Dornier Rs.II
Encyclopedia
The Dornier Rs.II was a large biplane
flying boat
, designed by Claudius Dornier
and built during 1914-15 on the German side of Lake Constance
. Initially this aircraft was powered by three engines mounted inside the hull driving three pusher propellers via gearboxes and shafts. The later version was powered by four engines in two push-pull nacelles mounted between the wings.
and open lattice tail unit.
The Rs.II, (Navy serial no 1433), as launched in 1916, consisted of a sesquiplane flying boat with a short but very broad fuselage and a tail unit supported at the end of a long open lattice box framework of tubular booms cross braced with cables. The short lower wings were intended to support stabilizing floats but these were found unnecessary due to the inherent stability of the broad hull. The tail unit comprised a biplane elevator
assembly with small separate tailplane
above a pair of all-flying rudders and the large upper wing was supported by struts which also supported the propellers.
Power was supplied by three Maybach HS engines mounted inside the hull, transmitting power to the three propellers via clutches, gearboxes and shafts. The three propellers were mounted as pushers aft of the wing support structure at approx mid-gap. Radiators for the internally mounted engines were mounted as a wide slab on the hull aft of the pilots cockpit.
Wing structure was formed by three built-up girder spars of triangular section with aluminium
wing ribs spaced fairly wide apart and wing fabric sewn to special eyelets, attached to the framework at evenly spaced intervals. The lower wings were attached directly to the fuselage, touching the water when afloat, improving water-borne stability. The low aspect ratio upper wing was supported by a central frame work and N strut assemblies at 1/3rd span and 2/3rd span. Incidence of the upper wing was adjustable by altering the length of the forward N-strut tubes.
Flying controls were fairly conventional despite their size, with unbalanced aileron
s on the upper wing and a large biplane elevator unit trailing a small tailplane and small rudders under the tailplane. To improve lateral control at low speeds, and improve spin resistance, the tip incidence was washed-out
, ensuring that the inner wing sections stalled first.
The hull, constructed of steel bulkheads and stringers with Duralumin
skinning on the sides and bottom but fabric on parts of the upper decking, housed the crew in a cockpit near the nose protected by a raised coaming. Engines and fuel were also housed inside the hull, serviced by a mechanic.
The first modification involved adding a third tall rudder between the original rudders. Flight tests resumed on 30 June 1916, take-off attempts were made with the wing incidence set at one, then two degrees and finally at three degrees which was successful at 07:30 hours. Two more flights were made that day and a further three flights proved the need for changes to the tail framework and tail surfaces; large diameter metal tubes replacing the upper booms and fixed fins fitted between the boom ends, as well as reducing the area of the central rudder and improving the planing surface shape.
Ready for continued flight tests on 17 July 1916, the RS.II still showed poor take-off characteristics and the aircraft was sluggish in roll. Rudder authority was also lacking as it was found impossible to maintain straight flight with the centre and starboard engines throttled back. During these tests the port transmission began to vibrate and eventually it failed, causing the port propeller to break. The aircraft dropped onto the water from about 10m (33ft), bounced into the air where the centre propeller transmission broke loose damaging the tail boom as the aircraft settled with the tail boom in ruins.
The much revised Rs.II had four more reliable Maybach Mb.IVa
engines fitted in push pull nacelles mounted on struts above the hull at approx. mid gap. Initially the biplane tail cellule was retained with large fins and rudders attached to the tail boom side members; later the tail unit was made more conventional with a large tailplane and twin fins with rudders. Take-off performance was improved by moving the step further aft but the take-off run was still excessive. The upper wing was also lowered by shortening the centre section struts and moving the mounts for the side struts to halfway down the sides of the fuselage. Other changes included aerodynamic balance surfaces for the ailerons, lower wings with reduced chord and rounded tips.
Flight tests of the revised Rs.II were still dogged by engine problems with the engines either over-cooling when un-cowled, or overheating when fully cowled, not to mention spark plug and equipment failures exacerbated by lack of spare parts. During May 1917, while practising landings, the Rs.II landed hard, breaking the central boom support. Unaware of the damage he pilot attempted to take-off again, but the sagging tail forced the Rs.II back on to the water, where the tail broke off and sank to the bottom of Lake Constance.
By June 1917 the cumbersome tail unit had been replaced by a cleaner design with a single tailplane and finely formed fins and rudders mounted at the end of each boom. The new boom structure was much stronger and of simpler design. Evaluation by he SVK (Seeflugzeugs-Versuchs-Kommando - Seaplane Testing Command) was carried from 23 to 26 June 1917 testing various engine off configurations and water-borne handling. Given a qualified clean bill of health the Rs.II was prepared for a transit flight to Norderney
on the North Sea
coast to carry out seaworthiness trials.
