flight trajectory 中文意思是什麼

flight trajectory 解釋
飛行軌跡
  • flight : n 1 飛行，飛翔；（鷹對獵物的）追趕。2 （候鳥等的）遷徙；飛行的一群。3 （光陰）飛逝。4 （思想等的...
  • trajectory : n （拋射體的）軌道，彈道；流軌；【幾】軌線。 a curved [direct fire flat highangle fire low] traje...
  1. 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。
  2. The doppler radar data processing of the first flight segment trajectory for the rocket - assisted and base bleed projectiles

    復合增程彈起始飛行段彈道測速數據處理方法
  3. Trajectory control algorithm is also presented to make the excursion of flight converge to zero in given limited time during flying. it is mainly used to control and reduce the excursion and crab angle within given limited time when the aerocraft is following the reference flight path

    然後本文提出了用於控制飛行器在跟蹤參考航跡過程中出現的航跡偏移和偏航角的航跡控制演算法，該演算法能有效地使航跡偏移量和偏航角在給定的時間約束內收斂。
  4. Article 86 the construction of a shooting range or other facilities that will possibly affect flight safety is prohibited within the area extending 30 kilometers from the edges of an air route, unless it is a shooting range for flat trajectory light weapon

    第八十六條在距離航路邊界三十公里以內的地帶，禁止修建靶場和其他可能影響飛行安全的設施；但是，平射輕武器靶場除外。
  5. Analyzing to a stand off missile ' s flight characteristics, the as missile trajectory simulation is completed

    在分析了典型防區外導彈飛行特點的基礎上，進行空地導彈彈道模擬。
  6. Firstly, the mathematical method, wavelet transform of random error processing and kalman filtering algorithm of system error estimation, is designated ; the process of development of wavelet transform and its present research is recommended ; and, the definition and development situation of real - time data processing and post - flight data processing of trajectory measurement data is summarized briefly

    首先指出了應用的數學方法，即處理隨機誤差的小波變換方法和估計系統誤差的kalman濾波演算法;介紹了小波變換方法的發展過程和國內外的研究現狀;綜述了彈道測量數據的實時數據處理和事後數據處理的概念和發展狀況。
  7. This design method overcomes the traditional autopilot ' s disadvantage that should shift the autopilot ' s gain according to flight phase ; it also can make the btt missile fly stably along the whole trajectory, and can intercept a maneuvering target accurately

    該設計方法克服了傳統自動駕駛儀在控制導彈飛行中需逐段切換增益的不足，能控制btt導彈在大空域內沿全彈道穩定飛行，並能精確攔截機動目標。
  8. According to purpose of the towed flight, a new trajectory consisting of taking off, climbing phase, level flight phase is presented with. trajectory pitch angle of the towing plane is optimized. according to the flight law of the towing plane, the fin deflection angle and amplification coefficient of particle - system trajectory of carrier rocket are designed, in order to realizing flight steadily of the carrier rocker

    根據牽引飛行的目的，對載機應用了「起飛?爬升?平飛」的變軌道飛行方案，同時對載機軌道的傾角、傾角變化規律進行優選設計；再根據載機的飛行規律，對運載器質點系軌道的舵偏規律及其放大系數進行了設計計算，實現運載器穩定牽引飛行。
  9. This paper presents a wider research field - risk analysis. through the study of the effects that threat factors and error factors impact on the flight risk and adjusting performance rules, the horizontal safe corridor, threat avoidance, vertical altitude real - time modification and the fastest trajectory programming are progressed

    總結前人在該方面的研究成果，提出一個更加廣義的研究角度? ?風險分析。通過對威脅因素、誤差因素對飛行風險的作用，調整性能準則而進行了水平安全走廊設計、威脅迴避、垂直離地高度實時修正以及最快速航跡規劃。
  10. Due to mission profile, launched conditions and trajectory, maneuver chains for stand off missile are designed. instruction control model and maneuver model is setup for ucav flight simulation

    結合作戰任務剖面、導彈發射條件和彈道，設計出無人機防區外攻擊導彈發射前、后的機動動作鏈。
  11. Use energy - based control method to achieve the entry flight control of reusable launch vehicle. the basic concept is to take the energy as primary control variables, reduce the order of the system and design a tracking law to follow a three - dimensional entry trajectory

    本文採用基於能量的控制方法實現對航天器再入軌跡的控制，將能量作為獨立參量，從而降低系統的階數，利用線性反饋的方法設計一個跟蹤三維再入軌跡的控制律。
  12. From then on it must coast in a trajectory, or flight path, to its target.

