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Sitara - Intermediate Jet Trainer - HJT-36

HJT Stands for Hindustan Jet Trainer.

* extremists can read it as Hindu Jet Trainer


Introduction

The seed to design and develop an Intermediate Jet Trainer was planted in July of 1999. This bold move bore fruit on 07 March 2003 when the IJT prototype flew for the very first time. The official flight followed on 21 March 2003 in the presence of many dignitaries. On both these occasions Squadron Leader Baldev Singh was able to execute planned manoeuvres for a duration of about twenty minutes on the aircraft. The rapid success of the IJT brings into focus numerous aspects within the Indian aeronautical industry. In this article we will briefly examine some of them. The IJT was conceived to replace the Kiran. The Kiran was designed in the 1960s and it is the current entry-level jet trainer. It is also used by the national aerobatic team, the Surya Kirans (Sunrays). The general level of satisfaction in the Indian Air Force with its performance is very high. However over the years the IAF had seen a sea of change in their operational aircraft. With the induction of several high-tech platforms like the MiG-29, Mirage 2000, and now the Su-30MKI, a need arose to revise the training of pilots.

The Kiran was able to meet the immediate expectations but emphasis was placed on acquiring an Advanced Jet Trainer (AJT). The AJT acquisition has run into rough weather over the issue of cost. At this point an indigenous alternative must have seemed attractive. However indigenous development of an AJT was a complicated matter. In the early 1980s, the Government of India had launched the Light Combat Aircraft (LCA) programme to indigenously design and produce a combat aircraft capable of meeting India's defence needs. The LCA programme though enormously slow in actually producing the aircraft, was very quietly contributing to the confidence and the technical competence of the aeronautical community in India. Thus in 1999 a proposal from Hindustan Aeronautical Limited (HAL) and a nudge from the heads of the technical advisory community was enough to drive the idea of designing and developing an Intermediate Jet Trainer (IJT) within a very reasonable price and little time.

Major Players

HAL's Aircraft Research & Design Center (ARDC) was tasked with design and development of the IJT. Partnering with the ARDC was the Aeronautical Development Agency (ADA), the agency responsible for the design and development of the Light Combat Aircraft (LCA). A number of Public Sector Units (PSUs) and associated government agencies also participated in the IJT project. Two foreign companies that made major contributions to the project were Snecma Moteurs/Turbomeca and Smiths Aerospace. As with all major defence projects, the Government of India (GoI) provided the financial support for the IJT.

Enablers

Clearly, the experience gleaned from the LCA project was arguably the most important of the enablers for the IJT. Teams that worked on the IJT had been exposed to the LCA while working in various capacities on that project. Beyond that, at this point in time, it is rather difficult to pin point the contributions made by the LCA project, time will expose those important details. The role of Government of India (GoI) is also describable as that of an enabler. The GoI has shown interest in defense related fields in the recent past, however, this is one effort that stands out. It is interesting to note that the GoI has visibly seized upon the ability, confidently 'pick a winner' in the aerospace market. Although difficult to quantify, this will definitely bode well for the Government in the future.

The ARDC relied on software to reduce the design & development cycle. The software from Unigraphics provided two major functionalities: 3-D CAD/CAM and data management. The 3D CAD/CAM was used to design subcomponents, components, and large assemblies and even complete mock-ups of the aircraft. The data management software allowed the data associated with these designs to be shared among various teams. Coupled with Virtual Product Development (VDP) modeling and support for product development process threads, various teams were able to create, test, document and manufacture components digitally. Collaborative building and the ability to test different versions of the same component in real time optimized time utilization.

Snecma Moteurs and Turbomeca delivered two of the Larzac 04H20 engine that powers the current and probably the next IJT. The 1440 dN jet engine was first fully flight qualified on an Alpha Jet flying test-bed. Smiths Aerospace was selected to provide an open architecture mission control computer, head-up display units, HUD repeater, a rear entry panel, and altitude and heading reference system and air data computers. It may be noted that Smiths also works with HAL on supplying instruments for the IAF's Jaguars and the proposed BAE Hawks. Thales of France supplied the 3ATI and 4ATI displays, along with angle-of-attack, temperature sensors and accelerometers.

Human Engineering

In our discussion, we rarely make an argument for basing aircrafts acquisition on Human Engineering (HE) factors. Basically HE, with respect to an aircraft, relates to aircrew-aircraft compatibility. The clearance over the head of a pilot, the ability to see over the nose or over either sides, seat shape and size, clearance during ejection, reach to various instruments: mostly associated with dimensions within the cockpit. The Hindustan Jet Trainer (HJT) 36 is the first Indian trainer built with Indian anthropometrical data of a male pilot in mind. The entire layout of the cockpit, including the main instrumentation panel, is based on HE. Again, software was used to design and animate human movements. With emphasis on HE during the design phase and with total control over it due to the acquiring of data related specifically to Indian pilots, training future pilots should become that much more efficient.

