Energy-based hybrid reentry guidance for hypersonic vehicles
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摘要: 针对大升阻比高超声速飞行器滑翔再入制导问题,提出一种基于能量的混合制导方法.建立以能量为自变量的三自由度运动学方程,利用拟平衡滑翔特性将过程约束转换成倾侧角约束.纵向制导在初始下降段采用固定数值倾侧角飞行,在拟平衡滑翔段基于剩余航程随能量单调变化的特性将标准轨迹进行分段,然后分段进行在线预测校正制导.侧向制导基于横程与能量的近似线性关系,设计了由分段漏斗形横程走廊控制的倾侧角反转逻辑,以保证侧向制导精度.分析研究和仿真结果表明该方法易于实现,有效减小了制导指令的解算时间,制导和落点精度高,且对再入初始偏差及过程扰动不敏感.Abstract: An energy-based hybrid reentry methodology was developed for hypersonic vehicles. The three-degree-of-freedom reentry kinematic equations was conducted based on energy, and typical inequality constraints was converted to the constraints of bank-angle by using quasi-equilibrium glide condition (QEGC). Longitude guidance used a constant bank angle in initial descent, and segmented the standard trajectory in quasi-equilibrium glide phase since the range-to-go was monotonically decreased with energy, then used predictor-corrector online in every segment to reduce the calculating time. Lateral guidance designed a lateral reversal logic based on the crossrange corridor for crossrange varied almost linearly with energy between two bank reversals. The simulation results show that the proposed algorithm has the obvious decrease of calculating time, high guidance precision and is not sensitive to initial errors and disturbers.
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[1] 赵汉元. 飞行器再入动力学和制导[M].长沙:国防科学技术大学出版社,1997:7-22 Zhao Hanyuan.Fight vehicle reentry dynamics and guidance[M].Changsha:National University of Defense Technology Press,1997:7-22(in Chinese) [2] Dukeman G A. Profile-following entry guidance using linear quadratic regulator theory[C]//AIAA Guidance,Navigation,and Control Conference and Exhibit.Monterey:AIAA,2002,4457:1-10 [3] Joshi A, Sivan K.Predictor corrector reentry guidance algorithm with path constraints for atmospheric entry vehicles[J].Journal of Guidance Control and Dynamics,2007,30(5):1307-1318 [4] Xue S B, Lu P.Constrained predictor-corrector entry guidance[J].Journal of Guidance Control and Dynamics,2010,33(4): 1273-1281 [5] Masciarelli J P, Westhelle C,Grave C.Aerocapture guidance performance for the neptune orbiter[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit.Rhode Island:AIAA,2004,4954:1-7 [6] 任章,袁国雄. 轨道武器战斗舱再入制导技术研究[J].航天控制,2005,23(2):4-7 Ren Zhang,Yuan Guoxiong.Study on reentry guidance technique for orbit weapon fighting cabin[J].Aerospace Control,2005,23(2):4-7(in Chinese) [7] 王俊波, 田源,任章.基于最优化问题的混合再入制导方法[J].北京航空航天大学学报,2010,36(1):736-740 Wang Junbo,Tian Yuan,Ren Zhang.Mixed guidance method for reentry vehicles based on optimization[J].Journal of Beijing University of Aeronautics and Astronautics,2010,36(1):736-740(in Chinese) [8] Hu J X, Chen K J,Zhao H Y,et al.Hybrid entry guidance for reusable launch vehicles [J].Journal of Astronautics,2007, 28(1): 213-217 [9] 水尊师,周军, 葛致磊.基于高斯伪谱方法的再入飞行器预测校正制导方法研究[J].宇航学报,2011,32(6):1249-1255 Shui Zunshi,Zhou Jun,Ge Zhilei.On-line predictor-corrector reentry guidance law based on Gauss pseudospectral method[J].Journal of Astronautics,2011,32(6):1249-1255(in Chinese) [10] Vinh N X, Busemann A,Culp R D.Hypersonic and planetary entry flight mechanics[M].Ann Arbor:Michigan University of Michigan Press,1980:26-27
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