attitude angle
英 [ˈætɪtjuːd ˈæŋɡl]
美 [ˈætɪtuːd ˈæŋɡl]
网络 方位角; 空间方位角; 偏位角; 而稳态偏位角; 姿态角
双语例句
- Simulation on Quaternion Calculate Attitude Angle of the Strapdown Inertial Navigation System
捷联惯导系统中四元素法求解姿态角仿真模拟 - After analysed recognition criteria, an horizon detection algorithm and transform formula for attitude angle are attained.
文中给出了地平线判别准则及相应的算法和姿态角变换公式。 - In consideration of the uncertain initial landing attitude angle of lunar lander and the unknown slope of lunar surface, a soft landing dynamic model is built.
考虑到着陆初始姿态角的不定和月面斜角的未知，建立起着陆器软着陆动力学模型。 - 4m × 3m low-speed tunnel model attitude angle control system
4米×3米低速风洞模型姿态角控制系统 - Real-time attitude angle estimation for unmanned aerial vehicle based on skyline detection
基于天际线识别的无人机实时姿态角估计 - Furthermore, when the initial landing attitude angle and lunar slope are very large, the attitude angle of lunar lander changes little, which ensures a smooth landing of the lunar lander.
而且当着陆初始姿态角以及月面斜角很大时，月球着陆器姿态角变化少，保证月球着陆器平稳着陆。 - The measurement and control of the model attitude angle in airfoil wind tunnel test
翼型风洞实验模型姿态角的测量与控制 - Through experiment to obtain approximate impulse response of target model, then analyzes echo features of target model compared to changes in sensitivity of launch wave attitude angle.
通过试验获取目标模型的近似冲激响应，然后分析目标模型的回波特征相对于目标姿态角的变化敏感度。 - Furthermore, the computer simulation technique is applied to study initially the distortion law of CCD satellite images caused by errors of ephemeris parameters and initial attitude angle.
利用计算机仿真技术初步研究了星历参数和初始姿态角误差引起的CCD卫星影像畸变的规律。 - These coefficients are nonlinear functions of journal eccentricity and attitude angle and can be calculated using FEM.
线性函数中包含的6个系数是轴颈偏心和偏位角的非线性函数，而这些系数可以通过文中建立的有限元模型获得。 - Subsequently, the control loop of attitude angle is designed with dynamic inversion scheme.
随后本文基于动态逆思想设计了武装直升机姿态角控制回路。 - The measurement process of the attitude angle based on single trailing earth horizon sensor is investigated, and an analytical formula of attitude compensating error is obtained.
基于单轨迹地平仪研究了地平仪测量姿态角的过程，得到了解析形式的姿态角误差补偿公式。 - This paper describes the characteristics of model attitude angle measurement and control system for normal and dynamic test, and the effective methods for advancing the precision and accuracy of angle measurement in NF 3 low speed airfoil wind tunnel.
介绍NF3低速翼型风洞常规和动态实验模型姿态角测量和控制系统的特点以及为提高角度测量精度和准度所采取的措施。 - Finally, according to the geometry relations between runway boundary and horizon, attitude angle and altitude estimation algorithms based on runway boundaries and horizon are applied to acquire the value of attitude angle and altitude.
最后充分利用跑道的两条边线和地平线所构造的几何关系，采用基于地平线和跑道边界的姿态角和高度值估计算法，从理论上导出了姿态角和高度估计的结果； - The mechanics equation and the attitude angle differential equation of the inertial navigation system are deduced.
推导了惯导系统的比力方程和姿态微分方程； - The calibration system of sensor is designed and realized. Sensors in the unmanned aerial vehicle system such as attitude angle sensor, barometric height sensor and airspeed sensor are calibrated times without number. Each of their stationary models is deduced.
设计实现了传感器标定建模，以无人机系统中倾角传感器、气压高度传感器和空速传感器等为例，进行了传感器数据的标定拟和，得到了各传感器的静态模型。 - This guidance law ensure the appropriate terminal attitude angle when dispenser arrives at the open-cabin-point upon the target.
该导引律保证了布撒器在飞抵目标点上方抛撒点时具有合适的末端姿态角。 - It deducts the formulas of azimuth angle and attitude angle and uses fixed-point DSP to realize the arithmetic of the angle.
推导了方位角和姿态角的理论公式，并实现了角度的定点DSP算法。 - In this paper a method for measuring the relative position and attitude angle of the spacecraft during rendezvous and docking.
本文叙述了一种测量空间飞行器交会对接过程中位置和姿态角的方法。 - The transfer alignment method can solve for many unknown parameters when the slave platform is aligning and also can eliminate the effect of attitude angle sensor error on the estimations automatically.
载体姿态角度差传递对准法解决了子平台对准中的多个未知数的求解问题，并可自动消除载体姿态角传感器误差对其估计的影响。 - This paper presents the operating principle of attitude angle sensor and analyzes the accuracy of angle measurement, and describes a calculating method of eliminating pitch measurement principle error.
阐述了姿态角传感器的工作原理，分析了测角精度，提出了消除纵倾角测量原理误差的计算方法。 - The results indicate that both Kalman filtering algorithm and second difference algorithm can be used to well estimate the attitude angle and attitude angular velocity of the satellite.
结果表明，Kalman滤波算法和二阶差分算法均能较好地实现对日观测卫星三轴姿态角和姿态角速度的估计。 - The qualitative analysis of the dynamic procedure of the missile's attitude angle changing was made in the same case.
进行了导弹后射姿态角变化动态过程的定性分析。 - And then the simulations of them are made and the analysis of the simulation results is made. The mechanics equation and the attitude angle differential equation of the inertial navigation system are deduced.
对速度匹配、姿态匹配、角速度匹配和比力匹配传递对准进行了数字仿真，并且对数字仿真的结果进行了分析。推导了惯导系统的比力方程和姿态微分方程； - The method to aquire the angle of attack and sideslip approximately in engineering by the deviation between apparent acceleration and attitude angle was analyzed, and the control model was given.
研究了工程上用实时视加速度与姿态角偏差近似获得实时攻角和侧滑角的方法，并给出了控制模型。 - By changing tension range of the cable, attitude angle of end-effector, external force screw and redundancy rate their influence on the workspace performance are analyzed and obtain a general conclusion used to design a good performance mechanism.
通过改变绳索拉力范围、末端执行器的姿态角、外力旋量和驱动冗余度，分析对机构工作空间性能的影响，获得了可用于设计性能良好的机构的一般性结论。 - After a deep discussion of the method, it is generalized to the nonlinear MIMO system and the convergence of the algorithm is proved strictly. Subsequently, the control loop of attitude angle is designed with dynamic inversion scheme.
在此基础上，进一步对该方法进行了深入研究，并将其推广到非线性MIMO系统控制理论，严格证明了该方法的收敛性。随后本文基于动态逆思想设计了武装直升机姿态角控制回路。 - Starting with the axis vector, the attitude angle is derived.
从弹轴矢量出发，推导了姿态角的数学公式。 - The attitude angle measurement module of the system verifies the theory, further more research on precision and stability will be meaningful.
系统姿态测量部分对实现原理进行了验证，其精度和稳定性有待进一步研究。 - Software design to Expand Kaman filtering and surveillance methods to achieve the status of navigation systems, Real-time access to a helicopter at any moment the attitude angle, angular velocity and acceleration.
传感器信号采集软件设计中采用了扩展的卡曼滤波和状态监视算法，实现了组合导航所需的航姿信息的解算，实时获得直升机在任意时刻的姿态角、角速度和加速度项。