Multi-UAV coordination control by chaotic grey wolf optimization based distributed MPC with event-triggered strategy

This paper overviews research undertaken to develop and demonstrate active flow control technologies based on the application and manipulation of Coanda flows, with the objective of developing syst...

Fluidic Flow Control Effectors for Flight Control

Multi-Disciplinary Design and Performance Assessment of Effective, Agile NATO Air Vehicles

This paper reports on a numerical investigation of the use of trailing-edge circulation control as a roll effector on a generic unmanned combat aerial vehicle: the DLR-F19 stability and control configuration. The Coanda effect induced by fluidic injections at the trailing edge of a wing is used to increase circulation and generate lift. Reynolds-averaged Navier–Stokes predictions are validated against wind-tunnel experiments conducted at the Georgia Institute of Technology and NASA’s basic aerodynamic research tunnel on an airfoil employing trailing-edge circulation control. Two turbulence models are used: the Wilcox k-ω model and Menter’s shear-stress transport, showing that the Wilcox k-ω model provides the best comparisons with the experimental data. Baseline data for the stability and control configuration with conventional control surfaces from wind-tunnel experiments done at the low speed wind-tunnel owned by the German- Dutch Wind Tunnels foundation (DNW-NWB) are used to ensure the correct flow fea...

Circulation Control as a Roll Effector for Unmanned Combat Aerial Vehicles

The flow above delta wing shaped UCAV (Unmanned Combat Air Vehicle) configurations is often
dominated by strong vortices, especially at moderate and high angle of attack. On delta wings with
sharp leading edges, the flow separates at the leading edges already at small angles of attack. The shear
layer rolls up and two vortices are formed on each side of the wing starting close to the wing apex and
increasing in size towards the wing aft. The vortices produce strong suction peaks on the upper wing
surface, so that additional lift is generated which is of benefit by performing low speed manoeuvres like
take-off and landing. UCAV configurations often consist of rounded leading edges to improve their
performance under cruise conditions. In this case the flow topology becomes more complicated because
the flow separations at the leading edges are delayed to higher angles of attack and depend strongly on the
Reynolds and Mach number. In regions of attached flow around blunt leading edges, other flow
effects may produce additional vortices as observed on the VFE2 delta wing where vortices develop
inboard the leading edge vortices caused by a kind of instability within the boundary layer. The onset
of the leading edge vortices, their interactions and accompanying phenomena like vortex breakdown can
cause adverse loading effects. To avoid such non-linear aerodynamic characteristics detailed flow
investigations are of great importance during the design chain by improving the understanding of the
aerodynamics. This all the more so if the dynamic behaviour of the vehicle has to be considered as the
flow effects become even further complicated.
Within the scope of the Task Group of AVT-161 (Chapter 1), Stereoscopic Particle Image
Velocimetry (PIV) has been applied for flow field investigations on a SACCON (Stability And Control
CONfiguration) wind tunnel model.

Chapter 1 – Static and Dynamic SACCON PIV Tests - Part II: Aft Flow Field

The ability of computational fluid dynamics to predict the steady and unsteady fluid flow over a generic UCAV configuration, with and without control surface deflections, at off design conditions is investigated. The complex, non-linear flow, various combinations of control surface deflection and the presence of multiple interacting vortices on the flow histories provides a challenging test for current capability. A range of static and dynamic test cases have been computed, for both low and high speed flows, for comparison with experimental data, obtained as part of the NATO STO AVT-201 Task Group. The simulations are performed using a multiblock code to solve the Reynolds-Averaged Navier-Stokes equations; and the control surfaces are modelled with a deformed mesh and blended gaps that simplify the geometry. These tests will provide an assessment of the ability of computational fluid dynamics to evaluate such flows, and will allow for deficiencies in the state of the art to be identified.

Numerical simulation of control surface deflections over a generic UCAV configuration at off-design flow conditions

A study into the prediction of the effectiveness of different trailing-edge controls on an unmanned combat aerial vehicle configuration, on which complex vortical flow develops at moderate to high angles of attack, is described Stability and control of these vehicles is demanding and requires early knowledge of the changes in forces and moments from control-surface deflections Computational results are compared with data from wind-tunnel tests over the Mach number range 0146≤M≤09 for undeflected controls The effectiveness of the controls at subsonic and transonic conditions is then discussed The influence of the mesh treatment and turbulence model on the realism of the predictions is considered The computational-fluid-dynamics predictions show good agreement with measurements and show limited sensitivity to geometry treatment and turbulence model for the flow conditions where the controls are effective Computational fluid dynamics is shown to be capable of predicting the control-surface influence,

Prediction of Control Effectiveness for a Highly Swept Unmanned Air Vehicle Configuration

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Circulation Control as a Roll Effector for Unmanned Combat Aerial Vehicles

Numerical simulation of control surface deflections over a generic UCAV configuration at off-design flow conditions

Prediction of Control Effectiveness for a Highly Swept Unmanned Air Vehicle Configuration