In this paper, a novel composite efficiency factor model has been proposed for the trajectory optimization of gun-launched gliding guided projectiles. The composite efficiency factor is based on the reduction of glide efficiency associated with the maneuvering capability. The influences of the composite efficiency factor on flight parameters have been investigated. Both the constant composite efficiency factor and an equilibrium glide assumption are simulated, and both are feasible by adjusting the composite efficiency factor with no terminal constraints. Additionally, the optimized composite efficiency factor model with a tightened constraint of the canard deflection angle has been performed and has demonstrated its applicability and effectiveness through case studies with different impact constraints, which can effectively eliminate the oscillatory phenomenon produced by only optimizing the glide efficiency. In comparison with several traditional optimization indices, the validity and superior features of optimizing the composite efficiency factor have also been analyzed in detail. Moreover, a simple simulation of the shaping optimization of the composite efficiency factor demonstrates an excellent improvement in the reserved terminal glide, the maneuvering capabilities, and the damage effect. These results demonstrate that the proposed approach provides a feasible application and potential workhorse for trajectory design and optimization.
Composite-Efficiency-Factor-Based Trajectory Optimization for Gliding Guided Projectiles
Journal of Spacecraft and Rockets ; 55 , 1 ; 66-76
2017-10-06
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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