هواپیمای اف-16

هواپیمای اف-16 فایتینگ فالکون، ساخت شرکت جنرال داینامیکز، جنگنده ای در کلاس کوچک و چند مأموریته می باشد که نخستین پرواز خود را با اولین نمونه خود در سال 1976 به انجام رساند. این هواپیما توانایی حمله به صورت هوا به هوا علیه هواپیماهای دشمن و هوا به زمین علیه تجهیزات زمینی برای مثال تانک ها و زره پوش های دشمن را به طور کامل و بهینه داراست.فالکون در حقیقت آمیزه ای از هزینه نگهداری اندک و به صرفه و همچنین کارائی تسلیحاتی و تهاجمی بالاست. این جنگنده هم اکنون در اختیار نیروی هوایی ایالات متحده و همچنین متحدان این کشور مانند ترکیه یا امارات متحده عربی می باشد که البته

ادامه نوشته

مروري بر سري 83 از خانواده MD

MD-83 را بهتر بشناسيم
هواپيماي مدل MD-83 يكي از مدل هاي سري خانواده MD-80 است. بطور كلي سري MD-80 شامل مدل هاي MD-81 ، MD-82 ، MD-83 ، MD-87 و MD-88 است، كه مجموعه اي از جت هاي مقرون به صرفه با مصرف سوخت كم و بي صدا مي باشند. اين هواپيما اولين بار در آگوست سال 1980 از طرف سازمان هواپيمايي فدرال در ايالات متحده تائيد شد و از اكتبر همان سال به سرويس خطوط هوايي وارد شد.
توليد اين هواپيما ها در كارخانه ي هواپيما سازي LongBeachCA  انجام مي گرفت و اين كار تا سال 1999 به مدت 2 دهه ادامه داشت. سايت LongBeachCA يكي از زير مجموعه هاي كمپاني بوئينگ است كه در سال 1941 توسط كمپاني داگلاس افتتاح شد و به دنبال ادغام بوئينگ و مك دانل داگلاس در سال 1997 اين سايت رسما ً قسمتي از كمپاني بوئينگ شد. هواپيماي MD-83 به دو موتور قدرتمند توربوفن JT8D-912 Pratt & Whitney مجهز است و داراي طراحي فوق العاده آيروديناميكي مي باشد. از طرفي قابليت پروازهاي طولاني (تا 2880 كيلومتر) را دارد.

آسايش در آسمان
هواپيما ي MD بسيار كم هزينه و اقتصادي است. از اين رو گزينه اي بسيار مناسب در صنعت هواپيمايي به شمار مي رود. MD طلايه دار فصل هواپيماهاي راحت و مدرن و ايمن در سرويس هاي مسافربري است. در حال حاضر MD-83 در بسياري از خطوط هوايي داخل آمريكا و خطوط هوايي ملي و خصوصي ديگر كشورها بطور گسترده استفاده مي شود.
• آسيا: عربستان سعودي – مصر – نپال – اندونزي – فيليپين – تايوان – كره – چين – كشورهاي خاور دور
• اروپا: سوئيس – اطريش – ايتاليا – تركيه
• امريكا: آلاسكا – مكزيك – امريكا - كانادا
به تازگي نيز سفارس هاي ساخت بسياري براي اين مدل هواپيما به كمپاني بوئينگ داده شده است. علاوه بر اين از آنجائيكه MD-83 امتحان خود را به خوبي پشت سر گذاشته است، بسياري از خطوط هوايي ِ تازه تاسيس و چارتر ها مشتاقانه درصدد بهره مندي از اين مدل مي باشند. بعد از امريكا كه سازنده ي اين خانواده هواپيماست، اطريش و سوئيس اولين كشورهاي اروپايي بودند كه MD-83 را در ناوگان هوايي خود گنجاندند. امروزه امريكا با بيشترين تعداد مدل هواپيماهاي MD-80 (275 فروند) در رديف اول و جمهوري خلق چين با 35 فروند در رديف بعد قرار دارند. مدل MD-80 يكي از موفق ترين برنامه هاي تكنولوژيك در تاريخ ساخت هواپيماهاي مسافربري است. در طول سال هاي 1979 تا 1999 كمپاني مك دانل داگلاس و بوئينگ تعداد 1191 فروند هواپيما از كليه مدل هاي MD-80 توليد كرده اند كه بيش از 1180 فروند آنها هنوز در ناوگان بيش از 50 خطوط هوايي داخلي و خارجي مشغول به كار هستند.
MD-83 از نظر اجرايي و اقتصادي به قدري توانمندي دارد كه از نظر بسياري از صاحبان فن و مديريتهاي خطوط هوايي بين المللي، مطمئن ترين و بهترين انتخاب ممكن است. بدين جهت خطوط هوايي اي كه قصد مدرنيزه كردن و بالا بردن ضريب امنيتي خود را دارند، هواپيماي MD-83 بيشتري در اختيار مي گيرند. در حال حاضر روزانه بيش از 4800 پرواز، در بيش از 420 فرودگاه جهان با اين هواپيما انجام مي گيرد. آخرين مدل ساخته شده از سري MD-80 دسامبر 1999 توليد شده است. بعد از آن، به دنبال ادغام مك دانل داگلاس و بوئينگ هواپيماهاي MD با نام بوئينگ به بازار آمدند.
به هر حال آنچه حائز اهميت است مطابقت بوئينگ MD با تكنولوژي پيشرفته قرن 21 به منظور كاهش هزينه، آلودگي صوتي و آلودگي هوا مي باشد.

