Motion-Specific Battery Health Assessment for Quadrotors Using High-Fidelity Battery Models
Authors: Joonhee Kim, Sanghyun Park, Donghyeong Kim, Eunseon Choi, Soohee Han
Organizations: Department of Convergence IT Engineering, Pohang University of Science and Technology, Choengam-ro 77, Nam-gu, Pohang-si, Gyeongsangbuk-do, Republic of Korea. · Department of Electrical Engineering, Pohang University of Science and Technology, Choeng-am-ro 77, Nam-gu, Pohang-si, Gyeongsangbuk-do, Republic of Korea.
Quadrotor endurance is ultimately limited by battery behavior, yet most energy aware planning treats the battery as a simple energy reservoir and overlooks how flight motions induce dynamic current loads that accelerate battery degradation. This work presents an end to end framework for motion aware battery health assessment in quadrotors. We first design a wide range current sensing module to capture motion specific current profiles during real flights, preserving transient features. In parallel, a high fidelity battery model is calibrated using reference performance tests and a metaheuristic based on a degradation coupled electrochemical model.By simulating measured flight loads in the calibrated model, we systematically resolve how different flight motions translate into degradation modes loss of lithium inventory and loss of active material as well as internal side reactions. The results demonstrate that even when two flight profiles consume the same average energy, their transient load structures can drive different degradation pathways, emphasizing the need for motion-aware battery management that balances efficiency with battery degradation.
Figures & tables
Electrochemical parameters
Symbol
Description
θpmax,θpmin,θnmax,θnmin
Stoichiometry limit
Rp,Rn
Solid particle radius
σp,σn
Solid-phase conductivity
ϵp,ϵsep,ϵn
Electrolyte porosity
ϵf,p,ϵf,n
Filler fraction
TABLE I: Battery model parameters to be estimated
Fig. 1 : Pipeline of motion-specific battery health assessment: reference tests calibrate an electrochemical model, flight data are acquired with a custom module, and virtual experiments evaluate degradation.
Fig. 2 : Experimental setup of the battery-in-the-loop system, consisting of a programmable power supply, an electronic load, and a battery pack under test.
Fig. 3 : Calibration results of the battery electrochemical model. (Top) Comparison between measured and simulated voltage responses under 0.1 C, 2 C, and pulse reference performance tests. (Bottom) Corresponding error profile, with segments distinguished by load conditions.
Fig. 4 : Custom current sensing module integrated into the quadrotor platform. The module consists of a wide-range current sensor, an STM32 Nucleo board for control and data processing, and an SD card module for onboard data logging.
Quadrotor specification
Parameter
Description
Frame
S500 Quadrotor
Controller
Pixhawk 6C
Motor
DJI NAZA 2212 Brushless Motor 920KV
Propeller
DJI 1045 propeller
Weight
975 g
TABLE II: Detailed specifications of the quadrotor platform and the 4S1P battery pack employed in this study.
Fig. 5 : Procedure of extraction and processing of motion-specific current profiles from quadrotor flight data. (a) Raw current signal with a moving-average filter. (b) Segmentation of the filtered data. (c) Periodic reconstruction of the segmented profiles. (d) Simulated voltage responses under the reconstructed profiles.
Fig. 6 : Motion-aware battery health assessment results under motion-specific (stars) and constant-current (circles) profiles with C-rates of 16, 18, 20, and 22. (a) Normalized degradation modes (b) Normalized capacity loss induced by side reactions.
Quadrotor specification
Parameter
Description
Frame
Custom carbon frame (arm length 300mm)
Controller
Custom
Motor
EMAX ECO2 2306 1700KV
Propeller
Gemfan 7040-3 7inch
Weight
455 g
TABLE III: Specification of the secondary quadrotor platform
Fig. 7 : Health assessment results for a secondary 455 g quadrotor platform. (a) Hardware configuration. (b) Segmented motion-specific current profiles. (c) Normalized degradation modes.
