INDIGENOUS DEVELOPMENT OF LINE REPLACEABLE UNITS (LRUé †OR LCA-TEJAS


LIGHT COMBAT AIRCRAFT (LCA) (Tejas)


Development Phase
 
 
Tejas is a single engined, light weight, highly agile, multi-role supersonic fighter. It has quadruplex digital fly-by-wire Flight Control System (FCS) with associated advanced flight control laws. The aircraft with delta wing is designed for 鲠combatᮤ 榥nsive air support穴h 壯nnaissanceᮤ -ship᳠its secondary roles. Extensive use of advanced composites in the airframe gives a high strength to weight ratio, long fatigue life and low radar signatures. Aeronautical Development Agency is the designated project manager for the development of LCA.
 

Specification            :          

Length

:

13.2 m

Span

:

8.2 m

Height

:

4.4 m

Max Take of Weight

:

13.5 t

Payload

:

5.3 t

         Speed

:

1.6 M

         Radius  of Action

:

300 km

         Takeoff distance

:

1700 m

         Landing distance

:

1300 m

         Service Ceiling

:

16 km

 

 

 

 

Power Plant

ã°¡n style="font:7.0pt "Times New Roman"">   GE 404F2/J-IN20 (1 in no.) (General Electric)

ã°¡n style="font:7.0pt "Times New Roman"">   Turbofan engine

ã°¡n style="font:7.0pt "Times New Roman"">   Max. Thrust : 5618 kgf

 
INTERMEDIATE JET TRAINER (IJT)

 
 
HAL has undertaken development of IJT to replace the ageing Kiran trainer aircraft in service with Defence Services. This aircraft will be used for Stage II training of pilots. IJT has cockpit with twin tandem seats with good visibility for the pilots, modern Active Matrix Liquid Crystal Displays and Head-Up Display (HUD). The aircraft is equipped with a Mission Computer and Integrated Avionics system. 1000 kg of external stores carrying capacity allows fitment of various armaments and fuel drop tanks on the aircraft for effective training. The aircraft is designed for a max. speed of 750 km/h, max. range of 1500 km, max. endurance of 2 hrs. with internal fuel.
 

Technical Parameters                     

Length

:

11.0 m

Span

:

10.0 m

Height

:

4.4 m

Max Take of Weight

:

4.5 t

Payload

:

1.0 t

         Speed

:

0.75 M

         Service Ceiling

:

9 km

         Takeoff distance

:

880 m

         Landing distance

:

890 m

 

 

 

Power Plant

Technical Parameters      :

Max. Thrust

:

1760 Kgf

Dry Weight

:

315 Kgs

Thrust / Weight Ratio

:

5.6

Sp. Fuel Consumption

:

0.69 Kg/Kg/Hr

TBO

:

1200 hrs
 
 
LIGHT COMBAT HELICOPTER (LCH)

 
 
Light Combat Helicopter (LCH) was proposed to meet IAFಥquirement of a dedicated light helicopter for combat operations. LCH will have maximum possible commonality with ALH. LCH with a narrow fuselage will have pilot and co-pilot/gunner in tandem configuration incorporating a number of stealth features, Armour protection, Night attack capability and crashworthy landing gear for better survivability. The major features of LCH are:
 
 Glass Cockpit
 Crashworthy under floor structure
 Crashworthy fixed tricycle type with tail wheel landing gear
 Canted flat panels for low Radar Cross Section
 Integrated Dynamic System
 Hingeless Main Rotor / Bearingless Tail Rotor
 Anti Resonance isolation system
 Integrated Avionics and Display System (IADS)
 IR Suppressor
 20mm Gun, Rocket & Missiles
 

Technical Parameters                      

MTOW

:

5.5 t

Max. speed

:

265 Kmph

Range

:

550 Km

Service Ceiling

:

6.5 km

Climb rate

:

5 m/s

Power Plant

SHAKTI engine (2 no.)
Power is 895 kW
LIGHT UTILITY HELICOPTER (LUH)

 
 
ã¡®ction for the development of LUH was accorded by GoI in Feb 09. The timeframe for development is 6 years.
䨥 helicopter in 3 Ton Weight class with Glass Cockpit with MFDs will be deployed for Reconnaissance and Surveillance role. It will be powered by a single engine. The helicopter will be capable of flying at 220 Kmph; service ceiling of 6.5 Km and a range of 350 Km with 500 kg payload.
 

