Helicopters used by India!!! A Discussion
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Zebra
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Bell 407 AH ,
Specifications
Speeds at max gross wt
Vne 140 kts 259 kph
Max cruise¹ 133 kts 246 kph
Range at VLRC¹ 330 nm 611 km
Max endurance¹ 3.8 hrs
Capacities
Standard seating 1 + 6
Maximum seating 1 + 6
Standard fuel 127.8 US gal 484 liters
Aux fuel 19 US gal 72 liters
Cabin Volume 85 ft³ 2.4 m³
Baggage Compartment Volume 16 ft³ 0.45 m³
Weights
Empty wt 2,668 lbs 1,210 kg
Std internal gross wt 5,000 lbs 2,268 kg
Optional internal gross wt 5,250 lbs 2,381 kg
External gross wt 6,000 lbs 2,722 kg
Useful load, standard 2,332 lbs 1,058 kg
Useful load, optional 2,582 lbs 1,171 kg
Max ext load (cargo hook limit) 2,646 lbs 1,200 kg
¹Std Max GW, ISA, Std fuel - no reserve @ sea level
Standard Specifications
- First Bell qualified armed/weaponized commercial helicopter
- Configurable for multiple weapons and surveillance packages including Mini-guns, rocket pods, FLIR and NVG capabilities
- Safety features include a rupture resistant fuel system, engine exceedence monitoring and a collective mounted throttle that keeps power at the pilot's fingertips
- Available suite of ASE (Aircraft Survivability Equipment)
World-Class Customer Support and Services the World Over
Every Bell Helicopter is backed by around-the-clock, award winning customer support. Bell Helicopter's comprehensive, global service network is rated #1 in the industry. On every continent, in every region, we stand behind each aircraft with the expertise, parts and service needed to meet your mission requirements.
Specifications
Specifications
Speeds at max gross wt
Vne 140 kts 259 kph
Max cruise¹ 133 kts 246 kph
Range at VLRC¹ 330 nm 611 km
Max endurance¹ 3.8 hrs
Capacities
Standard seating 1 + 6
Maximum seating 1 + 6
Standard fuel 127.8 US gal 484 liters
Aux fuel 19 US gal 72 liters
Cabin Volume 85 ft³ 2.4 m³
Baggage Compartment Volume 16 ft³ 0.45 m³
Weights
Empty wt 2,668 lbs 1,210 kg
Std internal gross wt 5,000 lbs 2,268 kg
Optional internal gross wt 5,250 lbs 2,381 kg
External gross wt 6,000 lbs 2,722 kg
Useful load, standard 2,332 lbs 1,058 kg
Useful load, optional 2,582 lbs 1,171 kg
Max ext load (cargo hook limit) 2,646 lbs 1,200 kg
¹Std Max GW, ISA, Std fuel - no reserve @ sea level
Standard Specifications
- First Bell qualified armed/weaponized commercial helicopter
- Configurable for multiple weapons and surveillance packages including Mini-guns, rocket pods, FLIR and NVG capabilities
- Safety features include a rupture resistant fuel system, engine exceedence monitoring and a collective mounted throttle that keeps power at the pilot's fingertips
- Available suite of ASE (Aircraft Survivability Equipment)
World-Class Customer Support and Services the World Over
Every Bell Helicopter is backed by around-the-clock, award winning customer support. Bell Helicopter's comprehensive, global service network is rated #1 in the industry. On every continent, in every region, we stand behind each aircraft with the expertise, parts and service needed to meet your mission requirements.
Specifications
SPIEZ
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The Bell helo already lost the competition.
bhramos
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Blackwater
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Here is a list of the Helicopters used by India. Both Indian Air Force, Indian Army!
