Aero Ae-45
| Aero Ae-45 / Ae-145 | |
|---|---|
 Ae-45S Super Aero |
|
| Type: | Touring plane |
| Design country: | |
| Manufacturer: | |
| First flight: |
July 21, 1947 |
| Production time: |
1949-1963 |
| Number of pieces: |
590 |
The Aero Ae-45 was a twin-engine touring aircraft made by the Czechoslovak manufacturer Aero based in Prague- Vysočany . Militarily it was used as a liaison aircraft.
history
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Development work began in 1945 and was headed by designers Jiří Bouzek, Ondřej Němec and František Vlk. The first prototype (license plate: OK-BCA) flew for the first time on July 21, 1947, the second with the license plate OK-CCA on March 12, 1948. The flight tests went without incident and the machine was released for series production. By 1951, 200 copies had been built, which, in addition to Czechoslovakia, flew in Italy, Hungary, the USSR, the GDR and Switzerland.
The Ae-45 was also briefly used with the Czechoslovak Air Force, where it was called the K-75 . In 1954 the improved version Ae-45S Super Aero appeared , the production of which was taken over by the LET company in Uherské Hradiště-Kunovice, because at Aero at that time the serial production of the MiG-15 license S-102 had priority. Another 228 machines were built, which were also exported. Some Ae-45S received radios and were suitable for night flight.
China acquired the license rights and manufactured the Super Aero under the name Suingari-1 . The Lufthansa of the GDR as well as the air force of the NVA also had some copies of this type in their inventory. The Aero 45 and Super Aero 145 were also available in the Federal Republic of Germany from the late 1950s; one of the first private owners was the Hamburger Bauer Verlag; flown by the publisher's son Heinz Bauer.
In 1959, the Ae-145 appeared as a further development with more powerful M-332 engines and a standard VKP-10 radio, 162 of which were produced at LET. The successors Ae-245 and Ae-345 remained experimental models.
technical description
The Ae 45 and Ae-145 are cantilevered low-wing aircraft in all-metal - semi-monocoque construction with a hull made of profiled sheet frames and continuous belts of rolled section . The wings are in three parts with two continuous spars , whereby the middle piece, which contains the fuel tank, forms a composite with the fuselage, to which the two engines are also attached. The two outer surfaces can be dismantled for transport by loosening several bolts. The tail unit is designed as a self-supporting standard construction. All oars are covered with fabric. The main wheels of the rear wheel chassis, which are equipped with hydraulic brakes, are retracted electrically or, in an emergency, mechanically backwards into the motor nacelles, the tail wheel is rigid. Snow runners can be fitted in winter ; in this case the undercarriage cannot be retracted and its shafts are covered by flaps.
Military users
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People's Republic of China : Buildings under license as Suingari-1
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German Democratic Republic : around nine were flown by the KVP-Luft , NVA and DLH -
India : 1 piece (gift from Czechoslovakia ) -
Romania
-
Czechoslovakia
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Hungary
-
Vietnam : 3 from Chinese license production
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Technical specifications
| Parameter | Aero Ae-45S Super Aero | Aero Ae-145 |
|---|---|---|
| Constructor (s) | Jiří Bouzek, Ondřej Němec, František Vlk | |
| Manufacturer | Aero, továrna letadel Dr. Kabeš | |
| Year of construction (s) | 1954– (?) | 1959– (?) |
| crew | 1 | |
| Passengers | 3 | |
| length | 7.54 m | |
| span | 12.25 m | |
| height | 2.35 m | |
| Wing area | 17.09 m² | |
| V position | 6 ° | |
| profile | Aero 3560/3525 | |
| Trunk width | 1.20 m | |
| Cabin dimensions (length × width × height) |
1.88 m × 1.12 m × 1.18 m | |
| Cabin volume | 2.48 m³ | |
| Cargo hold volume | 0.39 m³ | |
| Empty mass | 960 kg | 1000 kg |
| Payload | 640 kg | 600 kg |
| Takeoff mass | 1600 kg | |
| drive | two air-cooled 4-cylinder in- line engines | |
| Type | Walter Minor 4-III | LOM M 332 |
| power | 77 kW (105 PS) each | 103 kW (140 PS) each |
| Top speed | 265 km / h | 280 km / h |
| Cruising speed | 230 km / h | maximum 265 km / h economical 250 km / h |
| Rate of climb | 5.0 m / s | |
| Service ceiling | 4350 m | 5900 m |
| Range | 1350 km | 1700 km |
| Take-off run | 220 m | 250 m |
| Landing runway | 275 m | 225 m |
See also
literature
- Wilfried Copenhagen , Jochen K. Beeck: The large aircraft type book . Motorbuch, Stuttgart 2005, ISBN 3-613-02522-1 , p. 398 .
- Heinz A. F. Schmidt: Airplanes from all over the world . 3rd, revised edition. tape I . Transpress, Berlin 1970, p. 10 .
- letectvi + cosmonautics . No. 6 , 1967, p. 20-23 (Monograph Aero Ae-45).
- letectvi + cosmonautics . No. 25 , 1992, pp. 39 (ČSSR Aviation Register).
Web links
- Page about the Aero A.38 (Czech).