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首页> 外文会议>Proceedings the 16th IFAC (International Federation of Automatic Control) World Congress >LQG CONTROLLER DESIGNS FROM REDUCED ORDER MODELS FOR A LAUNCH VEHICLE
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LQG CONTROLLER DESIGNS FROM REDUCED ORDER MODELS FOR A LAUNCH VEHICLE

机译：降阶车辆降阶模型的LQG控制器设计

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摘要

The suppression of liquid fuel slosh motion is critical in a launch vehicle (LV). In particular, during certain stages of the launch, the dynamics of the fuel interacts adversely with the rigid body dynamics of the LV and the feedback controller must attentuate these effiects. This paper describes the effort of a multivariable control approach applied to the Geosynchronous Satellite Launch Vehicle (GSLV) of the Indian Space Research Organization (ISRO) during a certain stage of its launch. The fuel slosh dynamics are modelled using a pendulum model analogy.We describe two design methodologies using the linear-quadratic Gaussian (LQG) technique. The novelty of the technique is that we apply the LQG design for models that are reduced in order through inspection alone. This is possible from a perspective that the LV could be viewed as many small systems attached to a main body and the interactions of some of these smaller systems could be neglected at the controller design stage provided sufficient robustness is ensured by the controller. The first LQG design is carried out without the actuator dynamics incorporated at the design stage and for the second design we neglect the slosh dynamics as well.
机译：在运载火箭（LV）中，抑制液体燃料晃动至关重要。特别是，在发射的某些阶段，燃料的动力与LV的刚体动力产生不利的相互作用，并且反馈控制器必须使这些作用有效。本文描述了在印度航天研究组织（ISRO）发射的某个阶段中，将多变量控制方法应用于地球同步卫星发射飞行器（GSLV）的努力。燃油晃荡动力学采用摆式模型进行建模。我们使用线性二次高斯（LQG）技术描述了两种设计方法。该技术的新颖之处在于，我们将LQG设计应用于仅通过检查即可按顺序减少的模型。从一个角度来看，这可能是可行的，因为在控制器设计阶段，只要控制器确保足够的鲁棒性，就可以将LV视为附着在主体上的许多小型系统，而可以忽略其中一些较小系统的相互作用。第一个LQG设计在设计阶段就没有将执行器动力学纳入其中，而对于第二个设计，我们也忽略了晃动动力学。

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