attitude angle 中文意思是什麼
attitude angle
解釋
側滑角-
( 3 ) for a symmetrical distribution scene, the attitude information of the terrains is included in the variable of the orientation angle of the polarization ellipticity
Cd對於一個均勻分仆場景，地勢的姿態信息調制在極化橢圓力下0角的變化量中。 -
This dissertation is dedicated to the algorithm research of image registration applied to navigation. information such as attitude angle of aircraft is used to emendate the large - geometry - distorted image, so the research of this dissertation is based on the hypothesis that images used have small geometry distortion
針對圖像匹配在導航中的應用，提出了對于存在大的幾何失真的圖像利用飛行器本身信息進行幾何校正的方法，所以本文演算法的研究都是基於小的幾何失真這一假設的。 -
The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km. the three - ramp, mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed. nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given
根據飛行任務要求，以飛行馬赫數6 ，飛行高度25km為設計點，給定前體預壓縮角、隔離段高度，對具有不同前體長度和不同總壓縮轉角的帶隔離段的前體進氣道進行了設計。 -
Since the varies of gun attitude angle and the vertical vector of the homograph plane are one - to - one, all the elements of modulation gun can be transformed into the calculation of the vertical vector angle, which avoids the calculation accuracy loss of the traditional approach under the condition of the tiny attitude angle disturbance
由於火炮姿態角變化與相應平面的法向量是一一對應的，從而可將調炮諸元轉化為法向量夾角來計算，這樣可避免傳統方案在微小姿態角擾動情形下導致的計算精度可能的損失。 -
Because of the change of ship attitude ( rolling angle r, pitch angle p and course angle h ) led by ship rocked interference and windage, the los stabilization will be influenced obviously
由於艦船的艏搖、縱搖、橫搖等引起艦船姿態的變化以及風阻力矩的作用，對跟蹤系統的視軸穩定性產生明顯影響。 -
The experimental results show that the wave shaper can control the moving direction of the rod fragments after the warheads exploded and ensure the integrity rate of the rod and that there is a close relationship between the flight attitude and the positioned angle, which is mainly reflected by the rotation velocity of the rod
試驗結果表明：採用波形控制器可以較好地控制戰斗部爆炸后桿形破片的飛散方向，以及保證桿條的完整率；桿條的飛行姿態與放置角有密切關系，主要通過桿條旋轉速度表現出來。 -
The results of simulation given in this paper indicate that the sins / dtu can effectively improve on the following navigation parameters : velocity, latitude and longitude, yawing and attitude angle, position of track - reckoning etc
模擬結果表明，該組合導航系統可有效地減小速率、經度和緯度、航向角和姿態角及航跡推算下的位置等導航參數的累積誤差。 -
When the signal of gps is lost for five minutes, the position error is about 1400 meters, its velocity error is about 15m / s and its attitude angle error is about 10 degree
在gps信號丟失5分鐘時，位置誤差大約為1400米，速度誤差大約為15米/秒，姿態角誤差大約為10度。 -
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。 -
A multiloop antenna pointing controller has been designed while three feedforward schemes are used in this control design. the simulation results show that the antenna pointing control system can improve the precision of the attitude angle and the attitude angle rate, and the antenna can slew to the neighborhood of tdrs fast, search and then track tdrs
在設計好的天線跟蹤指向控制系統基礎上，採用前饋+反饋的復合控制策略設計了復合控制器，模擬結果表明設計的天線指向控制系統能夠較好的提高星體的姿態穩定度和控制精度，天線能夠快速回掃至中繼衛星附近並進行跟蹤，天線指向精度滿足設計要求，表明了所設計的天線指向控制系統的合理性和有效性。 -
In this dissertation the control loop of attitude angle and collective piston loop are separately. the controller is designed at two scales. and the simulation shows the uncoupling of three attitudes angle loop is achieved with dynamic inversion scheme
在姿態角通道的設計中，採用了動態逆思想，按照時標分離的原則將直升機飛控系統劃分為快慢迴路，並採用動態逆方法對飛行控制系統進行設計和模擬，模擬結果表明動態逆在通道解耦方面非常有效。 -
The mathematical model of attitude solving algorithm on high dynamic aircraft was established, and the method which used rotation vector algorithm to solve attitude angle was discussed, and the method was compared with quaternion
摘要建立了高動態飛行器姿態解算的數學模型，探討了利用等效旋轉矢量法解算姿態角的方法，並與四元數法進行了比較。 -
