utorak, 6. travnja 2010.

Bombardier Global Express

The Bombardier Global Express is an ultra long range corporate and VIP high speed jet aircraft produced by Bombardier Aerospace. The Bombardier Global 5000 is a slightly shorter version. The Global Express has also been modified for military missions, such as the Raytheon Sentinel R1.

Bombardier Aerospace began studies in 1991 and the aircraft was officially launched in 1993. The first flight occurred on October 13, 1996.

The Global Express can fly intercontinental ranges without refueling (e.g. New York - Tokyo) or between most two points in the world with only one stop. In this class the Global Express competes with the Airbus Corporate Jet, Boeing Business Jet, Dassault Falcon 7X and Gulfstream G550.

Bombardier subsidiaries have three specific roles in the project: Canadair is the design leader and manufactures the nose; Short Brothers, Belfast is responsible for the design and manufacture of the engine nacelles, horizontal stabiliser and forward fuselage; and de Havilland Canada builds the rear fuselage and vertical tail and carries out final assembly. The major external supplier is Japan's Mitsubishi Heavy Industries which builds the wing and centre fuselage sections.

The Global Express is powered by two Rolls-Royce BR710 turbofans.


Global Express XRS

The Global Express XRS is an improved version of the original aircraft, offering higher cruise speed, increased range, improved cabin layout and lighting. It is reported that the letters have no significance, but were chosen by focus groups simply to improve the brand image. The range increase is achieved by addition of a 1,486 lb (674 kg) fuel tank at the wing root. The Global Express XRS entered service in early 2006. The unit price is estimated to be $45.5 million (US). Bombardier claims it takes 15 minutes less to fuel the XRS than the original model thanks to improved computer systems and mechanical refinements.

The Global 5000 is built on the same production line as the Global Express XRS, and the two types' serial numbers are intermingled.

Global 5000

The aircraft is manufactured by Bombardier Aerospace in Toronto, Canada, and flown "green" to Montreal, St. Louis or Savannah for final completion.

The Global 5000 can fly close to 5,000 nautical miles (9,300 km) nonstop at Mach .80. The average trip lengths for most operators is 2.5 hours where the aircraft will cruise between Mach .85 and Mach .89, making it one of the fastest long range jets available today.

Typical configuration features 18 passenger seats including fully berthable seats and an aft lounge/bedroom. The aircraft has a full galley and two lavatories. The crew rest area was removed, but is being considered on newer versions).

Originally, the maximum takeoff weight was 89,700 lb (40,700 kg). With typical equipment and passenger accoutrements, the empty weight was 52,000 - 55,000 pounds (22600 – 25000 kg). In April 2008, Bombardier announced that the certified gross weight had been increased to 92,500 lb (41954 kg), which permitted an increased fuel load - projected maximum range increased to 5,200 nm (9637 km).

The maximum certified altitude is 51,000 ft (16,000 m) The typical approach speed is 108 knots (200 km/h) requiring approximately 2,600 feet (790 m) of runway for landing.

Specifications

Global Express XRS

General characteristics

  • Crew: Two (minimum) - four (typical)
  • Capacity: 8-19 passengers
  • Length: 99 ft 5 in (30.3 m)
  • Wingspan: 94 ft 0 in (28.65 m)
  • Height: 24 ft 10 in (7.57 m)
  • Wing area: 1,022 ft² (94.9 m²)
  • Empty weight: 49,750 lb (22,600 kg)
  • Useful load: 1,775 lb (w/full fuel) (805 kg)
  • Max takeoff weight: 99,500 lb (44,500 kg)
  • Powerplant: 2× Rolls-Royce Deutschland BR710A2-20 turbofans, 14,750 lbf (65.5 kN) each
  • Cabin length: 48 ft 4 in (14.73 m)
  • Cabin max width (centerline): 8 ft 2 in (2.49 m)
  • Cabin max width (floorline): 6 ft 11 in (2.11 m)
  • Cabin height: 6 ft 3 in (1.91 m)
  • Cabin floor area: 335 ft² (31.1 m²)

