Investigation of the flight behavior of a flare-stabilized projectile using 6DoF simulations coupled with CFD

Abstract

Purpose The present work aims to investigate the capabilities of accurately predicting the six-degrees-of-freedom (6DoF) trajectory and the flight behavior of a flare-stabilized projectile using computational fluid dynamics (CFD) and rigid body dynamics (RBD) methods. Design/methodology/approach Two different approaches are compared for calculating the trajectory. First, the complete matrix of static and dynamic aerodynamic coefficients for the projectile is determined using static and dynamic CFD methods. This discrete database and the data extracted from free-flight experiments are used to simulate flight trajectories with an in-house developed 6DoF solver. Second, the trajectories are simulated solving the 6DoF motion equations directly coupled with time resolved CFD methods. Findings Virtual fly-out simulations using RBD/CFD coupled simulation methods well reproduce the motion behavior shown by the experimental free-flight data. However, using the discrete database of aerodynamic coefficients derived from CFD simulations shows a slightly different flight behavior. Originality/value A discrepancy between CFD 6DoF/RBD simulations and results obtained by the MATLAB 6DoF-solver based on discrete CFD data matrices is shown. It is assumed that not all dynamic effects on the aerodynamics of the projectile are captured by the determination of the force and moment coefficients with CFD simulations based on the classical aerodynamic coefficient decomposition.

Wind tunnel measurements of dynamic aerodynamic coefficients using a freely rotating test bench

“…The first numerical approach forces the projectile to describe a pure oscillation motion with small amplitude along the pitch axis during a rectilinear flight (Klatt et al , 2019). Thanks to this small amplitude, the pitching moment coefficient can be described by a first-order Taylor series expansion, as it is shown in (8): …”

Research on the Penetrator Characteristics and Flight Stability of Explosively Formed Penetrator

“…EFP는 행안정성을 비교한 결과를 발표하였다 [5] . 2019년 Li 등은 EFP의 비행 안정성을 개선하기 위해 일반적인 형태의 구형이 아닌 다각형의 라이너를 제작하여 관 통자 꼬리 부분 날개 형성에 관한 부분을 해석으로 모사하고 이를 설계 한 결과를 발표하였다 [6] .…”