1) HAL DHRUV
ARMY ~ 45
AIR FORCE ~ 37
Dhruv based threads
http://defenceforumindia.com/defence-industry/19924-siachen-dhruv-proves-world-beater.html
http://defenceforumindia.com/indian-air-force/3144-alh-dhruv.html
http://defenceforumindia.com/military-multimedia/11796-exclusive-videos-weaponised-alh-dhruv-firing-trials.html
General characteristics
Performance
- Crew: 1 or 2 pilots
- Capacity: 4–12 passengers
- Length: 15.87 m (52 ft 0.8 in)
- Rotor diameter: 13.20 m (43 ft 3.7 in)
- Height: 4.98 m (16 ft 4.06 in)
- Disc area: 137 m² (1,472 ft²)
- Empty weight: 2,502 kg (5,515 lb)
- Useful load: 2,600 kg (5731 lb)
- Max takeoff weight: 5,500 kg (12,125 lb)
- Powerplant: 2 × Shakti turboshafts, 1,000 kW (1,400 shp[SUP][112][/SUP])
Alternate engine: 2x Turbomeca TM 333-2B2 turboshaft, 746 kW (1,000 shp) each
Armament
- Maximum speed: 290 km/h (180 mph, 156.58 kn)
- Combat radius: 320 km (200 mi, 175 nmi)
- Ferry range: 827 km (516 mi, 447 nmi)
- Service ceiling: 8,382 m (27,500 ft)
- Rate of climb: 8.9 m/s (1,771 ft/min)
- Power/mass: 329.73 W/kg (0.20 hp/lb)
- Missiles:
- 8 Anti-tank guided missiles
- 4 Air-to-air missiles
- 4 x 68 mm Rocket Pods (Air-Force & Army)
- 2 Torpedoes
- Depth charges or Anti-ship missiles
Note : the Weapon system integration is still in progress and not operational
DHRUV SALIENT FEATURES
In October 2007, a Dhruv Mk.3 flew to an altitude of 27,500 feet (8,400 m) in Siachen;two years earlier a HAL Cheetah (the HAL Cheetah powered by the Shakti engine) had set a world altitude record, landing at 25,150 feet (7,670 m) on Sasar Kangi peak in Siachen
Bangalore ALH pilots fly high - Times Of India
why the pilot inside is firangi??????
Blackwater
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Interestingly begger pakis already using these birds and we despite of money still testing ita) Eurocopter AS550 Fennec
General characteristics
Performance
- Crew: 2
- Capacity: 4 passengers
- Length: 10.93 m (35 ft 10 in) (fuselage length), 12.94 m (42 ft 6 in) (overall length, rotors turning)
- Height: 3.34 m (10 ft 11 in)
- Empty weight: 1,220 kg (2,690 lb)
- Max takeoff weight: 2,250 kg (4,960 lb)
- Fuel capacity: 540 L (143 US Gal)
- Powerplant: 1 × Turbomeca Arriel 2B turboshaft, 632 kW (847 shp) (limited to 500 kW (671 shp for take-off)
- Main rotor diameter: 10.69 m (35 ft 1 in)
- Main rotor area: 89.75 m[SUP]2[/SUP] (966.1 sq ft)
Armament
- Maximum speed: 246 km/h (153 mph; 133 kn) (max cruise)
- Never exceed speed: 287 km/h (178 mph; 155 kn)
- Range: 648 km (403 mi; 350 nmi)
- Service ceiling: 5,280 m (17,323 ft)
- Rate of climb: 10.30 m/s (2,028 ft/min)
- Provision for:
- 20 mm Giat M621 cannon
- Fabrique Nationale de Herstal twin 7.62 mm or 12.7 mm machine gun pods
- 7 x 2.75in Forges de Zeebrugge or 12 x 68 mm Thales Brandt rockets
- BGM-71 TOW anti-tank missiles
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Vip Visitor flying it for evalution at Aero-India..
Zebra
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Helicopters MD-520N .....
Country of origin : United States of America
Powerplants : One 280kW (375shp) Rolls-Royce 250-C20R turboshaft driving a five blade main rotor.
Performance : Max cruising speed at S/L 250km/h (135kt). Initial rate of climb 1850ft/min. Service ceiling 14,175ft. Hovering ceiling in ground effect 11,200ft, out of ground effect 6000ft. Range at S/L 424km (229nm). Endurance at S/L 2hr 24min.