The results indicate that : with sa, the position precision of the integrated system, whose gyro drifting is 50 degree / hour and whose accelerator offset is 0. 001g, is 60 meters, its velocity precision is about 1. 75m / s out and its attitude angle precision is about 0. 25 degree. without sa, the position precision is about 20 meters, its velocity precision is about 0. 5m / s and its attitude angle precision is about 0. 1 degree. when the signal of gps is lost, the growing rate of the integrated system error is much lower than that of sins system
模擬結果表明：對于陀螺漂移為50度/小時、加速度計零偏為0 . 001g的組合系統，在有sa的情況下，位置精度大約為60米，速度精度大約為1 . 75米/秒，姿態角精度大約為0 . 25度；在無sa的情況下，位置精度大約為20米，速度精度大約為0 . 5米/秒，姿態角精度大約為0 . 1度；在gps信號丟失時，系統誤差的增長速度比純sins系統明顯減緩。 -
Finally, the motion stability of the flexible deployable truss mentioned before was analyzed. according to the definition of motion stability, the simulation results under the conditions of different initial attitude angle velocities and pulse torque function indicate that the deployment motion of flexible truss under these initial distortions was steady. the drive angle velocity of deployment
根據無擾運動的穩定性定義，通過對衛星在不同初始姿態角速度下及受到力矩脈沖作用下展開時衛星的姿態角速度的影響的比較，說明在這兩種初始擾動下桁架的展開運動的穩定性情況;對不同驅動角速度下桁架展開的模擬結果比較得到該桁架的失穩條件。 -
At the end of the dissertation, the fuzzy pd track tail controller is designed. the pd controller and controller of attitude angle are made up of flight control system of helicopter
最後，本文設計了直升機模糊pd軌跡跟蹤控制器，與姿態角控制器相結合，完成了對整個飛行控制系統的設計。 -
Finally, the trajectory tracking controller based on cm ac and pid parallel control is designed, which is combined with attitude angle controller and complete whole flight controller system
本文最後設計了基於小腦模型神經網路（ cmac ）和pid并行控制的軌跡跟蹤控制器，與姿態角控制器相結合，完成直升機整個飛行控制系統的設計。 -
The control loop of attitude angle is designed with dynamic inversion method, and is divided into fast loop and slow loop at two time scales. in the end, the result of simulation showed that the three channels of attitude angle are discoupled by dynamic inversion method
在姿態角通道的設計中，採用動態逆思想，按照時標分離的原則將直升機飛控系統劃分為快慢迴路，並分別採用動態逆的方法進行設計，最後通過模擬得以證明直升機的三個姿態角通道得到有效的解耦。 -
The rigid and flexible trusses were simulated respectively. the dependences of the attitude angle degree and angle velocity of the spacecraft on the rigid and flexible situation in the deployment process and drive velocities loaded on the joints were derived. the frequency - amplitude characteristic curves were gained from the attitude angle velocity curves of the deployment of the flexible truss and locked flexible truss after deployment through the fast fourier transition ( fft ) method
文中給出了展開前後的動力學固有特性;對展開過程中分別為剛性桁架和柔性桁架兩種情況進行了模擬計算，對比了兩種情況的桁架展開過程中衛星姿態角及姿態角速度的變化;比較了柔性桁架不同展開速度對衛星姿態角及姿態角速度的影響;分析了柔性桁架展開過程對衛星非展開方向的姿態角度及角速度的影響及原因;對柔性桁架展開過程中及展開鎖定后的衛星姿態角速度的變化曲線進行快速傅立葉變換，得到柔性桁架展開過程即展開鎖定后衛星姿態角速度的頻幅特性曲線。 -
This paper studied zero - velocity correct technology for ins, based on analysis of ins error equation, it concluded the method by which we can use ins velocity output to estimate the attitude angle error when the vehicle halted, then it contrasted two schemes of conic approximation of attitude angle error and put forward a method to decide the approximation coefficient by time range
本文首先研究了車載捷聯慣導系統（ ins ）的零速修正技術，在分析捷聯慣導系統誤差方程特點的基礎上，推導了停車時利用ins速度輸出估計姿態誤差角的方法，並對用二次曲線擬合姿態誤差角的兩種方案作了比較，提出了按時間分段確定擬合系數的方法。 -
By comparing the ideal joint and clearance joint for the deployment process of a spatial deployable truss structure in multibody dynamics, it is found that the existence of the joint clearance makes the movement discontinuous, and also found the attitude angle degree and angle velocity of the spacecraft are affected in the deployment for the joint clearance
通過對有無鉸接間隙的剛性空間展開桁架模型的計算結果比較，說明鉸接間隙的存在對于桁架展開過程的影響及這一過程對衛星的姿態角速度的影響，同時比較了有無鉸接間隙時鉸接處在展開過程中接觸力的變化。
分享友人