IHAAA Applications to Reducing Store Separation Flight Testing

Cenko, A.; Lee, Jae; Getson, E.; Hallberg, Eric; Jolly, Bruce; Sickles, W. L.

doi:10.2514/6.2007-1653

Cited by 4 publications

(2 citation statements)

References 2 publications

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“…1 The TetrUSS flow solver, USM3d, has been used extensively in other store separation studies. [2][3][4][5][6][7][8][9][10] Geometry representing a symmetric half of an F/A-18C equipped with the Litening Pod and released Mk-83 JDAM was recreated using Rhino, a versatile Computer Aided Design (CAD) program compatible with TetrUSS. An unstructured threedimensional grid was then generated around the CAD model (associated surface grid shown in Fig.…”

Section: Flow Simulationmentioning

confidence: 99%

Litening Pod Modification to Improve Mk-83 Store Trajectories (Invited)

Constantino

Simpson²,

Shea³

et al. 2011

29th AIAA Applied Aerodynamics Conference

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In this paper we discuss a Computational Fluid Dynamics (CFD) study to determine the impact of moving an air cooling intake scoop on theLitening external targeting pod mounted on an F/A-18C. Specifically, we investigated whether a change in the location of the Litening Pod cooling air intake scoop creates more favorable store separation characteristics for the Mk-83 1000 lb gravity bomb. Previous research has shown that small changes to the geometry of external targeting pods can change generated shock waves that may result in adverse moments on the smaller Mk-82 gravity bomb. These adverse moments can result in the released bomb striking the aircraft. The Litening Pod is mounted on the starboard side of the F/A-18C fuselage adjacent to a pylon carrying a Mk-83 bomb. The air scoop is an approximately rectangular inlet on the side of the Litening Pod that collects ram air to cool internal electronics. Rotating the Litening Pod air scoop away from the store may reduce shock wave interaction with the released store. Our CFD simulations show that rotation of the air scoop to the down side of the Litening Pod significantly reduces adverse moments on the released Mk-83 bomb. Visualizations of the generated shockwaves also indicate reduced interaction with the released store for the Litening Pod air scoop in the down instead of the side position. Nomenclature CAD = computer aided design CFD = computational fluid dynamics CPU = central processor unit F/A-18C = US Navy fighter attack aircraft JDAM = joint direct attack munition Ma = Mach number Mk-83 = 1000 lb bomb TetrUSS = Tetrahedral Unstructured Software System

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Section: Flow Simulationmentioning

confidence: 99%

Litening Pod Modification to Improve Mk-83 Store Trajectories (Invited)

Constantino

Simpson²,

Shea³

et al. 2011

29th AIAA Applied Aerodynamics Conference

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“…5,6 The TetrUSS flow solver, USM3d, has been used extensively in other store separation studies. [7][8][9][10][11][12][13][14][15] Geometry representing the Mk-82 and ARA strut was recreated using Rhino, a versatile Computer Aided Design (CAD) program compatible with TetrUSS. An unstructured three-dimensional grid was then generated around the CAD model (associated surface grid shown in Fig.…”

Section: Numerical Simulationsmentioning

confidence: 99%

Strut Effects on Store Freestream Aerodynamics

Shah

O'Brien

Constantino

et al. 2011

29th AIAA Applied Aerodynamics Conference

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In order to maximize stealth, most new military fighter/attack aircraft are designed to carry weapons internally. Associated wind tunnel testing of stores inside an internal bomb bay or cavity can be problematic due to the use of a sting or strut to place the simulated store in the desired position inside the internal cavity. Since aft mounted stings are usually not feasible, a strut mounted sting is typically used for determination of moments on a simulated store in an internal cavity. However, these strut devices can impact store freestream aerodynamics. A study was completed to see if computational fluid dynamics could be used to identify the potential impact on the strut on store aerodynamics. NomenclatureARA = Aircraft Research Association CAD = computer aided design CFD = computational fluid dynamics CPU = central processor unit GBU = guided bomb unit NICS = Navy Internal Carriage and Separation Ma = Mach number Mk-82 = 500 lb bomb TetrUSS = Tetrahedral Unstructured Software System D = cavity depth L = cavity length W = cavity width Z = distance below internal cavity upper surface α = angle of attack β = side slip angle Cm y = pitching moment coefficient

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Influence of Aircraft Flow Field on the Longitudinal Stability of a Missile

Arora

Shah

Anandhanarayanan

et al. 2013

DSJ

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An air-to-air missile launched from a fighter aircraft needs to be stable at launch to enable safe separation from the aircraft, and less stable in the terminal phase of its flight to become highly maneuverable to intercept the targets. A study has been carried out to estimate the effect of the aircraft flow field on the longitudinal stability of the missile using an in-house developed 3-D grid-free Euler solver. Initially, the missiles are placed in the captive location in the launcher of the aircraft. One of the missiles is then moved to various pre-determined locations ahead of the wing of the aircraft, keeping the other missile at the captive location. The centre of pressure and stability margin of the missile is determined at these locations. It is observed that the presence of aircraft has a substantial effect on the longitudinal stability of the missile. The centre of pressure of the missile is seen to move aft as it leaves the launcher. As the missile moves, the centre of pressure reaches a maximum aft position and then moves forward till it reaches a position where the missile is free from the influence of the aircraft. It is observed that as the missile moves away from the region of strong influence of the aircraft, its aerodynamic characteristics approach asymptotically to that of the isolated missile.

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IHAAA Applications to Reducing Store Separation Flight Testing

Cited by 4 publications

References 2 publications

Litening Pod Modification to Improve Mk-83 Store Trajectories (Invited)

Litening Pod Modification to Improve Mk-83 Store Trajectories (Invited)

Strut Effects on Store Freestream Aerodynamics

Influence of Aircraft Flow Field on the Longitudinal Stability of a Missile

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