Technical Parameters                     

Max. TOW

:

2700 kg

Speed at Sea Level

:

Vcruise > 220 kmph
VNE       > 250 kmph

ROC

:

> 7.5 m/s

VROC

:

> 5.5 m/s

         Service Ceiling

:

6.5 km

         Range

:

350 km

         伯font>

:

+2 to îµ g at SL

 

 

 Power Plant

Technical Parameters      :

Max. Thrust

:

1760 Kgf

Dry Weight

:

315 Kgs

Thrust / Weight Ratio

:

5.6

Sp. Fuel Consumption

:

0.69 Kg/Kg/Hr

TBO

:

1200 hrs

 
JAGUAR DARIN-III Upgrade

 
ᩲcraft upgraded to DARIN-III standard would feature following equipment/systems in addition to those integrated as part of the recent strike aircraft produced (DARIN II + additional systems) :
í¯¤ified avionics Architecture
 cockpit with dual SMD on single seater A/C
é®´egration of MULTI MODE RADAR on single seater Aircraft
宧ine and Flight Instrument system/Integrated Standby Instrument system (EFIS/ISIS) Integration to replace existing electro-mechanical flight instruments and/or engine instruments.
㯬id State Flight Data Recorder and Solid State Video Recording System
ᤤitional functionalities related to display, data transfer and Auto Pilot
 Weapons
䥶elopment activities would involve major structural modification to the airframe to accommodate the radar (on the nose cone of Strike aircraft). On the Avionics front Mission computer software development, new cockpit design, radar integration and solid state video recording system is to be addressed. Modification will also be required to be carried out on the air-conditioning system to meet the equipment cooling requirements.

 
Mirage Upgrade

 
í©²age 2000 Upgrade is proposed in two Phases:
  • Phase-1: Development for Initial Operational Clearance (IOC) & Supply of IOC Equipment by French OEMs (Thales & Dassault)
  • Phase-2: Development for Final Operational Clearance (FOC) and series upgrade of the fleet by HAL:
    é®´egration of Buyer Furnished Equipment (BFE)
    Six subsystems viz. Laser Designation Pod (LDP), Air Combat Maneuvering Instrumentation (ACMI) pod, Helmet Mounted Display System (HMDS), Crystal Maze missile (CM), BDL-CMDS and Operational Data Link (ODL- provision only).
    䥳ign and development of HAL Mission computer
    å°§rade of two IOC standard aircraft to FOC standard.
    㥲ies Upgrade of aircraft.
FIFTH GENERATION FIGHTER AIRCRAFT (FGFA)

 
 

The proposed FGFA will have air combat superiority, high tactical capability, group action capability in the regions even with poor communication support. The aircraft will have advanced features like

  • Increased Stealth
  • Supersonic cruise
  • Data link and network centric warfare capability.

FGFA will be co-developed with Russians. Sukhoi Design Bureau (SDB) has been selected as the Russian agency for this development project.

MULTI-ROLE TRANSPORT AIRCRAFT (MTA)

 
 
  • Co-development and co-production of Multi-role Transport Aircraft, jointly by Russian partners and HAL, is being launched to meet the requirement of Russian and Indian Air Forces.
  • The aircraft will be designed for the roles of a 15-20 ton Cargo / Troop transport, Para trooping / Airdrop of supplies including Low Altitude Parachute Extraction System (LAPES) capability. It will be configured such that all types of cargo can be transported and the aircraft would be capable of operating from semi prepared runways.

    Technical Parameters                     

Length

:

35.2 m

Height

:

11.0 m

MTOW

:

60 Ton

Payload

:

20 Ton

         Speed

:

800 Km/hr

         Range

:

6000 km

         Takeoff distance

:

1300 m

         Landing distance

:

1200 m

         Engine Thrust

:

2X11,000 kgf

 

 

 

 
HTT-40

 
 
  • Roles
    ⡳ic flying training
    ᥲobatics
    鮳trument Flying
    igation
    ht Flying
    㬯se formation

    Technical Parameters                     

Max TOW

:

2800 Kg

         Speed

:

450 Km/hr

         Range

:

1000 KM

         Engine Thrust

:

950 SHP

         Cockpit

:

Tandem seating, Air conditioned cockpit

         Modern Aircraft System

:

All metal, FADEC control Turbo Prop trainer aircraft with Zero-Zero ejection seats and Multifunction displays

         Projected requirement

:

106

 

 

 

 
INDIAN MULTI ROLE HELICOPTER (IMRH)

 
 
  • Co-Design and co-production of a 10 Ton class Medium Lift Helicopter is proposed to be taken with an international helicopter manufacturer to meet the requirement of the 3 Indian Defence Services. This approach is taken to shorten the development timeframe.
  • The Helicopter will be powered by twin engines and will feature blade folding option for ship deck operations. The variant for Army/IAF will support Air assault, Air Transport, Combat logistic, Combat search & rescue and casualty evacuation operations. The naval variant will be developed for Anti Submarine Warfare and Anti Surface Vessel Strike roles