Zeppelin-Staaken L

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L, Warnemunde 43642775.jpg
The L on its beaching trolleys, Warnemünde, February 1918
RoleLong-range maritime patrol aircraft
National originGermany
Manufacturer Zeppelin-Staaken
First flight5 September 1917 (with floats)
Number built1 prototype
Developed from Zeppelin-Staaken R.VI heavy bomber

The Zeppelin-Staaken L was an experimental long-range maritime patrol floatplane developed during World War I by Zeppelin-Staaken for the Imperial German Navy's (Kaiserliche Marine) Naval Air Service (Marine-Fliegerabteilung). Derived from the Zeppelin-Staaken R.VI heavy bomber, it was a large, four-engine aircraft with its engines grouped in tractor-pusher pairs between the wings. A single aircraft was ordered for evaluation purposes in 1917. Six improved versions were ordered while the L was being tested. It was destroyed in a crash in June 1918 with the death of everyone aboard.

Contents

Background and description

By late 1916, the vulnerability of the Zeppelins on reconnaissance missions over the North Sea had been recognized by the Naval Air Service and Rear Admiral ( Konteradmiral ) Philipp, commander of the Naval Air Service, outlined requirements for three types of multi-engine seaplanes to replace the Zeppelins. The highest priority was for a four-engine maritime patrol aircraft with an endurance of 10–12 hours, capable of maintaining altitude on two engines, in a memorandum on 26 December. Philipp clarified that the reconnaissance aircraft's task would be mine spotting, anti-submarine duties, and shipping control on 10 February 1917. In response, Zeppelin-Staaken offered a floatplane version of their R.VI heavy bomber modified with additional fuel tanks and the Naval Air Service placed an order for a single aircraft on 15 February. [1]

The fuselage of the L was a lattice girder built from wood and steel tubing with the forward portion covered by plywood and the rest by fabric. The crew compartment housed both pilots, the bombardier/navigator, the wireless operator and the fuel attendant. In the nose of the fuselage was the bombardardier's position and the bombsight; it could be fitted with a machine gun. Behind the crew compartment was the dorsal gunner's position armed with two flexible machine gun mounts and the ventral gunner's position with a single gun. The L was built with the R.VI's conventional landing gear with a twin-wheel auxiliary undercarriage beneath the nose for use during landing, [2] but these were replaced once the aircraft had flown to the testing site in Potsdam with two large duralumin floats. [3] Each float was subdivided into a dozen watertight compartments. [4]

The L was a four-bay biplane with the fuselage attached to the lower wing. The wooden wings had two main spars and were built in three parts, a center portion and two end panels that were bolted to the center section. Balanced ailerons were only located on the upper wing. Unlike the R.VI they extended past the wingtips and the wings were slightly swept back at an angle of 1.5 degrees. The L was fitted with a biplane empennage with two horizontal stabilizers and two balanced rudders. Initially the upper horizontal stabilizer was only connected to the fuselage by struts, but a vertical stabilizer with an additional rudder was added during flight testing to improve directional stability. Elevators extended across the full width of both horizontal stabilizers. [5]

The 260- horsepower (190  kW ) Mercedes D.IVa straight-six engines were located between the wings on A-shaped struts positioned above the floats. Each pair of engines were housed in an aluminium nacelle that rested on the crossbar of each strut with an engine at the front and the other at the rear. Additional struts ran from the lower wings to the nacelles to support the weight of the gearboxes. The radiators for each engine were attached to the strut above the nacelle. A flight mechanic's cockpit was positioned between the engines in the nacelle. Four-bladed propellers were initially fitted to the rear engines, but these were replaced by two-bladed ones during flight testing. The L was fitted with fourteen 245-litre (54 imp gal; 65 US gal) fuel tanks in the central fuselage. In addition each nacelle contained two 150-litre (33 imp gal; 40 US gal) fuel tanks. A 155-litre (34 imp gal; 41 US gal) gravity tank was positioned under the upper wing above each nacelle. [6]

History

The Zeppelin-Staaken L was completed in August 1917 and had its floats installed before 5 September when it made two short flights from the Spree River. Taxiing trials revealed a need to reinforce the floats with additional struts. The aircraft attempted to fly to the Naval Air Service base at Warnemünde on 12 November, but one engine failed and it had to make an emergency landing at Saaler Bodden, 40 km (25 mi) from the base. Repairs took a couple of days and the L was turned over to the Seaplane Experimental Command (Seeflugzeug-Versuchs-Kommando) on 17 November for testing. The aircraft was too large to fit in any of the existing hangars and a special hangar had to be built for it. [7]

Flight testing showed that once enough fuel had been consumed to allow the L to fly on three engines, its range could be extended by turning one engine off. The only other result known from the testing is that it was not as stable on the water as the Zeppelin-Lindau flying boats like the RS.III designed by Claude Dornier. The Naval Air Service ordered six improved versions as the Zeppelin-Staaken 8301 in two batches in December 1917 and January 1918. The L crashed at Warnemünde on 3 June 1918, killing all aboard, possibly due to engine failure. [8] [9]

Specifications

Data from The German Giants: The German R-Planes 1914 – 1918 [10]

General characteristics

Performance

Armament

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References

  1. Haddow & Grosz, pp. 278–280
  2. Haddow & Grosz, pp. 248, 250–252
  3. Herris, p. 116
  4. Gray & Thetford, p. 589
  5. Haddow & Grosz, pp. 246, 280–281
  6. Haddow & Grosz, pp. 244–246; Herris, p. 117
  7. Haddow & Grosz, pp. 281–282; Herris, p. 117
  8. Haddow & Grosz, pp. 281–283; Herris, p. 117
  9. Nowarra, Robertson & Cooksley, p. 81
  10. Haddow & Grosz, pp. 280, 282–283

Bibliography