Improved Validation Methodology for Missile Datcom Development

Doyle, Josh B.; Rosema, Christopher; Arsenal, Redstone

doi:10.2514/6.2011-1241

Cited by 7 publications

(3 citation statements)

References 1 publication

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“…It gives very fast and accurate enough results for the initial design phase [18][19][20]. Detailed verification of DATCOM methods are also studied in the literature [21,24,25]. To conclude, Digital DATCOM program is considered as an effective way to estimate the wing-body aerodynamics with acceptable accuracy since the main focus of the study is not detailed aerodynamic modeling.…”

Section: Forward Flight Aerodynamic Model: Wing-body Aerodynamics At ...mentioning

confidence: 99%

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Suiçmez,

Kutay

2023

Aeronaut. j.

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On-demand urban air transportation gains popularity in recent years with the introduction of the electric VTOL (eVTOL) aircraft concept. There is an emerging interest in short/medium range eVTOL air taxi considering the critical advantages of electric propulsion (i.e. low noise and carbon emission). Using several electric propulsion systems (distributed electric propulsion (DEP)) has further advantages such as improved redundancy. However, flight controller design becomes more challenging due to highly over-actuated and coupled dynamics. This study defines and resolves flight control problems of a novel DEP eVTOL air taxi. The aircraft has a fixed-wing surface to have aerodynamically efficient cruise flight, and uses only tilting electric propulsion units to achieve full envelope flight control via pure thrust vector control. The aircraft does not have conventional control surfaces such as aileron, rudder or elevator. Using pure thrust vector control has some design benefits, but the control problem becomes more challenging due to the over-actuated and highly coupled dynamics (especially in transition flight). A preliminary flight dynamics model is obtained considering the dominant effects at hover and high-speed forward flight. Hover and forward flight models are blended to simulate the transition dynamics. Two central challenges regarding the flight control are significant nonlinearities in aircraft dynamics during the transition and proper allocation of the thrust vector control specifically in limited control authority (actuator saturation). The former challenge is resolved via designing a sensor-based incremental nonlinear dynamic inversion (INDI) controller to have a single/unified controller covering the wide flight envelope. For the latter one, an optimisation-based control allocation (CA) approach is integrated into the INDI controller. CA requires special attention due to the pure thrust vector control’s highly coupled dynamics. The controller shows satisfactory performance and disturbance rejection characteristics. Moreover, the CA plays a vital role in guaranteeing stable flight in case of severe actuator saturation.

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Section: Forward Flight Aerodynamic Model: Wing-body Aerodynamics At ...mentioning

confidence: 99%

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Suiçmez,

Kutay

2023

Aeronaut. j.

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“…The numerical calculations of aerodynamic characteristics of the original, 2M, 2T, and 2F models, performed using the CFD methods prior to the wind tunnel test campaign, were necessary in order to estimate the expected loads on the wind tunnel model. The numerical calculation was done in the FLUENT package, as it allows calculation of the aerodynamic characteristics of complex aerodynamic shapes [9][10][11][12][13][14][15][16][17][18][19]. The solid model of the missile is done in INVENTOR software.…”

Section: The Cfd Simulationmentioning

confidence: 99%

Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation

2017

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Original scientific paper https://doi.org/10.2298/TSCI150515184OThis paper presents modification of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and computational fluid dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute in order to determine the final geometry of the new front parts. The 3-D Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force, and pitching moment coefficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with.

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“…Experimental, empirical, and computational approaches were compared in a huge body of studies. Empirical and experimental approaches were compared in [1][2][3][4][5][6][7][8][9][10][11][12][13] whereas in [14][15][16][17][18][19][20][21][22], computational results were compared with experimental measurements. Computational techniques were also compared with empirical ones in [23].Comparative studies aggregating the three approaches were only conducted by Rosema el al.…”

Section: Introductionmentioning

confidence: 99%

A Comparative Study of Prediction Techniques for Supersonic Missile Aerodynamic Coefficients at Incidence

mahdi

Ahmed

Mahmoud

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Evaluating the aerodynamic coefficients of flying vehicles such as missiles is a key step in their design and development procedures. In practice, the aerodynamic coefficients can be estimated using experimental measurements, numerical simulations, or using empirical and semi-empirical engineering tools. In the present paper, these three approaches are compared in the context of examining the aerodynamic coefficients of a fin-stabilized tactical missile. Supersonic flight conditions up to Mach 4 at incidence up to 18 degrees are considered. Lift and drag coefficients as well as the centre of pressure locations based on the three approaches are compared. The flow features around the missile are explored based on the numerical simulations.

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Improved Validation Methodology for Missile Datcom Development

Cited by 7 publications

References 1 publication

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation

A Comparative Study of Prediction Techniques for Supersonic Missile Aerodynamic Coefficients at Incidence

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