ايمني بسيار بالا
بطور كلي سري خانواده MD-80 و خصوصا ً MD-83 از نظر طراحي بدنه، بال و موتور نسبت به سري هاي قبلي شركت هواپيمايي مك دانل داگلاس ساختاري كاملا ً متفاوت و متمايز دارند. در حقيقت MD-83 كه پايه گذار نسل جديد جت هاي مسافربري است، همواره به خاطر ظرفيت امنيتي فوق العاده بالا و ضريب اطمينان بالا و دوام، در صنعت هواپيمايي از اعتبار جهاني و وجهه متمايز برخوردار است و در اين زمينه ركورد دار است. اولين هواپيماي MD-83 در سال 1983 به وزن 41 تن و داراس مخزن سوخت بزرگتري نسبت به مدل هاي قبلي به پرواز درآمد. يكي ديگر از تكنولوژي هاي پيشرفته هوانوردي كه در MD-83 وجود دارد، نصب اولين سيستم راهنماي پرواز ديجيتال است. در مجموع بايد گفت كه سري هواپيما هاي MD-80 و خصوصا ً MD-83 نقطه ي اتكا خط توليد كمپاني مك دانل داگلاس و بوئينگ (از سال 1997 به بعد) بوده و هست. هواپيماي MD-83 به تنهايي باعث شد تا در سال 1985 بار ديگر كمپاني مك دانل داگلاس كه در ركود شديد اقتصادي به سر مي برد احيا شده و به سود دهي غير منتظره اي برسد.
آمار سوانح و حوادث MD-83 در طول حيات 2 دهه ي گذشته ي خود بسيار پايين بوده و تنها 8 مورد سانحه ي هوايي داشته است. تحقيقات نشان مي دهد، سوانح پيش آمده معلول عوامل انساني و محيطي بوده اند و نه عدم كارائي اين هواپيما و تكنولوژي آن. مثال هاي زير گواه اين مطلب اند:
• سانحه ي هوايي سال 1981 در امريكاي جنوبي به علت مه غليظ و عدم ديد كافي خلبان
• سانحه ي هوايي سال 1988 در آرژانتين به علت عدم ديد كافي
• سانحه ي هوايي سال 1993 در چين به علت طوفان و باران بسيار شديد
• سانحه ي هوايي سال 1993 بازهم در چين به علت مه غليظ
• سانحه ي هوايي سال 2000 در آلاسكا به علت برخورد با زمين

دوست محيط زيست
زمان توليد اولين هواپيماي MD-83 مقارن بود با زمانيكه از طرف دولت امريكا استاندارد هاي دقيق و سختي به منظور كاهش آلودگي صوتي اعمال مي شد. از اين رو اين هواپيما مطابق با آن شرايط و به عنوان اولين JetLiner به بازار آمد.
يكي از خصوصيات مدل هاي جديد MD-83 اين است كه كابين آن به دو كلاس تقسيم مي شود، به اين معني كه تركيبي از كلاس هاي مختلف در رديف هاي صندلي موجود مي باشد. يكي ديگر از امكانات پيشرفته اي كه در ساخت و طراحي بوئينگ MD-83 بكار رفته، سيستم مخزن سوخت كمكي است كه از طرف FAA  نيز مورد تائيد قرار گرفته است. اين سيستم البته سيستم جديدي نيست و از سال 1976 به اين سو در انواعي از بوئينگ هاي 727، 737، 757، 767، MD-82 و MD-83 بكار گرفته شده است. وجود اين مخازن كمكي سوخت براي پرواز هاي طولاني حائز اهميت بسيار است. هواپيماهاي MD-83 همچنين داراي ركوردهاي جهاني طولاني ترين پرواز در مسافت 3385 مايل دريايي است كه در سال 1993 به ثبت رسيده. البته اين ركورد به تازگي توسط يك جت بوئينگ مدل 737-700 كه در مسير بدون توقف سياتل – برلين مسافت 4511 مايل دريايي را پيمود، شكسته شد.
به هر حال آنچه بديهي است تمامي تلاش شركت جهاني هواپيماسازي بوئينگ و طراحان ِ MD لحاظ كردن نكات زير مي باشد:
• قابليت پرواز در ارتفاع بالاتر
• پرواز سريع تر و آرام تر از ساير مدل ها
• طراحي مدرن بدنه وموتور
• استفاده از تكنولوژي كاهش دهنده ي آلودگي صوتي و گازهاي آلاينده ي هوا

مشخصات فني MD-83
ارتفاع هواپيما: 9 متر
طول هواپيما: 45 متر
طول بال هواپيما: 32.9 متر
ارتفاع ِ پروازي: 10668 متر
حداكثر وزن: 72580 كيلوگرم
حداكثر تحمل وزن بار: 63280 كيلوگرم
حداكثر ظرفيت ترابري: 18721 كيلوگرم
حداكثر سرعت پرواز: 924 كيلومتر بر ساعت
سرعت عادي پرواز: 813 كيلومتر بر ساعت
خدمه ي پروازي: 2 نفر
تعداد صندلي: 172 عدد

TU-334 AIRCRAFT FAMILY

“TU-334” AIRCRAFT PROGRAM   TU-334 aircraft - is a Russian short-range turbojet aircraft designed for 102 passengers which flight range is equal to 3150 km with designed payload. TU-334 -100 a/c first flight was performed 8 February, 1999. TU-334 a/c was manufactured on the base of advanced developments in dynamics, design, materials science, airborne equipment and is provided with high efficient engines. This allowed to obtain high aerodynamic characteristics and low operational costs.

