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UID:0-323@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20190911T163000

DTEND;TZID=Asia/Jerusalem:20190911T173000

DTSTAMP:20230527T132229Z

URL:https://aerospace.technion.ac.il/events/wind-tunnel-tests-to-investiga
 te-the-behavior-of-a-dual-lift-system/

SUMMARY:Wind Tunnel Tests to Investigate the Behavior of a Dual Lift System
DESCRIPTION:Lecturer:Omer Fogel\n Faculty:Department of Aerospace Engineeri
 ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas
 sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \
 n Details: \n In many cases helicopters carry external loads that are conn
 ected by slings to a hook on the fuselage (slung loads). The main advantag
 es of this method are the capability to transfer big loads and the ease of
  handling those loads. When the load is too heavy to be carried by a singl
 e helicopter\, a multi lift technique can be applied: Connecting a single 
 load to the hooks of two (dual lift) or more helicopters. Dual lift presen
 ts a complex dynamic system. The possibility of dual lift was presented by
  limited flight tests and investigated by various numerical analyses. The 
 present research will present the use of wind tunnel tests to investigate 
 various aspects of dual lift operations.\nA rig has been designed and buil
 t to represent the helicopters hooks\, the suspension cables and the load 
 below the hooks. The rig includes a bar\, where the tips of this bar repre
 sent the hooks of the two helicopters. During the wind tunnel tests each t
 ip can move along the bar axis\, thus representing changes in the distance
  between the two helicopters. In addition\, the pitch and yaw angles of th
 e bar can be changed during the test\, representing changes in the relativ
 e altitude and flight formation of the two helicopters. In the present stu
 dy the load is a model of a CONEX container with two stabilizing fins. A n
 umerical simulation of the test was also developed where the coupled dynam
 ics of the system (suspension cables and the slung load) is modeled. The s
 imulation includes the influence of aerodynamic\, gravity and inertia effe
 cts. Results of the wind tunnel tests will be presented. The test results 
 will be compared with results of the numerical model. The validated numeri
 cal model will be used to study the influence of various parameters on the
  dual lift operation.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20190329T030000

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