AW609 vince gara negli Emirati Arabi battendo l'Osprey!

[Kimi]

L'Italiano AW609 si è aggiudicato la gara per un convertiplano SAR, contro l'unico concorrente l'americano V-22 Osprey, la scelta secondo al-Hashimi è dovuta al fatto che AW può stare in aria più tempo ed hà un raggio di azione di 1400Km con una velocità massima di 509Km/h.

[blobb]

L'Italiano AW609 si è aggiudicato la gara per un convertiplano SAR, contro l'unico concorrente l'americano V-22 Osprey, la scelta secondo al-Hashimi è dovuta al fatto che AW può stare in aria più tempo ed hà un raggio di azione di 1400Km con una velocità massima di 509Km/h.

ma come....... il v22 non era l'unico convertiplano in commercio???
mo vedrai la reazione di paulo...

[Kimi]

ma come....... il v22 non era l'unico convertiplano in commercio???
mo vedrai la reazione di paulo...

Ahahhaaa, aspettiamo domani cosa si inventa il trollone.
Mi sono dimenticato che la gara era per tre velivoli più opzione per altri tre.

[paulhowe]

ma come....... il v22 non era l'unico convertiplano in commercio???
mo vedrai la reazione di paulo...

Si lo e' infatti.

L'aw609 non e' operativo ne in produzione e non lo sara per i prossimi 3 anni.

[paulhowe]

Ahahhaaa, aspettiamo domani cosa si inventa il trollone.
Mi sono dimenticato che la gara era per tre velivoli più opzione per altri tre.

Me cojoni tre velivoli da consegnari nel 2019 !!!!


Porca che colpo ad effetto.


Ricordiamo al "trollone" come e' stato sviluppato l'AW609 perche lui "e un esperto" in queste cose.

https://en.wikipedia.org/wiki/AgustaWestland_AW609

The BA609 drew on experience gained from Bell's earlier experimental tiltrotor, the XV-15.^[1][2] In 1996, Bell and Boeing had formed a partnership to develop a civil tiltrotor aircraft; however, in March 1998, it was announced that Boeing had pulled out of the project. In September 1998, it was announced that Agusta had become a partner in the development program.^[1] This led to the establishment of the Bell/Agusta Aerospace Company (BAAC), a joint venture between Bell Helicopter and AgustaWestland, to develop and manufacture the aircraft

On 6 December 2002, the first ground tests of the BA609 prototype began, and the first flight took place on 6 March 2003 in Arlington, Texas, flown by test pilots Roy Hopkins and Dwayne Williams. After 14 hours of helicopter-mode flight testing, the prototype was moved to a ground testing rig to study the operational effects of the conversion modes.^[20] Following the completion of ground-based testing, on 3 June 2005 the prototype resumed flight testing, focusing on the expansion of its flight envelope.^[21] On 22 July 2005, the first conversion from helicopter to aeroplane mode while in flight took place.^[22]By October 2008, 365 flight-hours had been logged by two prototype aircraft.^[23] The AW609 demonstrated a safe dual-engine failure in normal cruise flight on 15 May 2009.^[24]By February 2012, this had risen to 650 hours, and it was reported that 85 percent of the AW609's flight envelope had been explored.^[18]
In 2011, AugustaWestland began construction of a third prototype; that prototype was still not fully assembled by February 2015. The company plans to conduct test flights in Italy in the summer of 2015. AugustaWestland will then disassemble it and ship it to Philadelphia, Pennsylvania, to prepare it for tests of the de-icing system in Minnesota. A fourth prototype, to be used in the development and testing of new avionics and control systems, was also underway.^[25][26] By November 2012, over 700 flight hours had been accumulated by the two operational prototypes.^[27] In January 2014, it was reported that in excess of 850 flying hours had been accumulated by the two prototypes; accumulated flight data is used to further develop representative simulators, which are in turn being used to support the development program

E ricordiamo sopratutto ai "trolloni" le prestazioni delle due macchine.


