Design
HJT-36 uses light alloys and composites, with a conventional low wing design with 18° leading edge sweepback and a 9.8m wingspan. It features a hydraulically retractable tricycle-type landing gear. The single-wheeled main units retract inward and the twin nose wheel unit retracts forward. About a quarter of the aircraft's line replaceable units are common between it and the HAL Tejas trainer variant.
In the cockpit, the HJT-36 has a conventional tandem two-seat configuration with the trainee pilot forward and the instructor in the raised seat to the rear. The single-piece canopy gives both pilots good, all-round vision. The prototype aircraft used Zvesda K-26LT lightweight zero-zero ejection seats. However, these may be replaced with Martin-Baker Mk.16 IN16S seats, due to a price escalation of the former. The pilots have both conventional and manual flight controls.
The trainer has a full glass cockpit with a layout similar to current generation combat aircraft. It uses an integrated digital avionics system from GE Aviation Systems. Active matrix liquid crystal multi-function displays from Thales and GE Aviation were evaluated. Head-up display and repeater is sourced from Elbit Systems. The instructor's station in the rear cockpit has a data entry display panel. The aircraft also has dual VHF and UHF communications systems.
The aircraft has five external hardpoints for weapons-training. There is one centre-line hardpoint under the fuselage and two weapon pylons under each wing for carrying rockets, gun pods and bombs. The maximum external payload is 1,000 kg.
The prototype aircraft were initially powered by a SNECMA Turbomeca Larzac 04-H-20 non-afterburning turbofan developing 14.12 kN of thrust. All production models will use the more powerful NPO Saturn AL-55I engine with about 16.9 kN of thrust, as stipulated by the 2005 air staff requirements from the Air Force.
Read more about this topic: HAL HJT-36 Sitara
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