Heinkel HD 41

Heinkel HD 41
Image wanted
Type:	Bomb and reconnaissance aircraft
Design country:	German Empire
Manufacturer:	Heinkel
First flight:	1929
Commissioning:	-
Production time:	1928-1931
Number of pieces:	4th

The Heinkel HD 41 is a German military multi-purpose aircraft that was developed and built by Ernst Heinkel Flugzeugwerke in Warnemünde in the 1920s .

development

On August 4, 1928, as part of the covert rearmament , the Army Weapons Office commissioned Ernst Heinkel to create a multi-purpose aircraft that was to be used for weapon tests as a reconnaissance aircraft and day bomber in the secret flying school and test site operated by the Reichswehr in Lipetsk , Russia . A total of four specimens classified as "engine test aircraft" were created, of which the first, designated as the HD 41a, was completed on February 1st of the following year and registered in July 1929 with the registration number later as re-registered. Holder was officially the testing department of the Albatros Flugzeugwerke , unofficially the aircraft went to the Soviet Union in the summer of 1930 and was used in Lipetsk for drop tests with the bomb magazine Mag 6W 12 / IIIa and for testing the aiming telescope Fl.218 (220) from Goerz . In January 1930, a secret construction program for the Army Air Force envisaged the production of 261 HD 41 aircraft, a project that was ultimately not implemented. D–1694D–IDYM

A second aircraft received the registration number in March 1930 D–1795and went to the test center of the Reich Association of the German Aviation Industry (RDL) in Berlin-Staaken , where it was officially used as a test vehicle for various engines. Later the aircraft, named HD 41b, was D–IXAZre-registered for.

The last two HD 41c were produced in 1931, one of which was also delivered to Staaken and handed over to the German Aviation School a year later , the other was transported to Lipezk and flew there from June to September 1931 as a L64. It was only deleted from the aviation role in 1938. The HD 41c were later given the type designation HD 45a and served as the starting sample for the He 45, which was built in large numbers .

construction

The HD 41 is a braced double-decker in composite construction. The fuselage is formed by a welded tubular steel frame with a square cross-section, which is rounded off by shaping strips. Most of it is covered with fabric and clad in light metal from the bow to the front cabin. The single-stemmed and strongly staggered structure consists of a wooden frame with two spars. It is connected to each other by N-posts. The leading edge of the wing is made of plywood, the remaining surfaces are covered with fabric. Both the upper and lower wings have ailerons with interconnected bumpers. The normal tail consists of a metal frame covered with fabric. The horizontal stabilizer is supported on the fuselage with I-struts. The rigid chassis consists of the main wheels, which are suspended from rubber cables and are not connected by an axle, and a grinding spur at the rear.

Technical specifications

Parameter	HD 41a	HD 41b	HD 41c (HD 45a)
crew	2
length	9.9 m	9.81 m	10.1 m
span	above 11.5 m below 10.0 m
height	4.1 m		4.3 m
Wing area	34.57 m²
Empty mass	1780 kg	1700 kg	1800 kg
Payload	790 kg	735 kg	850 kg
Takeoff mass	2570 kg	2435 kg	2650 kg
drive	a liquid-cooled, twelve-cylinder - four stroke - V engine	an air-cooled nine-cylinder four-stroke radial engine	a liquid-cooled twelve-cylinder four-stroke V-engine
Type	BMW VI 5.5	Siemens & Halske "Jupiter" VI 5.3 (Bristol license)	BMW VI 7.3Z
Starting power nominal power continuous power	630 PS (463 kW) 600 PS (441 kW) on the ground 500 PS (368 kW) on the ground	490 PS (360 kW) 440 PS (324 kW) on the ground 380 PS (279 kW) at a height of 500 m	750 PS (552 kW) 650 PS (478 kW) on the ground 500 PS (368 kW) at a height of 700 m
Fuel volume	550 l		520 l
Top speed close to the ground	240 km / h	232 km / h	270 km / h
Landing speed	100 km / h	95 km /	105 km / h
Rise time	2.8 min at 1000 m 6.8 min at 2000 m 14.8 min at 3000 m	3.2 min at 1000 m 7.8 min at 2000 m 16.2 min at 3000 m	2.12 min at 1000 m k. A. 8 min at 3000 m
Summit height	5400 m	5000 m	5800 m
Range	1070 km	1020 km	850 km
Take-off run	320 m	340 m	k. A.

literature

• Volker Koos: Ernst Heinkel Flugzeugwerke 1922–1932 . Heel, Königswinter 2006, ISBN 3-89880-502-6 , p. 99/100 .