rocket trajectory 中文意思是什麼

rocket trajectory 解釋
火箭彈道
  • rocket : n 火箭;火箭彈,火箭發動機;火箭式投射器;〈英俚〉斥責。 a carrier [freight] rocket 載運火箭。 an...
  • 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. As we all known, the ballistic trajectory is a pilotless missile, which loads rocket engine and control system, these will drop the missile to the target along its ballistic

    眾所周知,彈道導彈是一種無人駕駛的飛行器,它裝有火箭發動機和控制系統,其目的是把導彈沿一定的彈道送到目標區。
  2. Trajectory characteristics of hypersonic waverider missile with rocket extended range

    火箭增程乘波外形導彈彈道特性研究
  3. In this thesis, based on pershing ii surface to surface missile, a new kind of ballistic missile was designed with an additional rocket engine, which can be ignited twice. firstly, aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly, the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine. the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly, the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally, the ability of a missile ' s breaking through defence is analyzed

    以美國潘興導彈為原型,增加可兩次點火的末級發動機,改裝成具有跳躍能力的地地彈道導彈;首先,根據任務需求,建立了導彈的氣動模型,並建立了彈頭再入時高超聲速氣動模型;其次,建立了導彈推進系統模型,前兩級採用了固體火箭發動機,第三級採用了固?液組合火箭發動機,並在總體方案要求下,對發動機噴管和外形進行了設計;第三部分,建立了導彈質點彈道模型,設計了一條跳躍式彈道,並對跳躍式彈道進行了優化設計;最後,對導彈進行了突防能力分析,從分析的結果可以看出,跳躍式彈道的突防能力比常規的拋物線彈道要強。
  4. 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
  5. 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。
  6. In order to study on fire efficiency for the rocket - assisted torpedo, this paper has gone deeply into every stages of air trajectory and underwater trajectory, and established the fire efficiency model of the rocket - assisted torpedo with the monte - carlo

    摘要為解決火箭助飛魚雷的作戰使用問題,需要確定它對隨機機動目標的射擊效率,通過對該雷空中及水下彈道的各階段深入細致的分析研究,建立了火箭助飛魚雷射擊效率模擬模型。
  7. 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
  8. The child system of calculation analysis includes the optimization design of total parameters of solid rocket motor, the calculation of internal trajectory, the calculation of thermodynamic parameters, the limited element analysis for stress of motor shell, the calculation of structure characteristic parameters, the calculation of particle external trajectory, the design and calculation of the ignition device

    計算分析子系統包括火箭發動機總體優化設計、內彈道計算、熱力參數計算、發動機殼體應力有限元分析、結構特徵值計算、質點外彈道計算、點火裝置的設計計算。
  9. And the effect of the work order of the two propellant units to the performance of the trajectory and the matching conditions to obtain the theoretical optimum trajectory is discussed too. according to the ballistic speciality of a hybrid base - bleed - rocket extended - range projectile during base - bleed and rocket work, its physical parameter is non - constant, such as its mass position of mass centre polar and equatorial moment of inertia. after a mulriple ballistic model of constant physical parameter is established, a mulriple ballistic model of continuous and non - continuous physical parameter is educed and the program is compiled, the theoretical tool is constructed to study othe other pivotal technology of a hybrid base - bleed - rocket extended - range projectile

    本文根據底排?火箭復合增程彈其底排燃減阻和火箭助推階段的質量、質心位置、轉動慣量等結構特徵參量變化的彈道特徵,在建立底排?火箭復合增程彈結構特徵參量為不變常量的多元彈道計算模型基礎上,導出了結構特徵參量為連續變化量和非連續變化量的底排?火箭復合增程彈多元彈道計算模型,編制了相應的計算機數值分析程序,構建了研究底排?火箭復合增程彈其它關鍵技術的理論工具。
  10. Design of two propulsion systems is studied - solid rocket ramjet and liquid ramjet. the performance analysis models and design methods are set up for these two kinds of engines. the different characteristics are analyzed and compared, which provide basis for farther trajectory computation and conceptual optimization design

    ( 4 )研究了兩種動力裝置? ?固體火箭沖壓發動機和液體燃料沖壓發動機的設計問題,建立了兩種發動機的性能分析模型和計算方法,對固體火箭沖壓發動機和液體燃料沖壓發動機的特性進行計算分析及比較,為彈道計算及總體優化設計提供依據。
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