IJT Prototype

Sanctioned with a grant of Rs. 180 crore in 1999, the plan is to build a few more aircrafts for demonstration and certification processes. To the credit of the management team, these funds will suffice till the aircraft reaches serial production. Considering all factors, the development costs are a fraction of what most similar aircrafts have cost. As compared to the Kiran, plans call for an increased lifespan (10,000 hours), more armament carrying capabilities (1000 kg) and a higher maximum speed (700 kph). A second prototype is expected in August of 2003, which will be fitted with advanced avionics. As a vote of confidence, the Chief of Air Staff has placed an order for 16 HJT-36s, meant for the national aerobatic team, the Surya Kirans. A second vote came from the Scientific Advisor to the Defence Minister Dr. V.K. Atre, who said, "We are few more steps to the AJT and a larger LCA, the mid-combat aircraft".

The Future

As we look into the future we expect improvements in the present HJT-36 prototypes. Few details have been released by HAL on what the final HJT-36 will contain. One would expect it to be a mature product with standard features such as fly-by-wire flight controls, wide angle HUD, HOTAS controls, MIL STD data-bus, helmet-mounted target designation and integration with equipment and weaponry from disparate sources. Snecma has already proposed an enhanced jet engine for the production IJT and hopefully that is just the beginning. There is also talk of a production run of 200 aircraft.

A favourite with the crowd is the possibility of morphing the IJT into an AJT. Two design ideas leap out with this in the background. The first is to add another engine. A tandem engine configuration have been seen in recently designed AJTs, the HAL designed AJT would look fairly similar to those. The second suggestion revolves around replacing the present Larzac engine with a more potent engine, perhaps a de-rated Adour. The Adour is currently in use in the indigenously manufactured Jaguar aircraft. No matter which design is preferred by HAL and its design team, the pressure to design and develop an Indian AJT will be immense.

The HJT-36 allows India to build any of the following:

1] A basic trainer, suitable for basic jet training.
2] A trainer for basic combat use of unguided weapons, air-to-air missiles and sea targets.
3] A combat trainer with under-wing hardpoints capable of launching guided missiles and using guidance equipment pods.
4] A single-seater tactical fighter, with guns, all-weather radar for use of AAMs and ASMs.
5] A Coast Guard SAR aircraft, with a nose-mounted search radar.
6] A sporty private jet for enthusiasts.

Finally, the Intermediate Jet Trainer project has proved that international cooperation is the way of the future. This sort of venture is bound to attract several investors from all over. The author extends his congratulations to all the parties and wishes HAL and the development team the very best for the future.

Overall Wingspan: 10.00 metres.
Overall Length: 11.00 metres.
Overall Height: 4.40 metres.
Normal Training Weight: 3500 kg
Max Take Off Weight: 4500 Kg
Max Mach Number: 0.75 Mach
Max Dive Speed: 750 km/h
Service Ceiling: 9000 metres.
Maximum Load Factor: +7g / -2.5g

Miro
 
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The first single seater prototype HJT-36 (S3466) finally takes off, resulting in months of hard work by the engineers who built her. With an expected production run of 200 aircraft.

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S3474 the second prototype of HJT-36 (twin seater).

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The HJT-36 S-3474 is the second IJT prototype. It made its first flight on 26 March 2004 with Sqn Ldr S Sapra in the front seat and Sqn Ldr Baldev Singh in the rear seat. The first flight was of 20 minutes duration and was done with its undercarriage extended.

Thanks,

Miro
 
214mm PINAKA MRLS

Background

In 1983, the Indian Army formulated a General Staff Qualitative Requirement (GSQR) for a new Multiple Rocket Launcher System (MRLS). The system was expected required to allow engagements at ranges greater than the 20 km limit of the Soviet and Indian built BM-21. In December 1986, the Ministry of Defence (MoD) sanctioned a sum of Rs.264 million to cover the costs of development. Development was to have been completed by 1994. The MoD nominated Armament Research & Development Establishment (ARDE) as System Coordinator for execution of the project in association with seven other laboratories of Defence Research & Development Organization (DRDO), of which, the Combat Vehicle Research & Development Establishment (CVRDE), High Energy Material Research Laboratory (HEMRL) and Electronics & Radar Development Establishment (ERDE) were major participants. As part of the development DRDO was to fabricate seven launcher vehicles for launch of rockets, of which six were to be supplied to the Army for user trials and subsequent use, three replenishment-cum-loader vehicles including two for the Army’s user trials, one command post vehicle for command and control.

The GSQR prescribed that the MRLS system should attain a maximum range of 45 km and the circular error probability (CEP) should not exceed 1 - 2% of range. The system was to incorporate a twelve tube cluster configuration capable of firing a salvo in 30-50 seconds and neutralize the specified area by a salvo from six launchers. The entire operation of loading of one salvo from the replenishment vehicle to the launcher was required to be completed within four to five minutes. Eight types of warhead for different target effects were to be developed. The fabrication and delivery of different components of the system were to match user trials to be conducted in two phases to be concluded by December 1993.

