Used for long-range international routes, the passenger cabin has 124 seats. The cabin is divided into two parts: the front cabin is a first-class cabin, there are 16 first-class seats, *** 4 rows, 4 people per row, the row refuses to 1.05 meters, the aisle width of 500 millimeters; the rear cabin is a traveler-class cabin, there are 108 travel-class seats, *** 18 rows, 6 people per row, the row pitch of 0.88 meters, the aisle width of 430 millimeters. There is 1 service room, 1 kitchen, 1 storeroom and 1 toilet at the front end of the front cabin; 1 service room, 1 kitchen, 1 checkroom and 1 storeroom and 3 toilets at the rear of the rear cabin. When used for domestic routes, all economy seats are used, ****149 seats. If used for short and medium-haul routes, the number of seats can be increased to 178. Cabin air conditioning is powered by 2 engines and 2 pressurizers as the main air source, with a normal air supply of 6,400 kg/hour, cabin pressure of 0.6 atmospheres, and a temperature adjustment range of 16 to 30 degrees.
The landing gear is a front three-point type, the front landing gear has two 900mm x 300mm wheels, which are retracted forward in the fuselage. Each main landing gear is equipped with four 1150mm x 410mm wheels, which are retracted inward in the lower fuselage landing gear bay. The forward wheels have a turning angle of 56 degrees left and right. The elevator and ailerons are manually operated by means of manually operated adjusting tabs. Hydraulic boosters operate the spoiler and rudder. The flap maneuvering system is realized by the hydraulic follower system. The maneuvering of elevator, rudder, and ailerons is arranged with a balanced plate type pneumatic leveling system to reduce the pilot's load, and each system is also equipped with an emergency maneuvering system.
The hydraulic system of the aircraft consists of independent main hydraulic system and auxiliary hydraulic system which are backed up by each other, the two hydraulic pumps of the main system are driven by two inboard engines, and the energy source of the auxiliary system is two electric pumps. The working pressure of the hydraulic system is 210 kgf/cm2.
The maximum fuel capacity of the aircraft is 51 tons, and the fuel is contained in the wing integral tanks and the central wing soft tank. The aircraft can be refueled by pressure or normal gravity fueling, and has an emergency fuel draining system at the rear of the 4-10 rib fuel tanks. The aircraft's electronic equipment includes 627 navigation computer, 256 weather radar, 771 Doppler radar, WL-7 radio compass, 108 omnidirectional beacon/instrument landing receiver, Pilot-3 autopilot, and atmospheric data computer. It is also equipped with 2 sets of No. 70 shortwave single-sideband radios, 1 set each of intercom, announcing equipment and recording equipment, and tape recorder. The instrumentation equipment of the aircraft mainly includes altimeter, radio altimeter, Mach number meter, elevation speed meter, horizon meter, atmospheric temperature meter, heading indicator, exhaust temperature meter for engine, pressure ratio indicator, triple meter, fuel quantity meter, fuel consumption meter and so on.
The aircraft's electrical equipment is powered by four 30-kilovolt 120/208-volt, 400-hertz alternators, and DC power is supplied by four 75-amp variable voltage rectifiers. Emergency storage batteries are also provided. The aircraft is equipped with 2 sets of oxygen systems for the cockpit and cabin, each system includes a fixed oxygen supply equipment and portable oxygen supply equipment. 1, Yun-10 aircraft development breakthrough in the Soviet Union aircraft design specifications, is China's first reference to the U.S. airworthiness regulations FAR-25 part of the standard development of large passenger aircraft.
2. For the first time, the "Spike" type high-subsonic wing was adopted.
3. It is the first time that the concepts of "breakage safety" and "safe life" are fully adopted in designing and analyzing the aircraft structure.
4, the first to use the full wingspan integral fuel tank (maximum fuel capacity of 51 tons), the first to develop a large-capacity airtight cabin (maximum volume of 318 cubic meters)
5, the first to successfully adopt the overall aerodynamic layout of the wing hanging four engines.
6, the first time to adopt the form of pneumatic power-assisted maneuvering driven by the adjusting piece of the maneuvering surface, omitting the hydraulic power-assisting device.
7. It is the first time to conduct large-scale ground simulation tests for all systems of the aircraft.
8, the whole machine selection of new materials 76, accounting for 18%, selection of new standards 164, accounting for 17%; selection of new finished products 305, accounting for 70%. These new materials, new standards and new products have laid the foundation for the development of China's civil airplanes.
9. For the first time, type design was comprehensively carried out with electronic computers, and 138 calculation programs were written.
10, for the first time in accordance with the FAR-25 requirements to organize the development of large passenger aircraft test flights (*** flying 130 flights, 170 hours) .
The Yun-10 adopts the cusp wing type. Its drag divergence Mach number is 0.85, better than the Boeing 707's 0.84; maximum cruising speed is 974 kilometers per hour, higher than the IL-62 and the Boeing 707. transport-10 long range aerodynamic efficiency of the highest Mach number of 0.79-0.8, also higher than the Boeing 707.
The seat-kilometer fuel consumption of the transport-10 are lower than the IL-62 and Trident airliners, while comparable with the Boeing 707's. It is estimated that the seat rate of the transport-10 aircraft as long as it reaches 60%, you can recoup the fuel costs and aircraft depreciation costs.
Transportation-10 in the domestic route use has a better airport adaptability, the aircraft's Load Class Number (LCN) for 48-56, lower than the Trident airliner's 62-64.5. According to incomplete statistics, under the airport conditions at that time, the transport-10 aircraft can be used in 35 domestic airports, while the Boeing 707 and Trident airliners only 10, the transport-10 aircraft has a large thrust-to-weight ratio, single-engine lift of up to 9,500 meters, it is very suitable for flying to the Tibetan region. In the early 1980s, China was also trying to cooperate with foreign countries in the development of large jet airliners, and one of the candidate partners was the U.S.-based McDonnell Douglas Corporation. The aviation department, due to a number of factors, gave up acquiring foreign technology to further improve the Yun-10, and chose to cooperate in the form of assembling the McDonnell Douglas DC-9 Super 80 (i.e., MD-82) with spare parts. At the same time as the launch of the Yun-10, the Shanghai Aircraft Corporation (SAC), which was the trial production base for the Yun-10, cooperated with McDonnell Douglas in the final assembly of the MD-80/90 series of airliners.
On June 4, 1984, 219 comrades from the Shanghai Aircraft Research Institute jointly wrote a petition titled "Don't Spend Huge Amounts of Foreign Exchange to Assemble DC-9 Super 80, Suggest Developing China's Civil Aviation Industry on the Basis of the Yun-10".
On April 12, 1985 McDonnell Douglas signed a contract with Shanghai Aerospace Industry Corporation for the assembly of 25 MD-82s in Shanghai, which was completed in 1991 .