แจ้งเอกสารไม่ครบถ้วน, ไม่ตรงกับชื่อเรื่อง หรือมีข้อผิดพลาดเกี่ยวกับเอกสาร ติดต่อที่นี่ ==>
หากไม่มีอีเมลผู้รับให้กรอก thailis-noc@uni.net.th
หากไม่มีอีเมลผู้รับให้กรอก thailis-noc@uni.net.th
Thipyopas Chinapat. Design and analysis of self-adaptive in-flight foldable wing UAV. (). King Mongkut's University of Technology North Bangkok. Central Library. : , 2018.
Design and analysis of self-adaptive in-flight foldable wing UAV
Name: Limsumalee Nattawan
Organization :
Kasetsart University. Faculty of Engineering
Email :
nattawan.li@ku.th.fengcpt@ku.ac.th
Name: Thipyopas Chinapat
Organization :
Kasetsart University. Faculty of Engineering
keyword:
Folding Wing Drone
ThaSH:
Drone aircraft
-- Design and construction
ThaSH:
Drone aircraft
-- Control systems
ThaSH:
Drone aircraft
-- Aerodynamics
Abstract:
An experimental investigation of the interaction of a foldable-wing configuration for
a flying wing UAV was performed in a low speed wind tunnel. This study explores the effect
of gust perturbation process in turbulent environments. The primary aims was to design the
mechanism on a foldable wings of Mini-UAVs (Mini-UAVs are unmanned aerial vehicles
small enough to be transport by man) in order to reduce the wing span and increase portability.
The foldable wings could be potentially reduced the strength of the spar's structure. Thus, the
mechanism must also be designed to minimize any effect on lift force at each section of the
wings. The objective was to present the effect of the interactions between the force constant of
an elastic material which constitutive element of hinge at the folding mechanism and the loss
of lifting force from dihedral angle which occur by gust wind. The impact of lift forces while
flying cause an improve dihedral angle at the wings and hence changes of the aerodynamic
forces which helps improve the aircraft balance. This work is aimed to enabling safe, stable
and steady flight in cluttered gust environments. The forces are based upon calculations from
vortex lattice method (VLM) by XFLRS. The results are then compared to the wind tunnel
testing results. The experimental model is a flying wing with the foldable mechanism as elastic
hinges. All tests were conducted at low speeds at a range from 10 to 17 m/s and the angle of
attack range from -4 to 16 degrees. The results showed that the aerodynamic characteristics
of the wing were trending in the same direction as with the results from XFLRS.
King Mongkut's University of Technology North Bangkok. Central Library
Address:
BANGKOK
Email:
library@kmutnb.ac.th
Created:
2018
Modified:
2025-06-16
Issued:
2025-06-16
บทความ/Article
application/pdf
BibliograpyCitation :
In Thammasat University Faculty of Engineering. The 9th TSME International Conference on Mechanical Engineering 2018 (TSME-ICoME9) (pp.160-166) Pathum Thani : Thammasat University
eng
©copyrights King Mongkut's University of Technology North Bangkok
RightsAccess:
ใช้เวลา
0.020054 วินาที
Limsumalee Nattawan
| Title | Contributor | Type |
|---|---|---|
| Design and analysis of self-adaptive in-flight foldable wing UAV
มหาวิทยาลัยเทคโนโลยีพระจอมเกล้าพระนครเหนือ Limsumalee Nattawan;Thipyopas Chinapat | บทความ/Article |
Thipyopas Chinapat
| Title | Contributor | Type |
|---|---|---|
| Design and analysis of self-adaptive in-flight foldable wing UAV
มหาวิทยาลัยเทคโนโลยีพระจอมเกล้าพระนครเหนือ Limsumalee Nattawan;Thipyopas Chinapat | บทความ/Article |