Quantized Control Allocation of Reaction Control Jets and Aerodynamic Control Surfaces

2009 ◽  
Vol 32 (1) ◽  
pp. 13-24 ◽  
Author(s):  
David B. Doman ◽  
Brian J. Gamble ◽  
Anhtuan D. Ngo
Keyword(s):  
Control Allocation ◽  
Quantized Control ◽  
Aerodynamic Control ◽  
Control Surfaces

scholarly journals Disturbance Observer-Based Adaptive Control of Hypersonic Vehicles with Constrained Actuators

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Guan Wang ◽  
Li Li ◽  
Weihua Li ◽  
Huajun Zhou ◽  
Changbo Ma ◽  
...  
Keyword(s):  
Disturbance Observer ◽  
Input Saturation ◽  
Adaptive Controller ◽  
Hypersonic Vehicles ◽  
Control Allocation ◽  
External Disturbances ◽  
Nonlinear Disturbance Observer ◽  
Aerodynamic Control ◽  
Actuator Constraints ◽  
Control Surfaces

This study investigates an adaptive controller for the flexible air-breathing hypersonic vehicles (AHVs) subject to external disturbances and actuator constraints. The combination of nonlinear disturbance observer and adaptive mechanism is exploited to design an adaptive controller for each subsystem. For the velocity subsystem, an auxiliary system is employed to handle the scramjet input saturation issue. For the altitude subsystem, the magnitude/rate constraints and the dynamics of aerodynamic control surfaces are addressed by the control allocation module. Simulations show the effectiveness of the proposed control.

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.

scholarly journals Autopilot Design Method for the Blended Missile Based on Model Predictive Control

2015 ◽  
Vol 2015 ◽  
pp. 1-13 ◽  
Author(s):  
Baoqing Yang ◽  
Yuyu Zhao
Keyword(s):  
Model Predictive Control ◽  
Predictive Control ◽  
Design Method ◽  
Control Allocation ◽  
Piecewise Affine ◽  
Weighting Matrix ◽  
Aerodynamic Control ◽  
Simulation Results ◽  
Control Surfaces ◽  
Mixed Logical Dynamical

This paper develops a novel autopilot design method for blended missiles with aerodynamic control surfaces and lateral jets. Firstly, the nonlinear model of blended missiles is reduced into a piecewise affine (PWA) model according to the aerodynamics properties. Secondly, based on the equivalence between the PWA model and mixed logical dynamical (MLD) model, the MLD model of blended missiles is proposed taking into account the on-off constraints of lateral pulse jets. Thirdly, a hybrid model predictive control (MPC) method is employed to design autopilot. Finally, simulation results under different conditions are presented to show the effectiveness of the proposed method, which demonstrate that control allocation between aerodynamic control surfaces and lateral jets is realized by adjusting the weighting matrix in an index function.

scholarly journals Longitudinal Actuated Abdomen Control for Energy Efficient Flight of Insects

Energies ◽  
2020 ◽  
Vol 13 (20) ◽  
pp. 5480
Author(s):  
Titilayo Ogunwa ◽  
Blake McIvor ◽  
Nurkhairunisa Awang Jumat ◽  
Ermira Abdullah ◽  
Javaan Chahl
Keyword(s):  
Energy Efficient ◽  
Insect Flight ◽  
Design Feature ◽  
Unmanned Aircraft ◽  
Longitudinal Control ◽  
Flight Behaviour ◽  
Aerodynamic Control ◽  
The Cost ◽  
And Control ◽  
Control Surfaces

The actuated abdomens of insects such as dragonflies have long been suggested to play a role in optimisation and control of flight. We have examined the effect of this type of actuation in the simplified case of a small fixed wing aircraft to determine whether energetic advantages exist in normal flight when compared to the cost of actuation using aerodynamic control surfaces. We explore the benefits the abdomen/tail might provide to balance level flight against trim changes. We also consider the transient advantage of using alternative longitudinal control effectors in a pull up flight maneuver. Results show that the articulated abdomen significantly reduces energy consumption and increase performance in isolated manoeuvres. The results also indicate a design feature that could be incorporated into small unmanned aircraft under particular circumstances. We aim to highlight behaviours that would increase flight efficiency to inform designers of micro aerial vehicles and to aid the analysis of insect flight behaviour and energetics.

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

Lift Engine Bleed Flow Management for a V/STOL Fighter Reaction Control System

1973 ◽  
Author(s):  
C. N. Webster
Keyword(s):  
Control System ◽  
Performance Characteristics ◽  
Flow Management ◽  
Yaw Control ◽  
Control Power ◽  
Aerodynamic Control ◽  
Management Concept ◽  
Control Surfaces ◽  
Selection Of ◽  
Reaction Control System

In a lift-plus-lift/cruise V/STOL fighter, reaction control may be used to provide pitch, roll and yaw control power during hover and low speed flight when aerodynamic control surfaces are ineffective. This power is provided by reaction jets in the pitch, roll and yaw axes. Reaction thrust is derived from lift engine bleed air. This paper discusses the trade studies leading to the selection of a reaction control system arrangement and a bleed air management concept. The selected system, its performance characteristics, and flow management are discussed.

Longitudinal Flight Control for a Novel Airborne Wind Energy System: Robust MIMO Control Design Techniques

2011 ◽  
Author(s):  
Nicholas Tierno ◽  
Nicholas White ◽  
Mario Garcia-Sanz
Keyword(s):  
Wind Energy ◽  
Wind Turbine ◽  
Flight Control ◽  
Synchronous Generator ◽  
Energy System ◽  
Polar Coordinate System ◽  
Additional Information ◽  
Wind Energy System ◽  
Aerodynamic Control ◽  
Control Surfaces

This paper deals with the longitudinal flight control for a novel Airborne Wind Energy (AWE) system: the EAGLE System. It is a tethered lighter-than-air flyer wind turbine composed of a blimp, several aerodynamic airfoils (wings) with specific aerodynamic control surfaces (ailerons, elevator, rudder), a counter-rotating aerodynamic rotor for the wind turbine (four identical sections, symmetrically arranged, with three blades each), an electrical synchronous generator attached to the counter-rotating rotors, and a tether to secure the airship and to transmit the generated power. Additional information can be found in US Patent, Provisional Application No. 61/387,432 developed by the authors. The designed system proposed here supports a 2.5 kW generator and flies at approximately 100 meters. The mathematical model developed for the AWE system incorporates a hybrid blimp-airfoil design, modeled using a hybrid Cartesian-polar coordinate system to capture the dynamics of both the airship and the tether, and includes the effect of the counter-rotating aerodynamic rotor of the wind turbine, as well as the aerodynamic control surfaces. This paper presents the design of a robust Multi-Input Multi-Output (MIMO) controller for the 3×3 longitudinal flight dynamics of the tethered airborne wind energy system. The control system is designed by applying sequential MIMO robust Quantitative Feedback Theory (QFT) techniques.

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