Journal of Astronautics ›› 2017, Vol. 38 ›› Issue (10): 1048-1056.doi: 10.3873/j.issn.1000-1328.2017.10.005

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Range Estimation and Analysis for Extended Trajectory Based on Drag Reduction Design

LING Wang hui, XIAN Yong, GUO Wei lin, LI Jie, ZHANG Da qiao   

  1. 7th Department, Rocket Force University of Engineering, Xi’an 710025, China
  • Received:2017-05-24 Revised:2017-07-19 Online:2017-10-15 Published:2017-10-25


In order to realize the quantitative analysis of the trajectory and the evaluation of the extend range by using the drag reduction design, a fast and accurate estimation method is proposed based on the basic parameters of a missile. By establishing a drag reduction model, an aerodynamic drag coefficient table is calculated. Then the speed calculation formula is integrated item by item. The initial value of the state at the shutdown point and the range are obtained by the height approximation and the fitting aerodynamic coefficient. After the iteration, the result satisfies the accuracy requirements of the range. The simulation results show that the heuristic calculation of the height and the aerodynamic coefficients can effectively and quickly get the satisfying results. Under the drag reduction design, the final missile range is increased by 162.36 km and the extended-range effect is obvious.

Key words: Drag reduction design, Trajectory extension, Range rapid estimation, Aerodynamic coefficient fit, Iteration

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