發(fā)布時(shí)間：2018-06-30 22:17

  本文選題：改進(jìn)布谷鳥(niǎo)算法 + 微分對(duì)策　； 參考：《哈爾濱工業(yè)大學(xué)》2015年碩士論文

【摘要】：當(dāng)前空間技術(shù)發(fā)展迅速,并在國(guó)民的經(jīng)濟(jì),生活和軍事中扮演著重要角色,空間攻防技術(shù)的研究對(duì)國(guó)家空間資源的保護(hù)具有重要意義。本文對(duì)空間攔截中的一種重要方式,反衛(wèi)星攔截的軌道優(yōu)化和控制進(jìn)行了研究,主要內(nèi)容包括以下幾點(diǎn):針對(duì)精確動(dòng)力學(xué)遠(yuǎn)程多脈沖攔截問(wèn)題,建立了含有多種攝動(dòng)項(xiàng)的攔截動(dòng)力學(xué)方程,首先忽略攝動(dòng)項(xiàng),采用可行解迭代方法,將攔截末端約束和交會(huì)角約束包含在目標(biāo)函數(shù)中,得到了含有約束處理項(xiàng)的燃料優(yōu)化問(wèn)題。對(duì)布谷鳥(niǎo)算法進(jìn)行改進(jìn),利用該算法搜索得到該優(yōu)化問(wèn)題的全局解初值。再使用非線性規(guī)劃算法優(yōu)化的到燃料最優(yōu)時(shí)的脈沖矢量。通過(guò)仿真驗(yàn)證了修改的布谷鳥(niǎo)算法的有效性。針對(duì)J2項(xiàng)攝動(dòng)作用下攔截衛(wèi)星和目標(biāo)都采用連續(xù)小推力機(jī)動(dòng)時(shí)的雙邊最優(yōu)控制問(wèn)題,建立含有J2項(xiàng)攝動(dòng)時(shí)大地坐標(biāo)系下空間飛行器的動(dòng)力學(xué)方程,基于哈密頓函數(shù)得到了微分對(duì)策鞍點(diǎn)解時(shí)兩星的最優(yōu)控制輸出。將雙邊最優(yōu)控制問(wèn)題轉(zhuǎn)化為兩點(diǎn)邊值問(wèn)題。針對(duì)該情況下兩點(diǎn)邊值的多解性和初值難以獲取問(wèn)題,采用啟發(fā)式算法和非線性規(guī)劃算法混合求解的方法獲得精確解。對(duì)于控制角受限的情況,從二維平面攔截入手,得到了兩星的最優(yōu)推力角,并在三維情況中,利用幾何方法得到了此時(shí)鞍點(diǎn)解對(duì)應(yīng)的控制策略。仿真說(shuō)明了該方法可以解決該類問(wèn)題。在攔截末段我方衛(wèi)星和目標(biāo)同時(shí)機(jī)動(dòng)時(shí)的追蹤逃逸問(wèn)題中,基于虛擬軌道給出了末端攔截的軌道方程。采用微分對(duì)策理論研究了攔截逃逸過(guò)程中雙邊最優(yōu)的控制策略。對(duì)于無(wú)限時(shí)間攔截逃逸問(wèn)題,將問(wèn)題轉(zhuǎn)化為代數(shù)黎卡提方程的求解,給出了兩星控制輸出不受幅值限制時(shí)的最優(yōu)反饋控制和受到幅值限制時(shí)的次優(yōu)控制策略。而針對(duì)有限時(shí)間控制問(wèn)題,研究得到推力幅值限制時(shí)的次優(yōu)反饋控制律。根據(jù)零控脫靶量導(dǎo)數(shù)與兩星的控制輸出的關(guān)系,得到最優(yōu)反饋控制律,給出了攔截衛(wèi)星減少燃料消耗時(shí)的反饋策略,仿真分析了上述方法的優(yōu)缺點(diǎn)。在零控脫靶量的基礎(chǔ)上,研究了多星合作時(shí)攔截衛(wèi)星多目標(biāo)函數(shù)反饋控制策略和單一目標(biāo)合作時(shí)的反饋控制策略。對(duì)于攔截防御場(chǎng)景,在考慮防御衛(wèi)星作用時(shí)間較短的情況下,構(gòu)造包含防御衛(wèi)星和目標(biāo)衛(wèi)星零控脫靶量的目標(biāo)函數(shù),利用極值條件得到反饋控制策略。通過(guò)分析防御衛(wèi)星的攻擊時(shí)間,利用幾何方法,得到了攔截衛(wèi)星對(duì)防御衛(wèi)星躲避的同時(shí)進(jìn)行目標(biāo)追蹤的最優(yōu)控制方法。仿真分析了合作攔截的可靠性,快速性和防御衛(wèi)星存在時(shí)攔截衛(wèi)星反饋控制策略的優(yōu)越性。
[Abstract]:At present, space technology develops rapidly and plays an important role in the national economy, life and military affairs. The research of space attack and defense technology is of great significance to the protection of national space resources. In this paper, an important way of space interception, orbit optimization and control of anti-satellite interception, is studied. The main contents are as follows: aiming at the problem of precise dynamics long-range multi-pulse interception, In this paper, the interception dynamics equation with various perturbation terms is established. Firstly, the perturbation term is ignored, and the intercept terminal constraint and intersection angle constraint are included in the objective function by using the feasible solution iteration method, and the fuel optimization problem with constraint processing term is obtained. The Cuckoo algorithm is improved and the initial global solution of the optimization problem is obtained by searching the algorithm. Then the nonlinear programming algorithm is used to optimize the pulse vector when the fuel is optimal. The validity of the modified Cuckoo algorithm is verified by simulation. Aiming at the bilateral optimal control problem of intercepting satellites and targets under the