0
TECHNICAL PAPERS: Gas Turbines: Cycle Innovations

A Study on Transient Performance Characteristics of the Canard Rotor Wing Type Unmanned Aerial Vehicle Propulsion System During Flight Mode Transition

[+] Author and Article Information
Changduk Kong1

Department of Aerospace Engineering, Chosun University, #375 Seosuk-dong, Dong-gu, Kwangju 501-759, Republic of Koreacdgong@mail.chosun.ac.kr

Jongha Park

Department of Aerospace Engineering, Chosun University, #375 Seosuk-dong, Dong-gu, Kwangju 501-759, Republic of Koreajjonga29@nate.com

Myoungcheol Kang

Department of Aerospace Engineering, Chosun University, #375 Seosuk-dong, Dong-gu, Kwangju 501-759, Republic of Koreak0914@stmail.chosun.ac.kr

1

Corresponding author.

J. Eng. Gas Turbines Power 128(3), 573-578 (Sep 28, 2005) (6 pages) doi:10.1115/1.2135821 History: Received August 25, 2005; Revised September 28, 2005

A propulsion system of the CRW (Canard rotor wing) type UAV (unmanned aerial vehicle) was composed of the turbojet engine, exhaust nozzles (including some tip jet nozzles and a main nozzle), and the duct system (including straight ducts, curved ducts, and master valve). The CRW-type UAV has three different flight modes, such as the rotary wing mode for takeoff and landing, the high-speed forward flight mode with the fixed wing, and the transition flight mode between the previously mentioned two flight modes. In order to evaluate transient performance characteristics of the CRW-type UAV propulsion system during flight mode transition, the propulsion system was modeled using SIMULINK ®, which is a user-friendly graphical-user-interface-(GUI) type dynamic analysis tool provided by MATLAB , in this study. The transition flight mode between the rotary wing mode and the fixed wing mode was simulated by considering area variation of the master valve and the main exhaust nozzle. In order to verify acceptability of the main turbojet engine model, performance simulation results using SIMULINK were compared to results using the commercial program GSP. Through this simulation, proper operation of the master valve and the variable area main nozzle can be found for safe flight transition. Therefore, performance characteristics were investigated depending on various angle positions of the master valve.

FIGURES IN THIS ARTICLE
<>
Copyright © 2006 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Schematic layout of smart UAV propulsion system

Grahic Jump Location
Figure 2

Overall SIMULINK model

Grahic Jump Location
Figure 3

Straight and bend duct subsystem

Grahic Jump Location
Figure 6

Comparison of transient analysis results of turbojet engine by SIMULINK and GSP

Grahic Jump Location
Figure 7

Transient analysis result of rotary wing flight mode

Grahic Jump Location
Figure 8

Transient propulsion system performance characteristic during flight mode transition (from rotary wing mode to fixed wing mode)

Grahic Jump Location
Figure 9

Transient propulsion system performance characteristic during flight mode transition (from fixed wing mode to rotary wing mode)

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In