高超声速巡航导弹弹道设计与优化方法研究
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摘要
弹道设计是导弹总体设计和分系统设计(如发射系统、导航系统和结构设计等)的先导,是以空气动力学、飞行力学理论和方法为基础,根据技战术要求,综合考虑发动机性能、气动特性、发射/助推方式、过载、攻角等约束条件,进行设计与优化。本文以高超声速巡航导弹为背景,完成了弹道的设计与优化,主要工作包括以下几个方面:
首先,对与高超声速导弹弹道设计相关的关键技术进行了分析。比较了高超声速导弹几种常见构型的气动特性,重点对乘波体构形的优势进行了分析;介绍了几种类型的超燃冲压发动机,并将它们的性能与其余种类的发动机进行了比较;还对高超声速导弹的发射与助推方式进行了讨论和分析。为后续的弹道设计与优化在气动布局与推进系统两方面提供了基础。
其次,对弹道优化理论进行了介绍。分析了弹道优化的基本问题,包括弹道优化的本质、优化数学模型的建立、优化模型的迭代解法和收敛终止条件等;在此基础上引入了一种求解有约束优化问题的方法(SUMT法)和一种求解无约束优化问题的方法(Hooke-Jeeves模式搜索法)。
接着,对高超声速巡航导弹的纵向弹道进行了优化。结合高超声速巡航导弹的特点,建立了相应的数学模型。优化模型以射程最远为性能指标(目标函数),设计变量取为四维设计量(助推段攻角大小、助推段平均推重比、导弹平均推重比和最大巡航马赫数),在给定高超声速巡航导弹飞行过程中需要满足约束条件的基础上,采用SUMT法将有约束优化问题转化为无约束优化问题后,使用Hooke-Jeeves模式搜索法对最优解进行了求取。优化结束后,对优化参数进行了分析,以判断解的最优性和性能指标对设计变量的敏感度。
最后,对高超声速巡航导弹的主动规避弹道进行了初步设计。介绍了主动突防技术,在此基础上给出了一种针对比例导引拦截器的主动规避弹道设计方法。这种方法需要对拦截器种类进行识别和理论拦截点状态进行估计,以便求出正弦机动时需要的机动幅值和频率。
Trajectory design should be considered primarily in the integrated design and subsystem design (launch system, guidance system, structural system and etc.). Based on the actual technique and tactics requirements, it takes constraint conditions such as the engine’s performance, missile’s aerodynamic characteristic, launch/boost mode, overload and angle of attack into consideration and is built on the aerodynamics, flight dynamics theory and interrelated techniques. This thesis designs a hypersonic cruise missile’s trajectory and optimizes it. The main research is listed as below:
First of all, the characteristics of the hypersonic cruise missile are analyzed. It includes introduction of various styles of scramjet engine, analysis of the primary technical parameter of scramjet engine, the launching and boosting way of hypersonic vehicle and comparisons of pneumatic characteristics between aerodynamic configurations focus on configurative advantage of the wave-rider.
Secondly, trajectory optimization theories are introduced. Fundamental issues of trajectory optimization are analyzed, in which includes that the essence of trajectory optimization, establishment of optimization model, iterative solution of optimization model, convergent terminative conditions and etc. As a result, SUMT is applied to constrained optimization solution, and Hooke-Jeeves mode search method is applied to unconstrained optimization solution.
Thirdly, longitudinal trajectory of the hypersonic cruise missile is optimized. Considered characteristics of the hypersonic cruise missile, the trajectory prediction model is established. Valued by the range as performance index and four-dimensional variables taken as design variables, this constrained optimization problem is translated into unconstrained optimization problem in SUMT method after specify constraint conditions are defined. Then Hooke-Jeeves pattern search is applied. The optimized parameters are analyzed after steps above, in order to judge the optimality of solution and the sensitivity of performance index to design variables.
