针对机动目标存在的姿态扰动，研究了具有加速度和旋转运动的机动目标成像模型及其信号处理过程。
The dissertation demonstrates the maneuvering target imaging model with acceleration and rotating motion and its signal processing to solve attitude perturbation of the targets.
建立卫星姿态动力学数学模型，并分析星体所受的外部扰动力矩。
Mathematic model of satellite attitude dynamic is set up, and external disturbance torque is analyzed.
以典型的航天员推离动作对飞船的扰动力矩作为控制系统仿真的输入参数，分析姿态控制系统受到扰动后的响应。
Put the disturbance moments of typical astronaut's push-off act as the input datas of the control system simulation, and analyze the response of the attitude control system after disturbed.
反作用轮是影响航天器姿态控制系统精度的主要扰动源之一。
Reaction wheel is one of the main disturbance sources for the attitude control system accuracy of spacecraft.
提出了一种基于神经网络扰动补偿的姿态控制方法。
This paper presents a control scheme based on NN disturbance compensation for attitude control of satellite.
优化性能指标要求在阵风扰动下驾驶员处法向过载、飞机姿态变化以及控制信号能量损耗最小。
The optimization requires the minimization of the vertical overload at the pilot′s seat, the attitude variation and the control energy consumption under the gust disturbance.
优化性能指标要求在阵风扰动下驾驶员处法向过载、飞机姿态变化、以及控制信号能量损耗最小。
The optimization requires the minimization of the normal acceleration overload at the position of pilot, the attitude variation and the control energy consumption under gust disturbance.
反作用轮是影响航天器姿态控制系统精度的主要扰动源之一。
Reaction wheel is one of the main disturbance sources that affect the precision of attitude control system of spacecraft.
文中基于滑模控制方法提出一种改进的自适应姿态控制规律，适用于有内扰动力矩存在的航天器。
An improved adaptive control approach based on sliding-mode control is proposed in this paper for the spacecraft subjected to internal perturbation torque.
通过考虑单元间的边界条件可以得到姿态动力学的解析模型，并由此可以获得外扰动和姿态角到附件弹性位移之间的传递特性。
Boundary conditions are used to assemble the global system model, and transfer properties from external disturbance or attitude to elastic deflection of appendages are obtained.
利用伞-弹系统动力学模型，从工程应用的角度出发，分析了阵风小扰动作用下，子弹姿态的运动特性，并以此为基础给出了末修子弹弹下点的计算模型。
The dynamics model of parachute-munition system is used to analyze the motion characters of submunition under the effect of wind gust, and the calculation model of projective point is presented.
利用伞-弹系统动力学模型，从工程应用的角度出发，分析了阵风小扰动作用下，子弹姿态的运动特性，并以此为基础给出了末修子弹弹下点的计算模型。
The dynamics model of parachute-munition system is used to analyze the motion characters of submunition under the effect of wind gust, and the calculation model of projective point is presented.
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