TU-334 /ac first flight 08 February, 1999

CONCEPT • High comfort level • Passenger cabin arrangement as per customer request • Low noise level in passenger cabin and cockpit • State-of-the-art cabin design • Increased volume of overhead bins • Possibility of installation of audio/video systems • Possibility of installation of SATCOM satellite communcation systems

EFFICIENCY • Commonality with TU-204 a/c by components, systems and units • Modifications of different passenger capacity, flight range and comfort level to meet customer request • Performance of flights under visual and instrument meteorological conditions, on any airways, over water areas, non-reference terrain and Arctic area • Low specific fuel consumption • Simple operation and low maintenance labor content • Compliance with Chapter IV, ICAO regarding noise level • Assigned service life of airframe, engine and systems comply with current requirements of Operators • Decreased time period for flight preparation

SAFETY • Certification to AP-25 , JAR, FAR • State-of-the-art integrated flight and navigation complex • Availability of emergency avoidance systems • Conputerized built-in test of airborne systems • Use of fire safe masks for passengers and crew members

GENERAL VIEW OF TU-334-100 AIRCRAFT

	TU-334-100
AIRCRAFT DIMENSIONS
Aircraft length, m	31,26
Aircraft height, m	9,38
Wing span, m	29,77
Wing area, sq.m	83,226
Wing sweep, grad.	24,0
Fuselage section	3,4 x 4,1
WEIGHTS
MAX takeoff weight, t	47,9
Operating empty weight, t	38,360
Max payload, t	12
Fuel reserve, t	10,1
Max landing weight, t	43,5
Flight rangeat max payload, km	2040
Flight range with 102 passengers, km	3150
Cruise speed, km/h	8200
Runway length, m	1960
Passenger capacity (Tourist class)	102

TU-334-100 A/C PAYLOAD VS.RANGE DIAGRAM

PASSENGER CABIN DIMENSIONS • Length • Max width • Max height • Volume Passenger cabin layout can be designed as per customer desire Decorative finishing is made of incombustible materials. In passenger cabin overhead bins volume is increased. Noise level is low within cabin. Audio/video entertainment systems are provided and SATCOM satellite communication system is provided.

Cabin

ENGINES Turbofan D-436T-1 engine with reversers (2x73.6 kN, 2x7500 kgf) produced by Zaporozhie Engine Manufacturing Design Bureau provided . Engine was certified in 2000. Low fuel consumption, high ecological data, low operational costs at long life. Engine is produced in co-operation with “Motor Sich” JSC (Ukrain), “Moscow Engineering Manufacturing Corporation”Salut” JSC (Russia), “Ufa Engine Manufacturing Corporation” JSC (Russia). TU-334 a/c modifications are supposed to be provided with turbofan D-436T-2 engines with thrust of 80.4-83.4 kN (8200 kgf) each.

COCKPIT Cockpit is in commonality with TU-204 a/c. Cockpit was designed on the base of state-of-the-art ergonomic standards and new designers approaches associated with electronic displays and means of computerized aircrfat control. “Dark” cockpit concept was applied with illumination of certain areas.

TU-334 a/c cockpit

ادامه نوشته

TU-444

Starting from the XX-th century - age of world integration - time factor became especially important. More frequent business trips for longer distances and for longer periods of t time. There was pressing need for radical cut down of transportation. Partially this task was solved by business-aviation which speed and range characteristics were compared with those of advanced passenger trunk-route airplanes. Meanwhile capability of operation out of schedule and from RWY of not more than 2000 m made this type of transport substantially non-alternative for business community. However in view of intercontinental ranges of the most of the routes the issue of cardinal decrease of transportation time is not solved yet. Therefore we should accept supersonic passenger aviation to our life. The question is only on which technological basis and in which way. To some extent the answers to these questions were obtained in the course of investigation performed in various countries including joint investigations on the Program of the second generation supersonic passenger aircraft – STS-2. In Russia this issue was being investigated for a long time and successfully by Tupolev DB in co-operation with leading industry research institutes – TsAGI in the first place - basing on rich experience of building TU-144, TU-144L and long-range combat supersonic TU-22M3 and TU-160. The important fact is the long-term co-operation of Tupolev with Kazan Aircraft corporation – KAPO n.a. Gorbunov. For the time being this is substantially the only aircraft plant in Russia and Europe capable to produce thermally loaded, durable structures intended for operation under extreme conditions. Mostly due to this fact the unique strategic combat complex TU-160 could be embodied. But nevertheless of being a success in combat and passenger aviation and of substantial backlog regarding STS-2 it will not be possible to built economically efficient supersonic airbus in the nearest future because of very severe ecological requirements to civil airplanes. In this connection the most prospective and realistic way of introduction the scientific and research backlog of STS-2 can be building of small-size super-sonic business aircraft. In TUPOLEV DB this project was designated as TU-444. First of all building of such aircraft will be significantly cheaper than super-sonic airbuses. To solve technical problems caused by severe ecological requirements will be easier. According to famous analysts such aircraft market could be 400 to 700 units provided the STS operation prime cost will exceed this figure of sub-sonic aircraft by not more than 20%. The most important of STS features is possibility to perform travel for intercontinental range with coming back within a singe day at maximal use of working time.

When defining TU-444 layout following was taken into account 1. Analyses of possible routes with maximum passenger flow which link 75 the most important centers of the planet which was performed within TU-244 investigation has revealed - it is reasonable to assign estimated flight range equal to 7000-777500 km; - it is not necessary to built STS for fight range of 11000-12000 m since there will be quite seldom nee to travel over such distance and the aircraft will become significantly expensive; - to take passengers over super-long routes it is reasonable to fly with one intermediate landing. 2. TU-144 and TU-160 aircraft operation has demonstrated expediency of limitation of cruise supersonic speed of M=2,0 to provide structure service life and to limit cruising altitude. 3. TUPPOLEV DBB works on supersonic passenger airbus TU-244 has defined the envelope of optimal values of wing loading <=3320 kg/m2. 4. Operation of such well-known business-airplanes as Cessna II, XX, Learjet 60, BAe 125, Falcon 00, Chelleger, Gulfstream II, III, IV, VV, Global Express has revealed that average number of passengers per one flight does not depend on maximal passenger capacity and makes 3-6 persons. 5. Analysis of worldwide airfield net has demonstrated that it is necessary to use RWY not longer than 1800 m. Basing on the results of works and the experience gained when building TU-144, TU-144LLL, TU-22M3, TU-160 and TU-244 the layout of advanced serial STS TU-144 with following characteristics:

Crew (pilots+attendants), pers	2+1
Number of passengers, pers. (maximal)	6 (10)
Aircraft dimensions
length, m	36
height, m	6,51
wing span, m	16, 2
wing area, m2	136
Number of engines	2
Starting engine thrust at sea level, kg	9700
Maximal takeoff weight, kg	410000
Empty weight, kg	193000
Maximal fuel weight, kg	20500
	(50%)
Payload, kg (maximal)	6000
	(1000)
Cruising speed:
-         supersonic (M=2), km/h	2125
-         subsonic (M=0,95)), km/h	1050
Service range with fuel reserve (NBAA IFR), km	500
Demanded RWY length, m	1830

- However it should be noted that despite of the huge scientific and technical and production basis regarding long-range supersonic airplanes it is not possible to built high-efficient STS without solution of complicated technical problems which mostly are features of this very type of aircraft. The main problem of TU-444 project is simultaneous provision of prescribed flight data on flight range (000-500 km), RWY distance not longer than 1800 m) and community noise level (3(4) Chapter of Annex 16 to ICAO) the last is mainly due standards of RWY sideline noise level. Small dimensions of the aircraft (almost 2 times as small as STS-2 by geometric sizes and 6 times as small by weight) in combination with frontal area increase essentially prevent to obtain said characteristics. It makes it difficult to provide maximal L/D ratio Kmax≈8 at supersonic mode and demanded fuel efficiency Gf≈0,51…0,515. To decrease structural weight in order to improve Gf it is necessary to utilize advanced structural materials including composites, to perform careful optimization of primary structure to obtain prescribed service life (survivability) , to reach maximal critical flutter speed, minimization of controls efficiency loss caused by elastic deformation. Climbing path should be improved in comparison with TU-144. Weight can be decreased at the expense of equipment weight cutting down, hence the aircraft reliability should be provided not due to redundancy but due to equipment reliability level of TU-444. For example hydraulic system of TU-144 was duplicated for four times while on Concorde the system was duplicated for 2,5 times. Compliance with community noise level requirements of Part 3(4) of Annex 16 to ICAO at short RWY (1800 m) means decrease of noise level in comparison with TU-144 by not less than 14…18 EPMdb at each reference point. It will require development and maturation of noise abatement system , high-lift devices, study and maturation of engine throttling procedure and takeoff and landing procedures. Shirt RWY distance in combination with two-engine power unit requires decrease of the STS takeoff and landing speeds by approximately 100 km/h in comparison with that of TU-144, TU-244. In other words takeoff and landing of TU-444 will be performed “fighter” manner (using large angles of attack with powerful high-lift devices and with efficient controls and trimmers). The results of the works highlighted urgency to start building the airplane-demonstrator. This aircraft will serve during flight test for checking new technical approaches and revealing un-known features of STS, for measuring pressure, strain and temperature of the structure during each flight in order to exclude necessity of expensive thermal stand. The demonstrator is required to perform experimental flights aiming for maturing of optimal takeoff and landing programs, optimization of flight speeds and altitude according to terrain relief and weather conditions to minimize sound wave level.

Main features of demonstrator aircraft: To cut down costs for demonstrator aircraft building some deviations from production prototype regarding airframe design simplification, grades and brands of used materials, set of equipment. For example, flight compartment view during takeoff and landing in contrast to the production aircraft will be done by downward deviated nose fairing using TU-144 ac actuators; canopy design is similar to that of TU-144 a/c. However nevertheless of simplified design all safety requirements of AP25 (FAR, JAR) including ETOPS-1800, HIRF, HPMD etc. We suppose to use wide unification regarding equipment, systems and components with production aircraft being in operation. To progress in envelop testing (not full scope of ground tests), in getting experimental data enough for reliable development of production STS and certification for special contingent of passengers the demonstrator should be provided with enough amount of measuring and recording equipment to be used in each flight. Under said conditions the demonstrator does not allow to get flight data of production STS. But creation of the demonstrator and its flight tests will give us reliable scientific , technical and experimental data showing possibility to obtain required performance and economic figures for the STS and also will define a production basis for serial production of such airplanes.