Technical Characteristics

Mounted on a Bharat Earth Movers Ltd (BEML) license-built Tatra (8x8) Kolos cross-country truck chassis, the MRLS system compromises a fully enclosed five man cab at the front with two pods each containing six rockets mounted at the rear of the chassis. The cab is fitted with an NBC (Nuclear-Biological-Chemical) system and standard equipment fit includes a central type regulation system, which allows the driver to adjust the tire pressure to suit the type of ground being crossed and passive night vision driving equipment. Maximum road speed is listed at 80 km/h and can negotiate a slope of 30º.

The 214mm calibre rocket is four metres long, weighs around 275 kg, with the warhead weight of 100 kg. The warhead types which can be fired are anti-tank bomblets, anti-tank mines, incendiary and pilot shot. Maximum range of the rocket is in excess of 40 km with all twelve rockets being ripple fired in 40 seconds. The launcher assembly has electromagnetic elevation and traverse, with traverse being 90º left and right of the centerline and elevation up to 55º.

Both range and weight of firepower compare favorably with the BM-21. The BM-21&#39;s 40-round launcher can deliver 736 kg of explosives at a range of 20 km, while the 12-round launcher of the Pinaka can deliver 1200 kg at double the range. The Pinaka battery of six launchers, fitted in two pods that fire 72 rockets, can neutralize a target area of roughly 700 x 500 metres (350,000 square metres). The system has been designed for shoot-and-scoot fire missions with each launcher being provided with its own computerized fire control system and automatic positioning system.

Recent Developments

Despite the fact that the staff project was preceded by competence build up projects, ARDE sought periodical extensions. It admitted in October 1997, that this was due to incorrect estimation of all critical and technological issues during competence build up stage. As per its latest proposal additional funds of Rs.300 million would be required to complete the project by December 2000. This revised date for completion is more accurate and is likely to be met. ARDE in association with the participating laboratories conducted 32 flight trials between September 1988 and May 1998, initially with a single tube launcher developed under competence build-up projects and later with the launchers developed under this project.

First 12 trials were conducted for propulsion unit evaluation and performance. After proving launcher prototypes, performance of launcher and salvo firing capability was demonstrated to users in June 1996. Phase-I user trial was conducted in June 1997. In all 279 rockets were fired during these trials. The rocket developed by ARDE could achieve only 82% in terms of range (37 km). Accuracy at range was also considered less than satisfactory, with a CEP of 4%. Phase II trials were started from July 1998. During these trials consistency of salvo firing was proven. Both range and accuracy of the rockets also demonstrated improvement. CEP was down to 2-3% of range and maximum range attained was 40 km. In all 256 rockets were expended during Phase Two.

The Pinaka entered user trials in February 1999. During Army user assisted technical trials, it was fired in ambient temperatures ranging from -20° to +55°C. The war in Kargil during the summer of 1999 provided a perfect opportunity for tests under combat conditions. Consequently a section of two launchers were deployed to Kargil in June of 1999. Operated under the auspices of 121 Rocket Regiment, systems were proven in both the direct and indirect fire modes.

Following the end of user trials in September 1999, the Indian Army decided to accept the Pinaka. While certain user requirements remain to be fulfilled, the Army has decided that the Pinaka offers a quantum leap in capability vis-à-vis its existing rocket artillery. However, developmental work continues to increase the Pinaka&#39;s maximum range and develop two new types of warhead. DRDO is also working to cut salvo re-load time from 15 minutes to 4 minutes. The first Pinaka regiment was raised in February 2000. A regiment consists of three batteries of six Pinakas each, plus reserves. It is expected that one regiment will be added each year as the oldest BM-21s are withdrawn from service.

Thanks,

Miro
 
214mm PINAKA MRLS

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The 214mm Pinaka MBRL firing its payload of rockets, during a user evaluation by the Indian Army. Although advertised with a maximum range of 38 km, the Pinaka has achieved ranges up to 42 km during user trials. Each rocket is of 214mm calibre, is 4950mm long, weighs 276 kg and carries a 100 kg warhead. Minimum range is 10 km and the overall CEP (Circular Error Probable) is less than 1-2% of the total range.

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The Pinaka MRLS undergoing development trials with DRDO.

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The Pinaka MRLS undergoing user trials with the Army.

The 214mm Pinaka MBRL is an all weather, indirect fire, free flight, area saturation weapon system that has begun to enter service with the Indian Army. It consists of a Multi-Barrel Rocket Launcher (MBRL) vehicle with 12 tubes, three replenishment vehicles, a loader cum replenishment vehicle and a fire control system containing a command post and the DIGICORA MET eadar. A battery of six launchers can turn an area of 1000 x 800 meters into melted Swiss cheese in less than 44 seconds.

