The FMA SAIA 90 was a cancelled air superiority fighter aircraft project, designed by the FMA with the collaboration of Dornier in the mid-1980s. The SAIA 90 was the last stage of the ACA project, which was started by the National Reorganization Process to develop an Argentine fighter aircraft. The three stages of the project were:
By 1980 the Fabrica Militar de Aviones and Dornier had an ongoing relationship as a result of the combined development of the IA 63, and both were considered a cooperative agreement for the production of future airplanes. This agreement called to both parties to establish a common office in the city of Córdoba, Argentina within the year for the production, marketing and associated support services of their products. The development of a trainer was the first of three steps in Fábrica Argentina de Aviones' strategy, elaborated after the development of the IA 58 Pucará by the mid-1960s. The steps of this strategy included the Pampa, a light transport and a combat aircraft. The German maker produced a series of preliminary designs, which contemplated various aspects for a combat aircraft, which the air force could then adopt to its own requirements.
Description
The Dornier studies included analyses of the basic requirements, including air combat under anticipated operative conditions, and taking into account the characteristics of likely weapons. According to the analysis the aircraft should be capable of a sustained maneuvering speed of Mach 0.9 at an altitude of 6000 m; quick acceleration from Mach 0.9 to 1.5 at 9000 m, high deceleration, independent of the relative speed; reasonable combat autonomy with integral fuel tanks; and minimal radar and infrared signatures. Possible armament included:
The air-to-air radar was to be able to detect a 5 m2 target at a distance of 90 km without being detected by enemy ECM, and track 6 targets that could be identified with IFF. For air-to-ground attacks, the radar was to be able to map the terrain.
Configuration
Although it was desirable to achieve a combination of the advantages that a heavily loaded delta wing with low weight offers; the trans-sonic/subsonic turn rate, longitudinal stability and short field characteristics desired were impossible to combine into a single wing design. The opposing solution of commitment for the pattern, was the continuation of the border of attack of the wings that generated a vortex of high energy and it improved the aerodynamic yield notably in big angles of incidence. Another characteristic of the design was the artificial longitudinal stability that allowed equilibrating the airplane by means of the application of positive forces on the line planes. This way a direct wing was configured with big arrow angles, continuations in the union wing-fuselage and a double derives located before the stabilizers that it keeps certain likeness to the F/A-18C Hornet. Engines were two turbofan of 5600 kg of thrust Maximum speed was to ne around Mach 2. Empty weight was to be 7.800 kg. This relatively low value would be achieved by means of the use of compound materials. The experience of Dornier in these materials was wide. In the proposal for this airplane suggested the use in the wing of 65% Carbon-fiber-reinforced polymer, 20% aluminium and the rest in several materials as the titanium, the front fuselage would have 60% of CFRP, the central 18% and the bottom 10%, being completed with other materials employees in the wing, and the stabilizers would have 55% of CFRP, while the fin would take 70%, the same materials would be used for the intake ramps and the landing gear.
Terms of the project
The Fábrica Militar de Aviones estimated in about 12 to 15 years until crystallizing it from the moment the specifications they were approved, that in 1987 they were very high. In that time, the airplane would be able to replace the existent fighter fleet. The first flight of the prototype was foreseen later for 1989 and the deliveries two years later.
Looking for partners
By the middle of 1980 Fábrica Militar de Aviones faced serious financial difficulties, with a deficit of U$S 50 million annually. It searched for partners to face diverse business to allow it to survive, giving 49% of their property. It was evident that the factory could not complete the project by itself; it maintained diverse contacts, such as Aermacchi-Aeritalia, McDonnell Douglas and Fairchild, with the intention of attracting a partner with whom to share the project. Although the intention of the air force was to add McDonnell Douglas, which maintained negotiations for a possible license of production of the A-4M Skyhawk II and another one of ejection seats for the trainer IA 63 Pampa, but the American company resisted assuming the risk, because its offer of fighters was covered. Another possibility was explored then with Aeritalia-Aermacchi, but the financial problems that it crossed the country they made finally abandon the project.
Specifications
Role: multirole. Crew: 1, although there also would have been a 2-seat trainer version. Length: 15.53 m. Height: 3.96 m. Wing span: 10.95 m. Wing area: 30 m2. Wheelbase: 6.60 m. Empty weight: 7,800 kg. Max take-off weight: 14,500 kg. Max wing loading: 266.67 kg/m2. Max speed: Mach 2.25. Max climb rate: 15,000 m/min. Ceiling: 15,000 m. Range: 3380 km. Engine: 2 GE F404 turbofan. Armament: 11 hardpoints for a total of 5.000 kg : 4 under the fuselage, 2 under each wing, 2 wingtip and 1 central harpoint. It'd also had one revolver cannon 27 mm. Avionics: air-to-air radar capable to detect 5 m2 targets in a range of 90 km, 6-target multiple pursuit, 3D air-to-surface radar capable to receive the earth shape, digital flight control system, multi-function nav/attack system and secure communications. Cost: unknown but projected to be cheaper than 4.5th generation aircraft.