Features of the design: TU-444 aircraft is supposed to be built according to “tailless” aircraft with cantilever low-mounted wing provided with large root strakes. All-flying single-fin vertical tail. To improve aerodynamic quality and takeoff and landing characteristics the aircraft was designed to be pitch and laterally statically unstable with fly-by–wire control. The wing is provided with drooped elevons during takeoff and landing and adaptive deflectable leading edges. Tail portion of the wing is ended with powerful trimming surface. Necessity of retractable nose multislot destabilizer similar to that on TU-144 is currently under consideration. Adaptive leading edges designed to improve aerodynamic quality (L/D ratio) might not be used at the initial stage of the demonstrator flight test. The wing is characterized by mid-surface deformation and by geometric and aerodynamic twist along the span. The airfoild thickness ratio changes along the span from 2,5 to 3,5 %. All saw-tooth leading edge represents an integrated fuel tank. Wing root is provided with main LG legs stowage compartments between engine nacelles. On the lower surface of blended flying wing supersonic controlled air-intakes are located with vertical ramp which is a scaled copy of well tried air-intake of TU-160 a/c. Turbofan engines are moved aft from under torsion box and are turned up a small angle to shield the nozzle by rare fuselage and fin in order to cut down side noise level during takeoff run. To extend flight test range and to create back-log the demonstrator will be provided with afterburning turbofans. Production TU-444 is going to be used with AL-32M engine (NPO “Saturn”) without afterburning. The engine was built on the basis of AL-31F and advanced AL-41F-1 and completely meets all quality requirements. The fuselage with obvious “area rules” is divided into three parts: - nose pressurized fuselage with cockpit, equipment compartments, main LG leg stowage compartment, entrance vestibule and coat room, galley, in-built folded stairs, passenger compartment intended for 6-10 persons (depending on layout), lavatory; - mid-portion representing an integral fuel tank which bottom is provided with air-conditioning system compartment; - tail fuselage provided with electrical system and hydraulic system and APU compartments. Flight and navigation equipment should be made on the principle of open architecture with consequently added functions in the process of transfer from the demonstrator to production aircraft. The aircraft will be provided with full set of emergency equipment and means for passenger and crew members. No doubt Building of production TU-444 will require significant efforts and finances. In this aspect the demonstrator played some special role as a basis for development and try off technical approaches and technology of optimal interaction between the participants of the project. Simultaneously advertising and exhibition activities using the demonstrator will prepare the basis for wide introduction of supersonic business-airplanes.

TU-324|414 AIRCRAFT FAMILY

PERSPECTIVE FAMILY OF REGIONAL AIRPLANES

TU-324 and TU-414 airplanes are baaeline models of the family. The regional airplane family is intended for both domestic and international market.

Passenger, executive, cargo-passenger and cargo versions are provided.

TU-324

The airplane are designed to AP-25 Standards in view of future international requirements (FAR/JAR using CALS- technology) in a single medium of full electronic description of the product in the process of designing, production, servicing in operation, training of flight and maintenance personnel. The Procedure of single software and advanced design and production equipment was applied at TUPOLEV DB and on serial production plant (KAPO n. a. Gorbunov) and a number of co-executives.

TU-324

During the process of designing baseline airplanes of said family typical approaches are realized to piloting and cutting down of flight crew workloads. The cockpit created by TUPOLEV in cooperation with industrial institutes was approved by State Mock-up Committee. Special attention was paid to reliability and failure safety of power plant, a/c systems and avionics. Airborne flight and navigation complex provides a complete computerized of air navigation under any physical and geographical conditions at any time of day and night on domestic and international routes and out of routes at provision of automatic approach according to ICAO Category II with reaching Category IIIA. Wide application of digital computerized systems allows to operate the airplanes by two-members crew.

The most obvious advantages of TU-414 a/c family Program is increased safety and maintainability which were laid down into the airplane concept.

Comfortably arranged engines, low landing gear with low tire pressure are fully adjusted to operation from “B” class airfields in CIS and Asia- pacific region. Arrangement of the engines on tail pylons excludes possibility of getting foreign objects from RWY into the engines.

The a/c family is intended for field length up to 1800 m and is positively characterized by adaptability to native airfields by specific pressure and independence (stair/door, APU) which will cut down airlines costs.

To cut down the airlines expenses and to provide high maintainability level TUPOLEV and its co-developers are busy with ensuring service life of 6000 F.H. (25 years) with OC maintenance without overhauls.

TU-414

Geometric characteristics	TU-324	TU-324A	TU-414	TU-414A
A/c length, m	25,5	25,5	31,85	31,85
A/c Height, m	7,3	7,3	8,3	8,3
Wing span, m	23,2	23,2	27,7	27,7
Fuselage cross section, m	2,8х3,14	2,8х3,14	2,8х3,14	2,8х3,14
Weight characteristics
Max takeoff weight, t	23,7	23,7	38,15	40,35
Maximal fuel reserve, t	6,0	9,0	12,63	16,3
Maximal payload, t	5,5	1,8	8,0	2,5
Passenger capacity	52-56	8-19	72-76	8-26
Flight range at maximal passenger capacity	2500	7500	3500	8410
Cruising speed, km/h	810-870	870	850-900	900-950
Field length, m	1800	1800	1800	1800
Engines	AI-22	AI-22	BR-710	BR-710
Passenger cabin
Length, m	10,26	10,26	19,7	19,7
Width, m	2,64	2,64	2,64	2,64
Height, m	1,92	1,92	1,92	1,92

TU-330 AIRCRAFT FAMILY

TU-330 AIRCRAFT WITH PS-90A ENGINES

TU-330 layout

Aircraft Design Bureaus of CIS are currently busy with building of transport aircraft of new generation.

TU-330 a/c is provided with government support by way of Government Resolution of the RF No.369 of 23 April, 1994 “On building of mid-class transport aircraft TU-330”. Russian Government showed comprehensive understanding of the situation in the field of air cargo transportation. According to GosNIIGA 2/3 of mid-range aircraft total cargo turnover falls in flight range of 1000 to 4000 km. From the other hand exactly this area is the most critical since main mid-range aircraft An-12 being currently in operation is now intensively written off because its service life is served out.

According to practice of building new aircraft with high performance in the shortest dates laid by Andrey Tupolev, the greatest native aircraft designer, when designing a new aircraft novelties should be introduced basing on previous really successful projects. It is confirmed by the history of building of large family of “TU” aircraft:

- basing on TU-4 a/c - TU-75 a/c

- basing on TU-16 a/c - TU-104 a/c

- basing on TU-95 a/c - TU-114 a/c

This principle was also used when designing a special purpose middle-class cargo aircraft TU-330 which is being developed on the basis of a large scientific, technical and production work already done in Russian industry during development and manufacturing of passenger airliners of the third generation TU-204, TU-214 and TU-334.

