scholarly journals Helicopter Control Energy Reduction Using Moving Horizontal Tail

2015 ◽  
Vol 2015 ◽  
pp. 1-10 ◽  
Author(s):  
Tugrul Oktay ◽  
Firat Sal
Keyword(s):  
Flight Control ◽  
Control Strategy ◽  
Closed Loop ◽  
Energy Savings ◽  
Optimization Method ◽  
Constrained Control ◽  
Flight Control System ◽  
Helicopter Control ◽  
Helicopter Flight ◽  
Output Variance

Helicopter moving horizontal tail (i.e., MHT) strategy is applied in order to save helicopter flight control system (i.e., FCS) energy. For this intention complex, physics-based, control-oriented nonlinear helicopter models are used. Equations of MHT are integrated into these models and they are together linearized around straight level flight condition. A specific variance constrained control strategy, namely, output variance constrained Control (i.e., OVC) is utilized for helicopter FCS. Control energy savings due to this MHT idea with respect to a conventional helicopter are calculated. Parameters of helicopter FCS and dimensions of MHT are simultaneously optimized using a stochastic optimization method, namely, simultaneous perturbation stochastic approximation (i.e., SPSA). In order to observe improvement in behaviors of classical controls closed loop analyses are done.

scholarly journals Effect of the Simultaneous Variation in Blade Root Chord Length and Blade Taper on Helicopter Flight Control Effort

2017 ◽  
Vol 2017 ◽  
pp. 1-8 ◽  
Author(s):  
Tugrul Oktay ◽  
Firat Sal
Keyword(s):  
Flight Control ◽  
Closed Loop ◽  
Chord Length ◽  
Essential Dynamics ◽  
Flight Control System ◽  
Control Effort ◽  
Blade Root ◽  
Helicopter Flight ◽  
Output Variance ◽  
Simultaneous Variation

In this study, the effect of simultaneous variation in blade root chord length and blade taper on the control effort of helicopter flight control system (i.e., FCS) of a helicopter is investigated. Therefore, helicopter models (i.e., complex, control-oriented, and physics-based models) including the main physics and essential dynamics are used. The effect of simultaneous variation in the blade root chord length and blade taper (i.e., in both chordwise and lengthwise directions dependently) on the control effort of an FCS of a helicopter and also on the closed-loop responses is studied. Comparisons in terms of the control effort and peak values with and without variations in the blade root chord and blade taper changes are carried out. For helicopter FCS variance-constrained controllers, specific output variance-constrained controllers are beneficial.

Multivariable adaptive distributed leader-follower flight control for multiple UAVs formation

2017 ◽  
Vol 121 (1241) ◽  
pp. 877-900 ◽  
Author(s):  
Y. Xu ◽  
Z. Zhen
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Flight Control ◽  
Control Strategy ◽  
Formation Control ◽  
Parametric Uncertainty ◽  
Lyapunov Theory ◽  
Formation Flight ◽  
Flight Control System ◽  
Multiple Uavs

ABSTRACTThe Unmanned Aerial Vehicles (UAVs) become more and more popular due to various potential application fields. This paper studies the distributed leader-follower formation flight control problem of multiple UAVs with uncertain parameters for both the leader and followers. This problem has not been addressed in the literature. Most of the existing literature considers the leader-follower formation control strategy with parametric uncertainty for the followers. However, they do not take the leader parametric uncertainty into account. Meanwhile, the distributed control strategy depends on less information interactions and is more likely to avoid information conflict. The dynamic model of the UAVs is established based on the aerodynamic parameters. The establishment of the topology structure between a collection of UAVs is based on the algebraic graph theory. To handle the parametric uncertainty of the UAVs dynamics, a multivariable model reference adaptive control (MRAC) method is addressed to design the control law, which enables follower UAVs to track the leader UAV. The stability of the formation flight control system is proved by the Lyapunov theory. Simulation results show that the proposed distributed adaptive leader-following formation flight control system has stronger robustness and adaptivity than the fixed control system, as well as the existing adaptive control system.

Analysis of combined passively and actively morphing blade root chord length and blade taper for helicopter control

2019 ◽  
Vol 92 (2) ◽  
pp. 172-179
Author(s):  
Firat Sal
Keyword(s):  
Flight Control ◽  
Chord Length ◽  
Flight Control System ◽  
Control Effort ◽  
Simultaneous Application ◽  
Content Type ◽  
Helicopter Control ◽  
Helicopter Blade ◽  
Blade Root ◽  
Autonomous Helicopter

Purpose The purpose of this study is to examine the effect of passive and active morphing of blade root chord length and blade taper on the control effort of the flight control system (FCS) of a helicopter. Design/methodology/approach Physics-based helicopter models, which are functions of passive and active morphing, are created and applied in helicopter FCS design to determine the control effort. Findings Helicopters, having both passively and actively morphing blade root chord length and blade taper, experience less control effort than the ones having either only passively morphing blade root chord length or only blade taper or only actively morphing blade root chord length and blade taper. Practical implications Both passively and actively morphing blade root chord length and blade taper can be implemented for more economical autonomous helicopter flights. Originality/value Main novelty of our article is simultaneous application of passive and active morphing ideas on helicopter root chord length and blade taper. It is also proved in this study that using both passive and active morphing ideas on helicopter blade root chord and blade taper causes much less energy consumption than using either only passive morphing idea on helicopter blade root chord and blade taper or only active morphing idea on helicopter blade root chord and blade taper. This also reduces fuel consumption and also makes environment cleaner.

