Helicopter Control During Landing on a Moving Confined Platform

Topczewski, Sebastian; Narkiewicz, J.; Bibik, Przemysław

doi:10.1109/access.2020.3000294

Cited by 12 publications

(14 citation statements)

References 11 publications

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“…A broad description of the developed automatic flight control can be found in Topczewski et al (2020). Vessel position and attitude prediction system is used to estimate the future vessel deck movement.…”

Section: Control Methodologymentioning

confidence: 99%

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Impact of actuators backlash on the helicopter control during landing on the moving vessel deck

Topczewski

Żugaj

Bibik

2021

AEAT

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Purpose The purpose of this paper is to test the performance of the control system developed for the helicopter automatic approach and landing on the moving vessel deck, when different values of backlashes are applied to the four control actuators. Design/methodology/approach The system consists of automatic control algorithm based on the linear quadratic regulator and the vessel motion prediction algorithm based on autoregressive method with parameters calculated using Burg’s method. Necessary navigation data is provided by on-board inertial navigation system/Global Positioning System. Calculated control commands are executed by four electromechanical actuators. Performance of the mission, which is based on selected procedure of approach and landing of the helicopter on the moving vessel deck, is analyzed taking into account different values of backlashes applied to the actuators. Findings In this paper, a description of the control system dedicated for automatic approach and landing of the helicopter on the moving vessel deck is shown. Necessary information about helicopter dynamic model, control system and vessel motion model is included. Tests showing influence of actuator backlashes on the mission performance are presented. Practical implications The developed control methodology can be adapted for selected helicopter and used in prospective development of an automatic flight control system (AFCS) or in a simulator. The system can be used to define in which conditions helicopter can perform safe and successful automatic approach and landing on a moving vessel deck. Originality/value In this paper, an integrated control system is presented; influence of the control actuator backlashes on the mission performance is analyzed.

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Section: Control Methodologymentioning

confidence: 99%

“…A broad description of the developed automatic flight control can be found in Topczewski et al (2020).…”

Section: Control Methodologymentioning

confidence: 99%

Impact of actuators backlash on the helicopter control during landing on the moving vessel deck

Topczewski

Żugaj

Bibik

2021

AEAT

Self Cite

View full text Add to dashboard Cite

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“…The unmanned helicopter's trajectory tracking control system is a system for decoupling control of the multi-input/multioutput (MIMO) nonlinear system, challenging to design [1]. Traditional linear control methods generally rely on accurate mathematical models and the aircraft's physical parameters [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Trajectory Tracking Active Disturbance Rejection Control of the Unmanned Helicopter and Its Parameters Tuning

Shen

2021

IEEE Access

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To solve the problem that the trajectory tracking control system of the unmanned helicopter is limited by the accuracy of the physical model (parameters and dynamic characteristics) and external disturbance of the unmanned helicopter, this paper designs a trajectory tracking control system of the unmanned helicopter based on the linear/nonlinear hybrid Active Disturbance Rejection Control (ADRC). At the same time, this paper proposes a method for tuning the controller parameters based on the Bacterial Foraging Optimization-Flower Pollination Algorithm (BFO-FPA). Finally, the simulation test of spiral climb and "8"-figure climb is applied to verify the controller's performance. The results show that the controller proposed in this paper can effectively overcome the influence of the unmanned helicopter's internal and external disturbance, and the controller has the advantages of strong anti-disturbance ability and strong robustness. Simultaneously, the optimization algorithm can obtain the optimal global solution, and can improve the controller's performance.

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“…It is no doubt that flight safety is an issue of great importance in modern aviation and each risk should be reduced if possible. Thus, a lot attention is paid and numerous analyses are performed for each part of the design process e.g., in manufacturing [1], cockpit design [2,3], human-object interaction in terms of involuntary aircraft pilot interaction [4,5] or comfort assessment [6,7] and flight mechanics [8][9][10]. However, it still may happen that an adverse event occurs and it influences the flight safety.…”

Section: Introductionmentioning

confidence: 99%

Multi-Axis Inputs for Identification of a Reconfigurable Fixed-Wing UAV

Lichota¹

2020

Aerospace

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Designing a reconfiguration system for an aircraft requires a good mathematical model of the object. An accurate model describing the aircraft dynamics can be obtained from system identification. In this case, special maneuvers for parameter estimation must be designed, as the reconfiguration algorithm may require to use flight controls separately, even if they usually work in pairs. The simultaneous multi-axis multi-step input design for reconfigurable fixed-wing aircraft system identification is presented in this paper. D-optimality criterion and genetic algorithm were used to design the flight controls deflections. The aircraft model was excited with those inputs and its outputs were recorded. These data were used to estimate stability and control derivatives by using the maximum likelihood principle. Visual match between registered and identified outputs as well as relative standard deviations were used to validate the outcomes. The system was also excited with simultaneous multisine inputs and its stability and control derivatives were estimated with the same approach as earlier in order to assess the multi-step design.

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Helicopter Control During Landing on a Moving Confined Platform

Cited by 12 publications

References 11 publications

Impact of actuators backlash on the helicopter control during landing on the moving vessel deck

Impact of actuators backlash on the helicopter control during landing on the moving vessel deck

Trajectory Tracking Active Disturbance Rejection Control of the Unmanned Helicopter and Its Parameters Tuning

Multi-Axis Inputs for Identification of a Reconfigurable Fixed-Wing UAV

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