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The Pinaka program has a lot of contribution from the private sector. Larsen and Toubro (L&T) Ltd. claim credit for building the 2-axis DC servo drive for the Pinaka, while TATA Advanced Materials Ltd. (TAML) have developed launcher tubes and containers for the rockets and missiles. TATA Power&#39;s Strategic Electronics Division (SED) also developed the prototype Pinaka launcher which underwent extensive user field trials.

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The 214mm Pinaka MBRL firing its payload of rockets, during a user evaluation by the Indian Army. Although advertised with a maximum range of 38 km, the Pinaka has achieved ranges up to 42 km during user trials. Each rocket is of 214mm calibre, is 4950mm long, weighs 276 kg and carries a 100 kg warhead. Minimum range is 10 km and the overall CEP (Circular Error Probable) is less than 1-2% of the total range.

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The Pinaka replenishment vehicle at the Republic Day Parade in New Delhi, 26 January 2005. Please note that this image is very large (1900 x 1258 pixels) and may take a considerable time to load.

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The Pinaka loader vehicle at the Republic Day Parade in New Delhi, 26 January 2005. Please note that this image is very large (1900 x 1258 pixels) and may take a considerable time to load.

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Thanks,

Miro
 
155mm BHIM SELF PROPELLED GUN

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Prototype of the Bhim SPG --&#62; South African LIW/Denel self-propelled T6 155mmm/52-calibre gun mounted on the Arjun tank chassis. Successful user trials were conducted by the Indian Army in the summers of 1998 and 1999, with the Army reportedly favouring the Bhim SPG over other systems evaluated.

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With a VLAP/M53 charge the Bhim SPG can achieve ranges of nearly 53 km&#33; The Army has yet to make a decision. If selected the system will be assembled in India, with turrets supplied by Denel.

Thanks,

Miro
 
NAG ATGM

Background & Development

The Nag (Cobra) is a third generation, all weather, top-attack, fire-and-forget anti-tank guided missile. It is one of five missile systems developed by the Defence Research & Development Organization (DRDO) under the Integrated Guided Missile Development Program (IGMDP). Design work on the missile started in 1988 and the first tests were carried out in November 1990.

The missile uses a tandem HEAT (High Explosive Anti Tank) warhead to penetrate ERA (Explosive Reactive Armour) or composite (Chobham type) armour that is found in the latest tanks. The system is expected to supercede Indian production of the Soviet origin 9K113 Konkours (NATO: AT-5 Spandrel) and Euromissile Milan M2 anti-tank missiles.

Technical Characteristics

As originally conceived, the Nag would have been available with three different types of guidance, These included a wire guided version, an infra-red version and a millimetric wave (mmW) version. The cumbersome nature of a wire guidance system had led to plans for this being dropped. Currently, guidance is based on an imaging infra-red (IIR) passive seeker that ensures a high-hit accuracy in both top- and front-attack modes.

The mmW seeker, on the other hand, is intended to operate as an optional system that can replace the IIR passive seeker as a module. Also incorporated into the guidance system, is a CCD camera. The missile has a weight of 42 kg and can engage targets at ranges up to 6 km. The Nag is claimed to be first anti-tank missile which has a complete fiberglass structure.

The Nag will be produced in two main versions. The land version has been tested from a tracked vehicle known as NAMICA (Nag Missile Carrier). The carrier is a stretched BMP-2 with an additional pair of road wheels and is manufactured by the Ordnance Factory, Medak. It carries four missiles in a ready-to-fire mode on the turret and more missiles can be reloaded without exposing the crew on the battlefield. With the IR version of the missile, targets are acquired using a thermal sight, and are then assigned to the nose-mounted IIR seeker.

Missile guidance is initially by area correlation around the target, then by centroid tracking. Terminal homing is by area correlation around the centroid. Nag is also configured to be used on the Advanced Light Helicopter (ALH). Eight missiles are carried in two quadruple launchers. Launchers mounted on either side are linked to a nose-mounted stabilized thermal sight and a laser range-finder package.

Despite trials since 1990, problems with the guidance system held back successful trials for a long time. The first successful test firing of the missile using an IIR seeker was conducted on 09 September 1997. Of the two existing types guidance systems, the IIR seeker is now fully developed. The IIR version of the missile has undergone several rounds of successful flight trials since 1997. Flight testing of the helicopter-launched version was carried out from a specially rigged Mi-17 in March 1998. This was followed by integration with ALH in mid-1999. The Indian Army accepted the system for user trials in October 1999. The development of the mmW seeker has been more problematic and it is unlikely that the seeker will enter service any time soon. The missile also employs sensor fusion technology for flight guidance.

