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Semi-monocoque structure inside an aircraft's rear fuselage ARV Super2 with semi-monocoque fuselage. The term semi-monocoque or semimonocoque refers to a stressed shell structure that is similar to a true monocoque, but which derives at least some of its strength from conventional reinforcement. Semi-monocoque construction is used for, among ...
By contrast, a semi-monocoque is a hybrid combining a tensile stressed skin and a compressive structure made up of longerons and ribs or frames. [3] Other semi-monocoques, not to be confused with true monocoques, include vehicle unibodies, which tend to be composites, and inflatable shells or balloon tanks, both of which are pressure stabilised.
Both monocoque and semi-monocoque are referred to as "stressed skin" structures as all or a portion of the external load (i.e. from wings and empennage, and from discrete masses such as the engine) is taken by the surface covering. In addition, all the load from internal pressurization is carried (as skin tension) by the external skin.
It has a one-piece carbon fiber fuselage, said to replace "1,200 sheets of aluminium and 40,000 rivets." [11] The 2013 Bombardier CSeries have a dry-fiber resin transfer infusion wing with a lightweight aluminium-lithium alloy fuselage for damage resistance and repairability, a combination which could be used for future narrow-body aircraft. [3]
The Zeppelin-Lindau D.I had stressed skin fuselage and wings.. In mechanical engineering, stressed skin is a rigid construction in which the skin or covering takes a portion of the structural load, intermediate between monocoque, in which the skin assumes all or most of the load, and a rigid frame, which has a non-loaded covering.
The fuselage was entirely original, making use of semi-monocoque construction and being composed of duralumin. The internal volume of the fuselage was divided by a series of watertight bulkheads that would have slowed in ingress of water in the event of the aircraft being forced down over water. [2] A retractable undercarriage was fitted. [2]
It had a semi-monocoque fuselage of pod-and-boom arrangement with a large bubble-like front greenhouse, [1] a three-blade rotor, and quadricycle fixed landing gear replacing the earlier tricycle arrangement. [4] The production S-52-3 (HO5S-1) incorporated a downward sloping (anhedral) v-tail stabilizer. [6]
Historically, though, there is a subtle difference between the two terms. If the longitudinal members in a fuselage are few in number (usually 4 to 8) and run all along the fuselage length, then they are called "longerons". The longeron system also requires that the fuselage frames be closely spaced (about every 4 to 6 in or 10 to 15 cm).