星图识别则是星敏感器确定空间飞行器姿态的关键技术。
Star pattern recognition is the key technic of satellite position confirmation from start sensor.
提出了一种基于图像信息的微小型飞行器姿态测量方法。
An attitude measurement approach for micro air vehicles (MAVs) based on image information was presented.
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 .
飞行器姿态控制的驱动扭矩与系统的转动惯量之间存在密切的联系。
The driving torque requirements for attitude control of a space vehicle are typically closely related to the mass moment inertia of the system.
通过四元数法和欧拉角法描述飞行器姿态，并建立相应的运动学方程。
The attitudes of vehicle are described by both quaternion and Euler angles, and two kinds of motion equations are established accordingly.
要实现在真实飞行情况下对微型飞行器姿态等数据的测量，数据的无线收发是其关键技术。
To get the data of the micro air vehicle (MAV) 's attitude in true flight, the data transmit and receive equipment is the key technology.
本文针对空间飞行器姿态控制问题，给出了一种基于优化控制与有限时间控制技术的控制方法。
In this paper, a control approach based on optimal control and finite-time control technology is derived for spacecraft.
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.
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.
对于具有纯延迟、惯性和由开关控制的非线性飞行器姿态系统，本文提出了采用解耦变结构控制的方法。
For nonlinear attitude system of flying vehicle with pure time-delay, inertia and bang-bang control a control method using decoupling variable structure is given.
研究了刚体飞行器大角度机动的姿态控制问题。
In this paper, attitude control problem of a rigid spacecraft with large Angle maneuvers is investigated.
本文研究空间飞行器大角度姿态机动的控制问题。
This paper deals with the large Angle attitude maneuver control of spacecrafts.
姿态控制推力器(act)是飞行器控制系统的执行部件。
The attitude control thruster (ACT) is the control component of the flight vehicle.
文中给出了一个弹性飞行器的姿态控制系统作为设计举例。
An example of an attitude control system of a bending vehicle is given.
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.
摇摆台作为一种空间运动机械被广泛用来模拟舰船、车辆、飞行器、陀螺仪的运动姿态等。
Swaying test platform, as a space motion mechanical device, can simulate motion of ship, vehicle, space craft, gyro and so on.
CCD星跟踪器作为飞行器的姿态测量仪器有许多优点，它必须有一种全天自主星图识别算法来支持其工作。
As a spacecraft attitude measurement instrument, CCD star tracker has a lot of advantages. But it needs an all-sky autonomous star map identification algorithm to support its operation.
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.
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。
In this paper a method for measuring the relative position and attitude Angle of the spacecraft during rendezvous and docking.
研究空间飞行器大角度姿态机动反馈开关控制的消振参数优化设计问题。
The optimization design problem of controller parameters of optimal on-off times attitude maneuvers with switch moment is investigated.
当诊断出故障时，重构控制律的参数对系统进行补偿控制，使得故障下飞行器的姿态跟踪精度得以维持。
Once a fault is detected and isolated, controller parameters can be reconfigured to compensate the loss of performance and keep the good attitude tracking accuracy of the spacecraft.
当诊断出故障时，重构控制律的参数对系统进行补偿控制，使得故障下飞行器的姿态跟踪精度得以维持。
Once a fault is detected and isolated, controller parameters can be reconfigured to compensate the loss of performance and to keep the good attitude tracking accuracy of the spacecraft.
飞行器制导精度评估，特别是航天器的姿态与定点控制、落点预报等，都离不开高精度的外弹道测量数据。
Assessing the accuracy of guidance system, especially controlling of missile's attitude and station keeping maneuver and landing point forecasting all rely on the reliable trajectory measurement.
基于充液飞行器的简化模型，在状态空间中设计控制规律以约束状态至滑模。滑模通过在一个约化空间中求解最优控制问题获得，其解是角速度作为姿态变量的函数。
A control law, that constrains the state to follow the sliding mode in the state space, is designed on the basis of a nonlinear, simplified model of the completely liquid-filled spacecraft dynamics.
这样通过非线性状态变换和非线性状态反馈，将飞行器原来的6阶非线性姿态模型部分精确线性化为二阶线性系统。
Thus by nonlinear state transformation and nonlinear state feedback, the original 6 order nonlinear attitude model of a spacecraft is partially precisely linearized into a 2 order linear system.
本文工作目标是实现飞行器的平稳垂直起降和小角度内姿态调整。
The objective of the research is achieving the stable vertical take-off and landing of the aircraft and flying attitude adjustment in a small angle range.
本文工作目标是实现飞行器的平稳垂直起降和小角度内姿态调整。
The objective of the research is achieving the stable vertical take-off and landing of the aircraft and flying attitude adjustment in a small angle range.
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