弹道—飞航组合导弹的惯性弹道优化与质量分配问题研究
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摘要
弹道—飞航组合式导弹是一种基于助推—滑翔弹道概念的超声速跨大气层飞行器,是一种非常规弹道、能突破防御系统或航空母舰战斗群防线的精确制导武器。本文针对弹道—飞航组合式导弹的再入段轨道、弹道部分与飞航部分的质量分配问题展开研究与分析。
首先,对组合导弹的主要参数进行分析,包括空气动力系数分析和组合导弹的结构系数分析两部分,为后面的工作做准备。
其次,建立了组合导弹再入段的一般动力学方程和适合优化分析的查普曼变量方程,并简单介绍了优化方法,变分法和极大值原理。对于如何用变分法处理这类问题,也给出了简单的推导。这部分理论已得到充分发展,很适合飞行力学的最优化问题。
再次,对导弹的再入轨迹进行了研究,得出了变分方程,对轨道进行优化,并对两种飞行方案进行了仿真分析,它们是有弹翼和无弹翼两种方案,并对两种方案进行了比较。
之后,分别对弹道段,再入段和飞航段的质量—射程关系进行了仿真分析,由仿真结果可近似认为弹道段和再入段的飞行距离只与质量分配有关,弹道段与再入段射程随质量分配比增大而增大,飞航段则减小。在对再入段的分析中得到了利用最大升阻比滑翔飞行就射程来说具有良好近似的结论;得出了总质量和质量分配比的关系图。分析得:战斗部始终保持恒值的情况下最优比重则是随总重增加而减小的。
最后,对全文所作的工作进行了总结,并阐明了本文所存在的不足和需要进一步所作的研究。
The orbit of ballistic—cruise missile in reentry stage and the mass distribution between ballistic part and the cruise part are analyzed in this paper.
The major parameters of the Aerodynamical coefficients and the structure coefficients of the missile are analyzed.
The dynamics equation and modified Chapman equation are build. The optimization method with the variational method and the maximum principle is briefly introduced. The derivation of the variational method for reentry stage optimization is given. There is sufficient development for the theories, and it is suitable for optimization problem of flight mechanics.
The orbit of ballistic- cruise missile in reentry stage is studied. The optimization of flight trajectory and variational equation are obtained. Two kinds of programs are analyzed and solved. Which are flighting with the wings and flighting with only missile body. And the simulation results of the two schemes are analyzed.
The diagrams of ballistic stage, reentry stage and the cruise stage are obtained after the analysis has made. The similar conclusion from the analysis of reentry phase was gotten that flight with the maximum lift over drag ratio in the reentry stage could got the approximate answer; and diagrams between total missile range and weight allocation are gotten.
At last, all works in the discussion are summarized, and the content which not perfect is introduced.
首先,对组合导弹的主要参数进行分析,包括空气动力系数分析和组合导弹的结构系数分析两部分,为后面的工作做准备。
其次,建立了组合导弹再入段的一般动力学方程和适合优化分析的查普曼变量方程,并简单介绍了优化方法,变分法和极大值原理。对于如何用变分法处理这类问题,也给出了简单的推导。这部分理论已得到充分发展,很适合飞行力学的最优化问题。
再次,对导弹的再入轨迹进行了研究,得出了变分方程,对轨道进行优化,并对两种飞行方案进行了仿真分析,它们是有弹翼和无弹翼两种方案,并对两种方案进行了比较。
之后,分别对弹道段,再入段和飞航段的质量—射程关系进行了仿真分析,由仿真结果可近似认为弹道段和再入段的飞行距离只与质量分配有关,弹道段与再入段射程随质量分配比增大而增大,飞航段则减小。在对再入段的分析中得到了利用最大升阻比滑翔飞行就射程来说具有良好近似的结论;得出了总质量和质量分配比的关系图。分析得:战斗部始终保持恒值的情况下最优比重则是随总重增加而减小的。
最后,对全文所作的工作进行了总结,并阐明了本文所存在的不足和需要进一步所作的研究。
The orbit of ballistic—cruise missile in reentry stage and the mass distribution between ballistic part and the cruise part are analyzed in this paper.
The major parameters of the Aerodynamical coefficients and the structure coefficients of the missile are analyzed.
