Design work on the IAI-1126 Galaxy, initially called the Astra Galaxy, began in the early 1990s, based on the wing design on the swept high speed unit of the IAI-1125 Astra SP, but otherwise a completely new design. By the formal announcement of the programme launch in September 1993, the name Galaxy was adopted. The prototype IAI-1126 Galaxy was flown first on 25 December 1997. A second prototype flew on 21 May 1998, while the third aircraft first flew on 24 September that year. US FAA and Israeli certification was issued in December 1998. The first customer aircraft was handed over on 17 January 2000. The aircraft is powered by Pratt & Whitney Canada PW-306A turbofans.

Gulfstream G200 Article

The IAI-1126 Galaxy was originally marketed and supported by Galaxy Aerospace Inc. After Galaxy Aerospace Inc. was acquired by Gulfstream Aerospace Corporation in 2001, the IAI-1126 Galaxy was rebranded Gulfstream G200.

The cabin length is 24 feet 5 inches and 6 feet 3 inches high, with interior seating for 8 to 10 passengers. Its glass cockpit, featuring the Rockwell Collins ProLine 4 avionics suite, presents system status flight information on 7.25 inch-square displays, and colour weather radar with turbulence detection, the TCAS II (traffic alert and collision-avoidance system), and an EGPWS (Enhanced Ground Proximity Warning System) with wind shear detection. Gulfstream also offers an optional auto-throttle system to reduce pilot workload for improved safety.
Powered by two Pratt & Whitney Canada 306A engines controlled by a dual-channel FADEC (full authority digital engine control), the G200 is able to fly at speeds up to Mach 0.85 and at cruising altitudes up to 45,000 feet. Since joining the Gulfstream fleet in 2001, the G200 has benefited from several improvements, including a redesigned interior, a sound-proofing package and an aggressive weight-reduction program. The G200 offers several layout options and a competitive warranty. This large-cabin, mid-range aircraft can be tailored to meet individualized mission requirements.
The G200 received a Type Certificate from the European Aviation Safety Agency (EASA) on Sept. 7, 2004, an on June 4, 2008, the 200th G200 rolled out.

Israel Aircraft Industries is a shareholder in Galaxy Aerospace in U.S.A., which promotes the Astra SPX and promotes and fits out the new Galaxy wide-body bizjet developed by IAI.

IAI Galaxy
Engines: 2 x Pratt & Whitney Canada PW 306 A, 27959 N / 2850 kp
Length: 62.238 ft / 18.97 m
Height: 21.424 ft / 6.53 m
Wingspan: 58.104 ft / 17.71 m
Wing area: 368.99 sq.ft / 34.28 sq.m
Max take off weight: 34839.0 lb / 15800.0 kg
Weight empty: 18698.4 lb / 8480.0 kg
Max. speed: 470 kts / 870 km/h
Cruising speed: 432 kts / 800 km/h
Service ceiling: 45000 ft / 13716 m
Wing loading: 94.51 lb/sq.ft / 461.0 kg/sq.m
Maximum range: 3618 nm / 6700 km
Crew: 2
Payload: 8-19 (max. 2180kg)

G200
Engines: 2 x Pratt & Whitney PW306A, 6,040 lbs / 26.87 kN
Height: 21 ft, 5 in / 6.53 m
Length: 62 ft, 3 in / 18.97 m
Wingspan: 58 ft, 1 in / 17.70 m
Basic Operating weight: 19,950 lbs / 9,049 kg
Maximum Fuel: 15,000 lbs / 6,804 kg
Maximum Landing weight: 30,000 lbs / 13,608 kg
Maximum Payload weight: 4,050 lbs / 1,837 kg
Maximum Payload/Full fuel: 650 lbs / 295 kg
Maximum Ramp weight: 35,600 lbs / 16,148 kg
Maximum Takeoff weight: 35,450 lbs / 16,080 kg
Maximum Zero Fuel: 24,000 lbs / 10,886 kg
Long Range Cruise Mach 0.75
Mmo Mach 0.85
Normal Cruise Mach 0.80
Range at LRC 3,400 nm / 6,297 km
Range at Normal Cruise 3,050 nm / 5,649 km
Takeoff distance MAUW: 6,080 ft. / 1,853 m
Baggage Volume (Gross): 150 cu ft / 4.25 cu m
Cabin Length: 24 ft 5 in / 7.44 m
Cabin Volume: 868 cu ft / 24.56 cu m
Height: 6 ft 3 in / 1.91 m
Width: 7 ft 2 in / 2.18 m

A swept-wing development of the earlier Westwind (itself derived from the jet Commander, a US-design), the Astra business aircraft first flew on 19 March 1984, with deliveries beginning in June 1986. Astra Jet Corporation in the USA undertook marketing and support of the aircraft which has been produced at the rate of one per month since January 1988. The aircraft incorporates composite structure and a Sigma 2 aerofoil wing section. The rear-mounted turbofans are 3,650 lb st (16,23 kW) Garrett TFE731-3A-200Gs.