Finally, eluding trajectory is designed preliminarily. Based on intelligence penetration technology, a design method of intelligence eluding trajectory is showed which aims at the proportional navigation interceptor. There needs to identify the interceptor's sort and estimates its state at the intercept point in this method, so as to compute the sine-wave maneuver amplitude and frequency.
首先,对与高超声速导弹弹道设计相关的关键技术进行了分析。比较了高超声速导弹几种常见构型的气动特性,重点对乘波体构形的优势进行了分析;介绍了几种类型的超燃冲压发动机,并将它们的性能与其余种类的发动机进行了比较;还对高超声速导弹的发射与助推方式进行了讨论和分析。为后续的弹道设计与优化在气动布局与推进系统两方面提供了基础。
其次,对弹道优化理论进行了介绍。分析了弹道优化的基本问题,包括弹道优化的本质、优化数学模型的建立、优化模型的迭代解法和收敛终止条件等;在此基础上引入了一种求解有约束优化问题的方法(SUMT法)和一种求解无约束优化问题的方法(Hooke-Jeeves模式搜索法)。
接着,对高超声速巡航导弹的纵向弹道进行了优化。结合高超声速巡航导弹的特点,建立了相应的数学模型。优化模型以射程最远为性能指标(目标函数),设计变量取为四维设计量(助推段攻角大小、助推段平均推重比、导弹平均推重比和最大巡航马赫数),在给定高超声速巡航导弹飞行过程中需要满足约束条件的基础上,采用SUMT法将有约束优化问题转化为无约束优化问题后,使用Hooke-Jeeves模式搜索法对最优解进行了求取。优化结束后,对优化参数进行了分析,以判断解的最优性和性能指标对设计变量的敏感度。
最后,对高超声速巡航导弹的主动规避弹道进行了初步设计。介绍了主动突防技术,在此基础上给出了一种针对比例导引拦截器的主动规避弹道设计方法。这种方法需要对拦截器种类进行识别和理论拦截点状态进行估计,以便求出正弦机动时需要的机动幅值和频率。
Trajectory design should be considered primarily in the integrated design and subsystem design (launch system, guidance system, structural system and etc.). Based on the actual technique and tactics requirements, it takes constraint conditions such as the engine’s performance, missile’s aerodynamic characteristic, launch/boost mode, overload and angle of attack into consideration and is built on the aerodynamics, flight dynamics theory and interrelated techniques. This thesis designs a hypersonic cruise missile’s trajectory and optimizes it. The main research is listed as below:
First of all, the characteristics of the hypersonic cruise missile are analyzed. It includes introduction of various styles of scramjet engine, analysis of the primary technical parameter of scramjet engine, the launching and boosting way of hypersonic vehicle and comparisons of pneumatic characteristics between aerodynamic configurations focus on configurative advantage of the wave-rider.
Secondly, trajectory optimization theories are introduced. Fundamental issues of trajectory optimization are analyzed, in which includes that the essence of trajectory optimization, establishment of optimization model, iterative solution of optimization model, convergent terminative conditions and etc. As a result, SUMT is applied to constrained optimization solution, and Hooke-Jeeves mode search method is applied to unconstrained optimization solution.
Thirdly, longitudinal trajectory of the hypersonic cruise missile is optimized. Considered characteristics of the hypersonic cruise missile, the trajectory prediction model is established. Valued by the range as performance index and four-dimensional variables taken as design variables, this constrained optimization problem is translated into unconstrained optimization problem in SUMT method after specify constraint conditions are defined. Then Hooke-Jeeves pattern search is applied. The optimized parameters are analyzed after steps above, in order to judge the optimality of solution and the sensitivity of performance index to design variables.
Finally, eluding trajectory is designed preliminarily. Based on intelligence penetration technology, a design method of intelligence eluding trajectory is showed which aims at the proportional navigation interceptor. There needs to identify the interceptor's sort and estimates its state at the intercept point in this method, so as to compute the sine-wave maneuver amplitude and frequency.
