In 1958 a group of students from the faculty of aeronautical construction of the Moscow Aviation Institute (MAI) came together to create a construction bureau to build aircraft in a flying wing configuration. In this group the students A. Krivomlin, M. Alexandrov, Yu stood out. Belov, A. Bielosviet, V. Irinarjov, S. Kurilienko, Ye. Mizinov and V. Novikov among others.

The research carried out and the technical solutions of the LK-MAI would be used as the basis for the development of a new flying wing glider, which was called MAI-63 (Russian: МАИ-63).

The work began in the autumn of 1962 with the participation of members of the MAI sports aviation club under the direction of the head of the scientific-research sector AI Pitsuj. All the construction work was done by the students themselves.

The glider design featured a low elongation centroplane with a rhomboid shape in the plane to which consoles were attached with 30º inflection on their leading edge. The sagging of the centerplane and the consoles was the same. Aerodynamic blades were located where the fuselage was attached to the consoles.

The large swelling of the wings made it possible to locate double-surface elevator rudders (“crocodile” type) on the trailing edge of its extremities. This location guaranteed an adequate balance of the apparatus even with the flaps extended. The ailerons, located on the trailing edge, were of the conventional type.

The glider lacked a horizontal empennage. Longitudinal control was performed by a combination of the elevator rudders. When the left pedal was depressed, the surfaces on the left side opened up, increasing the resistance at that end, and the aircraft turned to the left. By keeping the pedals in a neutral position, both surfaces joined to form a single rudder.

The cockpit was designed to accommodate a semi-reclining pilot and was covered with a bubble-type lantern.
The entire construction was made of metal. The wing design had a laminar profile. The covering of the centroplane and the wing up to the middle of the chord was made of duralumin and from there on in fabric.

The landing gear was unicycle type with the wheel located on the axis of the device and conveniently fairing. In the rear area there was a amortized skate. Stabilization supports with small wheels were placed under the wing tips.

In 1963 the project for the new glider was ready and in that same year construction began in the workshops of the laboratories of the MAI aircraft construction and projection chair. The prototype was ready for 1964.
In the construction of the model stood out V. Rytsariev, G. Bespalov, O. Tischenko, Ye. Volkov, A. Turik, S. Turchkov, V. Fatyanov, V. Vasiliev, and V. Pushkin.

All the turning and milling jobs were developed by students. Many of them had the necessary qualifications and were masters of the sport in model aircraft. This made the job easier.

The 5th year student Yu. Shirokov, who designed the centroplane and the cockpit, was still in his school years champion of Moscow in model aircraft; V. Pushkin had attended various professions.

Structural strength calculations were developed by M. Stolyar, O. Derzhavin, V. Voronin, and V. Kuznietsov. As a consultant, Ye acted. S. Voit.

The MAI-63 tests were developed in Alferiev in 1964 and were in charge of AI Pietsuj. Several towed flights
were made approaching take-off speed, piloted by AI Pietsukh. Structural strength problems led to the decision no flights were done.

After the first tests, several corrections were made to the apparatus: the wing structure was reinforced and modifications were made to the landing gear.

In 1965, MAI-63 was modified to a motor-glider installing on a pole erected over the central part of the glider an air-cooled EP-760 23 HP, five-cylinder, two-stroke radial engine. The engine was designed by Polyakov specifically for motor-gliders and light aircraft. The modified glider got the designation MAI-63M. Tests were conducted at the flying club’s airport. The engine during the trial taxi runs was unstable so the powered version of the glider was never flown.

MAI-63
Wingspan: 12.60 m
Wing area: 9.00 m²
Aspect ratio: 17.5
Wing profile: Laminar
Empty weight: 126 kg
Normal weight: 200 kg
Wing loading: 22.2 kg / m²
Best glide ratio: 35
Descent speed: 0.61 m / s
Accommodation: 1

The glider was designed in response to a request from the DOSAAF Central Committee as a development of the PAI-6 glider, but project manager Alexei Ivanovich Pietsuj proposed an entirely new construction.

The MAI-56 (Russian: МАИ-56) was designed in 1956 as a two-seater training glider and was developed by the collective of the aircraft construction and projection chair at the Moscow Aviation Institute (MAI). The group of designers was made up of IV Kachanov, Ye. S. Voit, AA Liebiedinski and VA Manucharov under the direction of AI Pietsuj. An important group of students also joined this work.

The engineer AA Liebiedinski was assigned to the construction and all the calculations and plans were developed by students.

The MAI-56 featured a high cantilever wing structure and two-seater capacity, but unlike previous models, the fuselage was designed around a skeletal structure built with welded steel tubes with little lateral section covered with fabric.

The landing was made on a central wheel in the lower fuselage, which had a wooden skid at the front.
Stabilization straps were located under the wings.

The wing and tail were constructed entirely of wood with the use of steel fasteners. The wing was equipped with airbrakes.

The wing structure was designed with a single spar: the wings had a trapezoidal shape in the plane with some negative sagging. The wingtips were covered with plywood and worked by twisting. The louvered three-point ailerons featured aerodynamic and weight compensation.

The stabilizer and keel were covered with plywood. All surfaces had cable control.

The cockpit with two-seater capacity in tandem was closed by means of a transparent cover in line with the fuselage, with lateral opening towards the right. The bow fairing was attached to the cockpit deck, facilitating access to the cockpit for the pilot. The second crew member was located above the center of gravity of the model. In order to improve visibility from this second position, the wing leading edge, at the junction point with the fuselage, was made of transparent acrylic.

To improve the operation of the MAI-56, a trailer truck for transport was designed, which could be installed on a light car. The MAI-56 was generally superior to gliders of its Czechoslovakian “Pioner” type or its national “Primoriets” version, which was mass produced in the USSR. The Czechoslovakian glider had an aerodynamic quality of 17.5 against the 21 of the MAI-56, obtained thanks to the absence of wing braces and cleaner aerodynamic shapes.

The construction of the prototype was carried out in the UPM workshops of the MAI.

The first flight of the MAI-56 took place in August 1958 with the main constructor AI Pietsuj at the controls. The test program was carried out between May and September 12, starting the manufacturing tests, which took place at the airfield of the airfield the DOSAAF of Yegorievk having as pilot Pietsuj.

The pilots who participated in the tests gave a very positive evaluation of the model and recommended its series production. The test report was approved by the chairman and aeronautical constructor AS Yakovlev.

In addition to the drag tests from a Yakovlev Yak-52, four flights were made during the tests using drag from a motorcycle and six from a car. The MAI-56 glider passed the tests without difficulty. The piloting technique was considered simple and suitable for athletes of all categories, but the expected series production would never come to fruition.

Many MAI students completed their course and diploma work on topics related to the projection and development of the MAI-56. The consultations with the students were made by Professors Ye. S. Voit, IV Kachanov and AA Liebiadinski.

MAI-56
Wingspan: 15.60 m
Wing area: 18.10 m²
Aspect ratio: 13.1
Length: 7.61 m
Empty weight: 237 kg
Maximum weight: 273 kg
Wing loading: 21.9 kg / m²
Glide ratio: 21
Accommodation: 2