Longeron

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Interior of a Boeing/Stearman PT-17 showing small channel section stringers.

In aircraft construction, a longeron, or stringer or stiffener,[1] is a thin strip of material to which the skin of the aircraft is fastened. In the fuselage, stringers are attached to formers (also called frames) and run in the longitudinal direction of the aircraft. They are primarily responsible for transferring the aerodynamic loads acting on the skin onto the frames and formers. In the wings or horizontal stabilizer, longerons run spanwise and attach between the ribs. The primary function here also is to transfer the bending loads acting on the wings onto the ribs and spar.

Sometimes the terms "longeron" and "stringer" are used interchangeably. Historically, though, there is a subtle difference between the two terms. If the longitudinal members in a fuselage are few in number and run all along the fuselage length (usually 4 to 8), 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). If the longitudinal members are numerous (usually 50 to 100) and are placed just between two formers/frames, then they are called "stringers". In the stringer system the longitudinal members are smaller and the frames are spaced farther apart (about 15 to 20 in or 38 to 51 cm). Generally, longerons are of larger cross-section when compared to stringers. On large modern aircraft the stringer system is more common because it is more weight-efficient, despite being more complex to construct and analyze. Some aircraft use a combination of both stringers and longerons.[2]

Longerons often carry larger loads than stringers and also help to transfer skin loads to internal structure. Longerons nearly always attach to frames or ribs. Stringers often are not attached to anything but the skin, where they carry a portion of the fuselage bending moment through axial loading.[3] It is not uncommon to have a mixture of longerons and stringers in the same major structural component.

Notes[edit]

  1. ^ Shevell, Richard Shepherd (1989). Fundamentals of flight. Englewood Cliffs, N.J.: Prentice Hall. p. 375. ISBN 0-13-339060-8. 
  2. ^ Bruhn, E.F., page C11.29, "Analysis and Design of Flight Vehicle Structures", 1973
  3. ^ Michael C. Y. Niu (1988). Airframe Structural Design. Conmilit Press LTD. pp. 376.