missile attitude 中文意思是什麼
missile attitude
解釋
導彈姿態-
Omnidirectional quaternion algorithm and missile attitude control based on backstepping method in quaternion
基於四元數的導彈反步控制及全方位演算法應用 -
The missile is demanded for turning to necessary attitude from initial one in given time and its final speed becomes maximum
要求在給定的時間內使導彈由初始姿態轉到所要求的姿態，並使導彈終端速度最大。 -
( 2 ) to evaluate the effects of a reaction control jet on the aerodynamic performance of a missile operating at supersonic / hypersonic flight condition, the single and two attitude jet - interaction flow between a lateral jet and the external flow has been analyzed by detailed numerical simulation
（ 2 ）分別計算了單噴流和雙噴流干擾流場。詳細分析了流場結構和彈體表面壓力分佈特性，獲得了一些有實用價值的結果。 -
Study on attitude stabilization method of maneuver missile head
機動彈頭姿態解耦控制方法研究 -
To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation
為了解決攔截彈氣動參數隨飛行高度、速度、姿態的不同，變化范圍大，控制系統難以準確建模的困難，基於縱向平面攔截彈模型，採用模型參考變結構控制理論設計了俯仰通道姿控復合控制系統，以可測量變量過載和角速度作為狀態量建立了系統的狀態方程，討論了參考模型的選擇方法，並對系統的性能作了模擬分析。 -
Missile rudders are executive bodies of missile flight control system, all kinds of attitude motion of missile are depended on the actuator driver fins of rudders
導彈舵機是導彈飛行控制系統的執行機構，導彈的各種姿態運動都是靠舵機帶動舵面偏轉來實現的。 -
According to flight dynamics, a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established, the influence imposed by constant wind, thrust bias of the motor and connection bias are analyzed
應用飛行動力學理論，建立了發射坐標系與準彈體系下助推段和分離過程質點運動和姿態動力學模型，分析常風干擾、發動機推力偏差和裝配誤差影響等。 -
3 ) we research the attitude character of the radar target in the midcourse, analyse the rotation of the target in the midcourse on the basis of the attitude dynamics of space target. with the data of the trajectory in the midcourse, we calculate attitude parameter of the ballistic missile
在空間目標姿態動力學的基礎上分析中段目標的進動，結合中段軌道數據，給出了中段彈道導彈的姿態參數（目標雷達視線角）的計算結果。 -
At present, the most effective method of destroying the warhead of btm is the technology of directly hit kinetic kill, which can achieve precision control to the missile by adding the trajectory - control jet or attitude - control jet
目前對付來襲tbm彈頭最有效的手段就是採用直接碰撞動能殺傷技術。它是通過在導彈上安裝響應快速的雙組元軌、姿控發動機以實現對導彈的精確控制。 -
This paper provides a powerful method for the compatibility design of aircraft with external store, a missile, by calculating fast, conveniently and effectively the relative trajectory and relative attitude of the store with respect to aircraft during the separation process
此外，為了有效擊中目標，需要掌握投放初始階段外掛物姿態和運動軌跡數據。因此，研究機載發射過程中的彈機氣動干擾力，考慮其對導彈發射后的彈道模擬初始參數的影響十分必要。 -
Algorithm research of the early - warning satellite attitude control under the payload disturbance is a critical technology of ballistic missile early - warning system
預警衛星在其有效載荷干擾作用下的姿態控制演算法研究是彈道導彈預警系統的一項關鍵技術。 -
Lateral jet control technology is researched in this dissertation, based on supersonic / hypersonic missile aerodynamics and lateral jet interaction ( ji ) effects associated with the attitude control solid - propellant rocket motors system in the low endoatmospheric range
橫向噴流干擾效應研究在超聲速高超聲速導彈總體設計和精確制導技術研究領域一直佔有重要地位。本論文針對大氣層內超聲速高超聲速導彈採用姿態固體火箭發動機側噴流控制技術的一些問題進行了研究。 -
The motion model and dynamics model of the rolling missile was constructed, and the thrust performance of attitude control system were presented
建立了滾轉導彈運動學和動力學模型，以及姿控發動機的推力模型。 -
And then based on a surface - to - air missile that satisfies the requisition nearly, by means of reconstructing its geometry size, subsystems such as engine, the interceptor model used to continue the following studies is established. then the trajectory - control jet or attitude - control jet is added to the interceptor based on the analysis of the relationship between the missile performance and the thrust and configuration of the side jet
然後以基本滿足方案要求的某型防空導彈為基礎，對其幾何尺寸、發動機等分系統進行改進，並通過分析導彈性能與側噴發動機參數之間的關系，增加了姿控或軌控側向裝置，這樣得到了本文的研究工作所需的導彈模型。 -
Analysis on strength of the orbit and attitude control section body for missile
導彈軌姿控艙體的強度分析 -
Several forces are discussed to show the effect on stability. attitude feedback control stability is analyzed based on the close loop stability criterion, which gave a reference for attitude control system design of spinning ballistic missile
本文圍繞彈道導彈自旋飛行的幾個動力學與控制問題，進行了比較系統深入的研究，獲得了若干有意義的結論。 -
The thesis tracks the research about the intercept technology oversea. the rolling missile model with attitude - control - system is established by referring to the figuration dimension of pac - 3
本文跟蹤國外研究，以「愛國者? 3 」導彈外形尺寸為參考建立了具有姿態控制系統的滾轉導彈模型。 -
6. utilizing the new robust decoupling control method which is put forward above, the design problem of decoupling controller for large angle of attack reentry missile ' s attitude control system is mainly investigated
6 、針對大攻角再入飛行導彈通道間存在的氣動耦合現象，以及實際飛行中存在的個確定因素，分析了其進行解耦控制的必要性；探討了本文提出的基於互補靈敏度成形和h 。 -
C. based on a lot of referenced documents and tunnel experiment data, the phenomenon of lateral jet interception are analyzed, and the diagrams of the interaction factor " kcn " is presented. following, the airdefence missile model, trajectory model including attitude - control direct lateral force are constructed
3 、根據大量參考文獻和試驗數據，分析了側向噴流的干擾特性，並給出不同狀況下干擾因子k _ （ cn ）的變化曲線，在上述工作的基礎上，建立了帶有姿控側向力裝置的防空導彈模型和彈道計算模型。 -
Also, the attitude algorithm of the strapdown inertial system of shipboard missile is investigated. on the basis of analysis the sins error model, computer simulation of the sins error are given in accordance with the stochastic error of the inertial instruments
此外，還對艦船捷聯姿態演算法進行了研究，並在分析捷聯系統誤差模型的基礎上，針對慣性元件的隨機誤差給出了捷聯系統的誤差模擬。
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