Aiming at solving the midcourse guidance problem of exo-atmosphere missile under the influence of earth's oblateness perturbation
a prediction model for missile guidance was proposed based on BP neural network. This method provides a new training sample set constructed by the analytical formula of trajectory deviation. First
by using the pole transform method
the missile's J
2
perturbed gravity is decomposed into the disturbing function related to its flight trajectory. Then
with the state space matrix method
the analytic solution of trajectory deviation with the J
2
perturbation is calculated. Finally
using trajectory deviation function to construct a wide range of traini
ng sample set
the BP neural network of prediction model is established. The neural network can forecast the virtual target point information
so as to calculate the vector of gained velocity for midcourse guidance control. Using the modified algorithm
the trajectory deviation of J
2
perturbation can be directly solved by pole transform and state transition matrix
avoiding large-scale numerical calculation. The BP neural network has powerful learning and training ability
ensuring the comprehensiveness and accuracy of the prediction model and saving calculation time by the off-line training and learning before the simulation tests. In comparison with traditional correction method of Lambert guidance
this modified algorithm can satisfy the requirements on both efficiency and accuracy of real-time computation
being of practical engineering significance.
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references
BATTIN R H. Introduction to the mathematics and methods of astrodynamics [M]. Reston, VA, USA: AIAA, 1999: 325-417.
AHN J, lEE S. Lambert algorithm using analytic gradients [J]. Journal of Guidance, Control, and Dynamics, 2013, 36(6): 1751-1761.
AHN J, BANG J, LEE S. Acceleration of zero-revolution Lambert's algorithms using table-based initialization [J]. Journal of Guidance, Control, and Dynamics, 2015, 38(2): 335-342.
ZHANG Gang, CAO Xibin, ZHOU Di. Two-impulse cotangent rendezvous between coplanar elliptic and hyperbolic orbits [J]. Journal of Guidance, Control, and Dynamics, 2014, 37(3): 965-969.
WAILLIEZ S E. On Lambert's problem and the elliptic time of flight equation: a simple semi-analytical inversion method [J]. Advances in Space Research, 2014, 53(5): 890-898.
XU Ming, TAN Tian, LI Zhiwu, et al. Optimal correction strategy during Lambert transfer from view of probability [J]. Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(5): 574-578.
HU Zhengdong, GUO Caifa, CAO Yuan, et al. Transition trajectory planning and guidance for orbital bombing vehicle [J]. Journal of Solid Rocket Technology, 2009, 32(5): 473-479.
CHAI Hua, ZHONG Ming, LIANG Yangang. Midcourse guidance of interception using state transition matrix [J]. Journal of National University of Defense Technology, 2015, 37(4): 137-142.
YAMADA K, KIMURA M. New state transition matrix for formation flying in J2-perturbed elliptic orbits [J]. Journal of Guidance, Control, and Dynamics, 2012, 35(2): 536-547.
DENG Yibing, HU Wei, GAO Feng, et al. Application of genetic neural network to decision support system for environmental control and life support system [J]. Journal of Xi'an Jiaotong University, 2010, 44(7): 64-69.