I-38
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| Trinovantan Aerospace Systems I-38 | |
|---|---|
| Role | Air superiority |
| National origin |  Trinovantum
|
| Manufacturer | Trinovantan Aerospace Systems |
| First flight | June 9, 1990 |
| Introduction | March 14, 1995 |
| Status | In service |
| Primary user | Imperial Air Force of Temuair |
The Trinovantan Aerospace Systems Inc. (TAS) I-38 is a lightweight, supermaneuverable, single-engine canard compound-delta wing fighter aircraft designed for the Trinovantan Air Force to replace the older and less capable I-36 light fighter. Key features of the new aircraft include heavy use lightweight CFC materials in construction, a highly reclined (35 degrees from vertical) ejection seat to reduce the effect of G forces on the pilot, and a three-paddle thrust vector control nozzle for the engine.
Development
Development of the I-38 started with Air Force Operational Requirement 4.84. AFOR 4.84 outlined the requirements of a future aircraft that would replace the I-36, as the I-36’s performance was deemed inadequate after cross-testing against the Aisling Athar L-5B in 1983.
[wip]
Design
Overview
The I-38 is a supersonic, single-engine, highly maneuverable fighter aircraft. It is both smaller and lighter than most of its contemporary competitors. Much like TAS’s previous I-34, the I-38 has a canard compound-delta wing configuration. The combination of Thrust Vector Control (TVC), low wing loading, relaxed stability design, and a high thrust to weight ratio make the I-38 an extremely nimble and responsive aircraft. A frameless bubble canopy gives the pilot an unobstructed view around the aircraft, while the reclined seat and side mounted stick and throttle reduce the effect of the g-forces on the pilot from the strenuous maneuvering the aircraft is capable of.
The airframe features a composite construction, with 72% of the aircraft being made of either CFRP or GRP composites with the remainder of the airframe being made of aviation-grade aluminium and titanium alloys. The extensive use of composites results in an aircraft that is both light and sturdy, with an recommended airframe service-life of 6500 flight-hours. It is capable of 9g maneuvers at both high and low speeds with a full internal fuel and air-combat load.
Cockpit
The I-38’s cockpit takes many cues from the Athar L-5 tested in 1983. It features an all-glass cockpit with a frameless bubble canopy. The canopy provides an unobstructed 360 degree view around the aircraft, with a 32 degree look-down angle over the sides and a 16 degree angle over the nose. The canopy is constructed of thick polycarbonates that can effectively protect against bird-strikes and light shrapnel. Since the canopy is frameless, the entire canopy is explosively jettisoned prior to ejection. Access to the cockpit is provided by an internally stowable ladder.
The seat is reclined at a significant (35 degree) angle, providing a notable increase to effective G-tolerance. Due to the high reclination of the seat, the aircraft is capable of accommodating taller pilots. Flight controls consist of an arm-rested Hand On Stick And Throttle (HOTAS) and conventional rudder pedals. A large portion of both flight and combat controls are present on the flight stick, simplifying the operation of the aircraft.
Information is provided to the pilots via a wide-angle Heads Up Display (HUD) and a set of three LCD Multi-Function Displays (MFDs). The entire cockpit is compatible with night vision devices. The Block 5 upgrade adds compatibility for TAS’s Helmet Integrated Targeting System, allowing for extreme off-boresight targeting.
Avionics
[wip] RADAR overview
Navigation systems
Misc Sensors and Countermeasure Systems
Datalink and Sensor Fusion capabilities
Propulsion
The I-38 uses the UEA F-390/90-95V afterburning turbofan engine, rated for 95 kN of thrust. This is essentially same engine as UEA F-390/90-95 mounted on the I-34 but with its conventional nozzle replaced by 3 large TVC paddles. The use of paddle-type TVC as opposed to a movable nozzle was a compromise made to simplify maintenance, as the paddles could be easily replaced if rendered defective. The simplified export model of the I-38 uses the UEA F-390/90-95 equipped with a conventional nozzle.
Operational History
Variants
- XI-38: Prototype
- YI-38: Various pre-production models
- I-38: Initial service model
- T-38: Two seat advanced trainer
- I-38/5: Software compatibility update for HMD and advanced SRAAMs
- I-38/15: New AESA RADAR, improved all-aspect MAWS, DIRCM mount, high bandwidth datalink compatibility
- I-38E: Export model of the I-36/0, no TVC paddles and a simplified flight control system
- I-38E/10: addition of HMD and Advanced missile software compatibility, AESA RADAR, improved all-aspect MAWS.
Operators
Current
Past
Specifications (I-38/15)
General characteristics
- Crew: 1
- Length: 15.08 m ()
- Wingspan: 9.15 m (w/o wingtip missiles: 8.75 m) ()
- Height: 4.5 m ()
- Wing area: 25.6 m² ()
- Empty weight: 5700 kg ()
- Loaded weight: 8100 kg ()
- Max. takeoff weight: 13500 kg ()
- Powerplant: 1 × UEA F-390/90-95V Thrust vectoring afterburning turbofan
- Dry thrust: 64 kN ()
- Thrust with afterburner: 95 kN ()
Performance
- Maximum speed:
- At sea level: Mach 1.0 (915 mph, 1,470 km/h)
- At altitude: Mach 1.8 (2,230 km/h)
- Combat radius: 510 km () Combat Air Patrol
- Ferry range: 2650 km () with drop tanks
- Service ceiling: 17,000 m ()
- Rate of climb: ~280 m/s ()
- Wing loading: 316.4 kg/m2 ()
- Thrust/weight: 1.20
- Maximum g-load: +9.0 g
Armament
- Guns: 1 x 25 mm revolver cannon
- Hardpoints: 2 × wing-tip air-to-air missile launch rails, 4 × under-wing, and 1 × under-fuselage pylon stations with a capacity of up to 5,400 kg of stores