During recent test flights, the missile&#39;s fire-and-forget capability has been established using the day version of the IIR passive seeker. On 20 January 2000, field tests of the Nag’s Thermal Sight system saw the system identify and lock on to a T-55 tank at a range of 5 km. The tank was then engaged and destroyed at a range of over 4 km. In its IIR form the Nag has limited all weather capability. This has given added impetus to develop the mmW seeker. Efforts are on to provide special embedded on-board hunters, that can hunt for targets using &#39;day seekers&#39; and &#39;day-&-night seekers&#39;. A special nitramine based propellant has been developed for the Nag in order to meet its dual requirements of energy and smokelessness.

Low rate serial production of the Nag began in February 2000. 25 missiles produced by Bharat Dynamics Limited (BDL) in 2000, will all be earmarked for user trials. Full-scale production of up to 200 missiles per year is likely to be launched in early 2001. The Indian Army has a requirement for 500 missiles and the Indian Air Force has a requirement for 100 missiles by 2004.

Thanks,

Miro
 
NAG ATGM

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A Nag ATGM on display at Def Expo &#39;99 in New Delhi.

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The NAMICA (Nag Missile Carrier) missile tank destroyer - a modified BMP-1 chassis - is fitted with a hydraulically operated elevatable observation/launch platform for the Nag ATGM. This prototype vehicle, unveiled at Def Expo &#39;99 in New Delhi, has already undergone preliminary field trials.

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A Nag ATGM being test-fired from the NAMICA vehicle.

Thanks,

Miro
 
Tank-Ex

Tank-Ex is a significant development and is the second attempt (after the successful Combat Improved Ajeya /upgraded T-72M1)by the Arjun MBT developers to harness its technology spin-offs. The Tank Ex appears to be an ideal solution for upgrading the Indian Army&#39;s vast and aging T-72M1 fleet. Having undergone six months of trials in Rajasthan till now, it will presumably need many more to be fine tuned per Army requirements. However, it must be noted that the two crucial "parts" of the Tank Ex - namely the Arjun turret with its weapon system and the T-72M1 (Ajeya) platform/chassis are well tested and already certified by the Army.

General details:

Crew: 4 - commander, gunner, loader and driver.

Combat weight: The Tank -Ex at 47 tons is heavier than the T-72M1 (41 tons) and much lighter than the Arjun MBT, which tips the scales at 58.5 tons.

Power plant:The Tank-Ex has a 1000 hp power plant (as on the Combat Improved Ajeya) giving a power to weight ratio of 21 hp/ton for a weight of 47 tons. This represents an improvement over the T-72M1&#39;s 20 hp/ton with a weight of 41 tons and an 780 hp power plant.

Ground pressure: 0.94 Kgf/cm Square, marginally higher than the T-72M1&#39;s 0.90 Kgf/cm square.

Suspension: Torsion bar with hydrostruts; also an improvement over the T-72M1 torsion bar system.

Dimensions: The usage of the T-72M1 chassis gives the Tank Ex a lower silhouette than the Arjun MBT, which stands tall at 3.03 meters (over AD gun mount).

Length (gun forward): 9.19metres

Width(over tracks): 3.37metres

Height(over AD gun mount): 2.93metres

Ground clearance: 0.47metres

Armament: The Tank Ex utilizes the Arjun MBT&#39;s 120mm rifled gun firing unitary APFSDS and HESH semi combustible cartridge case ammunition. A total of 32 rounds are carried as compared to 39 in the Arjun and 45 two piece ones in the T-72.The Arjun&#39;s armament system is the most powerful one available to Indian developers today. The choice of calibre, weapon design and ammunition make it superior to the in-service 125mm 2A46 guns on the T-72M1. The Tank Ex retains the Arjun&#39;s third generation director type integrated FCS (Fire Control System) including a sophisticated digital ballistic computer. It may be noted that the Arjun FCS is an updated one(with digital components replacing the original analogue ones) as compared to the original, which faced numerous technical problems. Firepower trials validated the efficacy of the updated Arjun FCS and led to its recent acceptance by the Army. Capable of firing on the move, the Tank Ex also is fully "night ready" with the gunner having a thermal imager integrated with his main sight. A standby articulated sight is provided as backup for the main sight. The tank commander (as in the Arjun MBT) has his own fully stabilized sight with relevant controls for surveillance, target acquisition and engagement, giving excellent hunter-killer ability. The gun control system is electro-hydraulic. Gun elevation/depression is +16.5 deg/-10 deg , better than the T-72M1&#39;s + 14 deg/-6 deg. As in the Arjun MBT and the T-72M1, a co-axial 7.62mm PKT machine gun and a 12.7mm NVST Heavy Machine gun(air defense) are standard. The tank also incorporates an Auxiliary Power Unit (APU) to operate the weapons systems in silent watch mode.

Navigational aids: A global positioning system is provided for accurate navigation. This is a feature common to both the Arjun MBT as well as the Combat Improved Ajeya .