    從那時起，它就得沿著彈道，即沿著飛行航線滑向其目標。
  13. Then above the typical terrain and under the disturbance the terrain following system is simulated. the result shows the flight control system can withstand the disturbance and track the optimal trajectory

    在典型地形情況下進行地形跟隨模擬，並且為了真實模擬地形跟隨，在控制通道加入風擾動，結果表明該飛控系統能夠很好的抵抗風擾動，緊緊跟隨最優軌跡飛行。
  14. To the reference flight trajectory, the controller has good tracking ability and satisfies precision request

    模擬結果表明，對于飛行參考航跡，該軌跡跟蹤控制器具有很好軌跡跟蹤能力，滿足軌跡跟蹤精度的要求。
  15. A flight trajectory math model of an assumed cruise aircraft is built according to a simple blue print of the flight control system, with the foundation of a particular analysis of its kinematics and dynamics. a linear light - disturbed minor - cycled movement model and the transform function models are got through some simplifications

    本文以某個虛構的巡航式飛行器的飛行控制系統為研究對象，首先討論了一個簡單的總體方案，然後根據此方案，在詳細分析此飛行器運動學與動力學的基礎上，建立了飛行器飛行模擬數學模型，並在允許的條件下進行簡化得出了此飛行器線性化小擾動短周期運動模型與傳遞函數模擬模型。
  16. 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。
  17. The implement process using this method is given, and combined with the representative parameters at the entire missile flight trajectory, the control effect is analyzed by simulation, and the simulation result has demonstrated the method is valid

    給出了應用該方法的具體實現步驟，結合導彈飛行的全彈道典型特徵點參數，通過模擬實驗說明了設計方法的有效性。
  18. This thesis ’ research goal is carrying on the simulation using the view simulation technology to the missile launch process, so we can both simulate the missile ’ s flight trajectory and blast effect real time, and reappear the entire testing process after experiment

    本文的研究目的就是利用視景模擬技術對導彈的發射過程進行模擬，做到既可以實時地監控導彈的飛行狀態，又可以在試后直觀地重現整個試驗過程。
  19. 4. designing and realizing a missile testing and training view simulation system, that can simulate the flight trajectory real time and reappear the entire testing process after experiment. at last, this thesis provides the summarization of the work and the content of the future research

    4 、設計並實現了一個導彈試驗訓練視景模擬系統，既可以實時的模擬導彈的飛行狀態，又可以在試驗后直觀地重現整個試驗過程，便於分析試驗結果和數據。
  20. Abstract : two computational techniques for inverse fight dynamics, namely derivation - iteration and integration - iteration techniques, are investigated. the application of inverse dynamics to determine control power requirements for post - stall maneuvering is researched, and a maneuvering flight trajectory based algorithm is provided, which lays a numerical foundation for simplifying design criteria for post - stall aircraft. with the model of inverse dynamics employed, a flight control mode for the outermost loop of the control system, named maneuver generator, is designed to follow desired complicated maneuvering flight trajectories. an example of rapid heading - reversal maneuver and other numerical simulations show the feasibility of the algorithm and the design idea

    文摘:考察了求解輸入類飛行逆動力學問題的微分-迭代與積分-迭代演算法;探討了利用逆動力學確定過失速機動操縱效能要求問題，這構成了進一步提出過失速機動飛機設計簡化判據的數值基礎;利用逆動力學設計機動發生模塊進行飛控系統的最外環控制，以便跟蹤期望的復雜機動軌跡.飛機最速反向示例及其它數值模擬結果表明設計思想與演算法是可行的
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