Description AEREON III

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1 description

1.1 configuration
1.2 structure , materials
1.3 landing gear
1.4 propulsion
1.5 buoyancy control





description
configuration

the aereon iii comprised 3 rigid hulls, each 83 feet (25 m) in length , 17 feet 6 inches (5.33 m) in maximum diameter, connected truss members. connecting structures between hulls faired in airfoil section, , aircraft whole functioned airfoil aspect ratio of 0.74. design intended maximize dynamic lifting forces acting on airship hull , take fullest advantage of these forces in flight. each hull contained 6 gas cells, total lifting gas volume of 40,000 cubic feet (1,100 m). there ventral fins rudders @ aft ends of outer 2 hulls , elevons on trailing edges of connecting structures. two-seat cockpit located in nose of central hull.


structure , materials

the hulls had zeppelin-type structure comprising 7 20-sided main rings, 3 intermediate rings between each pair of main rings, , wire bracing; however, structural members of duralumin tubing, rather built-up girders of earlier rigids. structure described half heavy , twice strong structural material in ill-fated hindenburg. hulls enclosed double-layer outer cover, comprising outer tedlar layer , inner layer of ripstop nylon treated dope. gas cells made of tedlar. fins of sheet duralumin on frames of same material, joined epoxy resin rather riveting.


landing gear

the airship had tricycle undercarriage non-steerable nosewheel beneath central hull , steerable (via connection rudders) wheels @ tips of ventral fins @ aft ends of outer hulls. nosewheel functioned internal mooring mast, telescopic strut allowed ship s angle of attack varied while moored (e.g. nose down hug ground or nose in preparation takeoff) , tie-down fitting @ lower end.


propulsion

the aereon iii powered single engine located @ aft end of central hull. engine reported in 1962 being solar titan gas turbine of 80 horsepower (60 kw), engine installed described four-cylinder mccullough (sic—presumably mcculloch). engine drove 21 feet (6.4 m) diameter, two-bladed pusher propeller (actually helicopter rotor rotating in vertical plane). location of propeller @ aft end of hull stated assist in boundary layer control , cyclic pitch feature facilitate low-speed control. aereon patented propulsion , control system in 1966. however, propeller required shortening before trials commenced because of excessive vibration.


buoyancy control

five propane burners in each hull enabled helium heated increase lift; ship 400 pounds (180 kg) heavy (i.e. weight greater static lift) gas cells 83 percent filled helium, heating gas increase static lift 800 pounds (360 kg). helium cooled admitting air through vents in noses of hulls, assistance of blowers. double-layer outer cover, mentioned above, facilitated thermal insulation of gas cells. aereon patented pressurization , buoyancy-control system, in 1965.


one source states aereon iii s buoyancy-control capabilities allow fly using gravity propulsion —without assistance of engine—along lines of solomon andrews s original aereon substituting helium heating andrews s dropping of ballast , helium cooling valving of hydrogen. however, fitzpatrick quoted elsewhere deplor[ing] such exaggerations.








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