Flight Evaluation of a Reactionary Envelope Protection System for UAVs

Date

2011-01-01

Author

Unnikrishnan, Suraj
Prasad, J. V. R.
Yavrucuk, İlkay

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

142
views

0
downloads

This paper presents the development and flight test evaluation of a reactionary envelope protection method suitable for limit protection in uninhabited aerial vehicles (UAVs). The method is based on finite-time horizon predictions of limit parameter response for detecting any impending limit boundary violations. Limit violations are prevented by treating limit boundaries as obstacles and by correcting nominal control/command inputs to track safe-response profiles of limit parameters near the limit boundaries. The method is first evaluated in simulations using the Georgia Tech UAV simulation tool (GUST) for the load factor limit protection. The load factor limit protection system is then evaluated using flight tests on the Georgia Tech unmanned rotorcraft vehicle (GTMax UAV) at Georgia Tech. The flight test results show that the reactionary load factor limit protection system is successful at maintaining the vehicle load factor response within prescribed upper limit while executing an aggressive e-turn maneuver.

Subject Keywords

Rotorcraft, Avoidance

URI

https://hdl.handle.net/11511/33210

Journal

JOURNAL OF THE AMERICAN HELICOPTER SOCIETY

DOI

https://doi.org/10.4050/jahs.56.012009

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Flight Evaluation of Reactionary Envelope Protection System Yavrucuk, İlkay (2011-01-01) This paper presents the development and flight test evaluation of a reactionary envelope protection method suitable for limit protection in uninhabited aerial vehicles (UAVs). The method is based on finite‐time horizon predictions of limit parameter response for detecting any impending limit boundary violations. Limit violations are prevented by treating limit boundaries as obstacles and by correcting nominal control/command inputs to track safe‐response profiles of limit parameters near the limit boundarie...
Envelope Protection for Autonomous Unmanned Aerial Vehicles Yavrucuk, İlkay; Unnikrishnan, Suraj (2009-01-01) This paper describes the design, development, and testing of an automatic envelope protection system as implemented on Georgia Institute of Technology's unmanned helicopter GTMax. The envelope protection system makes use of online-learning adaptive neural networks to generate online dynamic models, which are used to estimate limits on controller commands. The system provides command capability up to the limit boundaries while preventing envelope exceedance. Simulation and flight-test results are provided fo...
Coordinated guidance for multiple UAVs Cakici, Ferit; Ergezer, Halit; Irmak, Ufuk; Leblebicioğlu, Mehmet Kemal (2016-05-01) This paper addresses the path planning problem of multiple unmanned aerial vehicles (UAVs). The paths are planned to maximize collected amount of information from desired regions (DRs), while avoiding forbidden regions (FRs) and reaching the destination. This study focuses on maximizing collected information instead of minimizing total mission time, as in previous studies. The problem is solved by a genetic algorithm (GA) with the proposal of novel evolutionary operators. The initial populations are generat...
Flight test maneuver design and aerodynamic parameter estimation for single use autonomous air vehicles Vefa Yavuzturk, N.; Topbas, Eren; Yazıcıoğlu, Yiğit (null; 2017-01-01) In this paper, a maneuver design and aerodynamic parameter estimation procedure is carried out for single use autonomous gliding air vehicles where allowable flight testing time is limited. At first, using the priori aerodynamics of a gliding vehicle, an aerodynamic model has been built and six degree of freedom simulation tool is generated. This priori aerodynamic knowledge is used to design a multi-sine input to excite the system at predetermined flight conditions during flight test. Afterwards, using the...
Flight control system design of an uncommon quadrotor aerial vehicle Baskın, Mehmet; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2021-9-01) In this thesis, design of a flight control system for an uncommon quadrotor aerial vehicle is discussed. This aerial vehicle consists of two counter-rotating big rotors on longitudinal axis to increase the lift capacity and flight endurance, and two counter-rotating small tilt rotors on lateral axis to stabilize the attitude. Firstly, full nonlinear dynamic model of this vehicle is obtained by using Newton-Euler formulation. Later, derived approximate linear model around hover is statically decoupled to sim...

Citation Formats

S. Unnikrishnan, J. V. R. Prasad, and İ. Yavrucuk, “Flight Evaluation of a Reactionary Envelope Protection System for UAVs,” JOURNAL OF THE AMERICAN HELICOPTER SOCIETY, pp. 0–0, 2011, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/33210.