Russian version

Aircraft's design and features

The plane is built according to "all wing" scheme with the tail section of extended surface and pilot-passenger cabin in the front. The main part of the aircraft is the diskshaped centerplane with the central tunnel where the cargo cabin and propeller system are located. The cantilevered wing parts are positioned on each side of the centerplane. Takeoff and landing device is placed underneath in the shape of inflatable landing torus which serves as an enclosure for air cushion, wheel and ski bearers and gliding surfaces: redan under pilot-passenger cabin and hydraulic wing behind the centerplane. This universal takeoff and landing device makes possible any off-field operations from water, marshy and snow covered surfaces, any ground. Located at the rear end of the centerplane propulsion propeller engines produce steady air stream on the tail section thus increasing aircraft's reliability and safety in various flight modes and in case of engine failure. The aircraft has the following features:
availability of the propeller engine along with the propulsion engine ultimately results in shorter takeoff and landing;
diskshaped centerplane serves not only as a cargo area but creates aerodynamic ascensional force during flight;
the glider is almost totally made of composite materials with the use of three layered wraps with foam and honeycomb fillers, that 1,5-2 times bring down the dead load in comparison with metal structures;
separate cargo cabin along with pilot-passenger one excludes all costs for converting the latter into cargo cabin;
availability of the universal takeoff and landing device makes any seasonal changes unnecessary;
outer cantilevered wing parts can be folded which makes possible its transportation by land or by air.

Major aircraft performance characteristics

Flight characteristics
Cruising speed, km/h 250
Unstick speed, km/h 50...60
Ceiling, km up to 3
Range ability:
- maximim load, km up to 1000
- ferrying with 2 pilots aboard, km 3000
Ground run, m/m 50/25
Noise level EPN, db FAR 36
Requirements certification -23
Power units
Propulsion (type, number of engines and power, h/p) "Teledyne continental",
10-360-ES, 2210
Lifting (type, number of engines and power, h/p) "Teledyne continental",
10L-200, 1110
Lifting propeller diameter, m 1,8
Lifting propeller load, daN/m2 100
Masses and loads
Takeoff mass, kg 2000
Zero fuel mass, kg 1100
Fuel load, kg 300
Payload, kg 600
or passenger load, people 5...6
Crew, pilots 1...2
Overall dimensions
Length, m 10
Span, m 11
Height, m 2,6
Centerplane disk diameter, m 4,6
Takeoff and landing conditions
Flat surface:
ground, water, marsh, snow, ice, conventional airstrip, etc.

Operational mode:
airplane and air cushion device

Operational effectiveness

Evaluation of "Bella-1" operational effectiveness was made in comparison with other aircraft: ground plane, amphibian plane and helicopter.

It is well known, that the cost value (Cvalue ) of 1 tone of fuel per 1 kilometer (t*km) is made up of fuel cost (Cfuel ), costs of ground and air maintenance including depreciation of an aircraft, airport facilities and runway. Statistically, the cost of fuel for a regular (ground) aircraft makes up approximately 40% out of total cost value. Assuming the fuel cost as equaled to 1 and after the analysis of all other expenses the following proportion was built (all costs against fuel cost): for "Bella-1" - 25%, for a helicopter - 50%, for an amphibian plane - 100%, for a ground plane - 150%.

The diagram below shows the operational effectiveness for four types of aircraft (relation of aircraft's type to specific productivity).

© "", 2003