| Citation: | HE Tailong, CHEN Wanchun, LIU Fanget al. Adjoint analysis of steady glide trajectory with disturbance motion for hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(1): 109-122. doi: 10.13700/j.bh.1001-5965.2017.0545(in Chinese)
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Aiming at the problem of steady glide trajectory for hypersonic vehicle with disturbance motion, the adjoint method and its application were studied. Based on the mathematical definition of adjoint system, interpretations of adjoint method were achieved in a new and general way, which include performance projections in error budget form and the general meaning of single adjoint computer run. For stochastic linear system, the adjoint of covariance analysis was derived. Then, based on the definition of glide dynamics model and the definition of steady glide trajectory, the consistency of the definition of steady glide trajectory was explored by simulation analysis. The dynamics model was built for glide with disturbances on initial states and aerodynamic forces. Under the assumption of small perturbations, the linearized differential equation was obtained as a perturbation to the nominal steady glide trajectory. Finally, adjoint simulation examples were taken to analyze the influence of the deterministic and stochastic disturbances on final states of the nominal steady glide trajectory, and the results agree closely with those by nonlinear simulations and Monte Carlo simulations, but the adjoint simulation offers a substantial increase in computing efficiency.
| [1] |
SÄNGER E, BREDT J.A rocket drive for long range bombers: Translation No.CGD-32[R]. Technical Information Branch, Navy Dept., 1944.
|
| [2] |
HARPOLD J C, GRAVES C A.Shuttle entry guidance[J]. The Journal of the Astronautical Science, 1979, 37(3):239-268. http://d.old.wanfangdata.com.cn/NSTLQK/NSTL_QKJJ024582690/
|
| [3] |
胡锦川, 陈万春.高超声速飞行器平稳滑翔弹道设计方法[J].北航空航天大学学报, 2015, 41(8):1464-1475. http://d.old.wanfangdata.com.cn/Periodical/bjhkhtdxxb201508015
HU J C, CHEN W C.Steady glide trajectory planning method for hypersonic reentry vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(8):1464-1475(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/bjhkhtdxxb201508015
|
| [4] |
胡锦川, 张晶, 陈万春.高超声速飞行器平稳滑翔弹道解析解及其应用[J].北京航空航天大学学报, 2016, 42(5):961-968. http://bhxb.buaa.edu.cn/CN/abstract/abstract13694.shtml
HU J C, ZHANG J, CHEN W C.Analytical solutions of steady glide trajectory for hypersonic vehicle and planning application[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(5):961-968(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract13694.shtml
|
| [5] |
LANING J H, BATTIN R H.Random processes in automatic control[M]. New York:McGraw-Hill, 1956:225-253.
|
| [6] |
ZARCHAN P.Tactical and strategic missile guidance[M]. 6th ed.Reston: AIAA, 2012: 35-105.
|
| [7] |
ZADEH L A, DESOER C A.Linear system theory:The state space approach[M]. New York:McGraw-Hill, 1963:337-367.
|
| [8] |
WEISS M.Adjoint method for missile performance analysis on state-space models[J]. Journal of Guidance, Control, and Dynamics, 2005, 28(2):236-248. doi: 10.2514/1.7342
|
| [9] |
HE T L, CHEN W C.A new interpretation of adjoint method in linear time-varying system analysis[C]//IEEE International Conference on CIS and RAM. Piscataway, NJ: IEEE Press, 2017: 58-63.
|
| [10] |
ZARCHAN P.Complete statistical analysis of nonlinear missile guidance systems-SLAM[J]. Journal of Guidance, Control, and Dynamics, 1979, 2(1):71-78. doi: 10.2514/3.55834
|
| [11] |
WEISS M, BUCCO D.Handover analysis for tactical guided weapons using the adjoint method: AIAA-2005-6157[R]. Reston: AIAA, 2005.
|
| [12] |
BUCCO D, WEISS M.Adjoint analysis of guidance systems with nonstandard inputs[J]. Journal of Guidance Control & Dynamics, 2015, 38(9):1800-1809. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=8a5acac7658069424e6deb169296573c
|
| [13] |
BUCCO D.Aerospace applications of adjoint theory: ADA526349[R]. Edinburgh: Defence Science and Technology Group, 2010.
|
| [14] |
SARACHIK P, KREINDLER E.Concerning adjoints of discrete-time systems[J]. IEEE Transactions on Automatic Control, 1965, 10(3):350-352. doi: 10.1109/TAC.1965.1098139
|
| [15] |
BROGAN W.Performance analysis of continuous, sampled, and multirate-sampled systems with random inputs[J]. IEEE Transactions on Automatic Control, 1967, 12(5):599-601. doi: 10.1109/TAC.1967.1098690
|
| [16] |
WEISS M, BUCCO D.Adjoint method for hybrid guidance loop state-space models[J]. Journal of Guidance, Control, and Dynamics, 2015, 38(4):614-622. doi: 10.2514/1.62954
|
| [17] |
林晓辉, 崔乃刚, 刘暾.伴随理论及其在仿真中应用的研究[J].航天控制, 1996(3):61-65. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK199600914687
LIN X H, CUI N G, LIU T.Research on adjoint system theory and its application in simulation technology[J]. Aerospace Control, 1996(3):61-65(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK199600914687
|
| [18] |
邹晖, 陈万春, 邢晓岚.导弹制导精度MATRIXx伴随分析系统[J].飞行力学, 2001, 19(4):73-77. doi: 10.3969/j.issn.1002-0853.2001.04.018
ZOU H, CHEN W C, XING X L.MATRIXx adjoint system for miss distance analysis[J]. Flight Dynamics, 2001, 19(4):73-77(in Chinese). doi: 10.3969/j.issn.1002-0853.2001.04.018
|
| [19] |
TSIEN H S.Engineering cybernetics[M]. New York:McGraw-Hill, 1954:178-197.
|
| [20] |
陈克俊, 刘鲁华, 孟云鹤.远程火箭飞行动力学与制导[M].北京:国防工业出版社, 2014:262-263.
CHEN K J, LIU L H, MENG Y H.Launch vehicle flight dynamics and guidance[M]. Beijing:National Defence Industry Press, 2014:262-263(in Chinese).
|
| [21] |
GREEN M, LIMEBEER D J N.Linear robust control[M]. Upper Saddle River:Prentice-Hall, 1995:85-86.
|
| [22] |
PHILLIPS T H.A common aero vehicle (CAV) model, description, and employment guide[R]. Arlington, VA: Schafer Corporation for AFRL and AFSPC, 2003.
|
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