基于姿控喷管开关控制的全量耦合动力学建模与控制优化技术研究

Modeling of Rocket Coupling Dynamics based on the Attitude Control Nozzle Working State

传统运载火箭姿态控制设计与仿真均采用小偏差线性化的动力学模型,该模型无法准确体现调姿过程对飞行轨道、推进剂晃动的影响,且干扰的合成与施加方法与实际飞行不符,无法精细化分析某项干扰对实际飞行过程的影响。为了解决以上问题,建立的基于姿控喷管开关控制的全量耦合动力学模型,实现姿控-轨道-推进剂晃动的一体化耦合仿真,具备精细化分析能力,提升了设计预示能力。该技术已在中国探月三期工程中成功应用,有效降低了姿控用推进剂耗量需求,提高了火箭运载能力。

The mall deviation linearization dynamics model has been used in the traditional design and simulation for rocket attitude control,while this model can hardly demonstrate the effect of attitude control on the trajectory and the propellant sloshing;moreover the effect of certain interference is quite different from the actual flight.In order to improve this,a new coupling model for trajectory-attitude-slosh dynamics is established,which is based on the attitude control nozzle working state.This model significantly decreases the propellant demand for the attitude control and increases the carrying capacity,furthermore effectively avoids the revision of the rocket structure which can not be achieved in fact,and finally Chinese lunar exploration program phase III was correspondingly guaranteed.