The Mi-34 helicopter began to be developed as a light training and sports helicopter to replace the Mi-1 and Mi-2 helicopters used for these purposes. It was originally decided to use the existing M-14V-26 piston engine designed by I.M. as a helicopter power plant. Vedeneeva take-off power of 242 kW, used on Ka-26 helicopters, given also the fact that the M-14 engines are widely used on sports aircraft used in DOSAAF. The use of the latest technological advances, new materials in the fuselage structure, main rotor and transmission, as well as simpler structural solutions, such as a ski landing gear, made it possible to obtain a helicopter with a simple design and easy to use with high flight characteristics. When designing the helicopter, high calculated loads were laid down – from 2.5g to -0.5g, which ensured the implementation of complex aerobatic maneuvers and allowed the helicopter to be used for performing sports exercises under international competition programs, including flying for precision piloting and navigation and helicopter slalom.
The first prototype Mi-34 helicopter made its first flight in November 1986. During tests on the Mi-34 helicopter, the performance of such aerobatics as the barrel and the Nesterov loop was demonstrated for the first time for our helicopters. In 1987, the construction of the second experimental helicopter was completed; in 1987, the Mi-34 helicopter was first shown at the Paris Aviation and Space Salon, and then at many other international exhibitions, demonstrating high flight performance.
In the process of developing the Mi-34 helicopter, the possibilities of its use as a multi-purpose helicopter for passenger and cargo transportation, as well as as a liaison and patrol helicopter, were expanded.
The fuselage of a frame structure made of aluminum alloys with the widespread use of KM smoothly passes into a conical tail boom with a casing on top for the tail rotor shaft, an arrow-shaped vertical tail with a T-shaped horizontal rectangular tail in the plan is installed on the left side of the tail boom.
In the cockpit with a large glazing area in the front seats are placed for pilots with dual controls, followed by a common seat for two passengers, with one pilot in the cockpit there are three passengers. There are two doors on each side of the cab.
The landing gear is non-retractable, skiing, there is safety support at the lower end of the vertical tail. Track ski chassis 2.06m.
The four-blade rotor with the elastic mounting of the blades. The sleeve has horizontal and axial joints and elastic elements that ensure the movement of the blades in the plane of rotation. The blades are rectangular in plan, made of fiberglass reinforced with carbon fibers; blade chord 0.22m, NACA 230 profile.
Steering propeller with a diameter of 1.98m, two-blade, pushing, with a common horizontal hinge. Blades of a rectangular shape in plan, with a chord of 0.1m, are made of fiberglass.
The power plant of the Mi-34 helicopter consists of one star-shaped nine-cylinder piston air-cooled engine M-14B-26, installed in the central part of the fuselage, equipped with a fan and gearbox. The engine has good throttle response and is immune to the ingress of exhaust gases into the air intake, which is very important when performing aerobatics.
The fuel system includes one light tank with a capacity of 160 liters in the central part of the fuselage under the engine and is designed to work when flying upside down.
The helicopter control system is mechanical, the cockpit control is double, the controls for the left pilot can be removed.
The equipment consists of a VHF radio station, an automatic radio compass, a radio altimeter, and a horizon.
- Flight Range: 450km
- Cruising speed: 180km / hour
- The highest flight altitude: 3000m
- The highest take-off weight: 1450kg
- Cabin Height: 1,3m
- Cabin Length: 3.1m
- The greatest number of passengers: 1/3 (4)
- Cabin width: 1.27 m
- Height: 2.75m (with screw)
- Length: 11.48m (with screw)