本文選題：改進布谷鳥算法 + 微分對策��； 參考：《哈爾濱工業(yè)大學》2015年碩士論文

【摘要】：當前空間技術(shù)發(fā)展迅速,并在國民的經(jīng)濟,生活和軍事中扮演著重要角色,空間攻防技術(shù)的研究對國家空間資源的保護具有重要意義。本文對空間攔截中的一種重要方式,反衛(wèi)星攔截的軌道優(yōu)化和控制進行了研究,主要內(nèi)容包括以下幾點:針對精確動力學遠程多脈沖攔截問題,建立了含有多種攝動項的攔截動力學方程,首先忽略攝動項,采用可行解迭代方法,將攔截末端約束和交會角約束包含在目標函數(shù)中,得到了含有約束處理項的燃料優(yōu)化問題。對布谷鳥算法進行改進,利用該算法搜索得到該優(yōu)化問題的全局解初值。再使用非線性規(guī)劃算法優(yōu)化的到燃料最優(yōu)時的脈沖矢量。通過仿真驗證了修改的布谷鳥算法的有效性。針對J2項攝動作用下攔截衛(wèi)星和目標都采用連續(xù)小推力機動時的雙邊最優(yōu)控制問題,建立含有J2項攝動時大地坐標系下空間飛行器的動力學方程,基于哈密頓函數(shù)得到了微分對策鞍點解時兩星的最優(yōu)控制輸出。將雙邊最優(yōu)控制問題轉(zhuǎn)化為兩點邊值問題。針對該情況下兩點邊值的多解性和初值難以獲取問題,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鞍點解對應的控制策略。仿真說明了該方法可以解決該類問題。在攔截末段我方衛(wèi)星和目標同時機動時的追蹤逃逸問題中,基于虛擬軌道給出了末端攔截的軌道方程。采用微分對策理論研究了攔截逃逸過程中雙邊最優(yōu)的控制策略。對于無限時間攔截逃逸問題,將問題轉(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的最優(yōu)反饋控制和受到幅值限制時的次優(yōu)控制策略。而針對有限時間控制問題,研究得到推力幅值限制時的次優(yōu)反饋控制律。根據(jù)零控脫靶量導數(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)星減少燃料消耗時的反饋策略,仿真分析了上述方法的優(yōu)缺點。在零控脫靶量的基礎(chǔ)上,研究了多星合作時攔截衛(wèi)星多目標函數(shù)反饋控制策略和單一目標合作時的反饋控制策略。對于攔截防御場景,在考慮防御衛(wèi)星作用時間較短的情況下,構(gòu)造包含防御衛(wèi)星和目標衛(wèi)星零控脫靶量的目標函數(shù),利用極值條件得到反饋控制策略。通過分析防御衛(wèi)星的攻擊時間,利用幾何方法,得到了攔截衛(wèi)星對防御衛(wèi)星躲避的同時進行目標追蹤的最優(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.
【學位授予單位】：哈爾濱工業(yè)大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V412.41;V448.2

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本文編號：2087025