Design, Development, and Modeling of EMLA-Based Wheel Brake Actuation System for an UAV

  • D. Satish BabuEmail author
  • P. N. Vijay Vittal
  • Pollov Sarmah
  • Veena G. Dikshit
Conference paper
Part of the Lecture Notes on Multidisciplinary Industrial Engineering book series (LNMUINEN)


Wheel brake systems are designed for aircraft became common ever since it participated in transportation and specific applications, as the intricacy and speed of operation amplified and the usage of different airstrips and land surfaces for different conditions. Wheel brake system operation solely depends upon aircraft safe operation on the different surface grounds. The brake system slows the speed of aircraft and stops it in a specific amount of reasonable time and distance. In general, most of the aircrafts having the main landing gear wheels are outfitted with a power-assisted brake assembly and the front or rear landing gear does not having the wheel brake system. This paper presented a development of electromechanical linear actuator (EMLA) based wheel braking system that contained linear actuator, crank arm, master cylinder, and a brake caliper control system. Dynamic model of EMLA-based system simulated with command from flight control computer and actuation system was established. The command control of actuation input and distribution of brake force approach were also discussed. Experiments conducted to estimate the performance of braking system and checked with real system. The simulation studies, and experimental performances show the practicability, effectiveness and implementation of this braking system on a typical unmanned aerial vehicle (UAV). The system was also implemented on a UAV platform, and the actuation requirements for the various braking conditions were quantified.


UAV wheel brake actuation EMLA Brake torque Actuation controller 



The authors sincerely thanks to the Director, Group Director (GD), Divisional Head (DH) and Head, HRD of ADE for giving encouragement and permission to publish this technical paper.

The author gratefully acknowledge the assembly, testing, integration of actuation system, conducting experiments in laboratory and on aircraft by Shafeer Ahmed, Vijay Kumar, Kunjappa, Jerome Marshal, Anoj Jacob, Rajasekhar, Shiva raj, and R1 Project team.

Conflicts of Interest: The authors declare no conflict of interest.

Copyright information

© Springer Nature Singapore Pte Ltd. 2020

Authors and Affiliations

  1. 1.Aeronautical Development Establishment (ADE)DRDOBangaloreIndia

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