F22 опять очень плох

[wind]

Тест-пилот сказал, а мы поверили?
Чтобы летать с М2.42, планер надо делать из стали и титана, а не из угля и алюминия, и очень желательно иметь регулируемый ВЗ.

- Так и расскажите, спецьялист, а почему - ещё и из стали? (титана там и так до хрена и больше).
http://www.globalsecurity.org/milita...ft/f-22-mp.htm
Есть и сталь маненько, куда ж совсем без неё?
Raptor materials
Traditional aircraft materials such as aluminum and steel make up about 20% of the F-22 structure by weight. Its high-performance capabilities require significant amounts of titanium (42% of all structural materials by weight) and composite materials (24% by weight). These are stronger and lighter than traditional materials, and offer better protection against corrosion. Titanium also offers tolerance to higher temperatures. In fact, titanium accounts for a larger percentage of the structural weight on the F-22 than any other current U.S. fighter.

The forward fuselage is just over 5.2 m (17 ft) long, slightly more than 1.5 m (5 ft) wide at its widest point, 1.7 m (5 ft 8 in.) tall, and weighs about 770 kg (1700 lb). Built up in two sections, the forward fuselage is joined together by two long and relatively wide side beams and two longerons that run the length of the assembly. The beams, which are made of composite materials, also provide an attachment point for the "chine," the fuselage edge that provides smooth aerodynamic blending into the intakes and wings. The 5.2 m (17 ft.) long aluminum longerons form the sills of the cockpit, and the canopy rests on them.
The canopy is about 356 cm long, 114 cm wide, 70 cm tall (140 x 45 x 27 in.), and weighs about 160 kg (360 lb). it is the largest piece of monolithic polycarbonate material being formed today. It is made of two 0.9 cm (0.375 in.) thick sheets that are heated and fusion-bonded, then drape-forged. It has no canopy bow, and offers superior optics throughout, as well as the requisite stealth features.
The mid-fuselage is also about 5.2 m (17 ft long), 2 m (6 ft) high, and weighs about 3900 kg (8500 lb). Almost all systems pass though this section, including hydraulic, electrical, environmental control, fuel, and auxiliary power systems. It also includes three fuel tanks, four internal weapons bays, and the 20-mm cannon. Only 35% of the mid-fuselage structure is aluminum. Composites make up 23.5%, and titanium is nearly 35%. The lower keel chord is a Ti6-22-22 alloy forging that weighs about 18 kg (40 lb). The four bulkheads are made of titanium Ti6-4; one of these is the largest single titanium part ever used on an aircraft.
The aft fuselage is 67% titanium, 22% aluminum, and 11 % composite by weight. It measures 5.8 in long by 3.6 m wide (19 x 12 ft), and weighs 2270 kg (5000 lb). About 25% by weight of the aft fuselage is comprised of large electronbeam-welded titanium forward and aft booms. The largest is the forward boom, which is more than 3 m (10 ft) long and weighs about 300 kg (650 lb). The welded booms reduce the need for traditional fasteners by about 75%.
The wings are composed of 42% titanium, 35% composites (including the skin), and 23% aluminum, steel, and other materials in the form of fasteners, clips, and other miscellaneous parts. Each wing weighs approximately 900 kg (2000 lb) and measures 4.8 in (16 ft) on the side-of-body, by 5.5 m (18 ft) along the leading edge. After analyzing the results of live-fire tests that simulated severe combat damage, engineers chose to reinforce the wing by replacing every fourth composite spar with one made of titanium. This reinforcement ensures that the F-22 will be even more survivable in combat situations.
The empennage consists of the vertical and horizontal tails. The verticals are a multi-spar configuration internally, and have a HIP'ed cast rudder actuator housing. The edges and rudder are made of composites, and have embedded VHF antennas. The horizontal surfaces, known as stabilators, are made of honeycomb materials with composite edges. They are movable assemblies, and are deflected by the composite pivot shaft described below.
The main landing gear is made of Carpenter Technology's Airmet 100 steel alloy. It is one of the first applications of a steel that has been specially heat treated to provide greater corrosion protection to the main gear piston axle.

http://kursy.rsuh.ru/aero/html/kurs_567_0.html
Температура атакующих кромок на высоте 11 км и М=2.42, равняется 197 градусов Цельсия. При такой температуре титан совершенно не теряет прочностных свойств.
Так что, сталь там на фиг ещё не нужна.