This aircraft was developed on the basis of experience and knowledge gained from the previous ALTO 912 TG model. The conceptual arrangement of the flight control system, landing gear and tail surfaces is based on the previous model. The ORANGE is designed especially for recreational flying, training and aero club use (glider towing). The low-wing ultralight aircraft is currently in the stage of development, prototype building and preparation for the wing strength test. The following technical specifications are based on preliminary calculations.
Compared to its predecessor, the low-wing ultralight aircraft ORANGE offers more crew space in the form of an extended cockpit. The rigidity of the fuselage is secured by a system of longitudinal webs and bulkheads. The shape of the fuselage has been modified to improve the overall appearance and to reduce drag.
|Wing area||10,8 m2|
|Cockpit width||1,20 m|
|Number of seats||2|
|Fuel tank capacity||100 l|
|Take-off distance||90 m|
|Landing distance||150 m|
|Empty weight||305 kg|
|Maximum take-off weight (UL/LSA)||472,5 kg|
|VNE (never-exceeded speed) (UL/LSA)||255 km/h|
|Maximum speed||230 km/h|
|Stalling speed, landing configuration (UL/LSA)||62 km/h|
|Stalling speed, clean configuration (UL/LSA)||80 km/h|
|Multiples of G-force||+4 / -2|
|Maximum climbing speed (UL/LSA)||8 m/s|