With Chinglish translation ...
AD100 is a single ultralight aircraft developed by China University of Aeronautics and astronautics to meet the needs of the foreign market, in cooperation with US AI Dassault Limited (Adaso, INC.). May 1984, Nanjing University of Aeronautics and Astronautics (NAI) and the United States of America AI Dassault Co., Ltd. agreed to jointly develop, Nanjing University of Aeronautics and Astronautics undertook all the design and development The company is responsible for providing the latest information, equipment and sales in foreign markets.
August 1985 completed the prototype flight test, designed to meet the United States
FAR103 Department of the relevant provisions.
AD100 single Super Light aircraft in November 1985 to participate in the United States Light Aircraft Expo in Los Angeles, 1986, respectively, in Shanghai, Nanjing held in the Foreign Trade fair and Beijing domestic civil aircraft reporting exhibition, was widely praised. May 1986, the Australian fitness Sports equipment company came to Nanjing to buy a AD100 aircraft. AD100 can be used for aerial photography, topographic surveying, forest protection, agricultural transportation and so on after proper modifications.
The AD100 development AD200 (double seater) is scheduled to complete the prototype test by the end of 1986.
Design features
AD100 adopts advanced duck-style layout, fully enclosed cockpit and whole FRP composite body structure. AD100 can be easily decomposed into front wings, fuselage, two main wings and two small wings. Can be loaded into the supporting design of the special trailer. Trailers can be towed by a car or limousine and stored in a general home garage. AD100 shape novel, beautiful appearance, cabin comfort, open vision, simple operation, flight safety. The plane can take off on the dirt track or on the lawn.
Wing: Cantilever type upper monoplane, relative thickness is 20%, leading edge sweep is 12 °. TAN type structure. Skin is a FRP honeycomb sandwich panel. The trailing edge is fitted with a pair of aileron flaps. When used as flaps, it can be 20° downward. As aileron use can be deflected 15 °. The wing tip is fitted with a composite small wing, which is both directional and directional, and the rudder deflection range is 25°.
Front wing: straight wing full composite honeycomb sandwich structure. Elevator maximum lower 25°, maximum -5°, front wing and fuselage through three bolts connected.
Fuselage: shell-shaped long circular section structure. The shell is made of honeycomb panels and aviation laminates. The fuselage equivalent diameter is 0.89 meters. The machine has a number of reinforced frames made of aerial laminates.
Landing gear: first three points. The main landing gear for the overall arched FRP structure, with the fuselage reinforced box bonding, no metal connectors. The front landing gear is a metal welded structure that can be manipulated to turn and glide, linkage with the rudder and equipped with a front-wheel brake mechanism.
Powerplant: Equipped with a Rotax-277 two-stroke single-cylinder piston engine, power 19.9 kw (27 hp), using a standard two-blade propulsion propeller. The middle part of the fuselage is equipped with a 19 litre tank.
The cockpit is fitted with adjustable seats. The front and back of the seat is 200 mm. Open with adjustable vent.
System: three-axis control system. Equipped with independent working flaps. The elevator and flaps are hard to manipulate, and the rudder is a soft type.
Airborne Equipment: Equipped with general international instrumentation, but also equipped with the latest American life-saving umbrella, in case of emergency, can ensure that the crew and aircraft safely landing.