action of J2 perturbation, the dynamic equations of space vehicles in geodetic coordinate system with J2 perturbation are established. Based on Hamiltonian function, the optimal control output of two stars for saddle point solution of differential game is obtained. The two-sided optimal control problem is transformed into a two-point boundary value problem. In view of the multi-solution of two-point boundary value and the difficulty of obtaining initial value, the exact solution is obtained by combining heuristic algorithm and nonlinear programming algorithm. In the case of restricted control angle, the optimal thrust angle of two stars is obtained from two-dimensional plane interception, and the corresponding control strategy of saddle point solution is obtained by using geometric method in three-dimensional case. Simulation shows that this method can solve this kind of problem. In the problem of tracking and escaping during simultaneous maneuvering of our satellite and target at the end of interception, the orbit equation of terminal interception is given based on virtual orbit. In this paper, the differential game theory is used to study the bilateral optimal control strategy in the process of interception and escape. For the problem of infinite time interception and escape, the problem is transformed into the solution of algebraic Riccati equation, and the optimal feedback control and the suboptimal control strategy are given for the two-star control output without amplitude restriction. For the finite time control problem, the suboptimal feedback control law is obtained for the thrust amplitude limitation. According to the relation between the derivative of zero control miss distance and the control output of two stars, the optimal feedback control law is obtained, and the feedback strategy for intercepting satellite to reduce fuel consumption is given. The advantages and disadvantages of the above methods are analyzed by simulation. Based on the zero-control miss distance, the multi-objective function feedback control strategy and the feedback control strategy for multi-target cooperative interceptor satellite are studied. Considering the short time of defense satellites, the objective function including the zero control miss distance of defense satellite and target satellite is constructed, and the feedback control strategy is obtained by using extremum condition. By analyzing the attack time of the defense satellite and using the geometric method, the optimal control method for the interception satellite to evade the defense satellite and to track the target at the same time is obtained. The reliability, rapidity and superiority of feedback control strategy of cooperative interception are analyzed by simulation.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V412.41;V448.2

【參考文獻(xiàn)】

相關(guān)期刊論文 前2條

1 譚拂曉;劉德榮;關(guān)新平;羅斌;;基于微分對(duì)策理論的非線性控制回顧與展望[J];自動(dòng)化學(xué)報(bào);2014年01期

2 諶穎,黃文虎,倪茂林,王旭東,白拜爾;多沖量最優(yōu)交會(huì)的動(dòng)態(tài)規(guī)劃方法[J];宇航學(xué)報(bào);1993年02期

相關(guān)碩士學(xué)位論文 前1條

1 劉恒;天基反衛(wèi)飛行器軌道優(yōu)化設(shè)計(jì)與應(yīng)用研究[D];哈爾濱工業(yè)大學(xué);2008年

，

本文編號(hào)：2087025