Weights : Empty 742kg (1636lb), max takeoff 1520kg (3350lb), or 1745kg (3850lb) with an external sling load.
Dimensions : Rotor diameter 8.33m (27ft 4in), length overall rotor turning 9.78m (33ft 2in), fuselage length 7.77m (25ft 6in), height with standard skids 2.74m (9ft 0in), height with extended skids 3.01m (9ft 11in). Rotor disc area 54.5m2 (586.8sq ft).
Capacity : Standard seating for pilot and four passengers, with pilot and passenger on front bucket seats, and three passengers on rear bench seat.
Type : Light utility helicopter
History : The MD Helicopters MD-520N introduced a revolutionary advance in helicopter design as it dispensed with a conventional tail rotor in favour of the Hughes/McDonnell Douglas' developed NOTAR (NO TAil Rotor) system.
Development of the revolutionary NOTAR system dates back to late 1975 when Hughes engineers began initial concept development work. In December 1981 Hughes flew an OH-6A fitted with NOTAR for the first time. This prototype was modified several times, notably in 1985 when it was fitted with the more streamlined MD-500E forward fuselage, an Allison 250-C20B turboshaft, a second blowing slot and a new fan. By then Hughes had become McDonnell Douglas.
Although the concept, which uses the Coanda effect, took some time to refine, the NOTAR system is simple in theory and works to provide directional control the same way a wing develops lift. Low pressure air is forced through two slots on the right side of the tailboom, causing the downwash from the main rotor to hug the tailboom, producing lift, and thus a measure of directional control. This is augmented by a direct jet thruster and vertical stabilisers.
NOTAR system benefits include far lower external noise (the MD-520N is the quietest certificated helicopter in the world), increased safety due to the lack of a tail rotor, improved handling and performance, reduced vibration and easier maintainability.
McDonnell Douglas originally intended to develop the standard MD-520N alongside the more powerful hot and high optimised MD-530N (both were launched in January 1989 and were based on the conventional MD-500E). The MD-530N was the first to fly, on December 29 1989, the MD-520N first flew on May 1 1990. Development of the MD-530N was suspended when McDonnell Douglas decided that the MD-520N met most customer requirements for the 530N. Certification for the MD-520N was awarded on September 13 1991, and the first was delivered on December 31 that year.
Following the 1997 Boeing/McDonnell Douglas merger, Boeing sold the former MD civil helicopter lines to MD Helicopters in early 1999.
At the 2000 Farnborough Airshow MD Helicopters announced enhancements to the MD-520N including an improved Rolls-Royce 250-C20R+ engine with 3-5% more power for better performance on warm days, and, with changes to the diffuser and fan rigging, increased range and payload capability.
MD Helicopters MD-520N | Airliners.net
Country of origin : United States of America
Powerplants : One 280kW (375shp) Rolls-Royce 250-C20R turboshaft driving a five blade main rotor.
Performance : Max cruising speed at S/L 250km/h (135kt). Initial rate of climb 1850ft/min. Service ceiling 14,175ft. Hovering ceiling in ground effect 11,200ft, out of ground effect 6000ft. Range at S/L 424km (229nm). Endurance at S/L 2hr 24min.
Weights : Empty 742kg (1636lb), max takeoff 1520kg (3350lb), or 1745kg (3850lb) with an external sling load.
Dimensions : Rotor diameter 8.33m (27ft 4in), length overall rotor turning 9.78m (33ft 2in), fuselage length 7.77m (25ft 6in), height with standard skids 2.74m (9ft 0in), height with extended skids 3.01m (9ft 11in). Rotor disc area 54.5m2 (586.8sq ft).
Capacity : Standard seating for pilot and four passengers, with pilot and passenger on front bucket seats, and three passengers on rear bench seat.
Type : Light utility helicopter
History : The MD Helicopters MD-520N introduced a revolutionary advance in helicopter design as it dispensed with a conventional tail rotor in favour of the Hughes/McDonnell Douglas' developed NOTAR (NO TAil Rotor) system.
