本文選題：近空間飛行器 + 主動(dòng)控制技術(shù)　； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：近空間可變翼飛行器具有大飛行包絡(luò)和高空高超聲速飛行的能力,這些特點(diǎn)存在的同時(shí)也帶來(lái)了更多的研究難點(diǎn)。飛行器高超聲速飛行時(shí)氣動(dòng)焦點(diǎn)會(huì)大幅度后移,將產(chǎn)生很大的穩(wěn)定裕度,形成很大的負(fù)俯仰力矩,需要尾翼提供抬頭俯仰力矩以平衡。一方面機(jī)翼升力除了要與飛行器重量平衡,還要平衡尾翼的負(fù)向升力,使總升力減少;另一方面飛行器高速飛行段的機(jī)動(dòng)性能也因?yàn)榉�(wěn)定裕度大大增加而變壞。同時(shí)本文研究的近空間可變翼飛行器要求實(shí)現(xiàn)自主水平起降,然而由于其采用大后掠翼細(xì)長(zhǎng)比結(jié)構(gòu),低速飛行過(guò)程時(shí)升力系數(shù)較常規(guī)飛行器明顯偏小,將嚴(yán)重影響飛行器起飛性能。針對(duì)上述問(wèn)題,本文提出采用放寬靜穩(wěn)定性技術(shù)改善近空間可變翼飛行器升力特性不足、高速機(jī)動(dòng)性能不佳的問(wèn)題,采用直接力技術(shù)解決飛行器起飛性能不佳的問(wèn)題。本文的主要研究?jī)?nèi)容包括:(1)定性和定量的分析放寬靜穩(wěn)定性對(duì)近空間可變翼飛行器升力特性及機(jī)動(dòng)性能的影響收益,定量得到在保證高速巡航段飛行器機(jī)動(dòng)性能良好前提下需要放寬的靜穩(wěn)定度,并分析實(shí)現(xiàn)放寬指定靜穩(wěn)定度的工程實(shí)現(xiàn)方法,為工程實(shí)現(xiàn)提供解決思路。(2)放寬靜穩(wěn)定性后的飛行器在亞聲速階段變?yōu)殪o不穩(wěn)定,本文分別采用基于經(jīng)典反饋的線性控制方法和基于動(dòng)態(tài)逆-PID的非線性控制方法為亞聲速飛行器設(shè)計(jì)增穩(wěn)控制系統(tǒng)。仿真結(jié)果表示,后者能夠使飛行器具有更良好的穩(wěn)定性。(3)飛行器在高超聲速階段外部干擾頻繁、內(nèi)部變化劇烈,呈現(xiàn)嚴(yán)重的非線性特性。本文利用回饋遞推方法在處理非線性問(wèn)題上的獨(dú)特優(yōu)越性,設(shè)計(jì)基于回饋遞推的智能非線性控制器,并用其對(duì)放寬靜穩(wěn)定后的飛行器在高超聲速段進(jìn)行跟蹤控制,仿真結(jié)果說(shuō)明控制器具有良好的跟蹤性能和魯棒性能。(4)本文最后定量研究采用矢量噴管與鴨翼協(xié)同配合產(chǎn)生直接力對(duì)改善近空間可變翼飛行器水平起飛性能的收益。仿真結(jié)果表明,該方法明顯改善了飛行器的起飛性能。
[Abstract]:Near-space variable wing aircraft has the capability of large flight envelope and hypersonic flight at high altitude. These characteristics also bring more research difficulties. During hypersonic flight, the aerodynamic focus will move backward by a large margin, which will produce a large stability margin, and form a large negative pitch moment, which requires the tail wing to provide a lift pitch moment to balance. On the one hand, the lift of the wing must be balanced with the weight of the aircraft, but also the negative lift of the tail should be balanced to reduce the total lift. On the other hand, the maneuverability of the high-speed flight section of the aircraft is also deteriorated because of the increase of the stability margin. At the same time, the near-space variable wing aircraft studied in this paper requires autonomous horizontal take-off and landing. However, the lift coefficient in low speed flight process is obviously smaller than that of conventional aircraft because of its large swept wing slenderness ratio structure. Will seriously affect the aircraft takeoff performance. Aiming at the above problems, this paper puts forward the problem of using relaxation static stability technology to improve the lift characteristics of near space variable wing aircraft and poor performance of high speed maneuverability, and using direct force technology to solve the problem of poor take-off performance of aircraft. The main contents of this paper are as follows: (1) qualitative and quantitative analysis of the impact of relaxation of static stability on lift characteristics and maneuverability of near-space variable wing aircraft; The static stability degree which needs to be relaxed under the premise of good maneuverability of the aircraft in high-speed cruising section is obtained quantitatively, and the engineering realization method to realize the relaxation of specified static stability degree is analyzed. It provides a solution for engineering implementation. (2) after relaxation of static stability, the aircraft becomes static instability in the subsonic phase. In this paper, the linear control method based on classical feedback and the nonlinear control method based on dynamic inverse pid are used to design the stability enhancement control system for the subsonic vehicle. The simulation results show that the latter can make the aircraft have better stability. (3) the external interference of the aircraft in hypersonic phase is frequent, the internal changes are severe, and the aircraft presents serious nonlinear characteristics. In this paper, an intelligent nonlinear controller based on feedback recursion is designed based on the unique superiority of feedback recursive method in dealing with nonlinear problems, and it is used to track and control the aircraft at hypersonic speed after relaxation of static stability. The simulation results show that the controller has good tracking performance and robust performance. (4) in the last part of this paper, the direct force generated by the coordination of vector nozzle and duck wing is quantitatively studied to improve the horizontal take-off performance of the near-space variable wing aircraft. The simulation results show that this method can improve the take-off performance of the aircraft.
【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
【分類號(hào)】：V249.1

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