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25-892: (Redirected from X-22 ) X22 or X-22 may refer to: Bell X-22 , an American experimental tilt-fan aircraft of the 1960s Kh-22 (Russian: X-22 ; AS-4 'Kitchen'), an anti-ship missile developed by the Soviet Union Paul Magriel (born 1946; nicknamed "X-22"), American professional backgammon and poker player \x22 , the quotation mark (Unicode codepoint hex &x22;) See also [ edit ] [REDACTED] Search for "x22"  or "x-22" on Misplaced Pages. General Aircraft Hotspur X.22/40; military glider All pages with titles beginning with X22 All pages with titles containing X22 All pages with titles containing x-22 X2 (disambiguation) [REDACTED] Topics referred to by

50-573: A rigid fixture . These formers are then joined with lightweight longitudinal elements called stringers . These are in turn covered with a skin of sheet aluminum, attached by riveting or by bonding with special adhesives. The fixture is then disassembled and removed from the completed fuselage shell, which is then fitted out with wiring, controls, and interior equipment such as seats and luggage bins. Most modern large aircraft are built using this technique, but use several large sections constructed in this fashion which are then joined with fasteners to form

75-485: A design is intended to be "self jigging", not requiring a complete fixture for alignment. Early aircraft were constructed of wood frames covered in fabric. As monoplanes became popular, metal frames improved the strength, which eventually led to all-metal-structure aircraft, with metal covering for all its exterior surfaces - this was first pioneered in the second half of 1915 . Some modern aircraft are constructed with composite materials for major control surfaces, wings, or

100-472: A large warplane which uses this process). The logical evolution of this is the creation of fuselages using molded plywood, in which several sheets are laid with the grain in differing directions to give the monocoque type below. In this method, the exterior surface of the fuselage is also the primary structure. A typical early form of this (see the Lockheed Vega ) was built using molded plywood , where

125-447: 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. The proportioning of loads between the components is a design choice dictated largely by the dimensions, strength, and elasticity of the components available for construction and whether or not

150-548: A scratch pane near the passenger. Acrylic is susceptible to crazing  : a network of fine cracks appears but can be polished to restore optical transparency , removal and polishing typically undergo every 2–3 years for uncoated windows. " Flying wing " aircraft, such as the Northrop YB-49 Flying Wing and the Northrop B-2 Spirit bomber have no separate fuselage; instead what would be

175-445: Is composed of 4–6 panels, 35 kg (77 lb) each on an Airbus A320 . In its lifetime, an average aircraft goes through three or four windshields , and the market is shared evenly between OEM and higher margins aftermarket . Cabin windows, made from much lighter than glass stretched acrylic glass , consists of multiple panes: an outer one built to support four times the maximum cabin pressure, an inner one for redundancy and

200-628: Is different from Wikidata All article disambiguation pages All disambiguation pages Bell X-22 The X-22 was not a prototype of the V-22 Osprey , although it was a part of the development of tilt-rotor aircraft and Bell's work in this field of study. In 1962, the United States Navy announced their request for two prototype aircraft with V/STOL capability, powered by four ducted fan nacelles. Bell Helicopters already had extensive experience with VTOL aircraft and

225-469: Is prevalent in the series production of many modern sailplanes . The use of molded composites for fuselage structures is being extended to large passenger aircraft such as the Boeing 787 Dreamliner (using pressure-molding on female molds). This is the preferred method of constructing an all- aluminum fuselage. First, a series of formers in the shape of the fuselage cross sections are held in position on

250-427: Is required for aircraft stability and maneuverability. This type of structure is still in use in many lightweight aircraft using welded steel tube trusses. A box truss fuselage structure can also be built out of wood—often covered with plywood. Simple box structures may be rounded by the addition of supported lightweight stringers, allowing the fabric covering to form a more aerodynamic shape, or one more pleasing to

275-528: The French fuselé "spindle-shaped") is an aircraft 's main body section. It holds crew , passengers, or cargo . In single-engine aircraft, it will usually contain an engine as well, although in some amphibious aircraft the single engine is mounted on a pylon attached to the fuselage, which in turn is used as a floating hull . The fuselage also serves to position the control and stabilization surfaces in specific relationships to lifting surfaces , which

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300-481: The Rutan VariEze ). An example of a larger molded plywood aircraft is the de Havilland Mosquito fighter/light bomber of World War II . No plywood-skin fuselage is truly monocoque , since stiffening elements are incorporated into the structure to carry concentrated loads that would otherwise buckle the thin skin. The use of molded fiberglass using negative ("female") molds (which give a nearly finished product)

325-556: The advantage of being made almost entirely of wood. A similar construction using aluminum alloy was used in the Vickers Warwick with less material than would be required for other structural types. The geodesic structure is also redundant and so can survive localized damage without catastrophic failure. A fabric covering over the structure completed the aerodynamic shell (see the Vickers Wellington for an example of