Due to the recurring problems with the engines and the lack of clean high grade fuel, the Rs,II was required to carry out a practice delivery flight to ensure that the aircraft could reach its destination. During one of these practice flights, number 4 engine back-fired violently and number 1 engine's propeller disintegrated, showering the wings and hull with splinters. With two engines shut-down the pilot throttled back number 2 and 3 engines, gliding to a safe landing. The damage caused by the disintegrating propeller was deemed uneconomical to repair.
Biplane
A biplane is a fixed-wing aircraft with two superimposed main wings. The Wright brothers' Wright Flyer used a biplane design, as did most aircraft in the early years of aviation. While a biplane wing structure has a structural advantage, it produces more drag than a similar monoplane wing...
flying boat
Flying boat
A flying boat is a fixed-winged seaplane with a hull, allowing it to land on water. It differs from a float plane as it uses a purpose-designed fuselage which can float, granting the aircraft buoyancy. Flying boats may be stabilized by under-wing floats or by wing-like projections from the fuselage...
, designed by Claudius Dornier
Claudius Dornier
Claude Honoré Desiré Dornier born in Kempten im Allgäu was a German airplane builder and founder of Dornier GmbH...
and built during 1914-15 on the German side of Lake Constance
Lake Constance
Lake Constance is a lake on the Rhine at the northern foot of the Alps, and consists of three bodies of water: the Obersee , the Untersee , and a connecting stretch of the Rhine, called the Seerhein.The lake is situated in Germany, Switzerland and Austria near the Alps...
. Initially this aircraft was powered by three engines mounted inside the hull driving three pusher propellers via gearboxes and shafts. The later version was powered by four engines in two push-pull nacelles mounted between the wings.
Design and development
After the disastrous storm which wrecked the Rs.I, Dornier continued development of large seaplanes with the Rs.II. The design and construction drawings of the Rs.II had been prepared during 1915 and the airframe was completed rapidly after the loss of the Rs.I. Although resembling the Rs.I there was little in common, with a much broader short hull, low aspect ratio upper wingAspect ratio (wing)
In aerodynamics, the aspect ratio of a wing is essentially the ratio of its length to its breadth . A high aspect ratio indicates long, narrow wings, whereas a low aspect ratio indicates short, stubby wings....
and open lattice tail unit.
The Rs.II, (Navy serial no 1433), as launched in 1916, consisted of a sesquiplane flying boat with a short but very broad fuselage and a tail unit supported at the end of a long open lattice box framework of tubular booms cross braced with cables. The short lower wings were intended to support stabilizing floats but these were found unnecessary due to the inherent stability of the broad hull. The tail unit comprised a biplane elevator
Elevator (aircraft)
Elevators are flight control surfaces, usually at the rear of an aircraft, which control the aircraft's orientation by changing the pitch of the aircraft, and so also the angle of attack of the wing. In simplified terms, they make the aircraft nose-up or nose-down...
assembly with small separate tailplane
Tailplane
A tailplane, also known as horizontal stabilizer , is a small lifting surface located on the tail behind the main lifting surfaces of a fixed-wing aircraft as well as other non-fixed wing aircraft such as helicopters and gyroplanes...
above a pair of all-flying rudders and the large upper wing was supported by struts which also supported the propellers.
Power was supplied by three Maybach HS engines mounted inside the hull, transmitting power to the three propellers via clutches, gearboxes and shafts. The three propellers were mounted as pushers aft of the wing support structure at approx mid-gap. Radiators for the internally mounted engines were mounted as a wide slab on the hull aft of the pilots cockpit.
Wing structure was formed by three built-up girder spars of triangular section with aluminium
Aluminium
Aluminium or aluminum is a silvery white member of the boron group of chemical elements. It has the symbol Al, and its atomic number is 13. It is not soluble in water under normal circumstances....
wing ribs spaced fairly wide apart and wing fabric sewn to special eyelets, attached to the framework at evenly spaced intervals. The lower wings were attached directly to the fuselage, touching the water when afloat, improving water-borne stability. The low aspect ratio upper wing was supported by a central frame work and N strut assemblies at 1/3rd span and 2/3rd span. Incidence of the upper wing was adjustable by altering the length of the forward N-strut tubes.
Flying controls were fairly conventional despite their size, with unbalanced aileron
Aileron
Ailerons are hinged flight control surfaces attached to the trailing edge of the wing of a fixed-wing aircraft. The ailerons are used to control the aircraft in roll, which results in a change in heading due to the tilting of the lift vector...
s on the upper wing and a large biplane elevator unit trailing a small tailplane and small rudders under the tailplane. To improve lateral control at low speeds, and improve spin resistance, the tip incidence was washed-out
Washout (aviation)
Washout refers to a feature of wing design to deliberately reduce the lift distribution across the span of the wing of an aircraft. The wing is designed so that angle of incidence is higher at the wing roots and decreases across the span, becoming lowest at the wing tip...
