本文選題：無人機 + 導(dǎo)彈發(fā)射��； 參考：《中北大學(xué)》2016年碩士論文

【摘要】：在現(xiàn)代戰(zhàn)爭中,作為信息化武器裝備的無人機發(fā)揮著越來越重要的作用,集偵察、監(jiān)視和攻擊能力于一體是無人機未來發(fā)展方向之一,掛載精確制導(dǎo)武器是該方向無人機的主要攻擊手段。武器與載機的分離屬于多體分離問題,分離初期存在顯著的氣動干擾,導(dǎo)彈點火時產(chǎn)生的尾噴流對無人機的氣動干擾尤為嚴重,影響載機的飛行穩(wěn)定性。因此,研究無人機掛載導(dǎo)彈發(fā)射時產(chǎn)生的氣動干擾問題對無人機的飛行安全和導(dǎo)彈的安全分離具有重要意義。本論文著重研究機載導(dǎo)彈滑彈一體式發(fā)射過程中尾噴流對無人機的氣動影響。研究以計算流體力學(xué)為理論依據(jù),以CFD軟件Fluent為研究平臺,結(jié)合二維非結(jié)構(gòu)動網(wǎng)格技術(shù),模擬機載導(dǎo)彈滑彈一體式發(fā)射的過程。文中使用CATIA建立簡化的模型,采用非結(jié)構(gòu)網(wǎng)格生成技術(shù)對流場域進行網(wǎng)格的劃分。考慮到導(dǎo)彈與無人機之間的相對運動,使用Fluent的動網(wǎng)格技術(shù)對計算過程中較大變形的網(wǎng)格進行自動更新。與機翼相連的網(wǎng)格靜止,固聯(lián)于導(dǎo)彈的網(wǎng)格跟隨導(dǎo)彈運動,是運動網(wǎng)格。在Fluent中定義流場域的性質(zhì)以及邊界條件等,并監(jiān)控機翼升、阻力系數(shù)的變化情況。通過對機載導(dǎo)彈滑彈一體式發(fā)射過程的模擬得到:使用滑彈一體式發(fā)射裝置在一定程度上降低了導(dǎo)彈尾噴流對機翼的氣動影響以及彈射后不同時間點火對機翼的氣動干擾。同時,對無人機不同的飛行速度下,導(dǎo)彈的發(fā)射過程進行模擬,發(fā)現(xiàn)不同馬赫數(shù)下,尾噴流對機翼的氣動影響不同。該模擬結(jié)果為無人機導(dǎo)彈滑彈一體式發(fā)射裝置的研究提供一定參考。
[Abstract]:In modern warfare, UAV, as an information-based weapon, plays an increasingly important role. It is one of the future development directions of UAV to integrate reconnaissance, surveillance and attack capabilities. Mounted precision guided weapon is the main attack method of UAV in this direction. The separation of weapons and aircraft is a multi-body separation problem. There is significant aerodynamic interference in the initial stage of separation. The aerodynamic interference caused by the tail jet produced by missile ignition is especially serious, which affects the flight stability of the aircraft. Therefore, it is of great significance to study the aerodynamic interference caused by the launch of unmanned aerial vehicle (UAV) mounted missile for UAV flight safety and missile safety separation. In this paper, the aerodynamic effect of tail jet on UAV is studied. Based on the theory of computational fluid dynamics (CFD) and CFD software fluent, this paper simulates the integrated launching process of airborne missile with unstructured dynamic grid technology. In this paper, CATIA is used to build a simplified model, and unstructured mesh generation technique is used to generate meshes in the flow field. Considering the relative motion between missile and UAV, fluent dynamic grid technology is used to automatically update the large deformation mesh in the calculation process. The grid attached to the wing is stationary, and the mesh attached to the missile follows the missile's motion, which is the moving grid. The properties of flow field and boundary conditions are defined in fluent, and the change of wing lift and drag coefficient is monitored. Through the simulation of the integrated launching process of airborne missile, it is concluded that the aerodynamic effect of missile tail jet on the wing and the aerodynamic interference caused by ignition at different time after ejection are reduced to some extent by using the integrated missile launcher. At the same time, the missile launch process is simulated at different flight speeds, and it is found that the tail jet has different aerodynamic effects on the wing under different Mach numbers. The simulation results provide a certain reference for the research of UAV missile sliding missile integrated launcher.
【學(xué)位授予單位】：中北大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V279;TJ760

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