TU-330 aircraft is made as a monoplane with large aspect ration high wing provided with winglets. Two turbojet high by-pass ratio engines PS-90A are installed on pylons under wings. Tail is of usual layout with adjustable stabilizer and elevators. Landing gear is composed of six fully independent undercarriages - two brake wheels per each; and with one nose controlled undercarriage with two wheels. The landing gear provides operation from paved and unpaved RWY.

MAIN PERFORMANCE OF TU-330 AIRCRAFT
1. Maximal payload - 35 t
2. Cruising speed - 800-850 km/h
3. Maximal cruising altitude - 11000 m
4. Servicing flight range with payload of 30 t when operating from concrete airfields with RWY length 2200 m - 138-140
5. Flight fuel consumption for servicing range with max payload - 3000 km

GEOMETRIC CHARACTERISTICS OF TU-330 AIRCRAFT
1. Length - 42.0 m
2. Wing span - 43.5 m
3. Height - 14.0 m
4. Wing area - 195.5 m2

TU-330 A/C CARGO CABIN DIMENSIONS
1. Length - 19.5 m (23.5 m including ramp)
2. Width (on the floor) - 4.0 m
3. Height - 4.0 m (3.55 m under wing center section)

TU-330 powered by PS-90A

The aircraft is capable to operate on routs of 5600 km with payload of 20 t and for 3000 km range with payload of 30 t. Thus this aircraft can fully replace AN-12 a/c and partially IL-76 a/c on mid-range flights.

TU-330 a/c has been optimized to operate on mid-range routes wherein the aircraft has the best prime cost parameters.

Further important advantage of TU-330 a/c is a deep (up to 75%) commonality with certified passenger aircraft TU-204 and TU-214. Wide application on TU-330 aircraft the TU-204 and TU-214 a/c units and components tried out and tested during operation made it possible to cut down sharply the dates of research and development works and certification process for TU-330 a/c.

The aircraft will have more favorable market situation especially among airlines which operate TU-204 and TU-214 a/c. It also can be provided with engines of foreign production – Rolls-Royce, Pratt Whitney - which will facilitate its realization in western markets.

Airlines of Eastern and Western Europe, Middle East and South-East Asia express their keen interest in TU-330 a/c project during International Airshows.

TU-330 a/c Program has started the way of real solution of transportation problems in Russia regarding mass cargo transportation within the shortest periods and at the lowest expenses. In this case by its technical level TU-330 a/c is comparable with Passenger aircraft of new generation TU-204, TU-214. and IL-96M.

 

TU-330 a/c has no limitation regarding flight conditions and can be operated in any

climatic zone, under visual and instrument meteorological conditions, in day and night, at different altitudes; the aircraft can be operated from available airfields (including unpaved RWY). The aircraft does not require a new ground infrastructure since loading and unloading operations are performed autonomously by crew supported by aircraft transportation and cargo cabin equipment. High effective engines PS-90A used on the aircraft meet the most strict international noise level requirements and substantially do not affect environment.

TU-330 a/c aerodynamic cleanness is mainly defined by use of high-effective wing and power unit tested and tried out during long-term investigations carried out by TsAGI, TsIAM and LII scientists on TU-204, TU-214 and IL-96M a/c.

This will make the TU-330 a/c to be the most cost effective cargo aircraft in the world with specific fuel consumption of less than 140 g/g km. For example, the TU-330 a/c fuel consumption per one hour is two times less that of cargo IL-96 a/c being currently in operation.

For typical range of mid-class transport a/c non-stop flight equal to 1700 km and basing on existing network of cargo airlines (according to Gos NII GA estimation) the TU-330 a/c showed to be substantially two times more cost effective than that of Russian cargo medium capacity a/c An-12 by absolute fuel consumption per transport unit.

The most cost-effective operation of TU-330 a/c turned to be when making mass cargo carriage for 1500 – 4500 km range. In 85% of the events weight of goods to be transported does not exceed 25 t. In this case take-off weight of the a/c is less than 100 t which allows to use for take-off and landing RWY not exceeding 1800 m and typical transport task (20 t of cargo to be carried for 3000 km) can be solved in 75% of the events. In this case the landing gear design can provide operation from soft-surface paved RWY and from unpaved RWY with runway sub-soil strength about 7 kgf/cm2.

It does not mean that TU-330 a/c capabilities are limited by said figures. Maximal weight cargo carried by said a/c will make 35 t; typical cargo of 20 t weight the a/c is capable to carry for the range of 5 600 km; field length required being 2 200 m.

Cargo compartment dimensions make it possible to receive substantially entire range of cargo containers and pallets, packaged and long goods, most types of motor cars and other wheel and caterpillar machinery and also to carry military equipment and armament and to provide people and goods dropping.

TU-330 powered by NK-93

Special attention is paid to improvement of a/c operational characteristics, in the first place of ground maintenance. In this case of great importance is unification with mass passenger aircraft TU-204 and TU-214: substantially the same set of spare parts, similarity of technological operation of TU-204, TU-214 and TU-330 a/c ground maintenance and overhaul can significantly facilitate its operation by airlines. Specific expenses for TU-30 a/c maintenance meet future world level.

Thus TU-330 a/c is a really mass medium-capacity which maximally meets Russian demands of main cargo flow with the most fuel and transportation effectiveness. In the first place Russia needs exactly such cheap and simple aircraft capable to optimal cargo re-distribution between various types of transport taking certain amount of cargo from motor, rail and river transport.

None of cargo aircraft built in the past and being built now is optimized by main parameters to provide mass transportation in Russia and can compete with flexible TU-330 a/c.

One more design particularity of the aircraft should be mentioned – its engines can operate on LNG (liquefied natural gas). This prospective trend of aviation wherein Tupolev Design Bureau is absolute leader is especially actual for Russia having rich reserves of natural gas, especially in northern regions.

