固体火箭冲压发动机燃气流量-喷管喉部面积双变量调节特性研究

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英文篇名：Research on Regulation Characteristics of Flow and Area of Nozzle Throat of Ducted Rocket 作者：孙兴 ; 祝学军 ; 卢鑫 ; 李新田 英文作者：Sun Xing;Zhu Xue-jun;Lu Xin;Li Xin-tian;China Academy of Launch Vehicle Technology; 关键词：固体火箭冲压发动机 ; 双变量调节 ; 调节特性 英文关键词：ducted rocket;;two-variable control;;regulation characteristics 中文刊名：DDYH 英文刊名：Missiles and Space Vehicles 机构：中国运载火箭技术研究院; 出版日期：2018-10-10 出版单位：导弹与航天运载技术 年：2018 期：No.364 语种：中文; 页：DDYH201805007 页数：5 CN：05 ISSN：11-3263/V 分类号：35-39

摘要

对于采用几何结构可调技术的固体火箭冲压发动机,基于燃气流量-喷管喉部面积的双变量调节特性存在其固有的多样性和复杂性,包括调节方案的设计和调节结构的实现,为进一步优化双变量调节总体设计方案,分别从各部件着手建立了发动机性能仿真模型。在此基础上,针对不同的飞行状态,研究了双变量调节的变化关系,重点比较分析了单变量和双变量两种调节方案下发动机比冲性能的差异。结果表明:采用双变量调节的固体火箭冲压发动机比冲性能显著优于采用单变量调节的固体火箭冲压发动机,且双变量调节可改善发动机在高空下的喘振等不稳定工作状态,有效拓宽固体火箭冲压发动机的稳定工作范围。
        For adjustable geometric structure ducted rocket, the regulation characteristics of adjustable flow and nozzle are mulriple complex, including regulating scheme and regulating structure. To further optimize the overall design scheme of two-variable control system, the performance simulation model of ducted rocket is built. Aiming to different flight conditions, the differences of one-variable regulation and two-variable regulation in specific impulse are compared and analyzed. The changes of two-variable regulated quantities are studied as well. According to the results, the specific impulse performance of a ducted rocket with two-variable regulation is much better than a ducted rocket with one-variable regulation. In addition, the two-variable regulation can improve the aerodynamic stability of ducted rocket in high altitude greatly.

引文

[1]梁俊龙,吴宝元,李斌.几何结构可调的亚燃冲压发动机性能研究[J].火箭推进,2010,36(2):1-4.Liang Junlong,Wu Baoyuan,Li Bin.Performance research of adjustable geometric structure ramjet engine[J].Journal of Rocket Propulsion,2010,36(2):1-4.
    [2]邵明玉,王志刚.多变量调节固冲发动机动力学建模及仿真[J].固体火箭技术,2015,38(6):782-788.Shao Mingyu,Wang Zhigang.Dynamic modeling and simulation of multivariable-adjustable ducted rocket[J].Journal of Solid Rocket Technology,2015,38(6):782-788.
    [3]鲍福廷,黄熙君,张振鹏,等.固体火箭冲压组合发动机[M].北京:中国宇航出版社,2006.Bao Futing,Huang Xijun,Zhang Zhenpeng,et al.Integral solid propellant ramjet rocket motor[M].Beijing:China Aerospace Press,2006.
    [4]瞿章华,曾明,刘伟,等.高超声速空气动力学[M].长沙:国防科技大学出版社,1999.Qu Zhanghua,Zeng Ming,Liu Wei,et al.Hypersonic acrodynamics[M].Changsha:National University of Defense Technology Press,1999.
    [5]胡建新,张为华,夏智勋,等.冲压推进技术[M].长沙:国防科技大学出版社,2013.Hu Jianxin,Zhang Weihua,Xia Zhixun,et al.Ramjet propelled technology[M].Changsha:National University of Defense Technology Press,2013.
    [6]段晰怀,郑日恒,李立翰.基于亚燃的高超声速冲压发动机内流道研究[J].航空学报,2015,36(1):232-244.Duan Xihuai,Zheng Riheng,Li Lihan.Internal flowpath for hypersonic ramjet based on subsonic combustion[J].Acta Aeronauticaet Astronautica Sinica,2015,36(1):232-244.