Development of the revolutionary NOTAR system dates back to late 1975 when Hughes engineers began initial concept development work. In December 1981 Hughes flew an OH-6A fitted with NOTAR for the first time. This prototype was modified several times, notably in 1985 when it was fitted with the more streamlined MD-500E forward fuselage, an Allison 250-C20B turboshaft, a second blowing slot and a new fan. By then Hughes had become McDonnell Douglas.
Although the concept, which uses the Coanda effect, took some time to refine, the NOTAR system is simple in theory and works to provide directional control the same way a wing develops lift. Low pressure air is forced through two slots on the right side of the tailboom, causing the downwash from the main rotor to hug the tailboom, producing lift, and thus a measure of directional control. This is augmented by a direct jet thruster and vertical stabilisers.
NOTAR system benefits include far lower external noise (the MD-520N is the quietest certificated helicopter in the world), increased safety due to the lack of a tail rotor, improved handling and performance, reduced vibration and easier maintainability.
McDonnell Douglas originally intended to develop the standard MD-520N alongside the more powerful hot and high optimised MD-530N (both were launched in January 1989 and were based on the conventional MD-500E). The MD-530N was the first to fly, on December 29 1989, the MD-520N first flew on May 1 1990. Development of the MD-530N was suspended when McDonnell Douglas decided that the MD-520N met most customer requirements for the 530N. Certification for the MD-520N was awarded on September 13 1991, and the first was delivered on December 31 that year.
Following the 1997 Boeing/McDonnell Douglas merger, Boeing sold the former MD civil helicopter lines to MD Helicopters in early 1999.
At the 2000 Farnborough Airshow MD Helicopters announced enhancements to the MD-520N including an improved Rolls-Royce 250-C20R+ engine with 3-5% more power for better performance on warm days, and, with changes to the diffuser and fan rigging, increased range and payload capability.
MD Helicopters MD-520N | Airliners.net
Zebra
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I saw the post #19 .
Just to compare both US made helos , I post the Spcs here , for Bell 407 AH and MD 520N .
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SPIEZ
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Actually picked it up from public domain. Kunalji has given the ans!
The beggars accept anything given to them, unlike customers who really need satisfaction!
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SPIEZ
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Bell 407 AH was not considered asaik. Only the MD 520N was selected, no articles on it even being present for testing.
SPIEZ
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I believe the work on LCH is going on. MK2/3 version is being developed.
Zebra
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Indian Army Helicopter Contract: Bell 407, Eurocopter AS 350 Field Trials Completed | India Defence
Bell 407 was there , ( but I posted here for 407 AH ) ,
In other thread , some DFI member cleryfied the matter - why Bell kept them out from Indian Helo (new) Tender .
Zebra
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Sikorsky CH-53 E
The base model CH-53E serves both the US Navy and Marines in the heavy lift transport role. It is capable of lifting heavy equipment including the eight-wheeled LAV-25 Light Armored Vehicle, the M198 155 mm Howitzer with ammunition and crew. The Super Stallion can recover aircraft up to its size, which includes all Marine Corps aircraft except for the KC-130.
General characteristics :
Crew: 5: 2 pilots, 1 crew chief/right gunner, 1 left gunner, 1 tail gunner (combat crew)
Capacity: 37 troops (55 with centerline seats installed)
Payload: internal: 30,000 lb or 13,600 kg (external: 32,000 lb or 14,500 kg)
Length: 99 ft 1/2 in (30.2 m)
Rotor diameter: 79 ft (24 m)
Height: 27 ft 9 in (8.46 m)
Disc area: 4,900 ft² (460 m²)
Empty weight: 33,226 lb (15,071 kg)
Max takeoff weight: 73,500 lb (33,300 kg)
Powerplant: 3 × General Electric T64-GE-416/416A turboshaft, 4,380 shp (3,270 kW) each
Rotor systems: 7 blades on main rotor, 4 blades on anti-torque tail rotor
Performance :
Maximum speed: 170 knots (196 mph, 315 km/h)
Cruise speed: 150 kt (173 mph, 278 km/h)
Range: 540 nmi (621 mi, 1,000 km)
Ferry range: 990 nmi (1,139 mi, 1,833 km)
Service ceiling: 18,500 ft (5,640 m)
Rate of climb: 2,500 ft/min (13 m/s)
Armament :
Guns -
2× .50 BMG (12.7 x 99 mm) window-mounted XM218 machine guns
1× .50 BMG (12.7 x 99 mm) ramp mounted weapons system, GAU-21 (M3M mounted machine gun)
Unit cost - US $24.36 million (1992) average .