Activities on TU-330 a/c are performed in view of building a baseline model with structural elements which allow conversion into aircraft of different purposes and use LNG as a fuel.

According to Customer request the aircraft can be produced in following versions: refueler, ambulance a/c, hospital a/c, ecological monitoring a/c, a/c for hunting industry and fishery, icing survey, a/c for initial exploration under extraordinary conditions, fire fighting a/c, tanker to carry liquefied natural gas, repeater a/c, special administrative a/c (cabin +two motor cars) etc.

tupolev type

TU-204-100 aircraft

Mid-range aircraft is equipped with PS-90A engines. The aircraft was put in to operation in February, 1995. Currently operated by such leading Russian Airlines as “KavMinVodyAvia”, “Sibyr”, “Krasnoyarsk Airlines”. Operators appreciated highly reliability and cost efficiency of the aircraft both on domestic and international routes.

By its ecological parameters and perceivable noise data the aircraft complies completely with current and future ICAO and Eurocontrol requirements.

• TU-204|214 aircraft family

 

TU-214 aircraft

Long-range aircraft equipped with Russian PS-90A engines. The aircraft was certified in December, 2000 to Russian standards AP-25 (harmonized with foreign standards FAR-25 and JAR-25). Put in to operation in May, 2001 by “Dalavia” Airlines. Said Airlines operates TU-214 aircraft both on domestic and international routes under regular schedule. Main routes: Khabarovsk – Moscow; Khabarovsk – Soul; Khabarovsk – Inagata; Khabarovsk – Petropavlovsk –Kamchatskiy.

• TU-204|214 aircraft family

 

TU-204-120 aircraft

Mid-range aircraft TU-204-120 is equipped with Rolls-Royce RB211-535 engines. Have been successfully operated by Egypt “Air Cairo” airlines for several; years. TU-204-102 aircraft fleet performs regular flights on domestic and international routes. Main international routes are as follows: Cairo – Moscow; Cairo – Paris; Cairo – Madrid; Luxor - Paris.

Cargo version of the aircraft is operated since the year 2002 by TNT company – one of the largest cargo and mail carriers in the world. This Company expressed its intention to purchase the second aircraft.

Contract on delivery of 5 aircraft to China was signed in September, 2001; providing option for 10 airliners more both in passenger and cargo versions.

• TU-204|214 aircraft family

 

TU-334 aircraft

Short-range TU-334 aircraft is equipped with D-436T1 engines produced in co-operation by“Motor Sich”, MMPP “Salyut” and Ufa Engine Manufacturing Corporation. To customize the aircraft according to Airlines request possibility of installation of BR-715-55 (Rolls-Royce – Germany) engines and western avionics is provided.

TU-334-100 a/c was granted with a Type Certificate by Aviation Register of IAC

15 April, 2005 the Resolution of the RF Government No.217 “On Arrangement of serial production of short-range TU-334 a/c and its versions at federal state unitary enterprise “Kazan aviation corporation n.a.Gorbunov” has bee signed.

TU-204|214 AIRCRAFT FAMILY

Program on TU-204/214 a/c family

TU-204 aircraft arrangement

TU-204 is a mid-range aircraft for 210 passengers; was designed as the whole a/c family incorporating passenger, cargo, cargo-passenger and quick-change a/c. Complies completely with Russian and European Airworthiness standards, characterized by low operational cost, state-of – the - art interior, low noise level, low fuel consumption.

TU-204 layout

Engines of TU-204 a/c family: to the left RB211-5335E4, to the right - PS-90A

The aircraft is powered by PS-90A and RB211-535E4 engines. High aerodynamic efficiency of airframe combined with efficient wing extendible devices ensures efficient and safe cruising flight and landing at low speeds. Serial production is arranged at the largest Russian Aircraft Manufacturing Corporations in Ulianovsk and Kazan.

 

Characteristics of the aircraft and its versions

	TU-204-100	TU-204-120	TU-214	TU-204-300
Geometric characteristics
A/c length, m	46,0	46,0	46,0	40,0
A/c height, m	13,9	13,9	13,9	13,9
Wing span, m	42,0	42,0	42,0	42,0
Wing area, m2	184,2	184,2	184,2	184,2
Fuselage section, m	3,8 х 4,1	3,8 х 4,1	3,8 х 4,1	3,8 х 4,1
Weights
Max takeoff weight, t	103,0	103,0	110,75	107,5
Max landing weight, t	88,0	88,0	93,0	88,0
Max fuel reserve, t	32,8	32,8	35,710	36,0
Max payload, t	21,0	21,0	25,2	18,0
Passenger capacity	210	210	210	164
Flight range at max payload, km	4300	4100	4340	5800
Cruise speed, km/h	810-850	810-850	810-850	810-850
Field length, m	2250	2250	2250	2500
Engines	PS-90А	RB.211-535E4	PS-90А	ПС-90А

Passenger cabin

Length 30.18 m

Width 3.57 m

Height 2.16 m

 

Layout of passenger cabin

Different passenger cabin layouts are proposed:

Baseline variant of 210 passengers layout;

Combined layout variant (including first class and tourist class compartment;

business-class and tourist class; first class, business class and tourist class) designed for 164-193 passengers as per customer request.

Tourist class and business class compartments are provided with passenger seats of improved design according to layout 3+3, 2+2. First class compartments are provided with comfortable seats according to layout 2+2 with seat pitch equal to 810 mm.

Passenger cabin can be divided into compartments according to class with removable bulkheads and curtains. Compartments are illuminated by reflected light. Hidden luminescence lights located over and under overhead bins along sides create uniform and comfortable illumination. Overhead bins for passenger baggage and coats are of closed type. Volume of baggage overhead bins per one passenger makes 0.052 m3.

