Parameters identification of thrust generation subsystem for small unmanned aerial vehicles

Filatov, Denis M.; Friedrich, Anastasya I.; Devyatkin, A. V.

doi:10.1109/ctsys.2017.8109574

Cited by 4 publications

(3 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Typically, a force sensor and a reaction torque sensor are necessary to come up with the propeller thrust-torque and thrust-pulse width modulation (PWM) relationships [13,14]. However, these sophisticated sensors are highly expensive and not readily available.…”

Section: Propeller Parametersmentioning

confidence: 99%

Modeling and Implementation of Quadcopter Autonomous Flight Based on Alternative Methods to Determine Propeller Parameters

Rible¹,

Arriola²,

Ramos³

2020

Adv. sci. technol. eng. syst. j.

View full text Add to dashboard Cite

To properly simulate and implement a quadcopter flight control for intended load and flight conditions, the quadcopter model must have parameters on various relationships including propeller thrust-torque, thrust-PWM, and thrust-angular speed to a certain level of accuracy. Thrust-torque modeling requires an expensive reaction torque measurement sensor. In the absence of sophisticated equipment, the study comes up with alternative methods to complete the quadcopter model. The study also presents a method of modeling the rotational aerodynamic drag on the quadcopter. Although the resulting model of the reaction torque generated by the quadcopter's propellers and the model of the drag torque acting on the quadcopter body that are derived using the methods in this study may not yield the true values of these quantities, the experimental modeling techniques presented in this work ensure that the derived dynamic model for the quadcopter will nevertheless behave identically with the true model for the quadcopter. The derived dynamic model is validated by basic flight controller simulation and actual flight implementation. The model is used as basis for a quadcopter design, which eventually is used for test purposes of basic flight control. This study serves as a baseline for fail-safe control of a quadcopter experiencing an unexpected motor failure.

show abstract

Section: Propeller Parametersmentioning

confidence: 99%

Modeling and Implementation of Quadcopter Autonomous Flight Based on Alternative Methods to Determine Propeller Parameters

Rible¹,

Arriola²,

Ramos³

2020

Adv. sci. technol. eng. syst. j.

View full text Add to dashboard Cite

show abstract

“…7 , for the platform used in this study. The data-set for the empirical equation was obtained by performing lab tests using thrust stand and was also compared with [26] for the same propulsion system.…”

Section: Power Consumption By Motorsmentioning

confidence: 99%

Energy distribution in Dual-UAV collaborative transportation through load sharing

Mohiuddin

Zweiri

Almadhoun

et al. 2020

Journal of Mechanisms and Robotics

View full text Add to dashboard Cite

In this paper, a novel dual-UAV collaborative aerial transport strategy based on energy distribution and load sharing is proposed. This paper presents the first experimental demonstration of dual-UAV collaborative aerial transport while distributing power consumption. The demonstration is performed while distributing the power consumption between two drones sharing a load based on their battery state of charge. A numerical model of the dual-hex-rotor-payload is used to validate the proposed strategy. Numerical and hardware tests were conducted to demonstrate the load distribution using multiple UAV with certain spatial configurations. Finally, collaborative aerial transport test scenarios are performed numerically and experimentally. The simulation and experimental results show the effectiveness and applicability of the proposed strategy.

show abstract

“…A thrust measurement stand is used to obtain the rotor speed, thrust and energy consumption plots for the DJI E310 propulsion system, which includes 2312 motors with the DJI 9450 rotors. All values obtained were compared with the values given by [23] for the same propulsion system. A power law based empirical equation between the rotor speed and the power consumption is obtained using curve fitting as shown in Equation (20):…”

Section: Motor Energy Consumptionmentioning

confidence: 99%

UAV Payload Transportation via RTDP Based Optimized Velocity Profiles

Mohiuddin

Taha²,

Zweiri

et al. 2019

Energies

View full text Add to dashboard Cite

This paper explores the application of a real-time dynamic programming (RTDP) algorithm to transport a payload using a multi-rotor unmanned aerial vehicle (UAV) in order to optimize journey time and energy consumption. The RTDP algorithm is developed by discretizing the journey into distance interval horizons and applying the RTDP sweep to the current horizon to get the optimal velocity decision. RTDP sweep requires the current state of the UAV to generate the next best velocity decision. To the best of the authors knowledge, this is the first time that such real-time optimization algorithm is applied to multi-rotor based transportation. The algorithm was first tested in simulations and then experiments were performed. The results show the effectiveness and applicability of the proposed algorithm.

show abstract

Parameters identification of thrust generation subsystem for small unmanned aerial vehicles

Cited by 4 publications

References 14 publications

Modeling and Implementation of Quadcopter Autonomous Flight Based on Alternative Methods to Determine Propeller Parameters

Modeling and Implementation of Quadcopter Autonomous Flight Based on Alternative Methods to Determine Propeller Parameters

Energy distribution in Dual-UAV collaborative transportation through load sharing

UAV Payload Transportation via RTDP Based Optimized Velocity Profiles

Contact Info

Product

Resources

About