trajectory guidance 中文意思是什麼
trajectory guidance
解釋
彈道制導- trajectory : n （拋射體的）軌道，彈道；流軌；【幾】軌線。 a curved [direct fire flat highangle fire low] traje...
- guidance : n. 1. 向導，指引，指導。2. 導航；制導。3. 【機械工程】導槽，導板，導管。
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The guidance scheme includes a trajectory planner that generates a feasible flight trajectory and a control law that achieves bounded tracking of the downrange and crossrange distances as functions of energy
其中，軌跡規劃器可產生一個可行的飛行軌跡。控制律作為能量的函數可實現再入段對縱向和橫向航程的有界跟蹤。 -
It is generally impossible to obtain the analytic optimal guidance law for complex nonlinear guidance systems of homing missiles, and the open loop optimal guidance law is often obtained by numerical methods, which can not be used directly in practice. the neural networks are trained off - line using the optimal trajectory of the missile produced by the numerical open loop optimal guidance law, and then, the converged neural networks are used on - line as the feedback optimal guidance law in real - time. the research shows that different selections of the neural networks inputs, such as the system state variables or the rate of los ( line of sight ), may have great effect on the performances of the guidance systems for homing missiles. the robustness for several guidance laws is investigated by simulations, and the modular neural networks architectures are used to increase the approximating and generalizing abilities in the large state space. some useful conclusions are obtained by simulation results
對于復雜的非線性導彈制導系統，很難求得其解析的最優制導律，只能求得開環的數字解，不能適用於具有時變不確定性的導彈制導系統.利用神經網路的學習和推廣能力，對開環的數字最優制導律進行離線的學習，作為閉環的神經最優制導律在線應用.研究分別選擇系統狀態變量和視線角速率等不同的神經網路輸入對制導系統性能的影響，以及各種制導律的魯棒性問題，並採用模塊化神經網路結構提高神經網路的學習和推廣能力，模擬結果得到一些有益的結論 -
In the end of this thesis, on the basis of the mathematical model, three segments of trajectory : the vertical turn, the pn guidance and the direct lateral force control in terminal trajectory are simulated. the results show that with the direct lateral force control reduces in terminal trajectory, the miss - distance is reduced and the precision is improved
4 、論文最後根據前面建立的數學模型，對防空導彈垂直轉彎段、比例導引段以及末端直接力控制段進行了模擬計算，結果表明進行末端直接側向力控制可以有效減小攔截目標時的脫靶量，提高命中精度。 -
The saturn guidance and control systems are designed to provide the proper trajectory and attitude orientation for the vehicle over a range of expected missions.
土星的導引和控制系統的設計能使飛行器在規定的任務范圍內提供合適的彈道和姿態方位。 -
As far as the system observation for accuracy evaluation of carrier rocket is concerned, there may exist different types of observed data and priors. heterogeneous information means that the different information describing the different characteristics of the same object. since all of the information is relevant to the same object, the fusion is possible. it is a key problem that how to fuse the heterogeneous information to obtain the better evaluation result. therefore, the different heterogeneous information and data is thoroughly studied, moreover, the mathematical description for information fusion of different parameter priors and data is constructed in this paper. based on their relationship between different parameters, indirect prior and observation data is transformed into prior in impact point observation space, which is fused with original prior by weight determined by maximum entropy rule to obtain the mixed posterior distribution. therefore, the test results can be given by combining posterior distribution and impact error observed data. then its application on evaluating guidance systematic error is elaborated as it applies trajectory tracking data, test value of coefficients of guidance instrumentation systematic error, impact point observation data and prior. especially, the advantage of this method lies in its application in case that guidance instrumentation systematic error may not be computed precisely. finally a detailed example on evaluation of carrier rocket is given to verify the theory
為充分利用運載火箭觀測中的不同觀測空間和過程的信息來進行精度評估，針對該背景建立了異質先驗融合的數學描述.研究了飛行試驗中不同觀測空間和過程的異質先驗信息和數據，基於不同觀測過程的解析關系，將間接過程的先驗和觀測數據算出的后驗分佈轉換成落點觀測空間上的先驗，與原落點的先驗進行了最大熵加權融合，得到混合后驗分佈，從而結合落點觀測數據給出評定結果.在無法解算出精確的制導工具誤差系數的情況下，這種方法充分利用了彈道跟蹤數據、工具誤差系數的地面測試先驗值、落點先驗及落點數據，穩健性更好，準確性更高 -
