| Citation: | XIAN Yong, REN Leliang, GUO Weilin, et al. Design of ascent trajectory of space vehicle in mobile launch condition[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(9): 1713-1722. doi: 10.13700/j.bh.1001-5965.2018.0782(in Chinese)
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In order to improve the mobile launch capability of space vehicle, the position, height, velocity magnitude, velocity azimuth and trajectory inclination of the injection point were used as terminal constraints to design the ascent trajectory under the condition that the mid-flight trajectory was determined. The space vehicle could be launched at any position in a certain range centered on the original launch point, and the high-precision shift with the mid-flight trajectory was completed. Considering many constraints and high-precision requirements of the injection point, and the nonlinear and strong coupling characteristics of the ascent trajectory, the two-stage and three-stage energy management model and the changeable-launching-plane transverse maneuvering model were designed, and then the gradient particle swarm algorithm with the blended disturbance operator was used to solve the ascent trajectory. The simulation results show that the high-precision shift with the mid-flight trajectory can be realized smoothly by optimized transverse maneuvering trajectory, and the average deviation of the position, height, velocity, velocity azimuth and trajectory inclination of the terminal injection point for ascent trajectory are 27.506 2 m, 2.125 4 m, 1.652 2 m/s, 0.072 8° and 0.029 0° respectively.
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