Aerodynamics and Conceptual Design Studies on an Unmanned Combat Aerial Vehicle Configuration

Cummings, Russell M.; Liersch, Carsten M.; Schütte, Andreas; Huber, Kerstin Claudie

doi:10.2514/1.c033808

Cited by 21 publications

(16 citation statements)

References 23 publications

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“…Figure 3 shows a comparison of aerodynamic force and moment coefficients of the standard model. It can be seen that the calculation results have good agreement with the wind tunnel data or the reference data (Cummings et al 2016;, except for the pitching moment coefficient. As Fig.…”

Section: Research Objectsupporting

confidence: 60%

“…Compared to the vortex lattice method results and the experimental data, the lift curve has a slightly higher slope and a minimal shift in the zero-lift angle. By comparison with the lift curve in Cummings et al (2016), the error caused by this method is acceptable in conceptual design of aircraft. The side force coefficients and the rolling and yawing moment coefficients are all zero, which are reasonable for the symmetrical geometry under symmetrical flow conditions.…”

Section: Research Objectmentioning

confidence: 99%

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Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Pan

Huang

2019

J.Aerosp. Technol. Manag.

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Poor lateral-directional stability due to the absence of vertical stabilizer is a great risk to the aircraft with flying wing layout. In this paper, an unmanned aerial vehicle with this kind of configuration is chosen as the research object. A threedimensional model of the unmanned aerial vehicle is established, and then the sensitivity analysis is performed to obtain the effects of main aerodynamic shape parameters on lateral-directional flying quality. The results show that the roll mode and spiral mode of the aircraft meet the requirements of Level 1 flying quality in MIL-F-8785C. But the Dutch roll mode is generally divergent, which means that the flying quality of the aircraft is unacceptable. Thus it can be seen that the Dutch roll mode is the key to the dynamic stability of the aircraft. Further studies show that increasing the value of wing aspect ratio or decreasing the values of dihedral angle and torsion angle are useful for improving the Dutch roll mode. It is valuable to reveal the influence mechanism of aerodynamic shape parameters on lateral-directional flying quality for the design of flying wing aircraft.

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Section: Research Objectsupporting

confidence: 60%

Section: Research Objectmentioning

confidence: 99%

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Pan

Huang

2019

J.Aerosp. Technol. Manag.

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“…The presented paper deals with the computer-aided design of an S-shaped intake for the UCAV configuration created in the DLR project Mephisto [5]. For these investigations the automated optimizer AutoOpti is used, which needs an automated process chain for S-duct generation and meshing followed by 3D CFD and post-processing.…”

Section: Introductionmentioning

confidence: 99%

Automated Optimisation of the MULDICON Inlet with Minimum Losses and Reduced Sight onto the Compressor Front Face

Voß

Becker

Trost

2018

2018 Applied Aerodynamics Conference

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“…A CFD-CSM model with a DAKOTA gradient based optimization method is used to perform the optimization process. In 2016, Russell M. Cummings et al [2] introduced an aerodynamics and conceptual design studies on an unmanned combat aerial vehicle configuration by predicting both static and dynamic stability characteristics of air vehicles using computational fluid dynamics methods aiming to reduce the number of ground tests required to verify vehicle concepts. In this paper, a comprehensive study is introduced for extension kit and fins design optimization.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Design Optimization of Range Extension Kit of a Subsonic Flying Body

Elsherbiny¹,

Bayoumy

Elshabka³

et al. 2017

International Conference on Aerospace Sciences and Aviation Tec

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This paper aims to convert the aerodynamic shape of a conventional aerial subsonic flying body into a glide one by providing a range extension kit and fins. It describes the selection of configuration and airfoils depending on the tactical requirements and flight regimes. The wing and fins sizing is obtained using three different methods subjected to geometric constraints. The first method is an iterative optimization method using linear aerodynamic data. The second method is a genetic algorithm multi-objective function aims to maximize stability, controllability and lift-drag ratio within certain weights using linear aerodynamic data. The third method is a genetic algorithm optimization function integrated with MISSILE DATCOM aims to maximize lift-drag ratio. Then perform a direct uncontrolled six degree of freedom simulation for the three optimized designs and the conventional flying body. Comparing the results of ranges for these bodies reveals that the third method has the best range over the other designs including the conventional flying body.

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Aerodynamics and Conceptual Design Studies on an Unmanned Combat Aerial Vehicle Configuration

Cited by 21 publications

References 23 publications

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Automated Optimisation of the MULDICON Inlet with Minimum Losses and Reduced Sight onto the Compressor Front Face

Aerodynamic Design Optimization of Range Extension Kit of a Subsonic Flying Body

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