一种运载火箭第一子级回收方案设计方法

A Return Scheme Design Method for the First Sub-stage of a Launch Vehicle

针对可回收火箭的总体设计,提出了一种用于运载火箭第一子级回收方案的设计方法。首先,建立火箭子级运动模型,为便于确定回收推力大小和调节范围,在模型中引入了推力比例因子和推力调节因子。然后,探讨回收推力和推进剂剩余量的对应关系,并通过飞行时间给出剩余推进剂的约束条件。最后,从设计的角度确定回收基本过程,并通过仿真算例制定火箭子级的回收方案。所提方法详细给出了回收过程中火箭发动机的推力大小、推力调整范围、工作时间、落点位置、最大速度以及着陆段的起始速度和高度的估计。算例表明所提方法可以实现回收过程的关键参数确定。

A concept design method for the return of the first sub-stage of a launch vehicle is proposed.It provides a solution for the overall design of a recoverable Launch vehicle.Firstly,a motion model for return of first stage is built.In order to calculate the thrust and its adjustment range,two parameters that named thrust ratio and thrust adjustment factor are defined in the model.Secondly,relation between recovery thrust and left propellant is discussed.A constraint of left propellant is introduced.Finally,a return scheme of a first stage is planned through a simulation example.The method proposed answers such questions as how much propellant should be reserved to realize the return of the first stage,how much thrust should be used,what is the adjustment range of thrust during the return process,the landing point of the stage,the max velocity during the return,and height and velocity before the stage enters the landing phase.The example shows that this method can be used to plan a complete return scheme for the first stage of a launch vehicle.