Protection: The Tank Ex utilizes the state of the Art composite armor-"kanchan"-especially over its frontal arc(Turret as well as glacis) giving excellent protection against both Kinetic and Chemical rounds. The usage of the Arjun turret design indicates that the Tank-Ex may also have its "ready" ammunition stored in the bustle (as in the Arjun),separated from the crew and provided with blow off panels. This would be a significant protective feature in line with "western" design practices. Kanchan is an extensively tested and successful armor, which is available for retrofit to other IFV programs. The Tank Ex also has fully integrated Nuclear Biological and Chemical (NBC) protection The usual turret mounted 81mm antithermal smoke grenade launchers are also standard on the Tank-Ex.

Performance and Obstacle Negotiation: The Tank Ex retains the T-72 attributes of speed and agility with a maximum speed of 60 km/hr (on road) and 40 km/hr (cross country).While the gradient climbing at 30 degrees it remains in line with all variants of the T-72 like the B(M). The Tank Ex is better at trench crossing.(2.6 metres as compared to the T-72M1&#39;s 2.28 meters).Vertical Obstacles 0.85 metres tall can be surmounted, same as the T-72M1.Shallow fording is quoted as 1.2 metres.

Thanks,

Miro
 
Tank EX

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Thanks,

Miro
 
Il-214 Multi-Role Transport Aircraft (MTA)

In late 2000 the Government of India, the Aviation Complex after Ilyushin and the JSC "Irkutsk Aviation Industrial Association" signed an agreement stipulating development and production run of a multi-role transport aircraft IL-214T of 15-20 ton or 82 paratroopers load capacity and in its passenger version IL-214-100, for the capability of transportation of 100 passengers.

As a prototype of the new airplane, a military transport project of IL-214 aircraft was selected, the one that is being examined by the Air Force of Russia as a replacement for the obsolete Antonov An-12 as well as An-26. In India, the new aircraft is proposed to replace 110 An-32 transport aircraft.

By expert evaluation, the IL-214 could become a good alternative for the C-130, C-160, C-123, G-222 aircraft that operate in dozens of countries of the world in huge numbers. Financing of the project is planned in equal shares of the Parties. The production would possibly be run at both Indian HAL Corporation factory and the JSC "IAIA".

The business-plan for the project would be finalized by the end of the year 2001, after the completion of its technical feasibility studies. The cost of the program is estimated at &#036;300 million. Initial deliveries under the MMTA program could commence in seven years after the launch of the project,however, a detailed timetable for the program had not been specified yet. Estimated cost of the production aircraft would make &#036;20-25 million.

The IL-214 is an aircraft with top-mounted wing and T-shaped tail empennage. The aircraft would be equipped with twin bypass turbo-jet engines of 9-10 ton thrust. As a prospective powerplant, the PS-9 engine manufactured by the JSC "Perm&#39; Motor Works", Rolls-Royce BR-170, D-436T engines are contemplated. The cargo cabin is 13.85 m long (with account for the ramp - 17.8 m), and would be 3.0 m high and 3.15 m wide. The military transport version of the airplane would have the cargo ramp in the tail section and capable of paratroops deployment at flight speed of approximately 250 km/h. The aircraft estimated operational life is 20000 flight hours.

Specifications
Maximum takeoff weight 55000 kg
Fuel capacity 13500 kg
Maximum speed 850 km/h
Cruising speed 800 km/h
Length 33.2 m
Wing span 30.1 m
Height 10.0 m
Flight range 2500 km with payload of 18800 kg
Flight range 6000 km with payload of 4500 kg
Takeoff run 1300 m.
Landing run 1200 m.

Thanks,

Miro
 
IL-214

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An artist&#39;s computerized impression of Il-214.

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Both military and Civil models of IL-214 at HAL&#39;s stall in Aero-India 2005.

Thanks,

Miro
 
Airborne Surveillance Platform (ASP)

The Indian Airborne Surveillance Platform (ASP) is one of the key force multipliers in the modern war scenario. India&#39;s Defense Research and Development Organization [DRDO] is developing an advanced surveillance platform based on an HS-748 aircraft to detect targets at extended ranges with all round azimuth coverage. It is designed to handle 50 targets. It features a hybrid navigation system and the secure communication and data links. The DRDO has spent a little over Rs 200 crore to develop this early warning system, similar to the American E-2C Hawkeye. But, to get the capabilities of even the E-2C, India would have to spend at least Rs 2,000 crore. Three HS-748 Avros have been fitted with rotodomes.

Development of the ASP would permit fuller utilisation of the high performance MiG-29, Mirage-2000 and SU-30 planes in the IAF. The utility of ASP also lies in its ability to act as an airborne command and control center, overcoming the limitation of directing air operations from the ground.

Airborne Early Warning and AWACS, capable of providing continuous, comprehensive and long-range air defence cover against low-level attacks had emerged as new force multiplier in early 1980s. Based on the projection made by Air Force and Navy for such systems, a number of studies in the nature of lead-in-schemes were carried out under project "Guardian" from July 1985 at a cost of Rs 16.48 crore.