AW609
General characteristics[edit]

• Crew: 1 or 2
• Capacity: 6 to 9 passengers or 5,500 lb (2,500 kg) payload
  
  • Cabin height: 4 ft 8 in (1.42 m)
  • Cabin width: 4 ft 10 in (1.47 m)
  • Cabin length: 13 ft 5 in (4.09 m)
  
  
• Length: 44 ft (13.4 m)
• Height: 16 ft 3 in (5.0 m) nacelles vertical; 21 ft 10 in (6.7 m) nacelles horizontal
• Wingspan: 38 ft 5 in (11.7 m)
• Width with rotors: 60 ft 5 in (18.4 m)
• Rotor diameter: 25 ft 10 in (7.9 m) each
• Rotor area: 981.75 sq ft (91.2 m²)
• Empty weight: 10,483 lb (4,755 kg)
• Useful load: 5,500 lb (2,500 kg)
• Fuel: 2,480 lb (1,120 kg)^[94]
• Fuel burn: 1,000 lb (450 kg) per hour^[95]
• Max. takeoff weight: 16,800 lb (7,600 kg), 18,000 lb (8,200 kg) STOL
• Powerplant: 2 × Pratt & Whitney Canada PT6C-67A turboshaft, 1,940 shp (1,447 kW) each

Performance[edit]

• Maximum speed: 275 kn (509 km/h; 316 mph);^[81] 293 kn (543 km/h; 337 mph) tested^[31]
• Cruise speed: 260 kn (482 km/h; 299 mph)
• Range: 750 nmi (1,390 km; 860 mi). With external tanks: 1,100 nmi (2,000 km; 1,300 mi) ^[60]
• Ceiling: 25,000 ft (7,600 m),^[81] 6,000 ft (1,800 m) HOGE
• Rate of climb: 1,500 ft/min (7.6 m/s)
• Gravity load: +3.1, -1.0 g^[96]
• Disk loading: 15.8 lb/sq ft (77.1 kg/m²)

MV 22

General characteristics

• Crew: Four (pilot, copilot and two flight engineers/crew chiefs)
• Capacity:
  
  • 24 troops (seated), 32 troops (floor loaded), or
  • 20,000 lb (9,070 kg) of internal cargo, or up to 15,000 lb (6,800 kg) of external cargo (dual hook)
  • 1× Growler light internally transportable ground vehicle^[269][270]
  
  
• Length: 57 ft 4 in (17.5 m)
• Rotor diameter: 38 ft 0 in (11.6 m)
• Wingspan: 45 ft 10 in (14 m)
• Width with rotors: 84 ft 7 in (25.8 m)
• Height: 22 ft 1 in/6.73 m; overall with nacelles vertical (17 ft 11 in/5.5 m; at top of tailfins)
• Disc area: 2,268 ft² (212 m²)
• Wing area: 301.4 ft² (28 m²)
• Empty weight: 33,140 lb (15,032 kg)
• Loaded weight: 47,500 lb (21,500 kg)
• Max. takeoff weight: 60,500 lb (27,400 kg) (self-deploy/long runway)
  
  • Maximum rolling takeoff weight: 57,000 lb (STOL)
  • Maximum vertical takeoff weight: 52,600 lb^[51]

V-22's combat radius in Iraq, contrasted with the CH-46E's smaller combat radius.

• Powerplant: 2 × Rolls-Royce Allison T406/AE 1107C-Liberty turboshafts, 6,150 hp (4,590 kW) each

Performance

• Maximum speed: 275 knots (509 km/h, 316 mph^[271]) at sea level / 305 kn (565 km/h; 351 mph) at 15,000 ft (4,600 m)^[272]
• Cruise speed: 241 kn (277 mph, 446 km/h) at sea level
• Stall speed: 110 kn^[74] (126 mph, 204 km/h) in airplane mode
• Range: 879 nmi (1,011 mi, 1,627 km)
• Combat radius: 390 nmi (426 mi, 722 km)
• Ferry range: 1,940 nmi (2,230 mi, 3,590 km) with auxiliary internal fuel tanks
• Service ceiling: 25,000 ft (7,620 m)
• Rate of climb: 2,320–4,000^[74] ft/min (11.8 m/s)
• Glide ratio: 4.5:1^[74]
• Disc loading: 20.9 lb/ft² at 47,500 lb GW (102.23 kg/m²)
• Power/mass: 0.259 hp/lb (427 W/kg)

Ma guarda un po il mezzo viene costruito negli USA.

AgustaWestland to build AW609 in Philadelphia | Business Aviation News: Aviation International News


Fai il serio, trollone.