersonic flow field. The aerodynamic load of the hatch and missile also produces unsteady effect. The numerical simulation results of this study enrich the research of the embedded weapon technology to a certain extent and provide reference and basis for the structural design of the buried weapon cabin and the missile safety separation and other engineering practical problems.
【學(xué)位授予單位】：北京交通大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V271.4

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 許曉平;周洲;范銳軍;王軍利;;基于動態(tài)嵌套網(wǎng)格技術(shù)的機(jī)載武器投放研究[J];兵工學(xué)報(bào);2010年09期

2 馮必鳴;聶萬勝;車學(xué)科;;超聲速條件下內(nèi)埋式武器分離特性的數(shù)值分析[J];飛機(jī)設(shè)計(jì);2009年04期

3 黎軍;張群峰;曾宏剛;李天;;腔體閉式流動控制的實(shí)驗(yàn)和數(shù)值模擬[J];北京航空航天大學(xué)學(xué)報(bào);2008年01期

4 黃存棟;徐來武;吳繼飛;高鵬;;FL-24風(fēng)洞武器艙艙門動態(tài)試驗(yàn)裝置[J];兵工自動化;2014年02期

5 史愛明;葉正寅;楊永年;;內(nèi)埋式彈艙艙門氣動載荷計(jì)算分析研究[J];航空計(jì)算技術(shù);2007年03期

6 馬明生;張培紅;鄧有奇;吳曉軍;;超聲速空腔流動數(shù)值模擬研究[J];空氣動力學(xué)學(xué)報(bào);2008年03期

7 黎軍;李天;張群峰;;開式流動腔體的流動機(jī)理與控制[J];實(shí)驗(yàn)流體力學(xué);2008年01期

8 楊e，

本文編號：2137047