vehicle attitude

The attitude control is the base of autonomic flight control for unmanned aerial vehicle ( UAV). The control law is the most important part to the flight quality and it determines whether the UAV can fulfill the target of autonomic flight.

姿态控制是无人机自主飞行控制的基础，其控制律设计结果对无人机飞行特性的影响至关重要，它决定了无人机是否能够满足自主飞行要求。

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The suspension damping control strategy for vehicle attitude control system is presented.

提出了车辆姿态控制系统的悬架阻尼控制策略.

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Research on Launch Vehicle Attitude Control Based on Direct Lateral Force Exploring Interaction between Side Jet and Flow Stream and Its Effect on Aerodynamic Characteristics

基于侧喷流直接力技术的运载器姿态控制方法飞行器侧向喷流流动干扰与气动特性影响研究

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The space vehicle attitude system is a nonlinear, strongly coupled system with multi-input and multi-output.

空间飞行器姿态系统具有非线性 、 强耦合、多输入多输出的特点.

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Education and examination regarding traffic safety, vehicle hygiene, service attitude, and civilized language shall be carried out on drivers by Party B on a regular basis.

乙方应定期对司机进行交通安全、车辆卫生、服务态度、文明用语等相关服务要求进行教育和检查。

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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。

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For attitude control of micro aerial vehicle with flapping wings, a control method based on BP ( backpropagation) neural networks and average moments is proposed.

对于拍翅式微型飞行器姿态的控制，提出了一个基于BP神经网络和平均力矩的控制方案。

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Using kinetic kill vehicle to intercept tactical ballistic missile ( TBM) during terminal phase, the advantage of Divert and Attitude Control System ( DACS) whose response time is very short is taken to improve accuracy and destroy the target by hit-to-kill technology.

在末制导段采用动能拦截器拦截战术弹道导弹，可以利用其快速响应的直接力控制技术提高命中精度，达到直接碰撞杀伤目标的目的。

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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

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A launch vehicle with lateral jet as its attitude control mechanism during ascending stage was proposed.

建立了运载器起飞段侧喷流直接力姿态控制模型.

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