The dynamics equation and modified Chapman equation are build. The optimization method with the variational method and the maximum principle is briefly introduced. The derivation of the variational method for reentry stage optimization is given. There is sufficient development for the theories, and it is suitable for optimization problem of flight mechanics.
The orbit of ballistic- cruise missile in reentry stage is studied. The optimization of flight trajectory and variational equation are obtained. Two kinds of programs are analyzed and solved. Which are flighting with the wings and flighting with only missile body. And the simulation results of the two schemes are analyzed.
The diagrams of ballistic stage, reentry stage and the cruise stage are obtained after the analysis has made. The similar conclusion from the analysis of reentry phase was gotten that flight with the maximum lift over drag ratio in the reentry stage could got the approximate answer; and diagrams between total missile range and weight allocation are gotten.
At last, all works in the discussion are summarized, and the content which not perfect is introduced.
引文
1雍恩米,唐国金,陈磊.助推-滑翔式导弹中段弹道方案的初步分析.国防科技大学学报. 2006, (6):6~10
2关世义.向多极化发展的飞航导弹.飞航导弹. 2002, (6):20~27
3徐勤勇.高超声速飞行器总体概念研究.西北工业大学硕士学位论文. 2005:1~5
4臧国才,李树常.弹箭空气动力学.兵器工业出版社, 1989:202~230
5瓦弗洛缅也夫,科普托夫.弹道式导弹设计和试验.国防工业出版社, 1980:1~193
6乔洋.中远程高超音速空舰导弹关键技术研究.西北工业大学硕士学位论文. 2003:1~12
7韩品尧.战术导弹总体设计原理.哈尔滨工业大学出版社, 2002:15~50
8阮春荣.大气中飞行的最优轨迹.宇航出版社, 1987:1~97 156~200
9 A. Miele. Flight Mechanics Theory of Flight Path. Addison-Wesley Reading, 1962:20~27
10钱杏芳等.导弹飞行力学.北京理工大学出版社, 2000:1~200
11 J. S. Chern, N. X. Vinh. Optimum Reentry Trajectories of a Lifting Vehicle. NASA. CR-3236,1980:15~20
12 D. R. Chapman. An Approximate Analytical Method for Studying Entry into Planetary Atmospheres. NASA. TR-R-11, 1980:16~28
13 J. S. Chern, N. X. Vinh. Optimum Reentry Trajectories of a Lifting Vehicle. NASA. CR-3236,1980:20~30
14刑继祥,张春蕊,徐洪泽.最优控制应用基础.科学出版社, 2003:1~100
15 AIAA White Paper. Current State of the Art: Multidisciplinary Aerospace Design Optimization. AIAA. MDO Technical Committee. 1991:30~40
16 Jaroslaw Sobieszczanski-Sobieski, Haftka. Multidisciplinary erospace Design Optimization: Survey of Recent Developments. AIAA-96-0711:17~30
17谷良贤,温炳恒.导弹总体设计原理.西北工业大学出版社, 2004:10~40
18 K. F. Hulme, C. L. Bloebaum. A Comparison of Solution Strategies for Simulink-Based Multidisciplinary Aerospace Design Optimization. AIAA-98-4977:21~31
19 Srinivas Kodiyalam. Evaluation of Methods for Multidisciplinary Design Optimization (MDO). NASA. CR-2000-210313:31~40
20孙明玮,彭南楠,杨明.导弹最优滑翔弹道的设计及存在的问题。首届全国航空航天领域中的力学问题学术研讨会.北京. 2004:174~177
21彭伟斌,吴德隆.升力式航天器再入最优轨迹研究.弹道学报. 2003, (4):1~6
22颜仲新,刘鼎臣,胡海.反舰导弹飞行弹道探讨.飞航导弹. 2004, (2):33~36
23关世义.飞航导弹:概念和定义的探讨.飞航导弹. 2004, (9):1~7
24许志.高超声速飞行器动力学与动态特性分析.西北工业大学硕士学位论文.2005:1~5
25王勇.某型空地导弹总体设计.西北工业大学硕士学位论文. 2002:1~15
26孙洪梅.全程控制近程地地导弹总体方案设计.西北工业大学硕士学位论文. 2003:1~30
