The system consists of a guidance law and a basic attitude controller.
系统分为基本姿态控制器设计和制导系统设计两个部分进行研究。
The proposed method is applied to satellite attitude controller design to cope with the errors arising while linearization procedure.
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。
This method is applied to an unmanned helicopter, and the design of an adaptive attitude controller and a trajectory-tracking controller are presented.
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。
According to the singularity perturbation theory, dynamic inversion is adopted to design the basic attitude controller including fast inverse loop and slow inverse loop.
利用多重时间尺度奇异摄动理论，结合非线性动态逆方法设计了基本姿态控制器，包括快逆回路和慢逆回路两部分。
A synthesis method based on inverse dynamics and online parameter identification was developed and was directly used to design the attitude controller in the integrated control system.
提出了一种基于逆动力学和在线参数辨识的方法，用于直接设计综合控制系统中的姿态控制器。
In this paper, adaptive inverse attitude control of RLV (reusable launch vehicle) is studied. The mathematical model of the orbiter is built and adaptive inverse attitude controller is designed.
本文对可重复使用运载器的自适应逆姿态控制进行了研究，以航天飞机轨道器为模型，建立了自适应逆姿态控制的数学模型，设计了自适应逆姿态控制方案。
Then, base on the problem of attitude control of a satellite under development, we design a NN compensation controller for high accuracy orientation phase.
然后，基于某型小卫星的姿态控制问题，设计了高精度定向阶段的神经网络补偿控制器。
The recently developed nonlinear Active Disturbance Rejection Controller (ADRC) was applied to the attitude control of large flexible multi-body satellite with reaction wheels.
研究了最近提出的非线性自抗扰控制器在大挠性多体卫星姿态控制中的应用问题。
Finally, we use the designed PID controller to realize the longitudinal attitude tracking control of the helicopter.
最后，利用设计的PID控制器实现纵向姿态的跟踪控制，达到直升机纵向稳定控制的目的。
The recently developed nonlinear active disturbance rejection controller (ADRC) is applied to attitude control of large flexible multi-body satellite with reaction wheels.
研究了最近提出的非线性自抗扰控制器(adrc)在大挠性多体卫星姿态控制中的应用问题。
The nonlinear dynamic inversion controller based on online neural net is adopted for the attitude control loop.
基本姿态控制器采用基于在线神经网络的非线性动态逆控制器。
Finally, the dissertation designed the fuzzy PD controller of trajectory tracking, which is combined with attitude Angle controller, so that the whole flight controller is completed.
本文最后设计了直升机模糊pd轨迹跟踪控制器，与姿态角控制器相结合，完成对整个飞行控制系统的设计。
Then, the expected orientation of spacecraft with zero angular velocity was derived with a new attitude parameterization and LQR controller was designed based on the linearized system.
利用一种新的姿态描述形式推导出了角速度为零时航天器的目标姿态，然后基于线性化后的系统设计了线性二次型最优控制器。
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。
The optimization design problem of controller parameters of optimal on-off times attitude maneuvers with switch moment is investigated.
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。
A modified sliding mode fault tolerant controller is developed for flexible spacecraft attitude stabilization control in the presence of loss of actuator effectiveness fault and actuator stuck fault.
针对挠性航天器执行器卡死与失效故障的姿态稳定控制问题，提出了一种结构简单、计算量小的改进型滑模容错控制策略。
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.
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。
The design of hardware and software for small solid-state heading and attitude system using AT89C52 as main-controller is carried out.
完成了以at89 C5 2为主控制器的小型固态航姿系统软硬件设计。
The design of hardware and software for small solid-state heading and attitude system using AT89C52 as main-controller is carried out.
完成了以at89 C5 2为主控制器的小型固态航姿系统软硬件设计。
应用推荐