angular rate造句
例句与造句
- Sensor , piezoelectric , angular rate general specification for
压电角速率传感器总规范 - Barb british angular rate bombsight
英国角速度轰炸瞄准器 - When there is an angular rate input , the fluid will deflect by the effect of coriolis acceleration
当有角速度输入时，射流束在哥氏力的作用下发生偏转，偏转的大小和方向取决于输入角速度。 - A piezoelectric fluidic angular rate sensor ( pears ) is a kind of flow sensor . in this thesis peats were researched
Cjsys - a5型压电射流角速度传感器（以下简称压电射流角速度传感器）属于气流式传感器，本学位论文对压电射流角速度传感器进行了研究。 - Calibration results indicate that this angular rate gyro has good linearity with correlation coefficient of 0 . 9996 , and high precision with standard error of 0 . 0036
标定结果表明，该角速率陀螺线性度好，相关系数为0 . 9996 ；精度高，标准误差为0 . 0036 。 - It's difficult to find angular rate in a sentence. 用angular rate造句挺难的
- Neural network has the ability of approaching nonlinear function at random precision , so that correct non - linear errors of angular rate sensor on the basis of neural network method
神经网络具有理论上以任意精度逼近非线性函数的能力，故本文采用基于神经网络方法来校正角速度传感器的非线性误差。 - Both results show that the inertial coupling of the platform to infrared camera scanning mirror , to evaluate mirror motion , is negligible and so the mirror can perform scans of the earth at the specified angular rate
两方面的仿真分析表明:星体姿态运动干扰力矩对红外相机扫描镜转动影响很小,红外相机扫描镜能够按设计转速正常运行。 - This paper developed a micro angular rate gyro based on micro piezoelectric ceramic rod structure instead of the sensitive double - deck structure as well as piezoelectric ceramic strain foils , and designed a phase - sensitive detection circuit
摘要研制了基于微型压电陶瓷棒结构代替双敏感梁结构及压电陶瓷片的微型角速率陀螺，并设计了相敏检波电路。 - Based on the mathematical model developed by the paper , the trim calculations are carried out in the conditions that the example aircraft converts from helicopter to airplane mode in level flight with zero longitudinal acceleration and angular rate
本文依据所建立的样例机纵向动力学模型,假定飞机在给定高度平飞,纵向加速度和角加速度均为零,完成过渡模式下的动力学配平。 - Trough the analysis of the output of the detecting circuit of the capacitances , the processing circuit is designed , and the angular rate is separated : parameters computed of the gyroscope and the performance analyzed of the circuit show that the circuit can reach the base requirement
经过对电路性能的分析、陀螺主要参数的估算，确定所设计的电一几}北邢业人学学位论义路可以达至fj基本要求。 - The aerodynamics subsystem is designed employing classical control methodology , including the inner loop which adopt angular rate feedback to stabilizing the attitude , and the outer loop which track the guidance command , and the proper emendation nets are designed for each loop
采用古典控制理论来设计气动力控制系统，包括具有角速度反馈的稳定内回路、跟踪制导指令的外回路以及各校正环节的设计。 - Introduce the traditional two samples rotation vector algorithm and three samples rotation vector algorithm , which fit the incremental angular condition . but , the output of fiber optic gyro is angular rate of the vehicle , the error would increase serious if use traditional algorithm
由于光纤陀螺仪输出为角速率信号,而传统的旋转矢量算法输出为角增量信号,采用角增量提取算法,旋转矢量精度会大幅大降。 - This setting could increase the damping of angular rates and improve the stability . based on bell stabilizer bar , bell - hiller stabilizer bar adds small wing on the two ends of bar . compared with main blades the aerodynamic forces and moments generated by the bar could be neglected
希勒伺服旋翼在贝尔稳定杆的基础上,于两个质量块处添加了小翼,与贝尔稳定杆相比,希勒伺服旋翼自身的挥舞运动借助机械耦合引起旋翼二次变距,起到改善操纵性的作用。 - 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
为了解决拦截弹气动参数随飞行高度、速度、姿态的不同，变化范围大，控制系统难以准确建模的困难，基于纵向平面拦截弹模型，采用模型参考变结构控制理论设计了俯仰通道姿控复合控制系统，以可测量变量过载和角速度作为状态量建立了系统的状态方程，讨论了参考模型的选择方法，并对系统的性能作了仿真分析。 - Here , the aircraft is in extreme flight conditions that is high angles of attack and high angular rates . it can encounter severe nonlinear effects . detailed descriptions of the flight dynamic , aerodynamic models , inverse dynamic and the choice of the control variable are given
2 、应用经典的微分几何方法研究了一般的飞行状态下飞机飞行的控制律，指出不利用矢量推力的飞行系统的控制方程一般都是可以逐步通过动态状态反馈，适当的坐标变换和正则静态反馈等三个步骤得以线性化。
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