Gulfstream 100 / C-38 / IAI 1125 Astra Article

In 2001, Gulfstream acquired Galaxy Aerospace and with it, the mid-size Astra SPX and super mid-size Galaxy, which were later rebranded the G100 and G200, respectively.
In 2006, the 22-year production run of the G100 ended and the G150 entered service to take its place.

IAI 1125 Astra
Length: 55.446 ft / 16.9 m
Height: 18.045 ft / 5.5 m
Wingspan: 52.493 ft / 16.0 m
Wing area : 316.462 sqft / 29.4 sqm
Max take off weight : 23505.3 lb / 10660.0 kg
Weight empty : 12789.0 lb / 5800.0 kg
Max. weight carried : 10716.3 lb / 4860.0 kg
Max. speed : 465 kts / 862 km/h
Landing speed : 92 kts / 171 km/h
Cruising speed : 432 kts / 800 km/h
Initial climb rate : 3543.31 ft/min / 18.00 m/s
Service ceiling : 44997 ft / 13715 m
Wing load : 74.42 lb/sq.ft / 363.00 kg/sq.m
Range : 3110 nm / 5760 km
Engine : 2 x TFE 731 3A , 1627 shp
Crew : 2
Payload : 6-9pax

Gulfstream 100
Mmo: 0.875 Mach.
Cruise: M0.82-0.84 (470 to 480 kt).
Seats: 10.
Range IFR: 2,950 nm

Gulfstream completed the Gulfstream V Integration Test Facility and rolled out the GV – the first ultra-long range business jet – in 1995, which first flew in November 1995.

Gulfstream G-5 Article

The GV demonstrator flew a distance of 7999 mi / 12,973 km non-stop on 10 January 1997, carrying four crew and three passengers. In 1997, Gulfstream began the simultaneous manufacture of two different aircraft models – the GIV-SP and the GV. Within a few months of the GV’s first delivery in June 1997, it set nearly 40 city-pair and/or speed and distance records, and its industry team was awarded the 1997 Robert J. Collier Trophy, the highest honor in aeronautics or astronautics in North America.

The GV features a six-screen Honeywell SPZ-8500 electronic flight instrumentation system (EFIS).

New Gulfstream V global business jet; also forms the platform for an ASTOR contender under Lockheed Martin leadership.

In 2001 the USAF leased five Gulfstream Vs as C-37As.

Mid-2001 the GV-SP advanced long-range business jet made its first flight. The prototype went to 41,000 ft and flew near to M0.8.

Engines 2 x 12,420-lb. s.t. Rolls-Royce Tay turbofans.
Gross wt. 70,200 lb
Empty wt. 33,400 lb
Seats 14-24.
Fuel capacity 4,340 USG.
Top speed 564 mph.
Economy cruise 528 mph.
Stall 121 mph.
Ceiling 45,000 ft
Range 4,952 miles
Takeoff run 5,100 ft.
Landing roll 3,200 ft.

Engines: 2 x BMW R-R BR 700 Srs.
Cruise: 0.885M.
Max cruise alt: 51,000ft.
Range: 6500 nm.
Endurance: 14.5 hr.
Crew: 4.
Pax capacity: 8.

In 1982 the company’s name changed to Gulfstream Aerospace Corp. to reflect its worldwide scope, and a new plane, the Gulfstream IV, was conceived.

Gulfstream G 1159 G-IV Article

Launched on 19 April 1983, and first flown in September 1985, the Gulfstream IV received its certification by the FAA on 22 April 1987, and went into full production at the Savannah facility of Chrysler Corp subsidiary Gulfstream Aerospace Corp. A twin turbofan executive transport, although generally similar to the Gulfstream III, the IV includes a redesigned wing, a lengthened fuselage with a sixth window on each side and two 13,850 lb st (61,6 kN) R-R Tay Mk.611-8 turbofans. The cockpit incorporates advanced CRT displays and digital avionics.
At the time of certification, the company held orders for more than 100 Gulfstream IVs and by the end of May 1987 had delivered 16 aircraft. The complete flight management system, including EFIS, is included in the GIV during production, but, as is customary for corporate aircraft, they are delivered to their customers unfinished and go to approved finishing centres for customer-specified interiors to be installed.

