Articles

A Vacuum Adaptive Iterative Guidance Method of Launch Vehicle Based on Optimal Analytical Solution

Expand
  • 1. Department of Astronautics Engineering, Harbin Institute of Technology, Harbin 150001, China;
    2. China Aerodynamics Research & Development Center, Mianyang 621000, China

Received date: 2010-12-20

  Revised date: 2011-03-11

  Online published: 2011-09-16

Abstract

Along with the increasing diversity and complexity of space launch missions, it is of great significance to study new adaptive guidance methods that have higher precision and adaptability to satisfy the maneuverability, flexibility and high satellite injection accuracy requirements of launch vehicles. This paper presents a summary of the analytical solutions of optimal vacuum trajectories for launch vehicles and proposes a new iterative guidance method different from the traditional iterative guidance based on Newton method.This new method is particularly suitable for large attitude angles. Its analytic form of the Jacobian matrix is derived. Finally, numerical simulations are performed. Simulation results demonstrate that the adaptive iterative guidance proposed has higher precision and powerful adaptability. Besides, the algorithm in this guidance method is simple and easy to implement. Therefore, it possesses high engineering application value.

Cite this article

FU Yu, CHEN Gong, LU Baogang, GUO Jifeng, CUI Naigang . A Vacuum Adaptive Iterative Guidance Method of Launch Vehicle Based on Optimal Analytical Solution[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011 , 32(9) : 1696 -1704 . DOI: CNKI:11-1929/V.20110511.1345.001

References

[1] 陈新民, 余梦伦. 迭代制导在运载火箭上的应用研究[J]. 宇航学报, 2003, 24(5): 484-489. Chen Xinmin, Yu Menglun. Study of iterative guidance application to launch vehicles[J]. Journal of Astronautics, 2003, 24(5): 484-489. (in Chinese)

[2] 刘云凤, 罗俊, 赵世范. 闭路制导在小型固体运载火箭中的应用[J]. 航天控制, 2005, 23(3): 46-50. Liu Yunfeng, Luo Jun, Zhao Shifan. Application of closed loop guidance in small solid launch vehicle[J]. Aerospace Control, 2005, 23(3): 46-50. (in Chinese)

[3] 茹家欣. 液体运载火箭的一种迭代制导方法[J]. 中国科学E辑: 技术科学, 2009, 39(4): 696-706. Ru Jiaxin. An iterative guidance method for liquid launch vehicle[J]. Science in China Series E: Technological Sciences, 2009, 39(4): 696-706. (in Chinese)

[4] Chandler D C, Smith I E. Development of the iterative guidance mode with its application to various vehicles and missions[J]. Journal of Spacecraft and Rockets, 1967, 4(7): 898-903.

[5] 韩祝斋. 用于大型运载火箭的迭代制导方法[J]. 宇航学报, 1983, 1(1): 11-20. Han Zhuzhai. An iterative guidance method for the large launch vehicle[J]. Journal of Astronautics, 1983, 1(1): 11-20. (in Chinese)

[6] Lawden D F. Optimal trajectories for space navigation[M]. London: Butterworths, 1963:1-98.

[7] Jezewski D J. An optimal, analytic solution to the linear-gravity, constant-thrust trajectory problem[J]. Journal of Spacecraft and Rockets, 1971, 8(7): 793-796.

[8] Jezewski D J. N-burn optimal analytic trajectories. AIAA-1972-929, 1972.

[9] Calise A J, Melamed N, Lee S. Design and evaluation of a three-dimensional optimal ascent guidance algorithm[J]. Journal of Guidance, Control, and Dynamics, 1998, 21(6): 867-875.

[10] Dukeman G A. Atmospheric ascent guidance for rocket-powered launch vehicles. AIAA-2002-4559, 2002.

[11] Dukeman G A, Hill A. Rapid trajectory optimization for the Ares I launch vehicle. AIAA-2008-6288, 2008.

[12] Lu P, Sun H S, Tsai B. Closed-loop endo-atmospheric ascent guidance[J]. Journal of Guidance, Control, and Dynamics, 2003, 26(2): 283-294.

[13] Lu P, Zhang L J, Sun H S. Ascent guidance for responsive launch: a fixed-point approach. AIAA-2005-6453, 2005.

[14] Lu P, Griffin B, Dukeman G, et al. Rapid optimal multiburn ascent planning and guidance[J]. Journal of Guidance, Control, and Dynamics, 2008, 31(6): 1656-1664.

[15] Lu P, Pan B F. Highly constrained optimal launch ascent guidance[J]. Journal of Guidance, Control, and Dynamics, 2010, 33(2): 404-414.

[16] Su S. Advanced guidance algorithms for the Ares V cargo launch vehicle. Columbia: University of Missouri Columbia, 2008.

[17] McAdoo S F, Jr, Jezewski D J, Dawkins G S. Development of a method for optimal maneuver analysis of complex space missions. NASA TN D-7882, 1975.

[18] 于永江. 上面级制导方法研究. 哈尔滨: 哈尔滨工业大学航天学院, 2009. Yu Yongjiang. Research on guidance method of upper stage. Harbin: School of Aeronautics, Harbin Institute of Technology, 2009. (in Chinese)
Outlines

/