 

Aircraft certification

TU-204-100 a/c of “KrasAero” Airlines

In 1994 certificate for TU-204 a/c with PS-90A engines was issued. Each next certification is intended for extension of estimated operational conditions and improvement of a/c Type Design. That’s why in each certification only differences are certified.

TU-204-100 a/c – is TU-204 a/c version, was certified to Russian standards NLGS-3 and completely meets ICAO noise and emission requirements

TU-204-120 a/c of “Air Cairo” Airlines

TU-204-120 a/c – is TU-204 a/c version, was certified with Rolls-Royce RB211-535E4 engines, has aircraft noise type certificate in accordance with standards of Chapter 3 of Supplement 16 to ICAO, complies with all Eurocontrol and ICAO current requirements. Is currently under certification to JAA. The aircraft has cargo version which is successfully operated in Europe and Egypt.

TU-214 a/c

TU-214 a/c – is TU-204 version with increased takeoff weight. The aircraft has cargo version. The aircraft was certified to Russian standards AP-25 (harmonized with FAR-25 and JAR-25).

TU-204-300 a/c

TU-204-300 with PS-90A engines is a mid-range passenger a/c is intended to carry passengers, luggage and cargo on domestic and international trunk routes of 500 to 8500 km long . The airliner was built on the basis of TU-204-100 a/c and represents the continuation of TU-204/214 a/c family. TU-204-300 a/c performed its maiden flight 18 August, 2003. The aircraft is produced in series at “:Aviastar-SP” Closed Stock Company in Ulianovsk. Opposite to TU-204-100 the TU-204-300 a/c has a shortened fuselage (by 6 m) and increased fuel reserve. Set of equipment was updated. Improved comfort level of the cabin helps the passengers to withstand long flights. Maximal payload is cut down to 18000 kg at increased flight range.

Baseline layout of passenger cabin – three-cabin configuration is offered in three versions:

- 157 passenger economy class seats version

- 155 passenger economy class seats version

- two-class version for 142 passenger seats.

Mixed version of 142 passenger seats cabin provides 8 business-class sets (seat pitch is 1050 mm) and 134 passenger seats in economy class (seat pitch is 810 mm).

As per Customer desire the aircraft can be delivered with other layout of cabin to meet his requirements.

All seats of business class are equipped with information and entertainment systems providing watching of 4 video-channels. In the economy-class cabin video-monitors are installed at every three seat rows. Passengers will have opportunity not only to watch video-films, listen to music but also to get information on the a/c location, distance to the airport of destination and other data on the flight.

TU-204-300 passenger cabin design is characterized by possibility to convert the airliner from one version to other in short time in the airport.

The aircraft is provided with two pressurized cargo-luggage compartments. Volume of the forward cargo-luggage compartment is equal to 7.4 m3, of rear one – 20.4 m3.

The flight crew size is 3 persons. Further TU-204-300 two-member crew version is scheduled to be produced. 5 to 8 seats are provided for attendants.

Service range depending on payload at accepted fuel reserves is equal to following: at max payload of 18000 kg – 5800 km, at payload of 13500 kg – 7500 km. The values are given for maximal take-off weight of 105000 kg, flight level 10100 – 11600 m and M=0.76-0.78.

 

TU-134 AIRCRAFT FAMILY

 

TU-134A

Short­range jet aircraft TU­134 became one of the most successful projects in passenger aircraft building. TU­134 a/c entered history of Russian civil aviation as the most popular aircraft. TU­134 – is the first native passenger airliner which was certified to English standards of airworthiness.

Totally 852 a/c were produced in various versions: TU­134, TU­134A, TU­134B, TU­134 UB­L, TU­134Sh. Versions appeared with decreased crew size, increased passenger capacity, improved economic indices, etc. Furthermore basing on TU­134 a/c flying laboratory was designed to develop new prototypes of aircraft and space equipment.

Currently several hundreds of TU­134 a/c are being in operation in Russia and abroad. Our Company is busy with upgrading of the aircraft, extending service life, providing with advanced airborne equipment and avionics. VIP­class modernization is very popular.

Characteristics of the aircraft (Data for the model TU­134А)
Passenger capacity - ­ 76
Fuselage diameter - ­ 2,9 m
Aircraft length - ­ 37,1 m
Wing span - ­ 29,0 m
Aircraft height - ­ 9,02 m
Maximal Take­off weight - ­ 47,6 t
Payload - ­ 8,2 t
Cruise speed - ­ 850 – 900 km/h
Flight range - ­ 2000 km
First flight - ­ 1963

TU-154 AIRCRAFT FAMILY

TU-154

TU­154 is a passenger aircraft designed for medium range flights. Along with TU­134 a/c is main air carrier in Russia for several decades. Hundreds of these aircraft are still being successfully operated in other countries as well.

Tоday our company pays serious attention to TU­154 a/c fleet support. In view of the recent requirements the aircraft is being upgraded regarding systems and interiors. VIP cabin version has been developed.

For the time being more than 900 TU­154 a/c has been produced. The most successful among mass version became TU­154M modification which economic indices were substantially improved due to more efficient engines, improved local aerodynamics and new powerplant.

TU-154M

Characteristics of the aircraft (Data for the model TU­154М)
Passenger capacity - ­ 164 – 180
Fuselage diameter - ­ 3,8 m
Aircraft length - ­ 48 m
Wing span - ­ 37,5 m
Aircraft height - ­ 11,4 m
Maximal Take­off weight - ­ 104 t
Payload - ­ 18 t
Cruise speed - ­ 850 – 900 km/h
Flight range - ­ 4000 km
First flight of TU­154 - ­ 1968
First flight of TU­154M - ­ 1984