Separation Dynamics of Air-to-Air Missile Using a Grid-Free Euler Solver

Anandhanarayanan, K.; Arora, Konark; Shah, Vaibhav; Krishnamurthy, R.; Chakraborty, Debasis

doi:10.2514/1.c031791

Cited by 16 publications

(10 citation statements)

References 15 publications

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“…Solving the Motion Equations. Equations (10) and (13) form the kinematic equations of the missile, and with equation (9) and (5), it constitutes the six degrees of freedom rigid body equation of motion. The equations consist of 12 differential equations and are calculated using the fourth-order Runge-Kutta method.…”

Section: Dynamic Equationsmentioning

confidence: 99%

“…Zheng and Liao [4] studied the research on the criterion of safe separation of machine bombs and unified the basic concept of machine separation. Anandhanarayanan et al [5] conducted research on the separation process of powered rail-type aircraft missiles. Zhang and Ni [6] proposed that the rudder bias should be suppressed during the launching process to increase the tendency of the missile to roll, so the missile is as stable as possible during the offtrack process, and the safety of the separation of the missile is guaranteed.…”

Section: Introductionmentioning

confidence: 99%

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Horizontal Backward Launch Dynamics Modeling and Analysis

Zhao

Jiang

Wei

et al. 2019

International Journal of Aerospace Engineering

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Fighters’ air strikes play a vital role in modern warfare. But, with the development of fighters, the amount of bombs will inevitably become a major disadvantage due to the limitations of the invisible design and other functions, so a combination of the old model bombers and the advanced fifth-generation fighters has been proposed. This paper takes the aircraft missile horizontal backward launch system as the research object; firstly, the finite element model of the missile’s off-track is established, and the simulation calculation under the fixed platform is tested to verify the correctness of the finite element model. Meanwhile, the simulation parameters of the initial trajectory are obtained. Then, by establishing the separation model of the machine under the open state of the aircraft’s rear launcher, the variation of the flow field during the separation process of the missile is analyzed, and the variation of the force and the attitude of the missile is studied. It is found that the pitching motion of the missile is greatly affected by the initial pitch angle, it is always in the heading state during the whole separation process, and the yaw motion is not obvious.

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Section: Dynamic Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Horizontal Backward Launch Dynamics Modeling and Analysis

Zhao

Jiang

Wei

et al. 2019

International Journal of Aerospace Engineering

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“…While under the gust environment, the derailment process of missiles with large span and long guide rails becomes more complicated [22][23][24]. The longitudinal fluctuation of the platform obtained in Section 2 can be taken as the input to calculate the finite element simulation result and compare with the calculation result under the fixed platform.…”

Section: Analysis Of Initial Disturbance Of Horizontal Backwardmentioning

confidence: 99%

Study on Initial Disturbance of Airborne Missile’s Horizontal Backward Derailment under Continuous Gust

Pan

Jiang

Wei

et al. 2019

International Journal of Aerospace Engineering

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This paper studies the effect of continuous gusts on the initial disturbance of the airborne missile’s horizontal backward derailment on large transport aircraft. The longitudinal fluctuation of the airborne launching platform under continuous gust was obtained with different calculation methods, and the finite element model of the derailing process was established then verified by experiments. Finally, combined with the longitudinal fluctuation of the launching platform and the finite element model of the missile and launching platform, the influence of platform fluctuation on separation time, missile speed, pitch angle, and descending distance while derailing was studied and analyzed. It is found that the longitudinal fluctuation of the launching platform is similar to that of the gust but lags behind, and the missiles under the fluctuating platform have longer separation time, lower derailing speed, and greater derailing pitch angle and descending distance.

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“…The above codes are integrated to form SSD suite and is applied to separation studies of air to air missiles from fighter aircraft. 17…”

Section: Computational Toolsmentioning

confidence: 99%

Numerical simulation of fairing separation test for hypersonic air breathing vehicle

Raj

Anandhanarayanan

Krishnamurthy

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Fairings are provided to cover hypersonic air breathing vehicle to protect it from adverse aerodynamic loading and kinetic heating. Separation dynamics of fairings is an important event in the launch of vehicle. Extensive computational fluid dynamics simulations are carried out for the design of fairings and vehicle and selection of time sequences of various separation events. A ground test of fairing separation is conducted in the sled facility to check the structural integrity and functionality of various separation mechanisms and flight hardware. Simulations have been carried out to study the separation dynamics of fairings at test conditions using grid-free Euler solver to get the aerodynamic loads and the loads are integrated to get the trajectory of fairings. The aerodynamic loads are provided to verify the structural integrity of various components and the trajectory of panels is used in the test planning. The pressure distributions on the vehicle are compared with the test results.

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Separation Dynamics of Air-to-Air Missile Using a Grid-Free Euler Solver

Cited by 16 publications

References 15 publications

Horizontal Backward Launch Dynamics Modeling and Analysis

Horizontal Backward Launch Dynamics Modeling and Analysis

Study on Initial Disturbance of Airborne Missile’s Horizontal Backward Derailment under Continuous Gust

Numerical simulation of fairing separation test for hypersonic air breathing vehicle

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