RBCC-RKT两级入轨飞行器飞行轨迹优化方法
收稿日期: 2013-07-12
修回日期: 2013-09-13
网络出版日期: 2013-11-01
Trajectory Optimization Method in Two-stage-to-orbit RBCC-RKT Launch Vehicle
Received date: 2013-07-12
Revised date: 2013-09-13
Online published: 2013-11-01
针对火箭基组合循环（RBCC）发动机比冲和推进剂质量流量随飞行条件改变而不断变化的特点，提出了通过增广拉格朗日遗传算法优化飞行器飞行轨迹的方法，在飞行器气动参数和发动机比冲已知、最大飞行动压给定等条件下，进行了火箭基组合循环发动机-液体火箭（RKT）发动机推进的水平起飞两级入轨（TSTO）飞行器飞行轨迹优化计算。研究结果表明：在飞行俯仰角和发动机推进剂质量流量变化范围已知的情况下，利用该方法能够在较好满足给定约束条件的情况下，优化得到飞行俯仰角和发动机流量随时间的变化关系，为飞行轨迹初步设计提供参考。
阮建刚 , 何国强 , 吕翔 . RBCC-RKT两级入轨飞行器飞行轨迹优化方法[J]. 航空学报, 2014 , 35(5) : 1284 -1291 . DOI: 10.7527/S1000-6893.2013.0389
In view of the fact that the specific impulse and propellant mass flow rate of a rocket based combined cycle (RBCC) engine change constantly with flight conditions, a method based on augmented Lagrangian genetic algorithm for optimizing the trajectory of a RBCC-RKT two-stage-to-orbit (TSTO) horizontal takeoff launch vehicle is established when the aircraft aerodynamic parameters, the engine specific impulse and the maximum flying dynamic pressure are the constant values. The result shows that employed the method and given the range of flight program angle and propellant mass flow rate between a min and a max, the constraints can be satisfied and the history of flight program angle and propellant mass flow rate are optimized to provide a reference for the scheme demonstration and preliminary concept design of the vehicle.
[1] Chojnacki K T, Hawk C W. An assessment of the rocket-based combined cycle propulsion system for earth-to-orbit transportation, AIAA-1993-0183. Reston: AIAA, 1993.
[2] Xian Y, Xu L J. Study of designing trajectory missile's flight process based on genetic algorithm[J]. Journal of System Simulation, 2009, 21(5): 1502-1504. (in Chinese) 鲜勇, 许立军. 遗传算法在导弹飞行程序设计中的运用研究[J]. 系统仿真学报, 2009, 21(5): 1502-1504.
[3] Luo Y Z, Tang G J, Liang Y G, et al. Integrated optimization design for trajectory/system parameter[J]. Chinese Space Science and Technology, 2003(5): 16-21. (in Chinese) 罗亚中, 唐国金, 梁彦刚, 等. 近地轨道运载火箭轨迹/总体参数一体化优化设计[J]. 中国空间科学技术, 2003(5): 16-21.
[4] Hank J M. Comparative analysis of two-stage-to-orbit rocket and airbreathing reusable launch vehicles for military applications. Ohio: Air Force Institute of Technology, 2006: 26-28.
[5] Bradford J E, Olds J R. Improvements and enhancements to scream, a conceptual rbcc engine analysis tool, AIAA-1998-3775. Reston: AIAA, 1998.
[6] Olds J R. Two options for flight testing rocket-based combined-cycle engines[J]. Journal of Spacecraft and Rockets, 1999, 36(5): 693-700.
[7] Olds J R, Budianto I A. Constant dynamic pressure trajectory simulation in POST, AIAA-1998-0302. Reston: AIAA, 1998.
[8] Caldwell R A. Weight analysis of two-stage-to-orbit reusable launch vehicles for military applications. Ohio: Air Force Institute of Technology, 2005: 79-82.
[9] Brauer G L, Cornick D E, Stevenson R. Capabilities and applications of the program to optimize simulated trajectories, NASA-CR-2770. Washington, D.C.: NASA, 1977.
[10] Germaln B S, Olds J R, Mclntire J, et al. A small pay load-class TSTO vehicle concept utilizing rocket-based combined cycle propulsion, AIAA-2001-3516. Reston: AIAA, 2001.
[11] Wang H Q, He G Q, Liu P J, et al. Trajectory and mass analysis of RBCC-powered cruise vehicle[J]. Journal of Northwestern Polytechnical University, 2006, 26(4): 774-777. (in Chinese) 王厚庆, 何国强, 刘佩进, 等. 以RBCC为动力的巡航飞行器轨迹与质量分析[J]. 西北工业大学学报, 2006, 26(4): 774-777.
[12] Lu X, He G Q, Liu P J. Ascent trajectory design method for RBCC-powered vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(7): 1331-1337. (in Chinese) 吕翔, 何国强, 刘佩进. RBCC飞行器爬升段轨迹设计方法[J]. 航空学报, 2010, 31(7): 1331-1337.
[13] Chen G, Wan Z M, Xu M, et al. Overview of spacecraft trajectory optimization using genetic algorithm[J]. Journal of Ballistics, 2006, 18(1): 1-5. (in Chinese) 陈刚, 万自明, 徐敏, 等. 遗传算法在航天器轨迹优化中的应用[J]. 弹道学报, 2006, 18(1): 1-5.
[14] Wang Z G, Shi Z J. Long-range rocket and satellite orbit mechanics foundation[M]. Xi'an: Northwestern Polytechnic University Press, 2006: 74-97. (in Chinese) 王志刚, 施志佳. 远程火箭与卫星轨道力学基础[M].西安: 西北工业大学出版社, 2006: 74-97.
[15] Qian X F, Lin R X, Zhao Y N. Missile flight aerodynamics[M]. Beijing: Beijing Institute of Technology Press, 2003.(in Chinese) 钱杏芳, 林瑞雄, 赵亚男. 导弹飞行力学[M]. 北京: 北京理工大学出版社, 2003.
[16] Gan C X, Liu J X. Design for ballistic missile and launch vehicle[M]. Beijing: National Defence Industry Press, 1996.(in Chinese) 甘楚雄, 刘冀湘.弹道导弹与运载火箭总体设计[M]. 北京: 国防工业出版社, 1996.
[17] Conn A R, Gould N I M, Toint P L. A globally convergent augmented lagrangian algorithm for optimization with general constraints and simple bounds[J]. SIAM Journal on Numerical Analysis, 1991, 28(2): 545-572.
[18] Conn A R, Gould N I M, Toint P L. A globally convergent augmented lagrangian barrier algorithm for optimization with general inequality constraints and simple bounds, mathematics of computation[J]. Mathematics of Computation of the American Mathematical Society, 1997, 66(217): 261-288.
[19] Olds J, Bradford J. Simulated combined-cycle rocket engine analysis module: a conceptual RBCC engine design tool, AIAA-1997-2760. Reston: AIAA, 1997.
[20] Shaughnessy J D. Hypersonic vehicle simulation model, NASA-TM-10261. Washington, D.C.: NASA, 1990.
[21] Brock M A. Performance study of two-stage-to-orbit reusable launch vehicle propulsion alternatives. Ohio: Air Force Institute of Technology, 2004: 80-83.
/
| 〈 |
|
〉 |
CJA