Sikorsky CH-53 K
The US Marine Corps had been planning to upgrade most of their CH-53Es to keep them in service, but this plan stalled. Sikorsky then proposed a new version, originally the "CH-53X", and in April 2006, the USMC signed a contract for 156 aircraft as the "CH-53K". The Marines are planning to start retiring CH-53Es in 2009 and need new helicopters very quickly.
In August 2007, the USMC increased its order of CH-53Ks to 227. First flight is planned for November 2011 with initial operating capability by 2015. Deliveries are to end in 2022.
Sikorsky CH-53E Super Stallion - Wikipedia, the free encyclopedia
*****
wonder why Sikorsky ( Heavy-lift cargo helicopter- CH 53 K ) did not bid in Indian heavy lift helo tender ?
The base model CH-53E serves both the US Navy and Marines in the heavy lift transport role. It is capable of lifting heavy equipment including the eight-wheeled LAV-25 Light Armored Vehicle, the M198 155 mm Howitzer with ammunition and crew. The Super Stallion can recover aircraft up to its size, which includes all Marine Corps aircraft except for the KC-130.
General characteristics :
Crew: 5: 2 pilots, 1 crew chief/right gunner, 1 left gunner, 1 tail gunner (combat crew)
Capacity: 37 troops (55 with centerline seats installed)
Payload: internal: 30,000 lb or 13,600 kg (external: 32,000 lb or 14,500 kg)
Length: 99 ft 1/2 in (30.2 m)
Rotor diameter: 79 ft (24 m)
Height: 27 ft 9 in (8.46 m)
Disc area: 4,900 ft² (460 m²)
Empty weight: 33,226 lb (15,071 kg)
Max takeoff weight: 73,500 lb (33,300 kg)
Powerplant: 3 × General Electric T64-GE-416/416A turboshaft, 4,380 shp (3,270 kW) each
Rotor systems: 7 blades on main rotor, 4 blades on anti-torque tail rotor
Performance :
Maximum speed: 170 knots (196 mph, 315 km/h)
Cruise speed: 150 kt (173 mph, 278 km/h)
Range: 540 nmi (621 mi, 1,000 km)
Ferry range: 990 nmi (1,139 mi, 1,833 km)
Service ceiling: 18,500 ft (5,640 m)
Rate of climb: 2,500 ft/min (13 m/s)
Armament :
Guns -
2× .50 BMG (12.7 x 99 mm) window-mounted XM218 machine guns
1× .50 BMG (12.7 x 99 mm) ramp mounted weapons system, GAU-21 (M3M mounted machine gun)
Unit cost - US $24.36 million (1992) average .
Sikorsky CH-53 K
The US Marine Corps had been planning to upgrade most of their CH-53Es to keep them in service, but this plan stalled. Sikorsky then proposed a new version, originally the "CH-53X", and in April 2006, the USMC signed a contract for 156 aircraft as the "CH-53K". The Marines are planning to start retiring CH-53Es in 2009 and need new helicopters very quickly.
In August 2007, the USMC increased its order of CH-53Ks to 227. First flight is planned for November 2011 with initial operating capability by 2015. Deliveries are to end in 2022.
Sikorsky CH-53E Super Stallion - Wikipedia, the free encyclopedia
*****
wonder why Sikorsky ( Heavy-lift cargo helicopter- CH 53 K ) did not bid in Indian heavy lift helo tender ?
Last edited:
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Post some things on Rudhra & its weapons and power-plant...
SPIEZ
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Coming soon! Waiting for reliable sources, heard the second model is under testing.