Performance


Global 5000

General characteristics

  • Crew: Two - Three
  • Capacity: 8-17 passengers
  • Length: 96.8 ft (29.5 m)
  • Wingspan: 94 ft 0 in (28.65 m)
  • Height: 25.5 ft (7.7 m)
  • Wing area: 1,882 ft² (53.29 m²)
  • Useful load: 1,775 lb (w/full fuel) (805 kg)
  • Max takeoff weight: 92,750 lb (42,071 kg)
  • Powerplant: 2× Rolls-Royce Deutschland BR710A2-20 turbofans, 14,750 lbf (65.6 kN) each
  • Cabin length: 42.47 f (12.94 m)
  • Cabin width (centerline): 8.17 ft (2.49 m)
  • Cabin width (floorline): 6.92 ft (2.11 m)
  • Cabin height: 6.25 ft (1.91 m)
  • Cabin floor area: 317 ft² (29.4 m²)
  • Cabin Total Volume 1,884 ft³ (53.9 m³)

Performance

  • Maximum speed: Mach .89 (513 kt, 590 mph, 950 km/h)
  • Cruise speed: Mach .85 (488 kt, 562 mph, 904 km/h)
  • Range: 5,200 nm (9,360 km)
  • Service ceiling: 51,000 ft (15,554 m)
  • Basic Operating Weight: 50,840 lb (23,061 kg)
  • Maximum Ramp Weight: 92,750 lb (42,071 kg)
  • Maximum Takeoff Weight: 92,500 lb (41,957 kg)
  • Maximum Zero Fuel Weight: 56,000 lb (25,401 kg)
  • Maximum Fuel Weight 39,250 lb (17,804 kg)
  • Balanced field length (SL, ISA, MTOW): 5,540 ft (1,689 m)
  • Landing distance (SL, ISA, MLW): 2,670 ft (814 m)

Avionics

  • Rockwell Collins Pro Line Fusion avionics suite
  • Four 15.1-inch (38.4 cm) Liquid Crystal Display (LCD) screens
  • Head-Up Guidance System (HGS)
  • BEVS - Bombardier 3rd generation Enhanced Vision System
  • Data Link
  • SATCOM: triple channel Inmarsat, single channel Iridium
  • Ethernet-based Cabin Electronic System with on-board Local Area Network
  • Single channel high-speed data, printer/fax
  • Onboard Maintenance Systems(OMS)
    • Integrated within the Multi-Function Display (MFD)
    • Remote Maintenance Diagnostic
    • Fault Isolation using Boolean logic
    • NVM download
    • Real Time Parameter Display
    • Engine Trends and Exceedances
    • Aircraft Life Cycle Counters
    • LRU Tests, Rigging, and Calibration


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petak, 2. travnja 2010.

B-1 Lancer

The Rockwell (now part of Boeing) B-1 Lancer is a strategic bomber used by the United States Air Force. First envisioned in the 1960s as a supersonicbomber with sufficient range and payload to replace the B-52 Stratofortress, it developed primarily into a low-level penetrator with long range and supersonic speed capability. Its development was stopped and restarted multiple times over its history, as the theory of strategic balance changed from flexible responseto mutually assured destruction and back again. It eventually entered service more than 20 years after first being studied.

The B-1B production version has been in service with the United States Air Force (USAF) since 1986. The Lancer serves as the supersonic component of the USAF's long-range bomber force, along with the subsonic B-52 and B-2 Spirit. The bomber is commonly called the "Bone" (originally from "B-One"). With the retirement of the EF-111 Raven in 1998 and the F-14 Tomcat in 2006, the B-1B is the U.S. military's only active variable-sweep wing aircraft.

The first post-B-70 study was known as the Subsonic Low Altitude Bomber (SLAB), which was completed in 1961. This was followed by the similar Extended Range Strike Aircraft (ERSA), which added a variable-sweep wing planform, something then very much in vogue in the aviation industry. ERSA envisioned a relatively small aircraft with a 10,000 lb (4,500 kg) load and a range of 8,750 nautical miles (16,200 km), with 2,500 nmi (4,600 km) being flown at low altitudes. In August 1963 the similar Low-Altitude Manned Penetrator (LAMP) design was completed, which called for an aircraft with a 20,000 lb (9,000 kg) load and somewhat shorter range of 7,150 nautical miles (13,200 km).

