TY - GEN
T1 - Flying on air
T2 - Collection of Technical Papers - AIAA 3rd "Unmanned-Unlimited" Technical Conference, Workshop, and Exhibit
AU - Simpson, Andrew
AU - Santhanakrishnan, Arvind
AU - Jacob, Jamey
AU - Smith, Suzanne
AU - Lumpp, James
AU - Cadogan, Dave
AU - Mackusick, Matt
AU - Scarborough, Stephen
PY - 2004
Y1 - 2004
N2 - The paper presents work on developing and flight testing UAVs with inflatable wing technology. Two concepts have been explored and flight-tested and are presented and discussed herein: inflatable wings and inflatable/rigidizable wings. In the former case, the wings are stowed in the fuselage and are inflated as needed. Constant pressure is required to maintain wing shape and structural stiffness. In the latter case, the wings are stowed in the fuselage, deploy when inflated, and rigidize with exposure to an external catalyst, in this case, UV radiation. Internal pressurisation is not required after rigidization is complete (less than 10 minutes). Manufacturing capability is the primary design constraint in choosing the wing profile and planform, but both current designs perform exceptionally well in low speed flight tests. Results from combined experimental and analytical investigations on multiple geometries are presented. Low altitude flight tests using the different wing concepts are discussed, as well as high altitude wing deployment tests. Finally, design considerations in vehicle configuration options are addressed when using inflatable wings.
AB - The paper presents work on developing and flight testing UAVs with inflatable wing technology. Two concepts have been explored and flight-tested and are presented and discussed herein: inflatable wings and inflatable/rigidizable wings. In the former case, the wings are stowed in the fuselage and are inflated as needed. Constant pressure is required to maintain wing shape and structural stiffness. In the latter case, the wings are stowed in the fuselage, deploy when inflated, and rigidize with exposure to an external catalyst, in this case, UV radiation. Internal pressurisation is not required after rigidization is complete (less than 10 minutes). Manufacturing capability is the primary design constraint in choosing the wing profile and planform, but both current designs perform exceptionally well in low speed flight tests. Results from combined experimental and analytical investigations on multiple geometries are presented. Low altitude flight tests using the different wing concepts are discussed, as well as high altitude wing deployment tests. Finally, design considerations in vehicle configuration options are addressed when using inflatable wings.
UR - http://www.scopus.com/inward/record.url?scp=19644365823&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=19644365823&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:19644365823
SN - 1563477173
SN - 9781563477171
T3 - Collection of Technical Papers - AIAA 3rd "Unmanned-Unlimited" Technical Conference, Workshop, and Exhibit
SP - 855
EP - 869
BT - Collection of Technical Papers - AIAA 3rd "Unmanned-Unlimited" Technical Conference, Workshop, and Exhibit
Y2 - 20 September 2004 through 23 September 2004
ER -