| Description |
xxiv, 265 leaves : illustrations (most colored) ; 29 cm |
| Summary |
"Unmanned aerial vehicles possessing vertical takeoff and landing capabilities are receiving growing interest within the aerospace industry, as these aircraft can be operated in areas and on missions that preclude the use of conventional aircraft. This thesis presents the development and analysis of the triple tilt-duct aircraft configuration, an aircraft design suited for future generations of VTOL UAVs. The development of a conceptual design for a small-scale, "proof of concept" tilt-duct UAV is presented, culminating in a description of the final conceptual design. The methodology for a detailed analysis of the performance and the stability and control characteristics of the tilt-duct UAV design is outlined, along with the results from these analyses. The tilt-duct UAV has good stability and handling characteristics when in horizontal flight mode, but is highly unstable when hovering or in vertical flight mode. A study of the motion of the tilt-duct aircraft during transition maneuvers between horizontal and vertical flight modes is also presented; schemes for performing optimal transition maneuvers and maintaining adequate pitch control during the transitions are given as well. A flight simulation model was utilized to test the performance and stability and control of the tilt-duct UAV. Though it was not possible to accurately simulate transition maneuvers with the software package used, it was possible to obtain reasonable measurements of the aircraft's performance and response to control inputs. An outlook for the triple tilt-duct configuration is given, along with suggestions for future research. It is felt that the triple tilt-duct configuration is a viable design for future VTOL aircraft"--Abstract, leaf iii. |
|