引文
1朱荣昌.未来战争中的高超音速飞行器.国际航空. 1999(2):23~27
2康志敏.高超声速飞行器发展战略研究.现代防御技术. 2000,28(4):27~40
3马正兵.空中超级杀手—高超音速巡航导弹.中国航天. 2000(10):31~32
4刘英姿.国外高超音速飞行器研制动态.飞航导弹. 1998(7):11~16
5刘桐林.国外高超声速技术发展探析.飞航导弹. 2002(6):30~40
6周军.美国高超声速研制的最新进展.飞航导弹. 2003(1): 31~35
7丛敏.美国启动高超声速飞行计划.飞航导弹. 2002(11):6~8
8刘桐林.俄罗斯高超声速技术飞行试验计划.武器系统. 2000(4):23~30
9丛敏.俄罗斯试射高超声速导弹.飞航导弹. 2004(9):24~25
10徐文.德国的高超声速导弹.飞航导弹. 2004(1):1~4
11工淑芬.法国航空航天公司进行高超音速研究.武器系统. 1998(9):29~30
12丛敏.印度依靠本国力量开发导弹—问津可重复使用的高超声速导弹.飞航导弹. 2001(1):3~6
13何广.日本高超音速飞行技术发展迅速.中国航天. 1992(6):44~45
14 J. P. Marec. Optimal Space Trajectories. Elsevier, Amsterdam. 1979
15 V.F.Krotov, V.Z.Bukreev and V.I.Gurman. New Variational Methods in Flight Dynamics. NASA TTF-657. 1971
16 L. M. Shkadov, R. S. Bukhanova, V. F. Illarionov and V. P. Plokhikh. Mechanics of Optimum Three-Dimensional Motion of Aircraft in the Atmosphere. NASA TTF-777. 1975
17汤善同.飞行器的轨道优化与制导规律研究综述.现代防御技术. 2002, 30(1):32~37
18周浩,陈万春,殷兴良.高超声速飞行器滑行航迹优化.北京航空航天大学学报. 2006, 32(5):513~517
19陈志全,李忠应,关世义.巡航导弹航迹规划综述.战术导弹技术.1994 (3):29~32
20韩品尧.战术导弹总体设计原理.哈尔滨:哈尔滨工业大学出版社. 2000: 206~237
21俞玉森.数学规划的原理和方法.湖北:华中工学院出版社. 1985:246~251, 311~322
22 R. M. Stuckey, M. J. Lewis. Hypersonic Missile Requirements and Operational Tradeoff Studies. Journal of Spacecraft and Rockets. 2003, 40(2): 292~293
23 J. D. Shaughnessy, S. Z. Pinkckney, J. D. McMinn. Hypersonic Vehicle Simulation Model: Winged-cone Configuration. 1991, NASA-TM-1021610.
