國立虎尾科技大學 |

Methodology to Model Aircraft and Propulsor Performance of Advanced Air Mobility.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Methodology to Model Aircraft and Propulsor Performance of Advanced Air Mobility./
作者:	De la Cruz, Jessica J.
面頁冊數:	1 online resource (56 pages)
附註:	Source: Masters Abstracts International, Volume: 85-02.
Contained By:	Masters Abstracts International85-02.
標題:	Aerospace engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9798380131049

Methodology to Model Aircraft and Propulsor Performance of Advanced Air Mobility.
De la Cruz, Jessica J.

Methodology to Model Aircraft and Propulsor Performance of Advanced Air Mobility. - 1 online resource (56 pages)

Source: Masters Abstracts International, Volume: 85-02.

Thesis (M.E.)--University of California, Irvine, 2023.

Includes bibliographical references

Advanced Air Mobility (AAM) distributed propulsion vehicles are currently being proposed in industry and may be capable of flying various operations such as Short-Takeoff and Landing (STOL), Tilt-Rotor Vertical Takeoff and Landing (Tilt-Rotor VTOL) and Lift plus Cruise Vertical Takeoff and Landing (LPC VTOL). The effects of each propulsor configuration must be assessed for efficient and quiet low-altitude flight procedures. This thesis paper outlines a methodology to assess the aircraft performance of AAM vehicles with open rotor configurations by predicting operating states such as propeller RPM, power, thrust and drag characteristics within a given flight procedure. Such methodology utilizes a polar drag buildup to predict the aerodynamic losses of AAM vehicles during takeoff, transition and cruise conditions. MATLAB is utilized to generate a best-fit line of wind tunnel-tested experimental data from parallel, normal and inclined flow to compute the coefficient of drag. Simultaneously, this methodology utilizes the blade element momentum theory propeller design program XROTOR to size the distributed propulsors capable of operating the mentioned relevant flight segments. The propulsor design methodology outlined in this paper minimizes induced losses at the rotors by constraining a low Mach tip number, to lower community noise levels with a feasible motor torque. Propeller off-design conditions are presented in propeller contour maps obtained from XROTOR for fixed and variable pitch propeller settings, to provide the mentioned relationship between RPM and segment thrust. Such a relationship can be used to build flight procedure dynamics and predict overall efficiency and community noise levels. An application of the described methodology will be presented to determine the low-altitude flight aircraft performance of STOL, Tilt-Rotor VTOL, and LPC VTOL AAM vehicles.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798380131049Subjects--Topical Terms:

686400
Aerospace engineering.
Subjects--Index Terms:

Advanced Air MobilityIndex Terms--Genre/Form:

554714
Electronic books.

Methodology to Model Aircraft and Propulsor Performance of Advanced Air Mobility.
LDR:03228ntm a22003737 4500 001 1145124
005 20240617111350.5
006 m o d
007 cr mn ---uuuuu
008 250605s2023 xx obm 000 0 eng d
020 $a 9798380131049
035 $a (MiAaPQ)AAI30527518
035 $a AAI30527518
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a De la Cruz, Jessica J. $3 1470342
245 1 0 $a Methodology to Model Aircraft and Propulsor Performance of Advanced Air Mobility.
264 0 $c 2023
300 $a 1 online resource (56 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
338 $a online resource $b cr $2 rdacarrier
500 $a Source: Masters Abstracts International, Volume: 85-02.
500 $a Advisor: Huynh, Jacqueline.
502 $a Thesis (M.E.)--University of California, Irvine, 2023.
504 $a Includes bibliographical references
520 $a Advanced Air Mobility (AAM) distributed propulsion vehicles are currently being proposed in industry and may be capable of flying various operations such as Short-Takeoff and Landing (STOL), Tilt-Rotor Vertical Takeoff and Landing (Tilt-Rotor VTOL) and Lift plus Cruise Vertical Takeoff and Landing (LPC VTOL). The effects of each propulsor configuration must be assessed for efficient and quiet low-altitude flight procedures. This thesis paper outlines a methodology to assess the aircraft performance of AAM vehicles with open rotor configurations by predicting operating states such as propeller RPM, power, thrust and drag characteristics within a given flight procedure. Such methodology utilizes a polar drag buildup to predict the aerodynamic losses of AAM vehicles during takeoff, transition and cruise conditions. MATLAB is utilized to generate a best-fit line of wind tunnel-tested experimental data from parallel, normal and inclined flow to compute the coefficient of drag. Simultaneously, this methodology utilizes the blade element momentum theory propeller design program XROTOR to size the distributed propulsors capable of operating the mentioned relevant flight segments. The propulsor design methodology outlined in this paper minimizes induced losses at the rotors by constraining a low Mach tip number, to lower community noise levels with a feasible motor torque. Propeller off-design conditions are presented in propeller contour maps obtained from XROTOR for fixed and variable pitch propeller settings, to provide the mentioned relationship between RPM and segment thrust. Such a relationship can be used to build flight procedure dynamics and predict overall efficiency and community noise levels. An application of the described methodology will be presented to determine the low-altitude flight aircraft performance of STOL, Tilt-Rotor VTOL, and LPC VTOL AAM vehicles.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
650 4 $a Mechanical engineering. $3 557493
653 $a Advanced Air Mobility
653 $a Aircraft performance
653 $a Urban air mobility
653 $a Short-Takeoff and Landing
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
690 $a 0548
710 2 $a ProQuest Information and Learning Co. $3 1178819
710 2 $a University of California, Irvine. $b Mechanical and Aerospace Engineering. $3 1180333
773 0 $t Masters Abstracts International $g 85-02.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30527518 $z click for full text (PQDT)