高超声速助推飞行试验技术方案研究

Research on Overall Plan for Hypersonic Boostflight Experiment

以高超声速飞行器为有效载荷,进行了高超声速助推飞行试验技术方案研究,并通过分析气动力参数、设计变量参数的范围及约束条件,进行了助推弹道设计,确定了二级助推发动机设计要求,并利用调整发射俯仰角、滑行时间和配重物质量来调整助推弹道参数,将高超声速飞行器送入试验弹道.最后将计算结果与美国HyF ly计划陆基发射试验的弹道实测数据进行对比分析.结果表明,设计结果与HyF ly试验数据较吻合,验证了助推飞行试验技术方案的可行性与正确性.

Overall plan for hypersonic boost-flight experiment technology is investigated in detail for the free-flight test of hypersonic vehicle under nominal design conditions. Aerodynamic coefficients, some limitations and restrictions of design parameters are discussed for boost trajectory design while relevant two-stage engine technology requirements are determined. By adjusting initial launch angle, interstage coast time and ballasting, hypersonic vehicle can be ferried to DCR take-over flight condition. Therefore, hypersonic vehicle is used as the payload to design flight trajectory and the simulation results are compared with I-IyFly flight data. The results show that the deviations are very small, meeting the general requirement of overaU plan, while the feasibility of hypersonic boost-flight experiment is demonstrated.