Simulation of Missile with Spinning Tail Fin Using Chimera Moving Body Methodology

Hall, Les

doi:10.2514/6.2004-1249

Cited by 5 publications

(3 citation statements)

References 11 publications

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“…Previous results [33] describing the required grid resolution for accurate prediction of the aerodynamic forces acting on the body and the relative importance of the viscous effects and tail spin rate. Those results were generated using the UVI method and were found to be in good agreement with other grid topology approaches that have been successfully applied to this same problem: Murman et al [34] applied a Cartesian method and both Hall [35] and Nygaard et al [36] used Chimera overset structured grid methods. For the purpose of this work, the results generated using the UVI methods will serve to validate those using the new sliding interface method and comparison of these results will be made to the other topology approaches when available.…”

Section: Large Scale Applicationsupporting

confidence: 59%

A sliding interface method for unsteady unstructured flow simulations

Blades

Marcum

2006

Numerical Methods in Fluids

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SUMMARYThe objective of this work is to develop a sliding interface method for simulations involving relative grid motion that is fast and efficient and involves no grid deformation, remeshing, or hole cutting. The method is implemented into a parallel, node-centred finite volume, unstructured viscous flow solver. The rotational motion is accomplished by rigidly rotating the subdomain representing the moving component. At the subdomain interface boundary, the faces along the interface are extruded into the adjacent subdomain to create new volume elements forming a one-cell overlap. These new volume elements are used to compute a flux across the subdomain interface. An interface flux is computed independently for each subdomain. The values of the solution variables and other quantities for the nodes created by the extrusion process are determined by linear interpolation. The extrusion is done so that the interpolation will maintain information as localized as possible. The grid on the interface surface is arbitrary. The boundary between the two subdomains is completely independent from one another; meaning that they do not have to connect in a one-to-one manner and no symmetry or pattern restrictions are placed on the grid. A variety of numerical simulations were performed on model problems and large-scale applications to examine conservation of the interface flux. Overall solution errors were found to be comparable to that for fully connected and fully conservative simulations. Excellent agreement is obtained with theoretical results and results from other solution methodologies.

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Section: Large Scale Applicationsupporting

confidence: 59%

A sliding interface method for unsteady unstructured flow simulations

Blades

Marcum

2006

Numerical Methods in Fluids

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“…The time-dependent and relativemotion simulation methods were combined with an inviscid Cartesian-grid method and a constrained 6-DOF equation to model the motion of the spinning tail section. 26 Nygaard 27 from NASA, Eric 28 from Mississippi State University, and Hall 29 from the Dynetics Company used the overset grid technique and one degree of freedom (1-DOF) equation to predict the free-spinning tail's motion with a special configuration, and the results were in good agreement with the experimental data. Using the same method, Yang 30 from Korea studied the nonlinear rotation of a NASA configuration.…”

Section: Introductionmentioning

confidence: 83%

Numerical investigation of aerodynamic characteristics of free-spinning tail projectile with canards roll control

Jiawei

Lei

Niu

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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To reduce aerodynamic coupling between the canards and the tail fins of a canard-controlled projectile, the afterbody of the projectile is decoupled from the forebody by a bearing structure, namely, a free-spinning tail. A series of numerical simulations was conducted for different angles of attack using NASA’s canard-controlled projectile with a free-spinning tail. The results were then compared with the wind tunnel test data. The spin rate of the free-spinning tail shows that, with the canard roll control, the tail section will rotate at lower angles of attack and “lock-in” at higher ones, demonstrating nonlinearization between the rotating rate and the angle of attack. According to a flow structure analysis, the circular flow velocity induced by canards is responsible for the non-linear characteristics of the tail. Moreover, the change in position of the circular flow velocity results in a reverse of the rolling moment of the “+” fixed tail projectile at different angles of attack. Furthermore, a comparison of the aerodynamic characteristics of the fixed (“+” and “x”) and free-spinning tail configurations proves that when the tail is spinning, all the aerodynamic coefficients of the free-spinning tail projectile are between those of the “+” and “x” fixed tail projectiles. The longitudinal difference in aerodynamic characteristics is related to the rolling angle, whereas the lateral difference is related to both the rolling angle and rotation rate. When the tail section “locks-in,” different rolling angles lead to different characteristics in both the longitudinal and lateral directions.

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“…The above study has demonstrated that simple control algorithms used in situations as described above, can also minimize the actual control rotations. One of the attractive options of leading edge control surface is the canard that has found use in many aerospace vehicle applications for (i) providing better longitudinal stability 8 , (ii) compensating for inadequacy of the horizontal tail to trim aircraft configurations using blown flaps as high lift devices 9 and (iii) controlling the aerospace vehicle motion 10 . However, it should be kept in mind that such control surfaces can lead to aeroelastic instabilities at higher dynamic pressures and therefore there is a need to understand the behaviour of canards as flight control surfaces, in greater detail.…”

Section: Introductionmentioning

confidence: 99%

Optimal Location and Size of Canards for Aeroelastic Actuation in Aerospace Vehicles

Joshi

Suryanarayan

2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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The present study investigates the problem of locating and resizing canard control surfaces in order to achieve a desired trim flight control force. The problem of a generic flexible aerospace vehicle having canard as the main flight control surface is formulated and a simplified analytical model is developed which demonstrates the feasibility of determining the geometric configuration and location of the canard that recovers the desired control force by relocating and resizing the existing canard. Next, the above concept is extended to a practical aerospace vehicle configuration using an in-house software tool for performing the static aeroelastic load analysis and these results are obtained for the supersonic flight regime, by also considering variation in the structural stiffness of the body of the aerospace vehicle. The results are obtained for a trim analysis, with inertia force corrections taken into account, and plots are generated for the required canard location as a function of the vehicle body stiffness factor, for two different values of the canard size and for a typical supersonic Mach number. Lastly, the effect of canard structural flexibility on the overall control derivative is investigated, through an equivalent lumped torsional stiffness approach. These results clearly show that it is possible to locate and resize the canard such that the desired control force is recovered, using the favourable aeroelastic effects of the body of the aerospace vehicle. These results are considered to be applicable both for the multidisciplinary design of aerospace vehicle as well as for on-board implementation as a part of the flight control algorithm.

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Simulation of Missile with Spinning Tail Fin Using Chimera Moving Body Methodology

Cited by 5 publications

References 11 publications

A sliding interface method for unsteady unstructured flow simulations

A sliding interface method for unsteady unstructured flow simulations

Numerical investigation of aerodynamic characteristics of free-spinning tail projectile with canards roll control

Optimal Location and Size of Canards for Aeroelastic Actuation in Aerospace Vehicles

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