Numerical Investigation of Jet Interaction for Missile with Continuous Type Side Jet Thruster

Kang, Kyoung Tai; Lee, Eunseok; Lee, Soogab

doi:10.5139/ijass.2015.16.2.148

Cited by 8 publications

(3 citation statements)

References 11 publications

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“…Many researchers have studied the lateral jet via numerical simulation and wind tunnel tests. Kang et al [4] used numerical simulation to investigate the jet interference effects under various conditions for the missile equipped with a continuous type lateral jet thruster. Wang et al [5] studied the interaction flow fields of a supersonic lateral jet penetrating the crossflow of projectiles with different fin configurations by detached eddy simulation.…”

Section: Introductionmentioning

confidence: 99%

Control Strategies for Flight Stability of Trajectory Correction Projectile with Air-Ducts Structure

Cui

Liu

Jiang

et al. 2022

Mathematical Problems in Engineering

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Aiming at the controllability of spin-stabilized projectile trajectory correction, a new two-dimensional trajectory correction projectile model with a controllable air-ducts structure suitable for the spin-stabilized projectile is proposed in this paper. Furthermore, control strategies of the projectile in the corrected configuration are studied to ensure a stable flight. The correction scheme of the projectile is innovated on the basis of the ram air control mechanism. The air-ducts structure is designed inside the projectile body, and the internal air valve is used to control the lateral air-jet to achieve trajectory correction of the projectile. This is a new two-dimensional trajectory correction scheme with a relatively simple control method. Firstly, the correction mechanism of the new air-ducts structure projectile is analyzed. Secondly, based on the dynamic equation of the projectile, the key parameters of the impulse air valve control, including the safe range of the working pulse width and frequency, are calculated, and the corresponding control strategies are proposed. Finally, the flow field of the projectile in the corrected configuration of the terminal trajectory is numerically simulated, and aerodynamic parameters of the projectile are obtained. Through stability conditions established in this paper and combined with aerodynamic parameters, the validity of the proposed projectile stable flight control strategies is confirmed. The innovations of this paper include: (1) a proposed new aerodynamic configuration model with the air-ducts structure for the spin-stabilized projectile and (2) proposed innovative stable flight control strategies of the corrected configuration projectile. The numerical simulation results show that, compared with the reference projectile without air-ducts structure, the lateral force of the air-ducts structure projectile can produce a radial correction effect on the moving projectile. The simulation results of control strategies indicate that the control strategies can ensure stable flight of the corrected configuration projectile under different conditions.

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Section: Introductionmentioning

confidence: 99%

Control Strategies for Flight Stability of Trajectory Correction Projectile with Air-Ducts Structure

Cui

Liu

Jiang

et al. 2022

Mathematical Problems in Engineering

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“…Statistics obtained by the LES with turbulent crossflow showed good agreement with the experiment and a series of mesh refinement study showed reasonable grid convergence in the predicted mean and fluctuation flow quantities. Kang et al 17 conducted numerical and experimental analysis on the jet interaction of supersonic aircraft and obtained aerodynamic database. Kwak et al 18 introduced the influence of turbulence model on flow separation using wing structure.…”

Section: Introductionmentioning

confidence: 99%

Unsteady test technique of jet control with multi-parameter coupling

Xue

Cao

et al. 2022

Advances in Mechanical Engineering

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In this paper, the jet control effect of air vehicle is studied, and a new multi parameter coupling unsteady test technique is established, which can ensure that the test model is consistent with the real air vehicle, and the jet is carried out under the condition of complete freedom and no support constraints, so that the wind tunnel test can better simulate the jet control effect of real air vehicle. The new technique overcomes the shortcoming that the previous jet test can only carry out unsteady flow field or unsteady aerodynamic force research, and can ensure that in the whole process of jet flow, the interference flow field at the nozzle, the aerodynamic force of the air vehicle, especially the movement of the air vehicle, are coupled with each other all the time, so as to achieve the same effect as the real air vehicle. The establishment of the new technique overcomes many problems, including the total length of the model is 167 mm, no support for the model, storage of small volume/high-pressure gas in free state, on-time unlocking of sealed gas source in free state of the model, and connection of gas source and nozzle in the model. The test results show that when no jet, the revolution body is head up, which affected by the cavity shock wave. When jet on, the jet force continues to act on the revolution body, resulting in the revolution body lowering its head until it diverges. The new technique can achieve more advanced technical indicators, including: ensuring jet Mach number >1; Ensure that the static pressure ratio of the jet is more than 10 (the static pressure ratio can be greater at hypersonic speed). After the establishment of the new technique, the supersonic wind tunnel test is carried out, and the ideal test results are obtained, which shows that the new technique is reliable.

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“…There are mainly two ways of the jet using for missile control. One way is to increase the maneuverability at the terminal trajectory by the reaction force generated by the jet (Kang et al, 2015;. The other way is to change the flow structure by the jet to achieve the purpose of improving the aerodynamic characteristics.…”

Section: Introductionmentioning

confidence: 99%

The numerical investigation on the rolling decoupling of a canard-controlled missile using the jet control system

Zhang

Lei

Yin³

et al. 2020

Engineering Applications of Computational Fluid Mechanics

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When the canard-controlled missile is conducting roll control, the asymmetric downwash induced by the canard impacts on the fins and produces a reverse rolling moment, resulting in the aerodynamic coupling between the canards and the fins. The rolling coupling can cause the reduction and even failure of the missile roll control. However, the current rolling decoupling methods always have adverse effects on the lift-drag ratio or flight stability of the missile. Based on the numerical simulation, this paper proposes a new method to reduce the roll coupling by adding a jet system between the canards and the fins. The effect of jet control was obtained under different freestream conditions. The influence of jet control factors on the missile aerodynamic characteristics was investigated and analyzed. The outcomes demonstrate that the jet control can effectively decrease the roll coupling between the canards and the fins, and eliminate the reverse rolling problem in most cases. With the same mass flow rate, the control effect is better at lower Mach number. Jet location and jet mode have a higher influence on the control effect. An optimal mass flow rate exists for the best control efficiency. This decoupling method is simple in structure and can reduce the side force and yawing moment without destroying the lift-drag ratio.

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Numerical Investigation of Jet Interaction for Missile with Continuous Type Side Jet Thruster

Cited by 8 publications

References 11 publications

Control Strategies for Flight Stability of Trajectory Correction Projectile with Air-Ducts Structure

Control Strategies for Flight Stability of Trajectory Correction Projectile with Air-Ducts Structure

Unsteady test technique of jet control with multi-parameter coupling

The numerical investigation on the rolling decoupling of a canard-controlled missile using the jet control system

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