Dassault Mirage 4000 Jet Fighter Aircraft PhotosThe Mirage 4000 made use of the aerodynamic source computer control system with a fly-by-wire active and a center of gravity backwards. It was designed to be easy to maintain at airports forward. They also had a variable incidence sweptback foreplanes blister and a cockpit with a field of view of 360 °. Compounds of boron and carbon fiber is widely used in the fin, rudder, flaps, fuselage panels access foreplanes and elsewhere.
The wings were large radius root fairings. The entire trailing edge of each wing flaps was taken by two sections. Variable inclination was provided by fully automatic edge-span flaps. The rear fuselage was shorter, which made Karman fairings unnecessary. The rudder, ailerons, flaps and control system drives the fly-by-wire. The vertical fin was made of the fuel tanks and contents of carbon composite, which helped make the 4000 about three times more internal fuel as the Mirage 2000 (from other fuel tanks were on the wings and fuselage).
The fuselage was of conventional semi-monocoque structure. Type air brake door is in each intake trunk above the edges of the main wings. The tricycle landing gear was designed by Messier-Hispano-Bugatti and had twin nose and a single wheel on each unit. Each had a moving average intake centerbody cone. The two M53s provided a thrust-to-weight off 1:01 - if you had entered service, it would have been equivalent to the F-15 or Su-27.
Wherever possible, avionics systems and adapted to the Mirage 2000. The hydraulic system was made by Messier-Hispano-Bugatti, and was pressurized to 280 bars (4,000 lb / sq in). It was powered by four advanced pumps and used lightweight titanium pipelines. The Mirage 4000 Auxilec also used two electric generators. In a compartment behind the pilot was a Palouste Turbomeca gas turbine APU (to start the engines).
The prototype uses the same RDM multi-mode Doppler radar as the Mirage 2000, but radar as large as 80 cm (31.5 in) in diameter, could fit in the dome of the big nose. Other avionics included a digital autopilot, multi-mode displays, a SAGEM Uliss INS 52, Crouzet type 80 air data computer, a VE-130 HUD Thomson-CSF, and an automated digital delivery system of weapons.
The wings were large radius root fairings. The entire trailing edge of each wing flaps was taken by two sections. Variable inclination was provided by fully automatic edge-span flaps. The rear fuselage was shorter, which made Karman fairings unnecessary. The rudder, ailerons, flaps and control system drives the fly-by-wire. The vertical fin was made of the fuel tanks and contents of carbon composite, which helped make the 4000 about three times more internal fuel as the Mirage 2000 (from other fuel tanks were on the wings and fuselage).
The fuselage was of conventional semi-monocoque structure. Type air brake door is in each intake trunk above the edges of the main wings. The tricycle landing gear was designed by Messier-Hispano-Bugatti and had twin nose and a single wheel on each unit. Each had a moving average intake centerbody cone. The two M53s provided a thrust-to-weight off 1:01 - if you had entered service, it would have been equivalent to the F-15 or Su-27.
Wherever possible, avionics systems and adapted to the Mirage 2000. The hydraulic system was made by Messier-Hispano-Bugatti, and was pressurized to 280 bars (4,000 lb / sq in). It was powered by four advanced pumps and used lightweight titanium pipelines. The Mirage 4000 Auxilec also used two electric generators. In a compartment behind the pilot was a Palouste Turbomeca gas turbine APU (to start the engines).
The prototype uses the same RDM multi-mode Doppler radar as the Mirage 2000, but radar as large as 80 cm (31.5 in) in diameter, could fit in the dome of the big nose. Other avionics included a digital autopilot, multi-mode displays, a SAGEM Uliss INS 52, Crouzet type 80 air data computer, a VE-130 HUD Thomson-CSF, and an automated digital delivery system of weapons.
