Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft
The tilt-rotor aircraft has often been proposed as a means to increase the maximum speed of the conventional helicopter. The tilt-rotor aircraft consists of three primary flight modes that are the helicopter flight mode in low forward speed flight, airplane flight mode in high forward speed flight,...
Saved in:
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Wiley
2019-01-01
|
| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2019/5737212 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1832562149517426688 |
|---|---|
| author | Ke Lu Chunsheng Liu Chunhua Li Renliang Chen |
| author_facet | Ke Lu Chunsheng Liu Chunhua Li Renliang Chen |
| author_sort | Ke Lu |
| collection | DOAJ |
| description | The tilt-rotor aircraft has often been proposed as a means to increase the maximum speed of the conventional helicopter. The tilt-rotor aircraft consists of three primary flight modes that are the helicopter flight mode in low forward speed flight, airplane flight mode in high forward speed flight, and conversion flight mode. The aim of this paper is to develop a nonlinear flight dynamics mathematical modeling method of tilt-rotor aircraft and investigate the dynamic stability characteristics of tilt-rotor aircraft. First, a nonlinear tilt-rotor aircraft flight dynamics model is developed. The trim and linearized results are present to verify the model. Then, using a numerical differentiation technique, the dynamic stability of the tilt-rotor aircraft is assessed. The results show that the flight speed and nacelle angle would affect the magnitude and the trend of the aerodynamic derivatives. The damping of the pitch short period mode and the Dutch roll mode is insensitive to flight speed while they could be affected by nacelle angle. In all flight modes, as flight speed increases, the natural modes become more stable. |
| format | Article |
| id | doaj-art-29d73acb12354b60a0455935b2c2d2ad |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2019-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-29d73acb12354b60a0455935b2c2d2ad2025-02-03T01:23:19ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742019-01-01201910.1155/2019/57372125737212Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor AircraftKe Lu0Chunsheng Liu1Chunhua Li2Renliang Chen3College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210016, ChinaCollege of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210016, ChinaScience and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen, Jiangxi 333001, ChinaNational Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210016, ChinaThe tilt-rotor aircraft has often been proposed as a means to increase the maximum speed of the conventional helicopter. The tilt-rotor aircraft consists of three primary flight modes that are the helicopter flight mode in low forward speed flight, airplane flight mode in high forward speed flight, and conversion flight mode. The aim of this paper is to develop a nonlinear flight dynamics mathematical modeling method of tilt-rotor aircraft and investigate the dynamic stability characteristics of tilt-rotor aircraft. First, a nonlinear tilt-rotor aircraft flight dynamics model is developed. The trim and linearized results are present to verify the model. Then, using a numerical differentiation technique, the dynamic stability of the tilt-rotor aircraft is assessed. The results show that the flight speed and nacelle angle would affect the magnitude and the trend of the aerodynamic derivatives. The damping of the pitch short period mode and the Dutch roll mode is insensitive to flight speed while they could be affected by nacelle angle. In all flight modes, as flight speed increases, the natural modes become more stable.http://dx.doi.org/10.1155/2019/5737212 |
| spellingShingle | Ke Lu Chunsheng Liu Chunhua Li Renliang Chen Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft International Journal of Aerospace Engineering |
| title | Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft |
| title_full | Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft |
| title_fullStr | Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft |
| title_full_unstemmed | Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft |
| title_short | Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft |
| title_sort | flight dynamics modeling and dynamic stability analysis of tilt rotor aircraft |
| url | http://dx.doi.org/10.1155/2019/5737212 |
| work_keys_str_mv | AT kelu flightdynamicsmodelinganddynamicstabilityanalysisoftiltrotoraircraft AT chunshengliu flightdynamicsmodelinganddynamicstabilityanalysisoftiltrotoraircraft AT chunhuali flightdynamicsmodelinganddynamicstabilityanalysisoftiltrotoraircraft AT renliangchen flightdynamicsmodelinganddynamicstabilityanalysisoftiltrotoraircraft |