Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design

Kalpit S. Mehta, Kamlesh Kumar, R. B. Jagadeeshchandra

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

In this paper an autopilot system is designed for cruise mode of a fixed wing unmanned aerial vehicle (UAV). The biggest challenge is to maneuver UAV at lower altitudes while overcoming strong coupling between longitudinal and lateral mode. The six-DoF simulation model of the UAV plant under consideration is a non-linear one, to control it for cruise mode it is trimmed at cruise conditions for decoupling of plant model. The control design is divided into two phase, in first phase PID controllers are designed for individual parameter hold related to the cruise flight envelope. In the next phase a decoupled single control with the capabilities of controlling all the parameters for cruise mode is designed. Parallel control loop structure are designed to generate the throttle and elevator control command which indeed control forward speed and altitude of the UAV during cruise. This paper will thus discuss the steps by step procedures in setting up the non-linear flight model/plant, trimming method, flight dynamics, designing control laws and plant validation using simulation software. The mathematical modelling and simulation of UAV aerodynamic wind tunnel test data are adopted from Indian Institute of Science, Bangalore.

Original languageEnglish
Title of host publication2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014
PublisherInstitute of Electrical and Electronics Engineers Inc.
Pages515-520
Number of pages6
ISBN (Electronic)9781479941902
DOIs
Publication statusPublished - 01-01-2014
Externally publishedYes
Event2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014 - KanyaKumari District, Tamil Nadu, India
Duration: 10-07-201411-07-2014

Conference

Conference2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014
CountryIndia
CityKanyaKumari District, Tamil Nadu
Period10-07-1411-07-14

Fingerprint

Unmanned aerial vehicles (UAV)
Wind tunnels
Flight envelopes
Fixed wings
Flight dynamics
Trimming
Elevators
Aerodynamics
Controllers

All Science Journal Classification (ASJC) codes

  • Computer Science(all)
  • Engineering(all)

Cite this

Mehta, K. S., Kumar, K., & Jagadeeshchandra, R. B. (2014). Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design. In 2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014 (pp. 515-520). [6993016] Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ICCICCT.2014.6993016
Mehta, Kalpit S. ; Kumar, Kamlesh ; Jagadeeshchandra, R. B. / Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design. 2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014. Institute of Electrical and Electronics Engineers Inc., 2014. pp. 515-520
@inproceedings{79af910358294243a7f4c2afdf393761,
title = "Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design",
abstract = "In this paper an autopilot system is designed for cruise mode of a fixed wing unmanned aerial vehicle (UAV). The biggest challenge is to maneuver UAV at lower altitudes while overcoming strong coupling between longitudinal and lateral mode. The six-DoF simulation model of the UAV plant under consideration is a non-linear one, to control it for cruise mode it is trimmed at cruise conditions for decoupling of plant model. The control design is divided into two phase, in first phase PID controllers are designed for individual parameter hold related to the cruise flight envelope. In the next phase a decoupled single control with the capabilities of controlling all the parameters for cruise mode is designed. Parallel control loop structure are designed to generate the throttle and elevator control command which indeed control forward speed and altitude of the UAV during cruise. This paper will thus discuss the steps by step procedures in setting up the non-linear flight model/plant, trimming method, flight dynamics, designing control laws and plant validation using simulation software. The mathematical modelling and simulation of UAV aerodynamic wind tunnel test data are adopted from Indian Institute of Science, Bangalore.",
author = "Mehta, {Kalpit S.} and Kamlesh Kumar and Jagadeeshchandra, {R. B.}",
year = "2014",
month = "1",
day = "1",
doi = "10.1109/ICCICCT.2014.6993016",
language = "English",
pages = "515--520",
booktitle = "2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014",
publisher = "Institute of Electrical and Electronics Engineers Inc.",
address = "United States",

}

Mehta, KS, Kumar, K & Jagadeeshchandra, RB 2014, Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design. in 2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014., 6993016, Institute of Electrical and Electronics Engineers Inc., pp. 515-520, 2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014, KanyaKumari District, Tamil Nadu, India, 10-07-14. https://doi.org/10.1109/ICCICCT.2014.6993016

Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design. / Mehta, Kalpit S.; Kumar, Kamlesh; Jagadeeshchandra, R. B.

2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014. Institute of Electrical and Electronics Engineers Inc., 2014. p. 515-520 6993016.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

TY - GEN

T1 - Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design

AU - Mehta, Kalpit S.

AU - Kumar, Kamlesh

AU - Jagadeeshchandra, R. B.

PY - 2014/1/1

Y1 - 2014/1/1

N2 - In this paper an autopilot system is designed for cruise mode of a fixed wing unmanned aerial vehicle (UAV). The biggest challenge is to maneuver UAV at lower altitudes while overcoming strong coupling between longitudinal and lateral mode. The six-DoF simulation model of the UAV plant under consideration is a non-linear one, to control it for cruise mode it is trimmed at cruise conditions for decoupling of plant model. The control design is divided into two phase, in first phase PID controllers are designed for individual parameter hold related to the cruise flight envelope. In the next phase a decoupled single control with the capabilities of controlling all the parameters for cruise mode is designed. Parallel control loop structure are designed to generate the throttle and elevator control command which indeed control forward speed and altitude of the UAV during cruise. This paper will thus discuss the steps by step procedures in setting up the non-linear flight model/plant, trimming method, flight dynamics, designing control laws and plant validation using simulation software. The mathematical modelling and simulation of UAV aerodynamic wind tunnel test data are adopted from Indian Institute of Science, Bangalore.

AB - In this paper an autopilot system is designed for cruise mode of a fixed wing unmanned aerial vehicle (UAV). The biggest challenge is to maneuver UAV at lower altitudes while overcoming strong coupling between longitudinal and lateral mode. The six-DoF simulation model of the UAV plant under consideration is a non-linear one, to control it for cruise mode it is trimmed at cruise conditions for decoupling of plant model. The control design is divided into two phase, in first phase PID controllers are designed for individual parameter hold related to the cruise flight envelope. In the next phase a decoupled single control with the capabilities of controlling all the parameters for cruise mode is designed. Parallel control loop structure are designed to generate the throttle and elevator control command which indeed control forward speed and altitude of the UAV during cruise. This paper will thus discuss the steps by step procedures in setting up the non-linear flight model/plant, trimming method, flight dynamics, designing control laws and plant validation using simulation software. The mathematical modelling and simulation of UAV aerodynamic wind tunnel test data are adopted from Indian Institute of Science, Bangalore.

UR - http://www.scopus.com/inward/record.url?scp=84921682122&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84921682122&partnerID=8YFLogxK

U2 - 10.1109/ICCICCT.2014.6993016

DO - 10.1109/ICCICCT.2014.6993016

M3 - Conference contribution

SP - 515

EP - 520

BT - 2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014

PB - Institute of Electrical and Electronics Engineers Inc.

ER -

Mehta KS, Kumar K, Jagadeeshchandra RB. Six-DoF UAV simulation using wind tunnel test data and its cruise mode autopilot design. In 2014 International Conference on Control, Instrumentation, Communication and Computational Technologies, ICCICCT 2014. Institute of Electrical and Electronics Engineers Inc. 2014. p. 515-520. 6993016 https://doi.org/10.1109/ICCICCT.2014.6993016