The Ministry set up a dedicated laboratory, namely CABS (Centre for Airborne Systems) in February 1991 for progressing the technologies and sub-systems necessary for the ASP. The main task allotted to the CABS was design, development, integration and evaluation of airborne electronic systems on a suitably modified flying platform for surveillance of airspace together with command and control functions besides transfer of appropriate technologies to industry. Besides CABS, LRDE, Gas Turbine Research Establishment and Research and Development Establishment (Engineers) were entrusted with the development of ASP sub-systems.

The strategy adopted by CABS involved the development of an ASP using rotodomed HS-748 aircraft as the flight test bed, in the first phase for the development of the indigenous Airborne Early Warning technology to be evolved on a step by step, modular, low cost and low risk approach.

Air HQ while commenting on the system specification document stated, in October 1992, that while the specifications were meant for ASP and were not expected to meet the Air Staff Requirements at that stage, expected that the design philosophy was targeted towards meeting the Air Staff Requirements at a later stage. The Ministry stated, in February 1999, that ASP was not meant to meet the requirements of users but to induct and demonstrate the technology by utilising the only viable platform. The fact, however, remains that the ASP development programme was taken up as a first step towards the development of full fledged AWACS, the need for which was projected by the Services in early 1980s.

The 12 January 1999 crash of the prototype ASP could put India&#39;s AWACS program behind by three years, even though developers had completed about 90 per cent of the project. Some reports have blamed DRDO for selecting the &#39;unreliable&#39; Avro HS-748, but the officials say it was only an experimental platform. The crash, which killed all eight people on board including four scientists, was probably the result of fire or engine failure. Critics questioned whether the aircraft&#39;s twin Rolls-Royce Dart turbo-prop engines and metal-fatigued fuselage could withstand the modifications carried out in order to install a rotodome housing a radar on the top with the support of pylons. India does not build aircraft suitable for airborne surveillance; even the Avro was just a test platform. DRDO has contemplated building an operational system around a Russian aircraft, possibly the Il-76. Hindustan Aeronautics had produced 89 aircraft out of which 17 were meant for the Indian Airlines and the balance for the IAF. Though the Indian Airlines had phased out the aircraft in the interest of the passenger safety, the IAF continues to fly it not only as a military freighter but for the VIP duties in the Air Headquarters Communication Squadron. DRDO officials find it hard to believe the eyewitness accounts that the rotodome collapsed on the plane. The indigenous fabrication of the rotodome mounting had won the team the DRDO&#39;s&#39;outstanding contribution award&#39; in 1992, and no problem had been reported since. The ASP project was shelved in 1999 following the crash.

Studies and analyses began in July 1985 under project&#39;Guardian&#39;, later renamed &#39;Airawat&#39;. By the late 1980s an Avro had been modified with a 24 ft x 5 ft composite rotodome. The aircraft flew with a pylon (without the dome) in May 1989 and with the rotodome in November 1990. The Centre for Airborne Systems (CABS) was set up in February 1991, under Dr K. Ramchand to act as a system house and integration agency using all the expertise and infrastructure available in India. The project received public recognition when the aircraft was flown during the flight demonstrations at the inauguration ceremony of the first Aero India show held in Bangalore in December 1996. The Defence Research & Development Organisation, Ministry of Defence, provided the airborne surveillance platform to the Navy in August 1998. The program achieved success in most aspects, including airborne radar analysis, clutter (ground reflections) characterisation and measurement and developing a hybrid navigation system. The main challenge left was evolving the radar and support mission system avionics into a flying surveillance platform.

The antenna used in the rotodome of ASP is a low side lobe slotted wave guide planar array. The antenna features very low side lobe levels and a narrow beam width in azimuth. It handles high power (better than 3.3 KW average) and weighs 160 kg. For housing the primary and the secondary (IFF) antennas, an ellipsoidal structure (7.315 m x 1.524 m) rotodome has been indigenously fabricated. It largely comprises composites and aluminium alloy parts. The indigenous rotodome has since been successfully fabricated and flight tested on the ASP system. The rotodome is driven by a hydraulic servo system using aircraft hydraulic power.

The airborne radar data processor (ARDP), supporting track-while-scan, is required to form target tracks after receiving data from the various sensors of ASP, such as the primary radar (PR) and the secondary surveillance radar (SSR), which operate in TWS mode. The ARDP correlates the target plots from scan to scan to maintain the target tracks. It also performs the correlation of target information obtained from SSR and endorsement with the PR track information.

The ASP is guided by a high accuracy navigation system, which consists of an inertial navigation system (INS) and a Doppler navigation system. The velocity drifts of INS are contained by Doppler velocities using a Kalman filter, resulting in good navigation accuracy required for long duration flight of ASP. Work is in hand to integrate GPS receiver with INS to enhance performance, reliability and robustness.

The ASP project was shelved in 1999 following the 1999 crash.