, ensuring that the inner wing sections stalled first.
The hull, constructed of steel bulkheads and stringers with Duralumin
Duralumin
Duralumin is the trade name of one of the earliest types of age-hardenable aluminium alloys. The main alloying constituents are copper, manganese, and magnesium. A commonly used modern equivalent of this alloy type is AA2024, which contains 4.4% copper, 1.5% magnesium, 0.6% manganese and 93.5%...
skinning on the sides and bottom but fabric on parts of the upper decking, housed the crew in a cockpit near the nose protected by a raised coaming. Engines and fuel were also housed inside the hull, serviced by a mechanic.
Operational history
On 17 May 1916 the Rs.II left the hangar at Seemos for initial taxiing trials with Schroter at the controls, with Graf Zeppelin, Dornier and other important people from the Zeppelin works observing from Zeppelins motor boat Württemberg. Initial attempts were unsuccessful, attributed to the very calm conditions not allowing the hull to un-stick, they also highlighted the unacceptable rudder power for manoeuvring on the water.The first modification involved adding a third tall rudder between the original rudders. Flight tests resumed on 30 June 1916, take-off attempts were made with the wing incidence set at one, then two degrees and finally at three degrees which was successful at 07:30 hours. Two more flights were made that day and a further three flights proved the need for changes to the tail framework and tail surfaces; large diameter metal tubes replacing the upper booms and fixed fins fitted between the boom ends, as well as reducing the area of the central rudder and improving the planing surface shape.
Ready for continued flight tests on 17 July 1916, the RS.II still showed poor take-off characteristics and the aircraft was sluggish in roll. Rudder authority was also lacking as it was found impossible to maintain straight flight with the centre and starboard engines throttled back. During these tests the port transmission began to vibrate and eventually it failed, causing the port propeller to break. The aircraft dropped onto the water from about 10m (33ft), bounced into the air where the centre propeller transmission broke loose damaging the tail boom as the aircraft settled with the tail boom in ruins.
Second version
Rebuilding of the Rs.II was completed by 5 November 1916, with Schroter piloting the aircraft on its second flight the next day.The much revised Rs.II had four more reliable Maybach Mb.IVa
Maybach Mb.IVa
-Further reading:* Germany's giant aircraft of WWI the R-Planes...
engines fitted in push pull nacelles mounted on struts above the hull at approx. mid gap. Initially the biplane tail cellule was retained with large fins and rudders attached to the tail boom side members; later the tail unit was made more conventional with a large tailplane and twin fins with rudders. Take-off performance was improved by moving the step further aft but the take-off run was still excessive. The upper wing was also lowered by shortening the centre section struts and moving the mounts for the side struts to halfway down the sides of the fuselage. Other changes included aerodynamic balance surfaces for the ailerons, lower wings with reduced chord and rounded tips.
Flight tests of the revised Rs.II were still dogged by engine problems with the engines either over-cooling when un-cowled, or overheating when fully cowled, not to mention spark plug and equipment failures exacerbated by lack of spare parts. During May 1917, while practising landings, the Rs.II landed hard, breaking the central boom support. Unaware of the damage he pilot attempted to take-off again, but the sagging tail forced the Rs.II back on to the water, where the tail broke off and sank to the bottom of Lake Constance.
By June 1917 the cumbersome tail unit had been replaced by a cleaner design with a single tailplane and finely formed fins and rudders mounted at the end of each boom. The new boom structure was much stronger and of simpler design. Evaluation by he SVK (Seeflugzeugs-Versuchs-Kommando - Seaplane Testing Command) was carried from 23 to 26 June 1917 testing various engine off configurations and water-borne handling. Given a qualified clean bill of health the Rs.II was prepared for a transit flight to Norderney
Norderney
Norderney is one of the seven populated East Frisian Islands off the North Sea coast of Germany. It is also a municipality in the district of Aurich in Lower Saxony....
on the North Sea
North Sea
In the southwest, beyond the Straits of Dover, the North Sea becomes the English Channel connecting to the Atlantic Ocean. In the east, it connects to the Baltic Sea via the Skagerrak and Kattegat, narrow straits that separate Denmark from Norway and Sweden respectively...
coast to carry out seaworthiness trials.
Due to the recurring problems with the engines and the lack of clean high grade fuel, the Rs,II was required to carry out a practice delivery flight to ensure that the aircraft could reach its destination. During one of these practice flights, number 4 engine back-fired violently and number 1 engine's propeller disintegrated, showering the wings and hull with splinters. With two engines shut-down the pilot throttled back number 2 and 3 engines, gliding to a safe landing. The damage caused by the disintegrating propeller was deemed uneconomical to repair.
Specifications (Dornier Rs.II first version)
See also
External links
- http://www.iren-dornier.com/en/aircraft.html