Derived from the Dhruv helicopter; the Light Combat Helicopter uses the same rotor system, Integrated Dynamic System (IDS), transmission system, basic electrical line replaceable units (such as DC and AC power generating systems, indicators, battery junction box, control grips and fire detection systems) and avionic line replaceable units (i.e. communication system, cockpit voice and flight data recorders).

The most obvious changes from the Dhruv helicopter are the tandem seating, flat cockpit transparencies (to reduced glint/reflection), flat faceted fuselage panels of radar absorbing materials, pressurized cockpit cabin, armor panels, and IR engine suppressors.  The cockpit is compatible with night vision goggles.

The LCH equipment includes rockets, air-to-air and air-to-ground anti-radar missiles, iron and cluster bombs, and the nose-mounted turret gun.  The armament load is 1,000 kg.  The LCH is also capable of flying angles of 70-80 degrees nose down.


Data on design, manufacture and status

Design authority: Hindustan Aeronautics Limited

Primary manufacturer: Hindustan Aeronautics Limited

Parent type: No type defined

Aircraft status: In development


Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 2

Crew seating: Tandem

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Stub wing span: 4.00 m

Overall Dimensions
Overall Height:  
Overall Length: 15.86 m 52.0 ft
Overall Width: 13.20 m 43.3 ft
Airframe Dimensions
Airframe Length: 13.80 m 45.3 ft
Airframe Width:  
Airframe Height:  
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track: 2.30 m 7.5 ft
Cabin Dimensions
Cabin Internal Height:  
Cabin Internal Length:  
Cabin Internal Width:  

Weights and Performance

Data on aircraft weight and flight characteristics

Max Cruising Speed: 268 km/h; Max Oblique rate-of-climb: 12 m/s; Range (with drop tanks): 750 km

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: 2,250 kg 4,960 lb
Useful Load: 3,550 kg 7,826 lb
Empty Weight Fraction: 0.388
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Max Level Flight Speed:  
Never Exceed Speed: 330 km/h 178 kts
Service Ceiling: 6,500 m 21,325 ft
Range and Endurance
Max Range: 550 km 297 nm
Max Endurance:  

Engine Details

Aircraft powerplant (lift and/or propulsion)

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

Number of engines: 2
Normal Ratings
Max continuous:  
Take-off / rated:  
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
Direction of Rotation: Clockwise
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
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
Configuration: Pusher
Direction of Rotation: Unknown
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction:  
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

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Related Public Resources

Resources related to the LCH , provided by public sources across the internet.