As of 2005, India was working on developing another indigenous airborne early warning (AEW) system. According to the Defence Minister, Pranab Mukherjee, completion of development activities and commencement of user trials should occur in 2012. The aerial platform had not been chosen as of 2005 although the Brazilian Embraer was considered a contender.

Thanks,

Miro
 
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The Hs.748 AEW, takes-off from the Yelahanka AFS on 04 December 1996.


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Prototype of the Avro AEW on display at Yelahanka AFS during Aero India &#39;96.

Thanks,

Miro
 
Lakshya

Lakshya is a surface/ship launched high subsonic reusable aerial target system, remotely piloted from ground. It provides training to the gun/missile crew and to air defence pilots for weapon engagement. The country has reached self reliance in this class of unmanned Aerial Vehicles (UAVs). The Lakshya is a turbojet system designed as an RPV. India is also developing it as an air- or land-launched variant cruise missile system capable of carrying a 350 kg payload to a range of 600 kms. It was initially projected to enter service by 1998. By April 2002 the Pilotless Target Aircraft (PTA) Lakshya had been inducted by Indian Air Force and Indian Navy. The Lakshyas developed by the Defence Research and Development Organisation (DRDO) are fully operational with the users.

Training of pilots in air-to-air weaponry and target practice of surface-to-air missile batteries and guns is a regular peace time drill of all the three Services. In such training, certain amount of live firing practice is essential against realistic airborne targets for proper perception of actual threat parameters likely to be encountered. For this purpose, use of recoverable Pilotless Target Aircraft (PTA) with towed sub-targets had long been considered the most cost effective option. The PTA was also required for evaluation/development trials of new surface-to-air and air-to-air weapon systems.

Several indigenously developed payloads are now available for UAV applications, such as electro-optic imaging, laser ranging and designation system, airborne laser ranger and marker (ALARM), and airborne infra-red target sensor. The gimballed payload assembly (GPA), a two-axes stabilised platform for CCD camera and laser range finder payloads, has been developed to provide azimuth and elevation stabilisation of the sight line against aircraft motion and jitter. An advanced correlation technique-based video tracker has been integrated with this platform for automatic target tracking. The entire system can be installed on manned or unmanned aircraft. The system can also be configured to carry different electro-optic payload combinations.

Two types of scoring systems have been developed as a part of Lakshya aerial target tow body electronics for estimation of the miss distance. The acoustic miss distance indicator (AMDI), which utilises the over pressure produced by the supersonic projectile to estimate the miss distance, provides both distance and sector information. The other system is based on Doppler FM-CW radar principle.

Comprehensive capabilities have been established in all aspects of flight control design and engineering for unmanned air vehicles (UAVs) which include design of control laws, flight control electronics, sensors and actuators. Digital processors, software and analog flight control electronics and electromechanical actuators have been developed. The flight control electronics (FCE) for Lakshya aircraft employs an analog electronic design backed by an ASIC to perform flight control and recovery functions of the aircraft. In addition to altitude stabilisation and other flight control functions, the FCE also provides command and autopilot modes.

The need to develop PTA indigenously was identified in 1976. An Inter Services Qualitative Requirement (ISQR), common to the three Services, was formulated by a Working Group constituted by the Ministry of Defence in January 1977 and 35 ISQR points were identified. Subsequently, based on a feasibility study carried out by Aeronautical Development Establishment (ADE) , the project for the design and development of Inter-Services PTA by ADE, satisfying the ISQR was sanctioned by Government in September 1980 at a cost of Rs. 17 crore including a foreign exchange (FE) element of Rs. 8 crore. The development activity was planned for completion within five years. In parallel, a development project for indigenous development of PTA Engine (PTAE-7) was also sanctioned at an estimated cost of Rs.4.5 crore (FE Rs. One crore) to Hindustan Aeronautics Limited (HAL) in September 1980, based on a feasibility study and project proposal submitted by HAL. The engine was to be developed by HAL by September 1985, concurrently with the PTA.

At the time of conceptualising the PTA project, it was envisaged that development of PTA would be undertaken by ADE while the series production after successful development would be entrusted to HAL. As the Air Force and the Navy required PTA urgently, the Ministry decided in May 1994 and March 1995 that 10 PTA would be produced (five each for the Air Force and Navy) by ADE at a total cost of Rs.28.86 crore. Though the series production of PTA after its successful development was planned to be entrusted to HAL, DRDO did not transfer technology till 1997. Indian Air Force had received the phase I and II deliveries (3 aircraft, ground systems and expendables) in September 1999 and April, 2000. Indian Navy was scheduled to receive its first phase deliveries in November 2000. As per the projected requirement, during 1986-96, the Services should have required 935 (11x85) PTA for providing ideal air-to-air and surface-to-air weaponry target practices. Against this, a mere 25 PTA were imported between December 1985 and March 1995

Thanks,

Miro
 

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