27张明,田宏伟,梁彦.冲压发动机在战术导弹上的应用.飞航导弹. 2005, (6):7~12
28杨卫丽,陈雨杰.高超声速巡航导弹及其关键技术.现代军事. 2003, (10):8~12
29张磊.弹道导弹突防问题的研究.北京航空航天大学硕士学位论文. 2002:1~50
30关世义.飞航导弹弹道述评.飞航导弹. 1996, (8):1:7
31薛成位.弹道导弹工程.中国宇航出版社, 2002:1~30
32 R. S. Sellar, S. M. Batill, J. E. Renaud. Concurrent Subspace Optimization for Multidisciplinary System Design. AIAA-96-0714:20~30
33 M. Kroo, Valerie Manning. Collaborative Optimization: Status and Directions. AIAA-2000-4721:1~11
34 P. Giesing, M. Jean-Francois. A Summry of Industry MDO Applications and Needs. AIAA-98-4737:12~19
35 N. X. Vinh, A. Busemann, R. D. Culp. Hypersonic and Planetary Entry Flight Mechanics. The University of Michigan Press. Ann Arbor, 1989:15~22
36 H. W. Stone, R. W. Powell. Entry Dynamics of Space Shuttle Orbiter With Longitudinal Stability and Control Uncertainties at Supersonic and Hypersonic Speeds. NASA. TN-1084, 2001:1~20
37 N. X. Vinh, A. Dobrzelecki. Non-linear Longitudinal Dynamics of an Orbital Lifting Vehicle. NASA. CR-1449, 1996:9~20
38 E. Bryson, W. F. Denham. A steepest-ascent method for solving optimum programming problems. Applied Mechanics, 1962, (29): 247~257
39 E. Sanger, J. Bredt. A Rocket Drive for Long Range Bombers. Tanslation CGD-32. Navy Dept, 1994:111~130
40 E. Bryson, W. F. Denban, F. J. Canrroll, K. Mikami. Determination of lift or drag problems to minimize reentry heating. J. Aerospace Sci, 1998, (29):420~430
41 E. S. Levinsky. Applications of ineweight constraints to variational problems of lifting reentry. J. Aerospace Sci, 1992, (29):400~409
42 C. T. Leondes, R.A. Niemann. Optimization of aerospace reentry vehicle trajectories through independent control of lift and drag. J. Spacecraft, 1999, (3): 618~623
43 Tu Lianghui, Yuan Jianping, Fang Qun, Luo Jianjun. Reentry skipping trajectory optimization using direct parameter optimization method. A Collection of Technical Papers - 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference. Vol 1 2006: 824~837
44 Vinh Nquyen X, Shi Yawen. Optimum multiple-skip trajectories. Acta Astronautica. Vol 41, No 2. 1997: 103~112
2关世义.向多极化发展的飞航导弹.飞航导弹. 2002, (6):20~27
3徐勤勇.高超声速飞行器总体概念研究.西北工业大学硕士学位论文. 2005:1~5
4臧国才,李树常.弹箭空气动力学.兵器工业出版社, 1989:202~230
5瓦弗洛缅也夫,科普托夫.弹道式导弹设计和试验.国防工业出版社, 1980:1~193
6乔洋.中远程高超音速空舰导弹关键技术研究.西北工业大学硕士学位论文. 2003:1~12
7韩品尧.战术导弹总体设计原理.哈尔滨工业大学出版社, 2002:15~50
8阮春荣.大气中飞行的最优轨迹.宇航出版社, 1987:1~97 156~200
9 A. Miele. Flight Mechanics Theory of Flight Path. Addison-Wesley Reading, 1962:20~27
10钱杏芳等.导弹飞行力学.北京理工大学出版社, 2000:1~200
11 J. S. Chern, N. X. Vinh. Optimum Reentry Trajectories of a Lifting Vehicle. NASA. CR-3236,1980:15~20
12 D. R. Chapman. An Approximate Analytical Method for Studying Entry into Planetary Atmospheres. NASA. TR-R-11, 1980:16~28
13 J. S. Chern, N. X. Vinh. Optimum Reentry Trajectories of a Lifting Vehicle. NASA. CR-3236,1980:20~30
14刑继祥,张春蕊,徐洪泽.最优控制应用基础.科学出版社, 2003:1~100
15 AIAA White Paper. Current State of the Art: Multidisciplinary Aerospace Design Optimization. AIAA. MDO Technical Committee. 1991:30~40