24 C. Walter, D. Scott, Holland, E. Charles, J. Cockrell. Aerodynamic Database Development for the Hyper-X Airframe Integrated Scramjet Propulsion Experiments. AIAA-2000-4006
25潘腾等. VTVL高超声速航天飞行器优化气动布局研究.导弹与航天运载技术. 1995(6):25~30
26赵桂林,胡亮,闻洁等.乘波构型和乘波飞行器研究综述.力学进展. 2003, 33(3):357~371
27牛本兵.“乘波体”气动外形设计综述.飞航导. 1998(8): 25~29
28姚文秀,雷麦芳,杨耀栋,王发民.高超声速乘波飞行器气动实验研究.宇航学报. 2002, 23(6):82~85
29 C. F. Newberry. The Conceptual Design of Deck Launched Waveride Configured Aircraft. Aircraft Design, 1998(1):159~191
30郭振华,董长虹.关于高超声速飞航导弹总体设计问题的探讨.飞航导弹. 1999(3):9~13
31司徒明.波载形高超音速巡航导弹与超燃冲压发动机的性能分析.战术导弹技术,1995(4): 25~28
32 T. Mitani, T. Hiraiwa, S. Sato, S. Tomioka, T. Kanda, K. Tarsi. Comparison of Scramjet Engine Performance in Mach 6 Vitiated and Storage-HeatedAir. Journal of Propulsion and Power, 1997, 13(5):635~642
33 M. Sitn and Y. Sheng. Preliminary Analysis of Scramjet with an Integrated Waverider Cruise Vehicle. AIAA-94-3089. 1994
34 V. Gusev, N. Blagoveshchensky and S. Zdonsky. The Integration of a Hyper-sonic Vehicle Airframe with an Airbreathing Engine. AIAA-93-5034
35 F. S. Billig. SCRAM-A Supersonic Combustion Ramjet Missile,AIAA-93-2329. 1993
36 P. L. Moses, V. L. Rausch, T. Luat hypersonic fight demonstrators-overview, status and future plans. Acta Astronautica. 2004(55):619~630
37 H. Sobieczky. Hypersonic waverider design from given shock waves. In:Anderson. Procedings of the first International Hypersonic Waverider Symposium. Maryland: University of Maryland, 1990
38丛敏.高超声速导弹的使用要求和性能比较研究.飞航导弹. 2002(5): 23~29
39 C. H. Chuang and M. Hitoshi. Periodic optimal cruise for a hyper-sonic vehicle with constrains. Journal of Spacecraft and Dockets, 1997, 34(2): 165~171
40 R. Callies, G. Wimmer. Optimal hypersonic flight trajectories with full safety in case of mission abort. AIAA Atmospheric Flight Mechanics Conference, Denver, CO. 2000(8):322~331
41 C. V. Hargraves, S.W. Paris. Direct Trajectory Optimization Using Nonlinear Programming and Collocation. Journal of Guidance, Control, and Dynamics. 1987,10(4):338~342
42 D.K. Schmidt and T. A. Lovell. Mission Performance and Design Sensitivities of Air-Breathing Hypersonic Launch Vehicles. Journal of Spacecraft and Rockets. 1997,34(2):158~164
43谷良贤.导弹总体一体化设计方法研究.弹箭与制导学报. 1996(2):21~26
44丛敏.高超声速导弹弹体的创新设计方案.飞航导弹. 1999(11):28~32
