Abstract

The flow field phenomena that occur as a result of thrust vector control (TVC) system activity on a missile with lateral jets are very complex and influence all other components of the missile. Influence is more significant when TVC is generating commands, when jets are asymmetrically directed. The main goal of these study was to determine the influence of of the hot rocket motor's combustion products on the basis of the CFD model proven with the cold-jet simulation. Based on obtained experimental aerodynamic coefficients for the cold-jet simulation the preliminary aerodynamic CFD model was designed. Three-dimensional Reynolds averaged Navier-Stokes numerical aerodynamic and hot-jet simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. The study resulted in the definition of a methodology for the investigation of the jet reaction effects in a wind tunnel. A method for determining of the TVC system interference on the aerodynamic characteristics, as a basic prerequisite for structural, stability and performance analysis, was proposed. Mutual verification and validation process was carried out through experiment and proper application of the commercial CFD software code for calculation aerodynamic effects of the hot gases lateral jets on the performance of a guided missile. Experimental and computational results of the pitching moment coefficients are presented and agreed well with.

Highlights

  • Aerodynamic control, using canard or fin surfaces has several limitations, in response time due to the delay between the steering command and the effective manoeuvre, and in manoeuvrability when the dynamic pressure is low, i.e. at low velocity or high altitude [1],[2]

  • To ensure the required missile performance, modern air defence interceptors use lateral thrusters, especially at difficult targets or unusual conditions of use, even if this type of control leads to complex aerodynamic interactions, which are not foreseeable [3],[4]

  • Wind tunnel testing with cold jets sustainer simulation was performed for the determination of aerodynamics characteristics

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Summary

Introduction

Aerodynamic control, using canard or fin surfaces has several limitations, in response time due to the delay between the steering command and the effective manoeuvre, and in manoeuvrability when the dynamic pressure is low, i.e. at low velocity or high altitude [1],[2]. The resulting jet plume is deflected and acts as a massive obstacle located on the surface of the missile producing a complex flow developed by the interaction of the laterally blowing gas jet with the subsonic cross-flow, Figure 1., [5]. The objectives of the study were to fully analyze the effects of cold jet TVC system on the basis of the results of wind tunnel tests and CFD simulations, to complement the knowledge base about the influence of the supersonic lateral jet and subsonic crossflow, and to define the most appropriate similarity parameters for subsequent simulation of hot combustion products [5]. Wind tunnel testing with cold jets sustainer simulation was performed for the determination of aerodynamics characteristics. It was used for verification of the CFD model. With proven CFD model the influence of the hot rocket motor’s combustion product lateral jets was determined

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