16 Jaroslaw Sobieszczanski-Sobieski, Haftka. Multidisciplinary erospace Design Optimization: Survey of Recent Developments. AIAA-96-0711:17~30
17谷良贤,温炳恒.导弹总体设计原理.西北工业大学出版社, 2004:10~40
18 K. F. Hulme, C. L. Bloebaum. A Comparison of Solution Strategies for Simulink-Based Multidisciplinary Aerospace Design Optimization. AIAA-98-4977:21~31
19 Srinivas Kodiyalam. Evaluation of Methods for Multidisciplinary Design Optimization (MDO). NASA. CR-2000-210313:31~40
20孙明玮,彭南楠,杨明.导弹最优滑翔弹道的设计及存在的问题。首届全国航空航天领域中的力学问题学术研讨会.北京. 2004:174~177
21彭伟斌,吴德隆.升力式航天器再入最优轨迹研究.弹道学报. 2003, (4):1~6
22颜仲新,刘鼎臣,胡海.反舰导弹飞行弹道探讨.飞航导弹. 2004, (2):33~36
23关世义.飞航导弹:概念和定义的探讨.飞航导弹. 2004, (9):1~7
24许志.高超声速飞行器动力学与动态特性分析.西北工业大学硕士学位论文.2005:1~5
25王勇.某型空地导弹总体设计.西北工业大学硕士学位论文. 2002:1~15
26孙洪梅.全程控制近程地地导弹总体方案设计.西北工业大学硕士学位论文. 2003:1~30
27张明,田宏伟,梁彦.冲压发动机在战术导弹上的应用.飞航导弹. 2005, (6):7~12
28杨卫丽,陈雨杰.高超声速巡航导弹及其关键技术.现代军事. 2003, (10):8~12
29张磊.弹道导弹突防问题的研究.北京航空航天大学硕士学位论文. 2002:1~50
30关世义.飞航导弹弹道述评.飞航导弹. 1996, (8):1:7
31薛成位.弹道导弹工程.中国宇航出版社, 2002:1~30
32 R. S. Sellar, S. M. Batill, J. E. Renaud. Concurrent Subspace Optimization for Multidisciplinary System Design. AIAA-96-0714:20~30
33 M. Kroo, Valerie Manning. Collaborative Optimization: Status and Directions. AIAA-2000-4721:1~11
34 P. Giesing, M. Jean-Francois. A Summry of Industry MDO Applications and Needs. AIAA-98-4737:12~19
35 N. X. Vinh, A. Busemann, R. D. Culp. Hypersonic and Planetary Entry Flight Mechanics. The University of Michigan Press. Ann Arbor, 1989:15~22
36 H. W. Stone, R. W. Powell. Entry Dynamics of Space Shuttle Orbiter With Longitudinal Stability and Control Uncertainties at Supersonic and Hypersonic Speeds. NASA. TN-1084, 2001:1~20
37 N. X. Vinh, A. Dobrzelecki. Non-linear Longitudinal Dynamics of an Orbital Lifting Vehicle. NASA. CR-1449, 1996:9~20
38 E. Bryson, W. F. Denham. A steepest-ascent method for solving optimum programming problems. Applied Mechanics, 1962, (29): 247~257
39 E. Sanger, J. Bredt. A Rocket Drive for Long Range Bombers. Tanslation CGD-32. Navy Dept, 1994:111~130
40 E. Bryson, W. F. Denban, F. J. Canrroll, K. Mikami. Determination of lift or drag problems to minimize reentry heating. J. Aerospace Sci, 1998, (29):420~430
41 E. S. Levinsky. Applications of ineweight constraints to variational problems of lifting reentry. J. Aerospace Sci, 1992, (29):400~409
42 C. T. Leondes, R.A. Niemann. Optimization of aerospace reentry vehicle trajectories through independent control of lift and drag. J. Spacecraft, 1999, (3): 618~623
43 Tu Lianghui, Yuan Jianping, Fang Qun, Luo Jianjun. Reentry skipping trajectory optimization using direct parameter optimization method. A Collection of Technical Papers - 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference. Vol 1 2006: 824~837
44 Vinh Nquyen X, Shi Yawen. Optimum multiple-skip trajectories. Acta Astronautica. Vol 41, No 2. 1997: 103~112
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