Engine | Two-cycle, two-cylinder, opposite, of internal combustion | |
Statistical traction | N | 161 |
Volumetric capacity | cm3 | 56 |
Engine power | KW | 4,0 |
Hourly fuel consumption at V econom. | l/h | 0,68 |
Parachute rescue system is designed for emergency landing | ||
Min. height for activation of the parachute above the level of landing field | m | 100 |
Barometric height of location of the area above sea level | m | up to 2000 |
Key geometric characteristics | ||
Length | mm | 2693 |
Span of wings | mm | 6012 |
Wing load | g/dm² | 235 |
Weight data | ||
Takeoff mass | kg | 35 |
Standard fuel margin | l | 7 |
Basic flight characteristics | ||
Range of horizontal flight speed | km/h | 65-140 |
Cruise speed | km/h | 80 |
Takeoff speed | km/h | 67 |
Landing speed at glide path with extended flaps | km/h | 55 |
Planner’s quality | 13,63 | |
Contact velocity | km/h | 60 |
Flight attitude range | m | 50-3000 |
Practical flight length | km | 440 |
Flight duration | h | 5 |
Control | ||
Flight control | Automatic/dual | |
Communication range (within line of sight) | up to 50 km (video channel) | |
Communication range (within line of sight) | up to 100 km (telemetry) | |
Control system | Autonomous navigation, automatic performance of the flight task, automatic performance of procedures in case of loss of contact/accident, automatic waiting for commands, continuous/on request telemetry |
Copyright © 2010-2015 INDEPENDENT DEVELOPMENT LABORATORY Inc. All rights reserved. Pricing, specifications and content all subject to change without prior notice.