比冲是评价固体火箭发动机能量特性的综合因子,其与固体推进剂配方组成及发动机设计参数有关,对射程具有较大的影响。该文结合某远程TG-300发动机结构参数,针对喷管喉径、扩张半角和膨胀比的制造公差,研究了这些参数对比冲散布及纵向距离散布的影响。结果表明,喷管喉径制造公差对比冲的影响相对较大,扩张半角次之,膨胀比的制造公差对比冲影响较小; 这些公差应当在加工过程中合理控制。该文所得结果可对固体火箭发动机结构设计提供参考依据。
Abstract
The specific impulse is a comprehensive factor to evaluate the energy characteristics of solid rocket engine(SRE),and it affects the range of rocket greatly.It is relevant to the solid rocket propellant formulations and determined by the design parameters of SRE.The design parameters of long-distance rocket TG-300 engine were used to discuss the effects of manufacturing tolerance from throat diameter,expansion cone half angle and expansion ratio on the dispersions of specific impulse and longitudinal distance.The results show that the effect of manufacturing tolerance from throat diameter on specific impulse is greatest,and the effect of tolerance from expansion cone half angle takes the second place,and the effect of tolerance from expansion ratio is minor.The tolerance discussed in present paper should be controlled rationally in manufacture process,and the results obtained by current paper offer reference for structure design of SRE.
关键词
射程散布 /
固体火箭发动机 /
火箭喷管
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Key words
range dispersion /
solid rocket engine /
rocket nozzle
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参考文献
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