45魏权龄,王日爽,徐兵,汪家芸,白文林.数学规划与优化设计.北京:国防工业出版社. 1984:262~271, 411~443,542~566
46符曦.系统最优化及控制.北京:机械工业出版社. 2004:3~15, 388~402, 474~491
47郑权,张连生.罚函数与带不等式约束的总极值问题.计算数学. 1980, 2(2):13~21
48 www.nasa.gov/centers/langley/news/factsheets/FS-2004-03-85-LaRC.html
49刘陵,刘敬华,张榛.超音速燃烧与超音速燃烧冲压发动机.西安:西北工业大学出版社. 1993:19~30
50许志.高超音速飞行器动力学与动态特性分析.西北工业大学硕士论文. 2005:7~22
51谢春燕,李为民,娄寿春等.弹道导弹突防方案与拦截策略的对抗研究.现代防御技术, 2004(10):11~15
52张克等.巡航导弹攻防对抗策略研究.飞航导弹. 2001(6):1~5
53 I. Forte, A. Steinberg and J. Shinar. The Effects of Non-linear Kinematics inOptimal Evasion. Optimal Control Applications and Methods, 1983, (4):139 ~152
54 F. Imado and S. Miwa. Fighter Evasive Maneuvers Against Proportional Navigation Missile. Journal of Aircraft, 1986,23(11):825~930
55 Y. Yang and J. Jiang. Research of missile random maneuver strategy. Journal of Beijing University of Aeronautics and Astronautics, 2004,30(12): 1191~1194
56殷志红,崔乃刚等.主动机动突防导弹机动性能设计方法研究. 2006年中国飞行力学年会论文集.黄山. 2006: 124~130
2康志敏.高超声速飞行器发展战略研究.现代防御技术. 2000,28(4):27~40
3马正兵.空中超级杀手—高超音速巡航导弹.中国航天. 2000(10):31~32
4刘英姿.国外高超音速飞行器研制动态.飞航导弹. 1998(7):11~16
5刘桐林.国外高超声速技术发展探析.飞航导弹. 2002(6):30~40
6周军.美国高超声速研制的最新进展.飞航导弹. 2003(1): 31~35
7丛敏.美国启动高超声速飞行计划.飞航导弹. 2002(11):6~8
8刘桐林.俄罗斯高超声速技术飞行试验计划.武器系统. 2000(4):23~30
9丛敏.俄罗斯试射高超声速导弹.飞航导弹. 2004(9):24~25
10徐文.德国的高超声速导弹.飞航导弹. 2004(1):1~4
11工淑芬.法国航空航天公司进行高超音速研究.武器系统. 1998(9):29~30
12丛敏.印度依靠本国力量开发导弹—问津可重复使用的高超声速导弹.飞航导弹. 2001(1):3~6
13何广.日本高超音速飞行技术发展迅速.中国航天. 1992(6):44~45
14 J. P. Marec. Optimal Space Trajectories. Elsevier, Amsterdam. 1979
15 V.F.Krotov, V.Z.Bukreev and V.I.Gurman. New Variational Methods in Flight Dynamics. NASA TTF-657. 1971
16 L. M. Shkadov, R. S. Bukhanova, V. F. Illarionov and V. P. Plokhikh. Mechanics of Optimum Three-Dimensional Motion of Aircraft in the Atmosphere. NASA TTF-777. 1975
17汤善同.飞行器的轨道优化与制导规律研究综述.现代防御技术. 2002, 30(1):32~37
18周浩,陈万春,殷兴良.高超声速飞行器滑行航迹优化.北京航空航天大学学报. 2006, 32(5):513~517
19陈志全,李忠应,关世义.巡航导弹航迹规划综述.战术导弹技术.1994 (3):29~32
20韩品尧.战术导弹总体设计原理.哈尔滨:哈尔滨工业大学出版社. 2000: 206~237
21俞玉森.数学规划的原理和方法.湖北:华中工学院出版社. 1985:246~251, 311~322
22 R. M. Stuckey, M. J. Lewis. Hypersonic Missile Requirements and Operational Tradeoff Studies. Journal of Spacecraft and Rockets. 2003, 40(2): 292~293
23 J. D. Shaughnessy, S. Z. Pinkckney, J. D. McMinn. Hypersonic Vehicle Simulation Model: Winged-cone Configuration. 1991, NASA-TM-1021610.
