Study on reduction of waste grain rate for semi-spherical conic-column grain
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摘要: 为了减小半球锥柱型药柱的残药量,分别采用UG NX和MATLAB软件进行了建模和编程计算,得到了药柱燃烧规律和残药率与设计参数的函数关系图,进行了算例分析。计算结果表明,环向槽圆弧半径的取值越大,残药率越小,且残药率减少幅度增加;残药率与内孔半径呈现负相关关系;残药率与环向槽圆弧圆心旋转半径呈现近似抛物线关系,旋转半径值变大时,残药率先增大后减小;残药率与圆柱段长度呈现近似线性关系。计算结果与实际数据的最大相对误差为0.084%。Abstract: In order to reduce the waste grain of the semi-spherical conic-column grain, a model was built with the UG NX software and the calculations were programmed with the MATLAB software, the relations between the waste grain rate and the design parameters were obtained. The calculated results showed that the larger radius of circular groove meant the smaller waste grain rate and the decrease of waste grain rate. There was a negative correlation between the waste grain rate and the radius of the inner hole, the larger value meant the smaller waste grain rate. There was an approximate parabola relation between the waste grain rate and the radius of the circular center of the circular groove. When the value became big, the waste grain rate increased first and then decreased. The waste grain rate is approximately linear with the length of the cylinder, the larger value meant the higher residual rate. The maximum relative error between the calculated result and the actual data was 0.084%.
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[1] 曹军伟,徐东来,蔡选义,等.面向21世纪的空空导弹动力装置[J].航空兵器,1999(5):27-31.CAO Junwei,XU Donglai,CAI Xuanyi,et al.Air-to-air missile power plant facing the 21st century[J].Aviation Weaponry,1999(5):27-31.(in Chinese) [2] 王元有.固体火箭发动机设计[M].北京:国防工业出版社,1984. [3] 李昊.基于装药结构强度分析的药形优化设计研究[D].南京:南京理工大学,2016.LI Hao.Optimal design of propellant grain shape based on structural strength analysis[D].Nanjing:Nanjing University of Science and Technology,2016.(in Chinese) [4] KAMRAN A,LIANG G Z,SIDDIQUI M Z.Burning regression analysis for 3D grain configurations[J].Computer Aided Drafting Design and Manufacturing,2010,20(1):39-45. [5] SOE H T,XIANG Hongjun.Star grain regression analysis under spin effect and chamber pressure effect[J].Computer Aided Drafting Design and Manufacturing,2010,20(2):54-58. [6] ALI K,LIANG Guozhu.Design and optimization of solid rocket motor Finocyl grain using simulated annealing[J].Journal of Aerospace Power,2011,26(4):917-923. [7] KHURRAM N,LIANG Guozhu,QASIM Z.Finocy grain design and optimization using sequential quadratic programming[J].Computer Aided Drafting Design and Manufacturing,2008,18(1):2-11. [8] XIANG S H,WEI K X,LI S P,et al.Study on burning law of slotted tube grain[J].Journal of Solid Rocket Technology,2013,34(10):1383-1386. [9] XIANG Shenghai,WEI Kaixin,LI Shipeng,et al.Study on constant burning law for slotted tube grain based on simplex method[J].Journal of Propulsion Technology,2013,34(10):1383-1387. [10] HU Daning,HE Guoqiang,LIU Peijin,et al.Study on instable combustion of solid rocket motor with finocyl grain[J].Journal of China Ordnance,2011,7(1):24-28. [11] KHURRAM N,LIANG Guozhu,QASIN Z.A hybrid optimization approach for SRM finocyl grain design[J].Chinese Journal of Aeronautics,2008,21(6):481-487. [12] 张维星,唐国金.基于三维参数化建模的翼柱形发动机药形优化[J].固体火箭技术,2014,37(4):490-495.ZHANG Weixing,TANG Guojin.Optimization of finocyl grain based on the three-dimensional parameterized modeling[J].Journal of Solid Rocket Technology,2014,37(4):490-495.(in Chinese) [13] 夏冰戈,鲍福廷,惠卫华,等.考虑燃烧恒面性和结构完整性的翼柱形药柱形状优化[J].固体火箭技术,2013,36(5):620-625.
XIA Bingge,BAO Futing,HUI Weihua,et al.Shape optimization of SRM finocyl grain considering neutral burning and structure integrity[J].Journal of Solid Rocket Technology,2013,36(5):620-625.(in Chinese)[14] 周海清.复杂星孔球形药柱燃面近似解析计算方法[J].固体火箭技术,2015,35(5):85-91.ZHOU Haiqing.Approximate solution to combustion area of the spherical grain with complex star pore[J].Journal of Solid Rocket Technology,2015,35(5):85-91.(in Chinese) [15] 褚佑彪,张岗,苑博,等.固体火箭发动机装药燃面计算方法[J].固体火箭技术,2016,39(4):488-502.CHU Youbiao,ZHANG Gang,YUAN Bo,et al.Burning surface computing method for solid rocket motor grain[J].Journal of Solid Rocket Technology,2016,39(4):488-502.(in Chinese) [16] 詹君彪,相升海,李世鹏,等.减面燃烧规律的药柱选用准则[J].弹箭与制导学报,2015,35(5):86-91.ZHAN Junbiao,XIANG Shenghai,LI Shipeng,et al.Study on grain of regressive burning law selection criteria[J].Journal of Projectiles,Rocket Missiles and Guidance,2015,35(5):86-91.(in Chinese) [17] 令狐昌鸿,王高峰,钟亮,等.环形旋流燃烧室模型点火过程的实验[J].航空动力学报,2018,33(7):1767-1778.LINGHU Changhong,WANG Gaofeng,ZHONG Liang,et al.Experiment on ignition process in annular swirling combustor model[J].Journal of Aerospace Power,2018,33(7):1767-1778.(in Chinese) [18] 刘爱虢,朱悦,陈保东,等.航改型双环燃烧室燃烧反应特性试验[J].航空动力学报,2017,32(8):1793-1800.LIU Aiguo,ZHU Yue,CHEN Baodong,et al.Experiment on combustion characteristics of aeroderivative gas turbine twins annular combustor[J].Journal of Aerospace Power,2017,32(8):1793-1800.(in Chinese) [19] 迟鸿伟,魏志军,李彪,等.燃烧室构型对固体燃料超燃冲压发动机自点火的影响[J].航空动力学报,2016,31(8):1985-1994.CHI Hongwei,WEI Zhijun,LI Biao,et al.Influence of combustor shape on self-ignition in solid fuel scramjet[J].Journal of Aerospace Power,2016,31(8):1985-1994.(in Chinese) [20] 李长林,姚吉先,刘伟.环管形燃烧室燃气导管造型计算方法[J].航空动力学报,1992,7(1):43-46.LI Changlin,YAO Jixian,LIU Wei.Numerical modelling for gas duct in tuboannular combustor[J].Journal of Aerospace Power,1992,7(1):43-46.(in Chinese) [21] 杨月诚,艾春安,宁超,等.火箭发动机理论基础[M].西安:西北工业大学出版社,2010. [22] 余永刚.发射药燃烧学[M].北京:北京航空航天大学出版社,2016. [23] 张香伟.曲线弧的质心与旋转体侧面积的关系[J].河南教育学院学报(自然科学版),2012,21(3):8-10.ZHANG Xiangwei.Relationgship between curve segment’s centroid and lateral area for body of rotation[J].Journal of Henan Institute of Education(Natural Science Edition),2012,21(3):8-10.(in Chinese)
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