Free-Flight Investigation of High-Maneuverability Missile Dynamics

Beyers, Martin E.

doi:10.2514/3.57185

Cited by 6 publications

(4 citation statements)

References 5 publications

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“…3) using local aerodynamic analysis 65 (Fig. 16), reveals highly nonlinear behavior with complete loss of stability near a = 11 deg.…”

Section: Unconstrained Planar Pitchingmentioning

confidence: 98%

Interpretation of experimental high-alpha aerodynamics - Implications for flight prediction

Beyers¹

1995

Journal of Aircraft

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Nomenclature b= wingspan, or largest dimension C -aerodynamic coefficient; with no superscript, in body axes systemMach number /?, p x = local static pressure /?, q, r = body-axes angular velocities q^ = freestream dynamic pressure Re, -Reynolds number based on /, / -c, b, or d S = reference area V, V^ = freestream velocity w = minimum dimension of test section X, Y, Z = inertial axes system X f , Y f ; Z f = flight coordinate system, Fig. 2 x, _y, z = body axes system a, /3 = angles of attack and sideslip A = increment or amplitude A = inclination of rotation axis, Fig. 6 = coning rate, parameter fib/2V or £1 a) = reduced circular frequency, coll(2V), where / = c or b, as appropriate Subscripts a = apex av = asymmetric vortices c = rotation center, Fig. 2 s = support Superscripts = differentiation with respect to time A , ' = aerodynamic axes system *, ~ = composite derivative, Eq. (2) = oscillatory condition

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“…3) using local aerodynamic analysis 65 (Fig. 16), reveals highly nonlinear behavior with complete loss of stability near a = 11 deg.…”

Section: Unconstrained Planar Pitchingmentioning

confidence: 98%

Interpretation of experimental high-alpha aerodynamics - Implications for flight prediction

Beyers¹

1995

Journal of Aircraft

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“…21 Measurements of the model attitude in the vicinity of the window trailing edge could contain bias errors not present further upstream. By virtue of its high-drag characteristics, the 60-deg cone enters and leaves the field of view at approximately three times the speed of the 10-deg cone.…”

Section: J Spacecraftmentioning

confidence: 99%

Nonplanar effects on pitch-plane dynamics

Ericsson

Beyers²

1990

Journal of Spacecraft and Rockets

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A new interpretation of the free-flight data of a sharp 10-deg cone and a blunt 60-deg cone is presented. A reassessment of the analysis of the original data is made, and an appropriate nonplanar motion correlator is derived. It is shown that nonplanar motion effects are the probable cause of the observed anomalous motions. In the case of the 10-deg cone, the principal nonplanar flow mechanism is the coning-induced tilting of forebody vortices; in the case of the 60-deg cone, the principal mechanism is the coupling between body motion and the near-wake recirculation region, possibly amplified by test-related effects. d I L M m NPR P q s t t/oo u_ V X x,y,z A e P o(1)

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“…The trend toward increased manoeuvreability and higher angles-ofattack in aircraft and missile design has compounded difficulties involved in the dynamic stability predictions. Unsteady aerodynamic effects in general have a major impact on manoeuvreability and controllability of the aircraft (1) . In an oscillatory motion the element of time makes the flow pattern more complicated.…”

Section: Introductionmentioning

confidence: 99%

“…This delay is mainly due to the fluid inertia and can be considered as the main source of the hysteresis loops observed in the force and moment variations with the angle-ofattack for a vehicle in an oscillatory motion (2) . Numerous studies have documented the hysteresis and overshoot characteristics of aircraft and missiles undergoing pitch oscillations especially at high angles-of-attack (1)(2)(3)(4)(5)(6) . The flow mechanisms responsible for these unsteady effects are the dynamic lags of the vortex burst and flow separation phenomenon.…”

Section: Introductionmentioning

confidence: 99%

On self-similar behaviour of the hysteresis loops in pitching motions

Soltani

Davari

2004

Aeronaut. j.

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A new similarity parameter has been used for analyzing the unsteady aerodynamic behaviour of vehicles undergoing sinusoidal pitching motion. If this parameter is identical for two unsteady manoeuvres with different reduced frequencies and oscillation amplitudes, the corresponding hysteresis loops of the force and moment collapse on each other. To support and verify this, extensive unsteady wind tunnel tests have been conducted on a standard model, which is a well known fighter type configuration. The acquired data were used to train a certain type of neural network, called the Generalised Regression Neural Network (GRNN), to reduce the number of wind tunnel runs. The scheme, once proved to give the correct results for various conditions, was applied to extend the experimental data to other conditions that have not been tested in the tunnel. Both the predicted and acquired tunnel data were used to show the performance of the similarity parameter.

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Free-Flight Investigation of High-Maneuverability Missile Dynamics

Cited by 6 publications

References 5 publications

Interpretation of experimental high-alpha aerodynamics - Implications for flight prediction

Interpretation of experimental high-alpha aerodynamics - Implications for flight prediction

Nonplanar effects on pitch-plane dynamics

On self-similar behaviour of the hysteresis loops in pitching motions

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