These all culminated in the October 1963 Advanced Manned Precision Strike System (AMPSS), which led to industry studies at Boeing, General Dynamics, and North American. In mid-1964, the USAF had revised its requirements and retitled the project as Advanced Manned Strategic Aircraft (AMSA), which differed from AMPSS primarily in that it also demanded a high-speed high-altitude capability, albeit slower than the Valkyrie at about Mach 2. Given the lengthy series of design studies, Rockwell engineers joked that the new name actually stood for "America's Most Studied Aircraft".

The B-1 has a blended wing body configuration, with variable-sweep wing, triangular fin control surfaces and four turbofan engines, to improve range and speed with enhancedsurvivability. Forward-swept wing settings are used for takeoff, landings and high-altitude maximum cruise. Aft-swept wing settings are used in high subsonic and supersonic flight. The wings of the B-1B originally were cleared for use at settings of 15, 25, 55 and 67.5 degrees. The 45-degree setting was later cleared in 1998–99 timeframe. The length of the aircraft presented a serious flexing problem due to air turbulence at low altitude. To alleviate this, Rockwell included small canards near the nose on the B-1. An accelerometer would actuate the canards automatically to counteract turbulence and smooth out the ride.

Unlike the B-1A, the B-1B made no attempt at Mach 2+ speeds. Its maximum speed at altitude is Mach 1.25 (about 950 mph or 1,530 km/h), but its low-level speed increased to Mach 0.92 (700 mph, 1,130 km/h). Technically, the current version of the aircraft can exceed its speed restriction, but not without risking potential damage to its structure and air intakes. To help lower its radar cross section (RCS), the B-1B uses fixed air intake ramps with serpentine baffles, which limit its speed compared to the B-1A.

The B-1's defensive electronics include the Eaton AN/ALQ-161 radar warning and defensive jamming equipment, linked to a total of eight AN/ALE-49 flare dispensers located on top behind the canopy, which are handled by the AN/ASQ-184 avionics management system. The AN/ALE-49 dispenser has a capacity of 12 MJU-23A/B flares each. The MJU-23A/B flare is one of the world's largest infrared countermeasure flares having a gross weight of ~1170 g. The cylindrical Magnesium/Teflon/Viton pellet has a net weight of ~1470 g. The Plans for a defensive systems upgrade program (DSUP) were canceled for budgetary reasons. The B-1 has also been equipped to carry the ALE-50 Towed Decoy System. The Lancer has an additional Doppler tail-warning radar to detect aircraft or missiles approaching from the rear.

Also aiding the B-1's survivability is its relatively low radar cross-section (RCS). Although not technically a stealth aircraft in a comprehensive sense, thanks to the aircraft's structure, serpentine intake paths and use of radar-absorbent material its RCS is about 1/50th that of the B-52 (probably about 26 ft² or 2.4 m²), although the Lancer is not substantially smaller in mass than the Stratofortress.













Specifications (B-1B)

General characteristics

  • Crew: 4 (aircraft commander, copilot, offensive systems officer and defensive systems officer)
  • Payload: 125,000 lb (56,600 kg) ; internal and external ordnance total
  • Length: 146 ft (44.5 m)
  • Wingspan:
    • Extended: 137 ft (41.8 m)
    • Swept: 79 ft (24.1 m)
  • Height: 34 ft (10.4 m)
  • Wing area: 1,950 ft² (181.2 m²)
  • Airfoil: NA69-190-2
  • Empty weight: 192,000 lb (87,100 kg)
  • Loaded weight: 326,000 lb (148,000 kg)
  • Max takeoff weight: 477,000 lb (216,400 kg)
  • Powerplant: 4× General Electric F101-GE-102 augmented turbofans
    • Dry thrust: 14,600 lbf (64.9 kN) each
    • Thrust with afterburner: 30,780 lbf (136.92 kN) each
  • Fuel capacity, optional: 10,000 U.S. gal (38,000 L) fuel tank for 1-3 internal weapons bays each

Performance

Armament

Avionics

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