Su-80GP
|
|
|||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
) |
|||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
) |
|||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
)
Cargo and passenger aircraft.
The Su-80GP multifunctional aircraft is being developed by the Sukhoi Design Bureau in cooperation with the Komsomolsk-on-Amur Aircraft Production Association. The plane is to be op-erated by commuter and regional airlines and can be employed for a wide array of purposes in the national economy.
High efficiency of passenger and cargo transportation at minimum expenditures;
Self-sufficient operation from unprepared airfields with short and rough strips, with main-tenance and repair costs minimised;
Wide range of operational conditions ,ground-level temperatures varying from -50°С to +45°C, round-the-clock,all-weather capability.
High reliability and long service life of the aircraft determined by introduction of design and technological improvements;
Development of specialised derivatives with conversion costs minimised.
The options include:
- passenger aircraft for commuter and regional operations;
- tactical military transport;
- patrol/transportation aircraft;
- special ambulance aircraft;
- airborne relay aircraft;
- navigation trainer.
Compliance with the AP-25 and FAR-25 standards..
VARIANTS AND VERSIONS
Su-80GP cargo/passenger aircraft
The Su-80GP aircraft is designed to airlift 30 passengers and cargoes on commuter and regional routes. The design of the aircraft enables rapid conversion of the interior compartment providing passengers with adequate level of comfort. The cargo ramp in the rear fuselage is used to board passengers and load/unload cargoes. Detachable roller conveyer is attached to the com-partment floor and ramp to facilitate loading and unloading operations.
Su-80P passenger aircraft
The Su-80P aircraft is used to airlift 30 passengers on commuter and regional routes. The plane differs from the Su-80GP baseline version in that it offers a more comfortable passenger compartment.
AIRCRAFT DESIGN
The Su-80 is a conventional, high-wing, twin-boom aircraft. The high-aspect-ratio wing features high lift devices. The empennage is made up with two vertical tail surfaces with bridging horizontal surface. The air-tight fuselage is of an independent-module design and is attached with tailbooms by the wing and pylon surfaces between each tailboom and rear fuselage. The booms house engines and main undercarriage. The plane features retractable tricycle landing gear with a nose strut. The cargo ramp in the rear fuselage is used to board passengers and load/unload car-goes. In addition, the fuselage is fitted with a crew access door and emergency exit hatches as de-termined by the FAR-25 and AP-25 standards. The principal structural materials are the 1163, V95pch, AK4-1, ON4, VT-20, VT6, 30KhGSN2A, 0KhGSA, VNS-5, 12x18 alloys and the KMU composite material.
| Materials usage ratio: | |
| Aluminium alloys | 69-71% |
| Structural steel | 4-6% |
| Non-corrosive steel | 2-3% |
| Titanium alloys | 4-6% |
| Other metals | 0.5% |
| Composite materials | 7-9% |
| Other non-metals | 5-7% |
AVIONICS
The flight-control and navigation equipment of the Su-80GP aircraft employs cutting-edge components and uses satellite navigation data. A special emphasis has been put on economical efficiency and operational safety of the two-seat aircraft.
Avionics can be custom-made.
The flight-control and navigation equipment provides for:
- automatic, flight-director and manual operation,and optimisation of routing, while meeting standard navigation requirements in any geographical environment at day and night, in all weathers and at all flight stages;
- manual, automatic and flight-director final approach under ICAO Grade II meteorological minimal down to 60 m, as well as final approach to unequipped airfields down to 60-100 m with subsequent landing;
- automatic operation at ranges of up to 3,600 km, altitudes mounting up to 8,000 m and speed up to 600 km/h.
Navigation suite components:
- SSI-80 aerial navigation and indication system;
- SBKV-P strapdown heading and attitude system;
- SVS-80 aerial signals system;
- backup devices;
- air data probes.
Navigation, landing and air traffic control radio engineering equipment comprises:
- ARK-M automatic radio compass;
- A-076 radio altitude-sensing and speed-measuring system;
- VIM-95C (VOR/ILS/SP/MRK)navigation and landing equipment;
- VND-94S (DME)radio range-finder;
- SO-94R (UVD)radar responder;
- 4205 airborne national identification responder;
- RSBN-85C meteorological short-range navigation system;
- aerial feeder devices.
Navigation and display system is designed to receive process and visualize piloting, command and control data fed by navigation assets of the aircraft; it is also used to control opera-tion of radio equipment both in automatic and manual mode, warn of failures and record actions performed by the pilots in this regard.
The piloting system and display set comprise:
- two digital computers;
- two PUI-80 indicator display control units;
- five keypad MFD multifunctional displays;
- two display driver units;
- built-in NAVSTAR-GLONASS satellite navigation system;
- data input unit.
The radio communications equipment of the aircraft is used to provide:
- two-way simplex radio and phone communications in VHF and HF bands within radio visibil-ity range between the aircraft and the ground-based air traffic control stations, as well as beyond the radio horizon at ranges of up to 1,500 m;
- interphone and phone communications between the crew and ground-based personnel;
- public address system in the passenger compartment;
- voice notification of pilots and ground-based personnel about emergency situations onboard the aircraft; voice information on the status of the onboard systems and warning signals from avionics.
The radio communications assets comprise:
- two Yurok VHF radios;
- two R-805KZ HF radios;
- Izumrud intercom, switching and control system comprising two integrated radio control units;
- ARO-28S public address system;
- AB-2 phone with KS-20 cable used by attendants;
- R-855A1 VHF emergency radio powered with the Priboi-2S battery;
- ARB-PK portable emergency radio buoy operating in VHF-UHF bands;
- EM-6 electric megaphone.
