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Main spar of a de Havilland DH.60 Moth. In a fixed-wing aircraft, the spar is often the main structural member of the wing, running spanwise at right angles (or thereabouts depending on wing sweep) to the fuselage. The spar carries flight loads and the weight of the wings while on the ground.
Each single main wheel was on a vertical, shock absorbing leg. which joined the forward spar through the engine mountings. The wheels were hinged to the lower longerons with pairs of long V-form struts. It had an enclosed pilot's cockpit ahead of the leading edge of the wing, equipped with a single fixed, forward firing machine gun. Behind the ...
A fixed-wing aircraft is a heavier-than-air aircraft, such as an airplane, which is capable of flight using aerodynamic lift. Fixed-wing aircraft are distinct from rotary-wing aircraft (in which a rotor mounted on a spinning shaft generates lift), and ornithopters (in which the wings oscillate to generate lift).
Alisport Silent 2. The fuselage is carbon and glass fiber composite with epoxy resin. The wings have an elliptical planform, vertical or elliptical design winglets. The wing structure includes extensive use of carbon fiber, both in the sandwich skins and in the tapered I-beam wing spar which uses pultruded carbon rods for the spar caps.
It had a steel framed, canvas covered fuselage (engine part covered with duralumin). The elliptical wing was two-spar, of duralumin construction, canvas-covered, fitted with slats and flaps. The tail was made of duralumin. It had a conventional fixed landing gear with a rear wheel, main gear had teardrop covers. The closed cabin had a capacity ...
Wide-span ailerons were hinged to the rearmost wing spar, operated by torque-tubes with dog clutches at the junction between the centre section and the removable outer panels. The fixed undercarriage consisted of a pair of wheels on a short axle carried inside the fuselage, the lower part of the wheels projecting through slots.
It is a low-wing cantilever monoplane with a fixed tail-wheel landing gear and seats two side-by-side. It was designed for the Lycoming O-235 but accommodates engines from 100 to 160 hp (75 to 119 kW). The primary wing structure is a wood box spar connected to an aileron spar by ribs cut on a band saw.
The 2-33 was designed to be rugged, easy to maintain and with a high degree of crashworthiness. [1] [2] [3] [5] The 2-33 has a welded steel tube fuselage covered in aircraft fabric. The single-spar, aluminum structure wings are tapered from mid-span and feature top and bottom balanced divebrakes. The wings are covered in aluminum stressed skin.