Russia continues to impress the Independent Development Laboratory especially so.

In business since1996 with a short break in 2005 due to a lack of funds the team have 14 years of experience behind them and it shows. The focus of their early years was the development of telemetry and high-speed data transmission systems. Since 1999 they have been working on development of a unified, modular control system (on-board equipment and ground control stations) for unmanned craft.

On the airborne side they off a diverse stable of airframes and uses their own autopilot. The airframes that Indela produce cover the holy trinity of UAS, speed,endurace and VTOL. Twin turbine Berkut caught our eye and the unusual three point landing configuration of the Eye Sky is worth mention. Dynamic rollover is always an issue with helicopters. Will the tri foot arrangement reduce that?

Heres just some of the aircraft that INDELA produce, specifications from their website

Berkut :- Speed

Engine Twin jet Static thrust N 14-320 x 2 Motor speed rpm 32000-125000 Fuel consumption ml / min 240-1140 Exhaust gas velocity at the nozzle mph 1516 Basic geometric characteristics Length mm 2384 Span mm 2800 Weighted data Takeoff weight kg 42 Standard fuel ml 14000 The main flight characteristics Speed range of horizontal flight mph 100-360 Cruising speed mph 220 Required thrust at cruise speed N 107 Takeoff speed mph 91.8 Landing speed on the glide path flap mph 111 The vertical velocity at landing m / 6.5 Speed Touch mph 82 Flight altitude range m 50-5000 Practical range km 140 Flight duration minute 40

6M :- Endurance

Engine two-stroke two-cylinder reciprocating internal combustion Static thrust N 161 Volume cc 56 Motor speed rpm 1400-8500 Engine power KW 4.0 All fuel economy on V. l / h 0.68 The parachute recovery system, designed for emergency landing Max. (Barometric) altitude operation of the parachute system m 3000 Maximum input speed parachute m / 50 Minimum typing speed parachute m / 15 Min.vysota parachute deployment above the landing site m 100 Barometric height of the landing pad above sea level m to 2000 Basic geometric characteristics Length mm 2693 Span mm 6042 Wing loading g / dm ² 235 Weighted data Takeoff weight kg 30 Standard fuel l 4.8 The main flight characteristics Speed range of horizontal flight mph 65-140 High speed mph 140 Cruising speed mph 80 Takeoff speed mph 67 Landing speed on the glide path flap mph 75 Quality airframe 13.63 The vertical velocity at landing m / 5 Speed Touch mph 60 Flight altitude range m 50-3000 Practical range km 440 Flight duration h 5.5

Eye Sky :- VTOL