This paper presents a battery-aware predictive trajectory-planning and control framework for multirotors operating under spatially localized disturbances. Candidate trajectories are evaluated through closed-loop vehicle--motor--battery propagation, allowing disturbance-induced control demand, electrical energy, battery evolution, and terminal-voltage-dependent actuator capability to enter the planning process. % A reduced-order battery model is numerically benchmarked against an independently implemented Simscape equivalent-circuit reference, with a power NRMSE of 0.64% and a cumulative-energy discrepancy below 0.7%. % In a 150-s, 640-m mission containing three disturbance regions, the selected trajectory reduces electrical energy consumption by 7.46% and position-tracking RMSE by approximately 72% relative to the disturbance-aware fixed-reference baseline. % Planner ablations show that battery-dependent terms are nonbinding at nominal SOC but alter the selected trajectory under a depleted-battery stress condition. % Execution with multiple feedback controllers further demonstrates that controller selection changes the tradeoff among tracking accuracy, energy consumption, and actuator utilization. % The results demonstrate the benefit of accounting for predicted closed-loop energetic and battery--actuator consequences during trajectory selection.
Krishna Bhavithavya Kidambi
department of Mechanical and Aerospace Engineering at University of Dayton, Dayton, OH.
Agile flight tasks such as drone racing and pursuit-evasion require strong acceleration and precise turns, but the available thrust changes as the battery discharges and voltage drops under load. Conservative command limits make this variation easier to tolerate, at the cost of unused performance. We investigate how learned controllers can use that additional thrust while retaining the flight controller's voltage compensation and rate control. Our training simulator couples an identified load-transient battery model to rotor dynamics and firmware saturation. The feedforward policy receives filtered voltage during both training and deployment. Controlled ablations distinguish the benefit of a larger thrust-command range from that of voltage information. On a 38 g Crazyflie Brushless, the resulting policy reduces circle tracking error by 49% relative to stock-authority RL at 3.84 m/s, while preserving easy-task precision. Mean 20-lap race time decreases from 106.22 s to 95.24 s. Compared with a voltage-blind policy with the same increased authority, hardware error and race time are lower by 15.3% and 4.5%, respectively. In simulation, replacing the policy's voltage input with a recording from a different battery condition worsens hard-circle tracking, with a smaller, voltage-dependent effect in racing. Together, these results show where a simple voltage input complements existing actuator compensation in aggressive learned flight.
Alejandro Sanchez Roncero, Olov Andersson, Petter Ogren
Department of Robotics, Perception and Learning, School of Electrical Engineering and Computer Science, Royal Institute of Technology (KTH), SE-100 44 Stockholm, Sweden
Battery-powered multirotor unmanned aerial vehicles (UAVs) can rapidly map unknown environments, but mission performance is often limited by energy rather than geometry alone. Standard exploration policies that optimise for coverage or time can therefore waste energy through manoeuvre-heavy trajectories. In this paper, we address energy-aware autonomous 3D exploration for multirotor UAVs in initially unknown environments. We propose Energy-Aware Autonomous Exploration (EAAE), a modular frontier-based framework that makes energy an explicit decision variable during frontier selection. EAAE clusters frontiers into view-consistent regions, plans dynamically feasible candidate trajectories to the most informative clusters, and predicts their execution energy using an offline power estimation loop. The next target is then selected by minimising predicted trajectory energy while preserving exploration progress through a dual-layer planning architecture for safe execution. We evaluate EAAE in a full exploration pipeline with a rotor-speed-based power model across simulated 3D environments of increasing complexity. Compared to representative distance-based and information gain-based frontier baselines, EAAE consistently reduces total energy consumption while maintaining competitive exploration time and comparable map quality, providing a practical drop-in energy-aware layer for frontier exploration.
Jacob Elskamp, Moji Shi, Leonard Bauersfeld +2
Faculty of Aerospace Engineering, Delft University of Technology, Delft, The Netherlands · Institute for Informatics, University of Zurich, Zurich, Switzerland