Dynamic Flight Maneuvering Using Virtual Control Surfaces Generated by Trapped Vorticity

2010 ◽  
Author(s):  
Ari Glezer ◽  
Mark G. Allen ◽  
Anthony J. Calise ◽  
Anthony Leonard ◽  
James M. McMichael ◽  
...  
Keyword(s):  
Virtual Control ◽  
Control Surfaces

scholarly journals A control allocation method based on equivalent virtual control surfaces

2011 ◽  
Vol 15 ◽  
pp. 1256-1260 ◽  
Author(s):  
Shi Jingping ◽  
Zhang Weiguo ◽  
Li Suilao
Keyword(s):  
Control Allocation ◽  
Virtual Control ◽  
Allocation Method ◽  
Control Surfaces

scholarly journals Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

2018 ◽  
Vol 8 (1) ◽  
pp. 125 ◽  
Author(s):  
Valentina Motta ◽  
Leonie Malzacher ◽  
Dieter Peitsch
Keyword(s):  
Compressor Blades ◽  
Virtual Control ◽  
Numerical Assessment ◽  
Control Surfaces

Robust adaptive sliding sector control and control allocation of a missile with aerodynamic control surfaces and reaction jets

2016 ◽  
Vol 231 (3) ◽  
pp. 397-406 ◽  
Author(s):  
Biao Xu ◽  
Di Zhou ◽  
Zhuo Liang ◽  
Guofeng Zhou
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Control Law ◽  
Control Allocation ◽  
Parameter Uncertainties ◽  
Control Effort ◽  
Virtual Control ◽  
Aerodynamic Control ◽  
Robust Adaptive ◽  
Control Surfaces

Based on L2 optimal control allocation, an autopilot design approach is proposed for the missile with aerodynamic control surfaces and reaction jets. The control system involves a control allocator and a virtual control law. A robust sliding sector with a parameter update law is proposed to deal with unmatched parameter uncertainties and unknown disturbances in the system. Then a control law is designed to produce virtual control effort signals by using the robust adaptive sliding sector. In order to distribute the virtual signals to the aerodynamic control surfaces and reaction jets on the missile, a control allocator is designed by L2 optimal control allocation strategy. Simulation results show that the missile control system tracks the acceleration command fast and smoothly. In the tracking process, aerodynamic control surfaces cooperate with reaction jets, verifying the effectiveness of the proposed approach.

Aeroelastic Control on Compressor Blades With Virtual Control Surfaces: A Numerical Assessment

2018 ◽  
Author(s):  
Valentina Motta ◽  
Leonie Malzacher ◽  
Victor Bicalho Civinelli de Almeida ◽  
Dieter Peitsch
Keyword(s):  
Suction Side ◽  
Wave Mode ◽  
Compressor Blades ◽  
Aeroelastic Response ◽  
Virtual Control ◽  
Wide Range ◽  
Turbomachinery Blades ◽  
Induced Flow ◽  
The Stability ◽  
Control Surfaces

Plasma actuators are numerically implemented as virtual control surfaces to reduce turbomachinery blades vibration and enlarge flutter-free ranges. Actuators are located at the trailing edge of the blades, both on pressure and suction side, and are triggered either independently or alternately. Upstream blowing — i.e. plasma operating in a way that the induced flow is against the freestream — has been assessed by the authors in a previous work, and is now compared with downstream blowing — i.e. plasma-induced flow in the direction of the freestream. Steady state and traveling-wave mode calculations are performed. Transient results indicate that both upstream and downstream actuation increase remarkably the stability of the cascade. This improvement in the aeroelastic response is observed for the entire interblade phase angle range. Furthermore, the effects of locally actuating the flow on lift, drag and moment coefficients are typified. A wide range of angles of attack and blowing forces is simulated. The obtained results demonstrate that also downstream plasma actuation can be a powerful tool to deal with aeroelastic instabilities on turbomachinery, and make worthwhile to assess further in-depth the capabilities of the two actuation approaches.

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