| 高超声速助推飞行试验技术方案研究 |
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| 引用本文： | 范培蕾,张晓今,杨涛,张红朝.高超声速助推飞行试验技术方案研究[J].战术导弹技术,2009(1):1-7. |
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| 作者姓名： | 范培蕾 张晓今 杨涛 张红朝 |
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| 作者单位： | 国防科技大学,长沙410073 |
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| 摘 要： | 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HyFly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HyFly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．
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| 关 键 词： | 高超声速助推飞行试验 高超声速飞行器 弹道设计 滑行时间 |
Research on Overall Plan for Hypersonic Boost-flight Experiment |
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| Fan Peilei,Zhang Xiaojin,Yang Tao,Zhang Hongchao.Research on Overall Plan for Hypersonic Boost-flight Experiment[J].Tactical Missile Technology,2009(1):1-7. |
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| Authors: | Fan Peilei Zhang Xiaojin Yang Tao Zhang Hongchao |
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| Affiliation: | (National University of Defense Technology, Changsha 410073, China) |
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| Abstract: | 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. |
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| Keywords: | hypersonic boost-flight experiment coast time hypersonic vehicle trajectory design interstage |
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