Vertipedia - HAL ALH Dhruv Mark II

The Advanced Light Helicopter Dhruv Mark II features an Integrated Architecture and Display System (IADS) glass cockpit developed with IAI (Lahav Division) to integrate all the avionics, weapons and mission systems. Fuel capacity, useful load and under slung load are 1055 kg, 2100 kg and 1500 kg, respectively.

Overview

Data on design, manufacture and status

Design authority: Hindustan Aeronautics Limited

Primary manufacturer: Hindustan Aeronautics Limited

Parent type: HAL Dhruv

Aircraft status: Status unknown

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 1-2 in Side-by-side arrangement

Landing gear: Skids

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

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
Max Gross Weight (ground):	5,500 kg	12,125 lb
Max Gross Weight (airborne):
Max Take-off Weight:	5,500 kg	12,125 lb
Empty Weight:	2,744 kg	6,049 lb

Climb Performance
Max Rate of Climb:

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:

Limitations
Max Level Flight Speed:
Never Exceed Speed:	292 km/h	158 kts
Service Ceiling:	6,500 m	21,325 ft

Range and Endurance
Max Range:	640 km	346 nm
Max Endurance:	4 hrs

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

Powerplant
Number of engines:	2
Designation:	Turbomeca TM 333 2B2 turbine
Manufacturer:	Turbomeca

Normal Ratings
Max continuous:	736 kW	987 hp
Take-off / rated:	825 kW	1106 hp
Intermediate:
Maximum:

OEI Ratings
OEI contingency:	841 kW	1127 hp
OEI continuous:	807 kW	1082 hp
OEI 30-second:	910 kW	1220 hp
OEI intermediate:	807 kW	1082 hp

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:	40.19 kg/m²	8.232 lb/ft²
Solidity:

Main Rotor Blade Derived Characteristics
Blade area per blade:
Tip Speed:

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):

References

References and sources used

HAL Dhruv

Hindustan Aeronautics Limited
14 June 2017
Website

Hindustan Aeronautics Limited

Hindustan Aeronautics Limited
14 June 2017
Website

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Images

Layout

Attribution

Number of engines:	2 Turbines
Max Level Flight Speed:
Max Range:	640 km	346 nm
Max Endurance:	4 hrs	4 hrs

Main Rotor Diameter:	13.20 m	43.31 ft
Max Gross Weight (ground):	5,500 kg	12,125 lb