模型系统有三个自由度，即：俯仰，滚转，偏航。
The model system has three freedoms, namely: Pitch, Roll, and Yaw.
同时采用小扰动法推导了俯仰通道和滚动通道的简化模型，为空气动力和姿控发动机推力复合控制系统进行初步设计提供了依据。
What′s more, according to the method of little disturbance, the simplified model of pitching and rolling plane is derived, so preliminarily combined control system can be designed.
因此，本文采用了变结构控制理论设计倾斜角稳定系统，采用了模型跟踪变结构控制理论设计俯仰、偏航通道的加速度稳定回路。
So, variable structure control theory is used in Angle stabilization of roll, and model - following variable structure control theory is used in acceleration stabilization of pitch and yaw.
重复性实验结果表明，该装置可用在跨超音速风洞中测量飞行器模型的俯仰阻尼导数。
The results obtained in repeated tests show that this test mechanism can be used to measure the pitching damping derivatives for the vehicle models in the transonic and supersonic wind tunnel.
针对此翼面上有升降舵的多舵面布局，建立了俯仰运动下不同于翼面上只有副翼的动力学模型。
About multi - control surface configuration with elevators, its dynamic model was established under pitch movement, differing from wing with ailerons alone.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
应用rbf神经网络建立了汽车车身质心垂直加速度功率谱密度、俯仰角加速度功率谱密度和路面功率谱密度之间的非线性映射模型。
The nonlinear mapping relation among the PSD of vehicle body centroid vertical acceleration, pitching angular acceleration and the road surface were found by RBF neural networks.
针对俯仰运动模型，提出利用非线性最优滑模控制来设计某型导弹的俯仰运动控制系统。
Aiming at the pitching movement model, a nonlinear variable structure controller with an optimal sliding surface for the pitching control system of missile was presented.
建立了飞机在随机跑道激励下，考虑机身俯仰运动与弹性振动的非线性随机动力学模型。
A nonlinear stochastic dynamic model is established which takes into consideration aircraft body pitch movements and the elastic vibration excited by the random runway.
首先以无源声呐对目标的方位角、俯仰角和频率测量为依据，建立动态系统模型。
The model of motive system is made in the light of measurements of target bearings, elevation and frequency by passive sonar.
然后，用本文给出的模型跟随理论设计俯仰一偏航通道自动驾驶仪，用线性二次型理论设计滚动通道自动驾驶仪。
Then the pitch-yaw channel autopilot is designed by the model following design approach given in this paper while the roll channel autopilot is designed by using linear quadratic theory.
应用该模型对某飞机模型做俯仰滚转耦合运动的非定常气动力进行了辨识。
Using the model the unsteady aerodynamics of one aircraft in pitching-rolling motion is identified.
应用该模型对某飞机模型做俯仰滚转耦合运动的非定常气动力进行了辨识。
Using the model the unsteady aerodynamics of one aircraft in pitching-rolling motion is identified.
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