Equipped with Shakti engines, the Advanced/Armed Light Helicopter Dhruv Mark IV  Weapon System Integrated (WSI) variant features all that the Mark III does: a second generation Active Vibration Control System (AVCS) with bi-axial force generators. The helicopter has armor protection against 12.7 mm rounds.

A variant of the Mark III WSI, the Rudra (Mark IV) is equipped with the now deployable: 20 mm nose-mounted turret gun (by Nexter in France); rocket launcher (FZ, Belgium); air-to-air missiles (MBDA, Fance); and air-to-ground missiles.  Targeting systems for both day and night include electro-optical pod (Elop, Israel) and Helmet Pointing System (Elbit, Israel). The aircraft can be fitted with an electronic warfare suite (Avitronics, South Africa), flare/chaff dispensers (BDL, India) and an IR jammer.

Fuel capacity of the aircraft is 1055 kg; seating capacity is 12-14 passengers in addition to the crew.

Overview

Data on design, manufacture and status

Design authority: Hindustan Aeronautics Limited

Primary manufacturer: Hindustan Aeronautics Limited

Parent type: HAL Dhruv

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 1-2

Crew seating: Side-by-side

Landing gear: Skids

Layout and Dimensions

Data on aircraft size

Composite material air frame.

Overall Dimensions
Overall Height: 4.98 m 16.3 ft
Overall Length: 15.87 m 52.1 ft
Overall Width: 13.20 m 43.3 ft
Airframe Dimensions
Airframe Length:  
Airframe Width:  
Airframe Height:  
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height:  
Cabin Internal Length:  
Cabin Internal Width:  

Weights and Performance

Data on aircraft weight and flight characteristics

Weights
Max Gross Weight (ground): 5,800 kg 12,787 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 5,800 kg 12,787 lb
Empty Weight:  
Useful Load:  
Empty Weight Fraction:  
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed:  
Never Exceed Speed: 285 km/h 154 kts
Service Ceiling: 6,000 m 19,685 ft
Range and Endurance
Max Range: 640 km 346 nm
Max Endurance: 4 hrs 4 hrs

Engine Details

Aircraft powerplant (lift and/or propulsion)

Provided powerplant data is for uninstalled, sea level, static operations.

Powerplant
Number of engines: 2
Designation: HAL Shakti turbine
Manufacturer: Hindustan Aeronautics Limited (Engine)
Normal Ratings
Max continuous:  
Take-off / rated:  
Intermediate:  
Maximum: 899 kW 1205 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Main Rotor Characteristics
Diameter: 13.20 m 43.31 ft
RPM:  
Direction of Rotation: Unknown
Hub Type: Hingeless
Main Rotor Blade Characteristics
Blade Construction: Composite
Blade Chord:  
Blade Tip Geometry:
Blade Twist:  
Number of Blades: 4
Main Rotor Derived Characteristics
Disc Area: 136.85 m² 1473.1 ft²
Disc Loading: 42.38 kg/m² 8.681 lb/ft²
Solidity:  
Main Rotor Blade Derived Characteristics
Blade area per blade:  
Tip Speed:  

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Diameter:  
Configuration: Unknown
Direction of Rotation: Unknown
RPM:  
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction: Composite
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Solidity:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

Related VFS Resources

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Related Public Resources

Resources related to the ALH Dhruv Mark IV (Rudra), provided by public sources across the internet.

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