The Modeling and Simulation of Hydraulic Actuated Control System of Helicopter in Volumetric Speed Control

2015 ◽  
Vol 779 ◽  
pp. 169-174
Author(s):  
Feng Gu ◽  
Ji Hai Jiang ◽  
Fei Meng Diao ◽  
Quan Du ◽  
Lei Gao ◽  
...  
Keyword(s):  
Control System ◽  
Flight Control ◽  
Speed Control ◽  
Performance Curve ◽  
Generation System ◽  
Helicopter Control ◽  
Modeling Simulation ◽  
Helicopter Flight ◽  
Speed Control System ◽  
Wheel Brake

Hydraulic generation system on helicopter generally consists of flight control hydraulic actuating circuit, landing gear retraction/extension hydraulic circuit, and wheel brake circuit. This paper studies on a volumetric speed control system applied in helicopter flight control actuating system. The system performance curve, deduced from the modeling, simulation and testing of the tail-actuating system, reveals that this volumetric speed control system meets the requirements of helicopter control system actuating.

scholarly journals Survey on Flight Control Technology for Large-Scale Helicopter

2017 ◽  
Vol 2017 ◽  
pp. 1-14 ◽  
Author(s):  
Jinshuo Hu ◽  
Hongbin Gu
Keyword(s):  
Flight Control ◽  
Large Scale ◽  
Control Technology ◽  
Flight Control System ◽  
Future Directions ◽  
Research Issues ◽  
Advantages And Disadvantages ◽  
Helicopter Flight ◽  
Challenging Research ◽  
Theoretical Developments

A literature review of flight control technology is presented for large-scale helicopter. Challenges of large-scale helicopter flight control system (FCS) design are illustrated. Following this, various flight control methodologies are described with respect to their engineering implementation and theoretical developments, whose advantages and disadvantages are also analyzed. Then, the challenging research issues on flight control technology are identified, and future directions are highlighted.

Integration Design and Simulation of Hydraulic Actuated Control System of Helicopter

2015 ◽  
Vol 779 ◽  
pp. 182-186
Author(s):  
Feng Gu ◽  
Ji Hai Jiang ◽  
Fei Meng Diao ◽  
Yan Nan Song ◽  
Quan Du ◽  
...  
Keyword(s):  
Control System ◽  
Flight Control ◽  
Hydraulic System ◽  
Small Volume ◽  
Hydraulic Power ◽  
Helicopter Control ◽  
Helicopter Flight

Hydraulic system is one of the most important parts of helicopter. Its function is to supply hydraulic power to the utilities. This paper studies an integration hydraulic system applied in helicopter flight control actuating system and simulates the system. The system has a small volume, light mass, meeting the requirements of helicopter control system actuating.

Take-off and landing control for a coaxial ducted fan unmanned helicopter

2017 ◽  
Vol 89 (6) ◽  
pp. 764-776 ◽  
Author(s):  
Zhi Chen ◽  
Daobo Wang ◽  
Ziyang Zhen ◽  
Biao Wang ◽  
Jian Fu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Strategy ◽  
Sliding Mode ◽  
Engineering Practice ◽  
Unmanned Helicopter ◽  
Flight Control System ◽  
Content Type ◽  
Ducted Fan ◽  
Coupling Characteristics

Purpose This paper aims to present a control strategy that eliminates the longitudinal and lateral drifting movements of the coaxial ducted fan unmanned helicopter (UH) during autonomous take-off and landing and reduce the coupling characteristics between channels of the coaxial UH for its special model structure. Design/methodology/approach Unidirectional auxiliary surfaces (UAS) for terminal sliding mode controller (TSMC) are designed for the flight control system of the coaxial UH, and a hierarchical flight control strategy is proposed to improve the decoupling ability of the coaxial UH. Findings It is demonstrated that the proposed height control strategy can solve the longitudinal and lateral movements during autonomous take-off and landing phase. The proposed hierarchical controller can decouple vertical and heading coupling problem which exists in coaxial UH. Furthermore, the confronted UAS-TSMC method can guarantee finite-time convergence and meet the quick flight trim requirements during take-off and landing. Research limitations/implications The designed flight control strategy has not implemented in real flight test yet, as all the tests are conducted in the numerical simulation and simulation with a hardware-in-the-loop (HIL) platform. Social implications The designed flight control strategy can solve the common problem of coupling characteristics between channels for coaxial UH, and it has important theoretical basis and reference value for engineering application; the control strategy can meet the demands of engineering practice. Originality/value In consideration of the TSMC approach, which can increase the convergence speed of the system state effectively, and the high level of response speed requirements to UH flight trim, the UAS-TSMC method is first applied to the coaxial ducted fan UH flight control. The proposed control strategy is implemented on the UH flight control system, and the HIL simulation clearly demonstrates that a much better performance could be achieved.

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