350-636: The complete fuselage. As the accuracy of the final product is determined largely by the costly fixture, this form is suitable for series production, where many identical aircraft are to be produced. Early examples of this type include the Douglas Aircraft DC-2 and DC-3 civil aircraft and the Boeing B-17 Flying Fortress . Most metal light aircraft are constructed using this process. Both monocoque and semi-monocoque are referred to as "stressed skin" structures as all or

375-641: The entire fuselage such as the Boeing 787. On the 787, it makes possible higher pressurization levels and larger windows for passenger comfort as well as lower weight to reduce operating costs. The Boeing 787 weighs 1,500 lb (680 kg) less than if it were an all-aluminum assembly. Cockpit windshields on the Airbus A320 must withstand bird strikes up to 350 kn (650 km/h) and are made of chemically strengthened glass . They are usually composed of three layers or plies, of glass or plastic :

400-402: The eye. Geodesic structural elements were used by Barnes Wallis for British Vickers between the wars and into World War II to form the whole of the fuselage, including its aerodynamic shape. In this type of construction multiple flat strip stringers are wound about the formers in opposite spiral directions, forming a basket-like appearance. This proved to be light, strong, and rigid and had

425-497: The fuselage is a thickened portion of the wing structure. Conversely, there have been a small number of aircraft designs which have no separate wing, but use the fuselage to generate lift. Examples include National Aeronautics and Space Administration 's experimental lifting body designs and the Vought XF5U-1 Flying Flapjack . A blended wing body can be considered a mixture of the above. It carries

450-634: The inner two are 8 mm (0.3 in.) thick each and are structural, while the outer ply, about 3 mm thick, is a barrier against foreign object damage and abrasion , with often a hydrophobic coating. It must prevent fogging inside the cabin and de-ice from −50 °C (−58 °F). This was previously done with thin wires similar to a rear car window but is now accomplished with a transparent, nanometers-thick coating of indium tin oxide sitting between plies, electrically conductive and thus transmitting heat. Curved glass improves aerodynamics but sight criteria also needs larger panes. A cockpit windshield

475-420: The layers of plywood are formed over a "plug" or within a mold . A later form of this structure uses fiberglass cloth impregnated with polyester or epoxy resin as the skin, instead of plywood. A simple form of this used in some amateur-built aircraft uses rigid expanded foam plastic as the core, with a fiberglass covering, eliminating the necessity of fabricating molds, but requiring more effort in finishing (see

500-539: The rear wings. Maneuvering was achieved by tilting the propeller blades in combination with control surfaces ( elevators and ailerons ), which were located in the thrust stream of the propellers. The maiden flight of the prototype occurred on 17 March 1966. In contrast to other tilt-rotor craft (such as the Bell XV-3 ), transitions between hovering and horizontal flight succeeded nearly immediately. However, interest increased more towards VTOL and V/STOL properties, not

525-591: The remaining craft, 151521, is currently stored by the Niagara Aerospace Museum , New York . According to the employees at the Museum, the craft was held onto after being debated for scrapping by the Navy. General characteristics Performance Aircraft of comparable role, configuration, and era Related lists Fuselage The fuselage ( / ˈ f juː z əl ɑː ʒ / ; from

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550-495: The same term This disambiguation page lists articles associated with the same title formed as a letter–number combination. If an internal link led you here, you may wish to change the link to point directly to the intended article. Retrieved from " https://en.wikipedia.org/w/index.php?title=X22&oldid=1252600723 " Category : Letter–number combination disambiguation pages Hidden categories: Articles containing Russian-language text Short description

575-449: The specific design of the prototype. Due to failure of a propeller control, described by test pilot Stanley Kakol as the only non-redundant component in the power chain, the prototype crashed on 8 August 1966 and technicians stripped it for components in order to make the second prototype flight capable. The fuselage was still used as a simulator for some time afterwards. The second X-22 first flew on 26 August 1967. Early that year, it

600-593: Was able to utilize an already developed test mockup. In 1964 the prototype, internally referred to by Bell as Model D2127, was ordered by the Navy and received the X-22 designation. It was unveiled at an event in Niagara Falls in May 1965. Three-bladed propellers were mounted on four wings and synchronized through a wave-interconnection system, were connected to four gas turbines which, in turn, were mounted in pairs on

625-459: Was equipped with a variable flight control and stabilizer system from Cornell Aeronautical Laboratory , which improved flight performance. Although the X-22 was considered to be the best aircraft of its type at the time, the program was canceled. The required maximum speed of 525 km/h was never reached. The second prototype was moved to Cornell Aeronautical Laboratory for further testing; the last flight occurred in 1988. Although not on display,

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