Numerical simulation on the gas - solid multiphase flow in new type pulverized coal impact rich / lean burner is presented in it. under the guidance of the theory of computer aid test ( cat ), the dissertation uses particle - particle random impact model and the fluctuating - spectrum - random - trajectory ( fsrt ) model to simulate the gas phase flow and the particle phase flow based on the lagrange approach, compared with experimental results, and reaches satisfied efforts
在cat計算機輔助試驗理論的指導下，結合實驗研究，本文採用包括脈動頻譜隨機軌道（ fsrt ）模型、顆粒和顆粒的隨機碰撞模型等先進的氣固多相流模型，在高濃度氣固多相流動數值模擬這一前沿研究方面得到了很有價值的結果。 -
In this paper. the question of compound guidance about mid - long range air - to - air missle to be considered. the main contributions are as follows : first, two midcourse guidance laws are given. that is optimally predictable pn micourse guidance, which is suitable for middle range missle, and singularly perturbed midcourse guidance. which is suitable for long range missle guidance ; then two terminal guidance laws are given. that is variable structure guidance, which is suitable for passive radar guidance. and optimal guidance which is suitable for active radar guidance ; and then the error sourses of hand - off are researched, the hand - off law is given at the time ; fmally, the midcourse guidance laws and terminal guidance laws are tested by simulation, and the whole trajectory simulation are given through hand - off law, and the results are satisfied
主要工作如下：首先研究了用於中遠程空空導彈復合制導的兩種中制導律，即用於中程導彈的最優預測比例導引中制導律和用於遠程導彈的奇異攝動中制導律，它們均有很好的中制導性能，能夠滿足中末制導的交班要求；接著研究了兩種末制導律，即用於被動雷達末制導的變結構制導律和用於主動雷達導引頭的最優末制導律，均適用於復合制導末制導段；然後分析了中末制導的交班誤差源，討論了用於復合制導的交接律；最後通過模擬，驗證了提出的中制導律和末制導律，結合提出的交接規律，在不同的情況下對中末制導段彈道進行了模擬驗證，結果證明文中提到的中末制導律能夠達到性能指標要求。 -
The characteristics of the method is that it can modify the guidance coefficients automatically according to the errors between the actual trajectory and the standard trajectory, this is the essential of the standard trajectory guidance. it don " t need any pre - knowledge of the coefficients, this simplifies the problem greatly. following that, the method of predicting the falling site of the instant retuning trajectory is studied
這一方法的特點是從反饋增益系數對再入段縱程偏差修正的本質出發，利用實際彈道和標準彈道的偏差，通過調節升阻比增量，不斷修正再入段縱程偏差，最終確定反饋增益系數；這一方法的優點是在求解反饋增益系數時，不必依賴先驗知識選取初值，使反饋增益系數的確定更為簡便。 -
2. the control system has designed in this paper. and it includes two way : the schema trajectory and the proportion guidance
設計了採用標稱彈道和比例導引兩種導引率的質心控制迴路； 3 -
The main works of this thesis are research of lateral force control and guidance of interceptors, emphasized on the terminal phase when intercepting the tactical ballistic missiles, including the performance analysis of extra - atmospheric kinetic - kill vehicle piloted by trajectory - control and attitude - control systems, and combined control of aerodynamics with lateral jets in atmosphere
本文主要研究攔截彈在攔截戰術彈道導彈時，末段的制導和側向力控制問題，包括大氣層外動能攔截器在姿控與軌控發動機作用下的性能分析，和大氣層內側向力與氣動力復合控制研究。 -
The main work and achievements are described as follows : ( 1 ) the analysis of the extra - atmospheric kinetic - kill vehicle at first, the motion model and dynamics model of the kinetic - kill vehicle is constructed, and the thrust performance of trajectory - control system and attitude - control system are presented, then the algorithms of realizing the guidance law, the methods of trajectory and attitude control are studied
研究內容及成果主要表現在以下幾個方面： （一）大氣層外動能攔截器分析首先建立了動能攔截器運動學和動力學模型，以及軌控發動機和姿控發動機的推力模型，提出了攔截導引律的實現方法及軌控和姿控發動機的控制規律。 -
In the new guidance scheme, the flight trajectory restrained by a function of energy is tracked by commanding both the angle of attack and angle of bank
控制攻角和傾斜角，用來跟蹤一由能量函數界定的飛行軌跡。該控制方案包括一個軌跡規劃器和一個控制律。 -
Then on the base of the computer model, the standard reentry trajectory guidance law is studied, and an approach to obtain the guidance coefficients by modifying the initial value through feedback bias repeatedly is put forward. simulations have proved the feasibility of the method
在這個基礎上，本文對飛船再入標準軌道制導方法進行了研究，提出了一種利用制導參數偏差迭代求解反饋增益系數的方法，並通過大量模擬驗證了此方法的可行性。 -
First, the maximum principle is used to generate an optimal guidance law for lunar landing, and the tpbvp is to be solved as a result of the numerical solution for optimal trajectory
文中首先應用極大值原理設計了最優著陸制導控制律，此時求解最優軌跡變成一個兩點邊值問題（ tpbvp ） 。
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