the first ansat flight was on aug. 17, 1999. on 14 …optimized for use as a taxi, tour, offshore or...
TRANSCRIPT
Design work on the Ansat helicopter began at Kazan in 1993, with structural
strength and aerodynamic calculations subcontracted to Kazan State
Technical University, production of the rotor to Aviation Scientific Co. and
transmission to Aeromechanica Co.
The first Ansat flight was on Aug. 17, 1999. On 14 September 2001, Ansat
became the winner of a competition to supply 100 training helicopters to
Russian armed forces by 2015. “Ansat” name in Tatar language can be
translated as “easy or light”
Optimized for aerodynamic efficiency and survivability in case of
emergency landing (1m/s power-off touchdown speed) and with off-base
routine maintenance. Ansat features traditional metal structure for simplicity
and reliability. Meets FAR PT. 29 Category A and Russian AP-29 requirements
1. Equipped with shock absorbing seats for passengers. Conventional
configuration high mounted tail boom carrying fixed horizontal
stabilizer and two fins, two turbo-shaft power plants above the cabin
2. A fiberglass torsion bar with four main blades and a two-blade tail rotor
3. Two-stage, VR-23 main rotor reduction gear in magnesium case on
front of the engines; ratio 16.4; rotation speed 365.4 rpm; blade tip
speed 220m/s
4. Transmission rating 769kW
5. Tail rotor speed 2,000 rpm via single stage conical gearbox
6. Rotor brake
7. Manual blade –folding and main rotor aero foil section NACA 23012
Landing Gear:
Twin skids with Kazan transverse shock absorbers; tail bumper to
protect anti-torque rotor
Optional; tricycle configuration, with Yaroslav tyres and Gidroagregat
brakes
Optional emergency signalization system
Powerplant:
Two PRATT & WHITNEY P&W PW 207K turbo shaft engines each rated at
470kW for T- O, 410kW max continuous, 529kW for 30 s, 470kW
continuous OEI and 491kW, 2 minutes OEI. FADEC standard
Fuel Capacity:
700 liters either in external tanks or under floor fuel tanks. Optional
internal fuel-tank
Accomodation:
Up to 11 person, including one or two pilots, on energy-absorbing
seats; or two stretcher patients and three attendants; or internal or
externally slung freight
Two forward-hinged doors on each side of flight deck; two horizontally
divided doors on each side of cabin, baggage bay behind cabin, with
rear-facing door
Baggage door is also used for loading stretchers in medical variant
Cabin is ventilated and heated, air conditioning is optional
Avionic Systems:
Avionika FBW controls quadruple electronic system and duble
hydraulic system
Automatic flight control is standard on all piloting functions and
optional on navigation functions with KSU-A digital control system
Main transmission drives two alternators (each 200V, 400Hz), two
generators (each 27V), two fans and two hydraulic fuel pumps for
separate systems
Electrical system 27V, with battery, optional AC system is with second
battery
Electric de-icing optional
Option Equipment:
Rescue hoist
cargo tight ups
IRF
Radar:
Provision for it is in the nosecone
Operation Use:
Rescue, ambulance, firefighting, agriculture, police, TV, and military
Basic:
Optimized for transportation of passengers, or as an ambulance, S&R,
training, patrol and for other duties
Provision for the attachment of extra fuel tanks to the sides of the
cabin
Passenger modification can carry up to 10 passengers plus 1 pilot
Optimized for use as a Taxi, Tour, Offshore or Corporate helicopter
Transport:
Removed seats and additional tie down points the helicopter can
carry 1,000 kg of cargo inside the cabin, and 1,200 kg on external sling
The most spacious cabin in its category (6.7 m3)
Optimized for use as a Agriculture, Flying or Firefighting helicopter
"U Training":
Optimized for training includes dual controls system and three wheel
landing gear
Can be used for training of aviation cadets and civil persons, as well as
for pilot retraining
With the installation of two gas turbine engines and reliability of the
main helicopter components this variant can provide the highest
safety standard that is required for training flights
The only Russian helicopter equipped with digital fly-by-wire control
system (KSU-A), which allows simulation of the required engine shut off
training mode, without actually switching the engines off
AG Inspection:
Special version designed for Gazprom pipeline inspection.
Observation:
Prototype of scout helicopter based on the Ansat was first shown at
Moscow Aerosalon in August 2001, with GOES 521 turret in nose and
optical sensors developed by Optooil ZAO
Load-Carrying Capacity:
In Cargo:
---
On External Sling:
---
Crusing Speed:
250 km/h
Ceiling Under ISA Conditions:
Hovering OGE (min):
3300 m
Service (min):
5700 m
Powerplant: PW-207K
Fuel Consumption:
0.21 kg/hp*h
Service Life:
1500 h
Power:
2200 h.p.
Range:
With Max. Fuel:
635 km
Maximum Flight Duration:
3h
Performance
Max. speed 275 km/h
Cruise speed 220 km/h
Max. flight range with main fuel tanks 515 km
Operational ceiling 4800 m
Hover ceiling (OGE) 2500 m
Weight Parameters
Max. take-off weight 3600 kg
Max. payload in transport cabin 1234 kg
GT engines (2хPW207K, Pratt&Whitney)
Take-off power 630 h. p.
Contingency power 710 h. p.
Cabin Dimensions
Length 5,700 mm
Width 1770 mm
Height 1370 mm
Volume 8.0 m3
Capacity
Aircrew 1–2
Passengers 7+1
Take-off Weight:
Normal:
3000 kg
Maximum:
3300 kg
Empty Weight:
---
Cargo Compartment Dimensions:
Lenth:
3.15m
Height:
1.3m
Width:
1.68m
Dimensions of Airframe:
Lenth:
11.8m
Height:
3.5m
Width:
2.4m
Diameter of Main Rotor:
---
Number of Blades:
Main Rotor:
4
Crew:
2
Passengers:
Seated:
9 (airline)
VIP:
4 to 6 (airline)
Operational Activities:
Border Patrol
External Sling Load
Internal Cargo
Medical
Military
Offshore Transport
Passenger Transport
SAR
Training
VIP