As well as for the corporate role, the GIV is now being vigorously marketed in a number of military and quasi-military roles as the SRA-4 (Special Requirements Aircraft), first flown in 1988. The SRA-4 for mainly military roles including electronic warfare, search and rescue, anti-submarine/ ship, and communications.

The performance of the Gulfstream IV, particularly in payload/range terms, has already been demonstrated in several notable flights, including a round-the-world westbound flight (ie, against the prevailing wind patterns) made in the third production aircraft (s/n 1002). Starting and finishing at Le Bourget during the Paris Air Show, this Gulfstream, with a six-man crew headed by Gulfstream Aerospace chairman Allen E Paulson, completed the l9,847-naut ml (36832.44-km) circuit in 45 hrs 25 mm 10 sec. With five ground stops (at Rome, Mid¬way, Kinabalu, Dubai and Cairo) the aircraft averaged 4377 kts (810,79 km/h) and en¬countered head winds of up to 139 kts (257 km/ h). In addition to 22 city-to-city records, the flight set round-the-world westbound records for jet aircraft of unlimited weight and business jets of up to 35,000 kg (77 140 lb) gross weight.

Gulfstream used company demonstrators N404GA and N400GA to set westbound and eastbound around the world records in June 1987 and February 1988 respectively.

The Gulfstream IV-SP has more efficient engines and modifications revising operating weights and a better payload range combination.

In 1987, the 200th and last Gulfstream III produced was delivered, and the first delivery of a Gulfstream IV took place. The GIV was the first jet in business aviation to have an all-glass cockpit.

Gallery

Gulfstream G 1159 Gulfstream IV
Engine: 2 x Rolls Royce Tay 611-8, 60430 N / 6160 kp
Length: 88.255 ft / 26.9 m
Height: 24.934 ft / 7.6 m
Wingspan: 77.756 ft / 23.7 m
Wing area: 950.461 sq.ft / 88.3 sq.m
Max take off weight: 73206.0 lb / 33200.0 kg
Weight empty: 42512.4 lb / 19280.0 kg
Max. weight carried: 30693.6 lb / 13920.0 kg
Max. speed: 509 kts / 943 km/h
Landing speed: 108 kts / 200 km/h
Cruising speed: 459 kts / 850 km/h
Initial climb rate: 3937.01 ft/min / 20.0 m/s
Service ceiling: 44948 ft / 13700 m
Wing loading: 77.08 lb/sq.ft / 376.0 kg/sq.m
Range: 3696 nm / 6845 km
Crew: 2
Payload: 14-19pax

Gulfstram IV (Long range)
Engines: Two Rolls-Royce Tay 610-8 turbofans, 12,420 lb.st (5634 kgp)
Fuel capacity, 4,370 US gal (16,540 lt).
Max operating speed (VM0) 340 kts (630 km/h)
CAS, (MM0) M = 088.
Tur¬bulent air penetration speed (above 32,000 ft/ 9754 in), M=075.
Max cruising speed, 519 kts (962 km/h) or Mach = 088
Long-range cruise, 459 kts (851 km/h) or M = 080
Take-off balanced field length, 5,100 ft (1 554 m)
Initial rate of climb, 3,816 ft/min (19,4 m/sec)
Single-engine climb rate, 1,278 ft/min (6,5 m/sec)
Max operational altitude, 51,000 ft (15 544 m)
Single-engine cruise ceiling, 27,000 ft (8 230 m)
Landing distance, 3,200 ft (975 m)
Max range (NBAA IFR reserves, long-range cruise), 4,300 naut mls (7965 km) with 8 pax.
Typical operating weight empty, 41,100 lb (18 643 kg)
Max fuel load, 29,500 lb (13 381 kg)
Payload with max fuel, 1,600 lb (726 kg)
Max payload, 3,900 lb (1 769 kg)
Max take-off weight, 71,700 lb (32 523 kg)
Max zero fuel weight, 45,000 lb (20 412 kg)
Max landing weight, 58,500 lb (26 536 kg).
Wing span, 77 ft 10 in (23,7 m)
Overall length, 88 ft 4 in (26,9 m)
Overall height, 24 ft 10 in (7,6 m)
Wing area, 9504 sq ft (88,29 sq.m)
Wing sweepback, at quarter chord line, 2766 deg inboard, 2682 deg outboard.
Accommodation: Flight crew of two.
Typical executive layouts for 14 passengers; max cer¬tificated, 19 passengers.
Cabin length, 45 ft 1 in (13,7 m)
Max height, 6 ft 1 in (1,9 m)
Max width, 7 ft 4 in (2,2 m)
Total cabin volume, 1,513 cu ft (42,8 cu.m)
Baggage compartment volume, 169 cu ft (4,8 cu.m).