Rescue radio communications equipment is designed to:
- identify aircraft in distress, determine their coordinates and supply the data to rescue ser-vices;
- maintain communications with rescue services fixed-wing and rotary-wing aircraft and lead them to the site;
- provide speakerphone communications with passengers and enable the crew to give com-mands in open air.
The avionics suite also comprises the RPI-1 flight data recorder.
The engines feature a mechanical cable control system.
Engine specifications (H=0,M=0)
| Mode | Rate,hp h.p. | Specific fuel consumption g/(h.hp) |
| Max takeoff, | ||
| single engine failure | 1,870 | |
| Normal takeoff | 1,750 | 211 |
| Max continuous | 1,750 | 211 |
| Max cruise | 1,510 | 217 |
The Su-80 aircraft employs four-blade variable-pitch propellers, diameter 3.35 m, used to attain thrust reversing to diminishing the roll and perform emergency feathering.
The propellers are fitted with a de-icing system.
Propeller phase synchronisation mode is to be employed at cruising flights to muffle noise in the passenger compartment.
AIRCRAFT CONTROL SYSTEM
The principal roll, pitch and yaw control system is designed mechanical and redundant. Since no hydraulic servos are employed, control surfaces are actuated with pushrods and cables. Controls and instrumentation are accommodated in the cockpit. Ailerons and rudders mount electri-cally-operated trimmers and balancing tabs. The elevator trimming tab is mechanically-operated.
The elevator is fitted with a balancing tab.
Wing high lift devices comprise Fowler-type single-slotted flaps actuated by electric jacks. Flap angle is 150, at takeoff and 400 at landing.
The aircraft is also fitted with a two-channel digital-to-analog automatic flight control sys-tem.
ELECTRICAL GENERATING SYSTEM
The system is used to power radio and electronic equipment, external lighting equipment, lighting equipment in the cockpit and passenger compartment, de-icing system, etc.
The principal power supply units are:
- two Auxilec starter generators, 27V, 12kW;
- two Auxilec alternating current generators, 115/200V, 320-1,050 Hz, 40 kVA;
- two PTS-2500 converters, 115/200V, 400 Hz
- two Varta batteries are provided for backup.
HYDRAULIC SYSTEM
Hydraulic system consists of the main and backup loops used to operate:
Main loop:
- landing gear deployment and retraction system;
- steering and damping control system of the nose strut;
- cargo ramp control system;
- main braking system;
- automatic roll control spoiler deployment and retraction system.
Backup loop:
- emergency braking system;
- backup cargo ramp control system;
- parking wheels braking.
The pump station is the principal power-supply device used to maintain pressure of 204 kg/cm2.
Emergency landing gear deployment is performed by the pneumatic system.
The overall capacity of the system mounts up to 28 liters.
FUEL SYSTEM
The fuel system of the Su-80 aircraft is used to supply fuel to the power plant in any op-erational mode and in all types of operating conditions.
Fuel is accommodated in two wing caisson tanks, with fuel consumed compartments separated by pressure wing ribs.
| Fuel tanks capacity | |
| Total fuel | 2 x 1,515 l |
| fuel consumed compartments | 2 x 346 l |
Both single-point pressure and gravity fuelling modes can be employed.
Types of fuel cleared for consumption by the aircraft:
- JET A,JET A1 and JET B (ASTM D1655)
- JP-5 and JP-4 (MIL-T-5624)
- JP-8 (MIL-T-83133)
- RT (GOST 16565)
- TS-1 (GOST 10227).
DE-ICING SYSTEM
The aircraft mounts the BFGoodrich automatic pneumatic de-icing system to dispose of ice on:
- wing leading edge;
- fin leading edge;
- tailplane leading edge.
The British-produced Aerospace Composite Technologies LTD electrothermal de-icing system is used to remove ice from air intakes. Propellers feature an electrothermal self-contained de-icing system.
In addition, the aircraft is equipped with a windshield glazing and airspeed head de-icing system.
LIFE SUPPORT SYSTEM
The air conditioning system is used to maintain the required microclimate in the cockpit and the passenger compartment at all stages of the flight.
The system is designed for:
- engines air bleed and processing;
- automatic pre-programmed pressure control in the air-tight cockpit, including after the main system ’s failure;
- automatic adjust of temperature and air flows in the cockpit;
- cockpit windshield air heating.
The plane mounts oxygen-feed equipment to be used by pilots and passengers in emer-gency situations.
SU-80 is fitted with:
- fire-fighting equipment;
- household and rescue assets;
- water-supply and waste disposal system;
- external and internal lighting devices.
TECHNICAL MAINTENANCE SYSTEM
The technical maintenance system of the Su-80 aircraft has been developed with due consideration for the plane ’s operational modes:
- self-contained operation during 50 flight hours or 15 days in case the plane operates from unequipped airfields;
- high-and low-intensity operation;
- permanent operational readiness, minimum reaction time.
The technical maintenance and on-condition repair strategy ensures operational prepar-edness of aircraft and reduces maintenance costs.
The technical maintenance system provides for on-condition and regular repairs.
On-condition repairs are to be carried out prior to flight and after landing (Form A); these provide for basic services (Form B)rendered after 50 flight hours or 30 days of employment .
Regular repairs are to be conducted at base airfields in the course of the aircraft employ-ment, Form F1 (500 flight hours at least once a year),Form F2 (1,000 flight hours or two years of employment)and Form F3 (5,000 flight hours or seven years of employment).
The maintenance control concept provides for extensive employment of airborne monitor-ing assets based on built-in test facilities.
Additional materials about this theme:
Phone: +7 (4217) 52-39-59
E-mail: opgt@knaapo.com