返回式探空火箭裙锥减速器方案设计及分析

Scheme design and analysis of recoverable sounding rocket reducer

针对传统的探空火箭减速板质量大、展开角度不可调节等缺陷,提出一种新型探空火箭裙锥减速器减速方案。它具有质量小、可改变展开角、展开阻力面积大等优点。针对超声速探空火箭减速器再入时的气动特性,对其外围流场进行了仿真分析,得出了减速器不同锥角对气动特性及过载的影响,并给出了减速器外围流场、压力场以及减速器的应力应变分析,结果表明,减速器所受的气动阻力与其锥角有明显关系,具有非线性特点,且减速器的最大应力小于许用应力。该方案可为探空火箭的回收及新型减速器的设计提供一定的参考依据。

In order to meet the requirements of the rapid recovery of sounding rocket and reduce the development cost,a new type of sounding rocket skirt reel deceleration program was proposed.It has light weight,changeable expansion angle,expanded resistance area and some other advantages.The aerodynamic characteristics of the supersonic sounding rocket reducer were analyzed,the external flow field was simulated and analyzed.The influence of different taper angles on the aerodynamic characteristics and overload was given.The stress and strain of the external flow field,the pressure field and the gear unit were presented.The results show that the pneumatic resistance of the gear unit is obviously related to its cone angle and has the nonlinear characteristics,and the maximum stress of the reducer is less than the allowable stress.This paper can provide reference for the design of sounding rocket and new reducer.