基于大型翼伞可控回收的箭体结构与分离方案设计

Launch Vehicle Structure Design and Separation Technology Based on Controllable Recovery Using Large-scale Parachute System

对于高密度发射的运载火箭,迫切需要采取对火箭改动最小,风险和装备成本最小的控制措施,显著减小火箭落区面积,规避重要基础设施,减小对落区社会生活的影响。以某运载火箭助推器为例,在考虑现有火箭的运载能力、载荷与力学环境、结构气动外形及内部空间的基础上,提出了一种基于大型翼伞可控回收的箭体结构与分离方案设计构思,主要包括大型翼伞分离方案设计、助推器头锥结构改进设计及助推器头锥内伞系统结构集成化设计等。该技术的开展有效减少了箭体结构分离过程的分离能源,简化了结构方案,降低了结构质量,为长征系列运载火箭可控回收工作奠定了基础。

It is urgent for the highly active launch vehicles to take control measures with minimized change of launch vehicle structure,minimized risk and cost.Those measures should be able to effectively reduce the impact area of launch vehicle debris so as to evade important infrastructures in the area and to reduce the impact to the local residents.Based on the consideration of the launch capability,load and mechanical environment,aerodynamic configuration and internal space of the existing structure,boosters of the some launch vehicle is objected,on which a design concept for launch vehicle structure and separation technology using large-scale controllable parachute system is presented.The separation scheme design of large-scale controllable parachute system,the improved structure design of the booster nosecone and the integrated design of large-scale controllable parachute system in the nosecone are introduced.This technology effectively reduces the separation energy in the process of structure separation,simplifies the structure design,reduces the weight of the structure,and also lays the foundation for the controllable recovery of Long March series launch vehicles.