IV-SP
Engine: Roll-Royce Tay 611-8.

SRA-4
Engines: 2 x Rolls-Royce Tay 610-8 turbofan, 12420 lb thrust.

The Gulfstream line and the Savannah plant were sold to American Jet Industries, which was headed by little-known aviation entrepreneur Allen Paulson.

Paulson became the president and CEO of the company, renaming it Gulfstream America. He made a priority of developing the Gulfstream III, a new aircraft designed to achieve greater range and speed than the GII.

The G.III stretched development of the G.II featured an all new super critical wing.

A declining market caused Grumman to announce the cancellation of the G.III at the 1977 Paris air show.
The business was sold to American Jet Industries (later to be Gulfstream Aerospace).

The GIII made its first flight in December 1979, with the first delivery of the aircraft occurring in 1980. It was the first business jet to fly over both poles.

The G-1159A Gulfstream III was first built in 1980

In 1987, the 200th and last Gulfstream III produced was delivered, and the first delivery of a Gulfstream IV took place.

Based on the twin-turbofan Gulfstream III corporate jet, the C-20 Gulfstream III/TV has been purchased for US Air Force, Army, and Navy use as a VIP transport and oper¬ational support aircraft. Three aircraft were bought following an initial period of lease, and have been followed by 12 more. Three maritime patrol aircraft acquired by the Royal Danish Air Force are equipped with APS-127 search radars, INS, and a large cargo door. They can be reconfigured in less than two hours for VIP transport, troop carrying, or medevac. Another export customer, reported to be India, has bought three reconnaissance versions. Prod-uction of the Spey powered Gulfstream III ended in early 1987 with the transition to the Gulfstream IV, which uses Tay engines.

A Gulfstream III completed as the SRA-l de¬monstrator first flew on 14 August 1984 from Travis Field, Savannah, Georgia. It had been extensive¬ly tested with a number of the sensor systems proposed for some of the SRA-4 roles, including an under fuselage Side-Looking Airborne Modular Multimission Radar.

In 1987, the 200th and last Gulfstream III produced was delivered, and the first delivery of a Gulfstream IV took place.

G-1159A Gulfstream III
Engines: 2 x Rolls/Royce Spey 511-8, 11,400 lbs thrust.
Seats: 22.
Length: 83.1 ft.
Height: 24.2 ft.
Wingspan: 77.8 ft.
Wing area: 935 sq.ft.
Wing aspect ratio: 6.
Maximum ramp weight: 68,700 lbs.
Maximum takeoff weight: 68,700 lbs.
Standard empty weight: 32,200 lbs.
Maximum useful load: 36,500 lbs.
Zero-fuel weight: 42,000 lbs.
Maximum landing weight: 58,500 lbs.
Wing loading: 73 lbs/sq.ft.
Power loading: 3 lbs/lb.
Maximum usable fuel: 28,300 lbs.
Best rate of climb: 3800.
Certificated ceiling: 45,000 ft.
Max pressurisation differential: 9.5 psi.
8000 ft cabin alt @: 45,000 ft.
Maximum single-engine rate of climb: 1200 fpm @ 225 kts.
Single-engine climb gradient: 327 ft/nm.
Single-engine ceiling: 27,000 ft.
Maximum speed: 501 kts.
Normal cruise @ 45,000ft: 442 kts.
Fuel flow @ normal cruise: 2475 pph.
Stalling speed clean: 121 kts.
Stalling speed gear/flaps down: 105 kts.
Turbulent-air penetration speed: 270 kts.

SRA-1
Engines: 2 x Rolls/Royce Spey 511-8, 11,400 lbs thrust.