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The Maupin Carbon Dragon is an American, high-wing, single-seat, glider that was designed by Jim Maupin and made available as plans for amateur construction. Plans are no longer available.〔Maupin, Jim: ''Carbon Dragon'', sales brochure, October 1988〕〔Bertrand, Noel; Rene Coulon; et al: ''World Directory of Leisure Aviation 2003-04'', page 57. Pagefast Ltd, Lancaster OK, 2003. ISSN 1368-485X〕 ==Design and development== The Carbon Dragon was intended to take advantage of the US FAR 103 Ultralight Vehicles regulations that classify unpowered aircraft with empty weights of or less as hang gliders and thus allow them to be flown without a pilot license, Federal Aviation Administration aircraft registration or a Certificate of Airworthiness. The Carbon Dragon's standard empty weight is and the aircraft has a gross weight of , giving a payload of . The designer said "The philosophy behind its development was to try to bring foot launch soaring performance up into the lower performance range of sailplanes." The Carbon Dragon was intended to be similar in concept to the Hall Vector 1.〔〔 The original design was intended to be a much more complex aircraft, as Maupin explained: As a result the aircraft was redesigned to its final configuration, a simpler and lighter aircraft with a span wing.〔 The Carbon Dragon is predominantly a conventional wood and doped aircraft fabric glider, making judicious use of carbon fiber in the wing spar caps, control rods, flaperons and the elliptical tail boom to save weight. The control tubes are constructed by laying up the carbon fiber on aluminium tubing and then, when the carbon has cured, dissolving the aluminium with swimming pool acid. The cockpit is totally enclosed and the original design called for a cockpit width of at the hips and at the shoulder, although some have been modified to accommodate pilots of larger dimensions. The main aircraft structure consists of dual triangular torque boxes on each side of the fuselage. The wing employs a Culver SD airfoil that was designed by Irv Culver for the project and full-span flaperons of 30% chord. The flaperons can deploy from −5° to +15° as flaps and −4° to +16° as ailerons, with a 4:1 differential. The flaperons are driven by two, vertically mounted pushrods enclosed within the fuselage and connected to the side stick. The wing ribs forward of the spar are fabricated from 5-ply mahogany and aft of the spar from square spruce. The landing gear is a fixed monowheel, mounted on the hinged cockpit bottom door, that opens to allow the pilot to lift the aircraft for foot-launching. The aircraft was designed so that if the pilot falls while foot-launching his body will be in the rear fuselage cavity and not pinned under the aircraft. The ultimate structural load limit is +/-7.5 g, with a +/-5.0 g operational load limit.〔〔 The Carbon Dragon was designed to be launched by foot-launch, aero-tow, winch-launch, auto-tow or bungee launch.〔〔 In October 1988 Maupin reported that the prototype had been flown by ten different pilots ranging in weight from , had achieved a 100 fpm (0.51 m/s) sink rate and had been launched by auto-tow, aero-tow and bungee, but had not been foot-launched. In October 1988 Maupin estimated that building a Carbon Dragon would cost US$2000 and take 1000–1500 hours of construction time.〔 When they were available the plans consisted of 23 sheets of 2' X 4' (61 X 122 cm) blueprints and sold for US$150.〔 At least one Carbon Dragon was modified to include a cockpit roof-mounted pentagonal spoiler, similar to that used on the Maupin Windrose.〔 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Maupin Carbon Dragon」の詳細全文を読む スポンサード リンク
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