24 C. Walter, D. Scott, Holland, E. Charles, J. Cockrell. Aerodynamic Database Development for the Hyper-X Airframe Integrated Scramjet Propulsion Experiments. AIAA-2000-4006
25潘腾等. VTVL高超声速航天飞行器优化气动布局研究.导弹与航天运载技术. 1995(6):25~30
26赵桂林,胡亮,闻洁等.乘波构型和乘波飞行器研究综述.力学进展. 2003, 33(3):357~371
27牛本兵.“乘波体”气动外形设计综述.飞航导. 1998(8): 25~29
28姚文秀,雷麦芳,杨耀栋,王发民.高超声速乘波飞行器气动实验研究.宇航学报. 2002, 23(6):82~85
29 C. F. Newberry. The Conceptual Design of Deck Launched Waveride Configured Aircraft. Aircraft Design, 1998(1):159~191
30郭振华,董长虹.关于高超声速飞航导弹总体设计问题的探讨.飞航导弹. 1999(3):9~13
31司徒明.波载形高超音速巡航导弹与超燃冲压发动机的性能分析.战术导弹技术,1995(4): 25~28
32 T. Mitani, T. Hiraiwa, S. Sato, S. Tomioka, T. Kanda, K. Tarsi. Comparison of Scramjet Engine Performance in Mach 6 Vitiated and Storage-HeatedAir. Journal of Propulsion and Power, 1997, 13(5):635~642
33 M. Sitn and Y. Sheng. Preliminary Analysis of Scramjet with an Integrated Waverider Cruise Vehicle. AIAA-94-3089. 1994
34 V. Gusev, N. Blagoveshchensky and S. Zdonsky. The Integration of a Hyper-sonic Vehicle Airframe with an Airbreathing Engine. AIAA-93-5034
35 F. S. Billig. SCRAM-A Supersonic Combustion Ramjet Missile,AIAA-93-2329. 1993
36 P. L. Moses, V. L. Rausch, T. Luat hypersonic fight demonstrators-overview, status and future plans. Acta Astronautica. 2004(55):619~630
37 H. Sobieczky. Hypersonic waverider design from given shock waves. In:Anderson. Procedings of the first International Hypersonic Waverider Symposium. Maryland: University of Maryland, 1990
38丛敏.高超声速导弹的使用要求和性能比较研究.飞航导弹. 2002(5): 23~29
39 C. H. Chuang and M. Hitoshi. Periodic optimal cruise for a hyper-sonic vehicle with constrains. Journal of Spacecraft and Dockets, 1997, 34(2): 165~171
40 R. Callies, G. Wimmer. Optimal hypersonic flight trajectories with full safety in case of mission abort. AIAA Atmospheric Flight Mechanics Conference, Denver, CO. 2000(8):322~331
41 C. V. Hargraves, S.W. Paris. Direct Trajectory Optimization Using Nonlinear Programming and Collocation. Journal of Guidance, Control, and Dynamics. 1987,10(4):338~342
42 D.K. Schmidt and T. A. Lovell. Mission Performance and Design Sensitivities of Air-Breathing Hypersonic Launch Vehicles. Journal of Spacecraft and Rockets. 1997,34(2):158~164
43谷良贤.导弹总体一体化设计方法研究.弹箭与制导学报. 1996(2):21~26
44丛敏.高超声速导弹弹体的创新设计方案.飞航导弹. 1999(11):28~32
45魏权龄,王日爽,徐兵,汪家芸,白文林.数学规划与优化设计.北京:国防工业出版社. 1984:262~271, 411~443,542~566
46符曦.系统最优化及控制.北京:机械工业出版社. 2004:3~15, 388~402, 474~491
47郑权,张连生.罚函数与带不等式约束的总极值问题.计算数学. 1980, 2(2):13~21
48 www.nasa.gov/centers/langley/news/factsheets/FS-2004-03-85-LaRC.html
49刘陵,刘敬华,张榛.超音速燃烧与超音速燃烧冲压发动机.西安:西北工业大学出版社. 1993:19~30
50许志.高超音速飞行器动力学与动态特性分析.西北工业大学硕士论文. 2005:7~22
51谢春燕,李为民,娄寿春等.弹道导弹突防方案与拦截策略的对抗研究.现代防御技术, 2004(10):11~15
52张克等.巡航导弹攻防对抗策略研究.飞航导弹. 2001(6):1~5
53 I. Forte, A. Steinberg and J. Shinar. The Effects of Non-linear Kinematics inOptimal Evasion. Optimal Control Applications and Methods, 1983, (4):139 ~152
54 F. Imado and S. Miwa. Fighter Evasive Maneuvers Against Proportional Navigation Missile. Journal of Aircraft, 1986,23(11):825~930
55 Y. Yang and J. Jiang. Research of missile random maneuver strategy. Journal of Beijing University of Aeronautics and Astronautics, 2004,30(12): 1191~1194
56殷志红,崔乃刚等.主动机动突防导弹机动性能设计方法研究. 2006年中国飞行力学年会论文集.黄山. 2006: 124~130