主要节点负责执行通讯子系统与姿态控制系统。
The primary node is responsible for running the communications subsystems and the attitude control system code.
主要介绍了一种低速风洞模型姿态控制系统的组成。
This paper introduces composition of the kind of control system of model gesture in low speed wind-tunnel.
研究航天器集成能量与姿态控制系统中飞轮的控制律。
Research on Distributed Interactive Simulation Method of Missiles Attitude Control System;
目前空间飞行器的高精度姿态控制系统大多采用飞轮系统。
Now, flywheels systems are elected as the actuators of attitude control system with high precision for most spacecrafts.
在现代卫星的姿态控制系统中，反作用轮得到了广泛应用。
Reaction wheels are widely used in the modern spacecraft attitude control systems.
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.
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.
根据经典控制理论，设计了两类临界静不稳定姿态控制系统。
According to the classical control theory, this paper deals with two designs of critical statically unstable attitude control system.
星敏感器是为空间飞行器姿态控制系统提供姿态信息的测量系统。
The star sensor is a measuring unit used for providing information to the attitude control system on spacecraft .
机动弹头是复杂的非线性系统，它给姿态控制系统设计人员以极大的挑战。
Maneuverable warhead are the complex nonlinear system, which take a great challenge to the attitude control system designers.
作为一种高精度的执行机构，反作用飞轮已广泛应用于卫星姿态控制系统中。
As a kind of high accuracy executive machine, reaction wheel has been extensively applied to the attitude control system (ACS) of satellites.
气球吊篮姿态控制系统是吊篮在空中保持姿态稳定、进行姿态调整的关键部件。
The stratospheric nacelle attitude control system is the key technology in keeping position stabilization and posture adjustment.
推导系统参数间的关系式，分析挠性空间飞行器主轴姿态控制系统稳定性问题。
The relation among parameters is derived and the stability of single axis flexible spacecraft attitude control system is studied.
同时，万向磁悬浮动量轮的研究也为集成能源与姿态控制系统的研究提供了技术支持。
Simultaneously, the study for gimbal magnetic suspension momentum wheel can benefit the integrated power and attitude control system technologically.
实验表明，所建立的测试系统模型是合理的，能够正确反映姿态控制系统的工作模态。
The experimental results show that the testing model is reasonable, and can reflect the modes of attitude control system correctly.
本文把该方法应用于无人直升机，给出了自适应姿态控制系统和跟踪控制器的设计方法。
This method is applied to an unmanned helicopter, and the design of an adaptive attitude controller and a trajectory-tracking controller are presented.
将所得结果应用于卫星姿态控制系统的设计，以解决对模型进行线性化处理时产生的误差。
The proposed method is applied to satellite attitude controller design to cope with the errors arising while linearization procedure.
本文首先介绍了逆系统方法的基本思想，然后将其用于航天器非线性姿态控制系统的设计中。
In this paper, the basic theory of the inverse system method is introduced, and is used in the design of a spacecraft attitude control system.
本文对知识基故障容错姿态控制系统加以简单的介绍。并对一类运载器提出实现它的方案设想。
The paper introduces simply the knowledge-based tolerance attitude control system. The project idea for implementing the control in a class of vehicle is presented.
最后对整个系统进行了分布实时仿真，运行结果说明了这种空间站姿态控制系统方案是可行的。
Finally, the distributed real time simulation is realized. The simulating results show that this kind of attitude control systems of the space station is feasible.
微波移相器在雷达、通信、仪器仪表、重离子加速器及导弹姿态控制系统中有着广泛的应用前景。
Microwave phase shifter in phased-array radar, communications, instrumentation, heavy ion accelerator and the missile attitude control system has a broad application prospects.
本文应用区间矩阵的理论，研究三轴稳定的挠性空间飞行器姿态控制系统的鲁棒稳定性分析问题。
In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated.
该变结构控制律在实现姿态控制系统鲁棒控制的同时，有效地抑制了传统变结构控制的抖振现象。
This VS control law implements robust control of attitude control system, at the same time, it overcomes the traditional chattering problem.
该变结构控制律在实现姿态控制系统鲁棒控制的同时，有效地抑制了传统变结构控制的抖振现象。
This VS control law implements robust control of attitude control system, at the same time, it overcome the chattering problem.
所得结论可为旋转弹姿态控制系统的总体设计以及超音速射流元件的结构及气动参数选择提供依据。
These conclusions can be used for system design of rotating missile in the attitude control system and selection of structure and pneumatic parameters for supersonic fluidic elements.
动量轮作为卫星姿态控制系统的关键执行部件，对其故障检测对维持卫星的正常运行具有重要意义。
Momentum wheel is a key actuator of the attitude controlling system of a satellite. Thus, it is very meaningful to accomplish its fault detection to maintain the working order of the satellite.
基于正规性分析结果，使用系统不确定性反馈摄动描述对姿态控制系统的正规矩阵设计方法进行研究。
Based on the results, a normal matrix design approach for spacecraft attitude control systems is developed by using a feedback perturbation description for system uncertainties.
提出了一种基于最小二乘支持向量机(LSSVM)非线性观测器的卫星姿态控制系统故障诊断方法。
A fault diagnosis method for satellite attitude control systems is presented based on least squares support vector machine (LSSVM).
基于奇异摄动思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The spacecraft's attitude control system was divided into the outer loop that was Angle loop and the inner loop that was Angle velocity loop based on their time scales.
基于时标分离思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The aerocraft's attitude control system is divided into the outer loop that is an Angle loop and the inner loop that is an Angle velocity loop based on their timescale separation principle.
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