6R80 Transmission-Atlas 2 speed Transfer Case -Leather Customized interior -Clarion 7' Navigation Head Unit-2 6x9, 2 6.5' and 2 10' Subwoofers-2016 Mustang GT Center Console -3.5' Lift kit -Custom Paint - Yet to be Decided -Dakota Digital Gauges -Air Conditioning. Behind the Ford 6R80 automatic transmission is an Atlas 2-speed transfer-case to handle the power when in four wheel drive. We swapped out the weak Dana 35 rear differential for a Ford 8.8 with an LSD and disc brakes. Under the hood the Ford Coyote 5.0l V8 fits nicely between the Metal Cloak fenders. The aluminum radiator provides excellent.
We are pleased to announce we have partnered with Roadster Shop of Mundelein, Ill., for the distribution of our SB4 7.0 (small-block, four-valve) automotive aftermarket crate engine. The announcement comes one day prior to the opening of the annual SEMA Show in Las Vegas. The show runs October 31 through November 3.
The 32-Valve DOHC SB4 7.0 engine adapts Mercury Racing’s proven high-performance valve train to a customized LS-based engine that produces a staggering 750 naturally aspirated horsepower. Mercury Racing’s advanced four-valve cylinder head combustion system and dual overhead camshaft valve train provide significantly improved performance and durability compared to a standard two-valve design.
Roadster Shop has been an industry mainstay in performance chassis fabrication and custom car building for over 30 years. It produces innovative, performance-based vehicle-specific chassis & suspension components for top tier street rods, trucks and pro-touring muscle cars. The Mercury Racing SB4, available for immediate delivery, offers Roadster Shop customers a turnkey, fully calibrated high-performance engine package.
Water Gene
“Being avid powerboaters for three generations, we are extremely familiar with Mercury Racing’s offshore marine products and the incredible rigors they are built to withstand while maintaining top-level performance. We are excited to partner with a company that can provide that level of durability in a 750 HP automotive engine package,” said Jeremy Gerber, Roadster Shop vice president of operations.
Roadster Shop owner Phil Gerber agreed.
“We are excited to partner with Mercury Racing on bringing the SB4 engine to the hot rod industry.” “The SB4 is an incredibly unique package that fits perfectly with the direction of high-end custom cars being built today. This engine will certainly be a game-changer and we couldn’t be more thrilled to be a part of it.”
The feelings from Mercury Racing are mutual.
“We are excited to partner with Roadster Shop,” said our General Manager Erik Christiansen. “They are highly respected and passionate veterans of the automotive aftermarket industry. Our capabilities are complementary and we appreciate their approach to providing innovative, high-quality products and services.”
SEMA SB4s
Roadster Shop’s C07 Central Hall booth features a Mercury Racing SB4 engine is fitted in their all-new RS4R – a full independent front suspension, 4WD chassis developed for 1966-77 Ford Bronco SUVs. Designed and developed in-house, the custom chassis offers 12″ travel in the front and 13″ in the rear. Dual rate springs, combined with 2.5″ Fox Factory series twin tube bypass shocks and coilovers optimize ride quality and overall performance.
The RS4R is configured to accept Coyote/6R80 or LS/4L80 drive train packages with an Atlas 2 Speed transfer case. The design allows the use of 285 series tires and +17″ wheels on all four corners without the need for fender mods.
Call 847-949-7637 or email [email protected] for additional information.
Roadster Shop is also displaying a fully dressed SB4 engine along with our DOHC SB4 cylinder head in their Upper South Hall booth, #30280.
Follow us on Facebook, Twitter and Instagram for SEMA Show updates throughout the week.
Function | Medium expendable Launch vehicle |
---|---|
Manufacturer | Lockheed Martin |
Country of origin | United States |
Size | |
Height | 47.54 m (156 ft) |
Diameter | 3.04 m (10 ft) |
Mass | 204,300 kg (414,000 lb) |
Stages | 3.5 |
Capacity | |
Payload to LEO | 6,580 kg |
Payload to GTO | 2,810 kg |
Associated rockets | |
Family | Atlas |
Launch history | |
Status | Retired |
Launch sites | SLC-36, Cape Canaveral SLC-3Vandenberg AFB |
Total launches | 63 (II: 10, IIA: 23, IIAS: 30) |
Successes | 63 (II: 10, IIA: 23, IIAS: 30)[1] |
First flight | II: December 7, 1991 IIA: June 10, 1992 IIAS: December 16, 1993 |
Last flight | II: March 16, 1998 IIA: December 5, 2002 IIAS: August 31, 2004[1] |
Notable payloads | SOHO (Atlas IIAS) TDRS (Atlas IIA) |
Boosters (Atlas IIAS) - Castor 4A | |
No. boosters | 4 |
Engines | 1 Solid |
Thrust | 478.3 kN (107,530 lbf) |
Specific impulse | 266 sec |
Burn time | 56 seconds |
Fuel | Solid |
Boosters (all) - MA-5A | |
No. boosters | 1 |
Engines | 2 RS-56-OBA |
Thrust | 2,093.3 kN (470,680 lbf) |
Specific impulse | 299 sec |
Burn time | 172 seconds |
Fuel | LOX / RP-1 |
First stage | |
Engines | 1 RS-56-OSA |
Thrust | 386 kN (86,844 lbf) |
Specific impulse | 316 sec |
Burn time | 283 seconds |
Fuel | RP-1 / LOX |
Second stage Centaur | |
Engines | 2 RL-10A |
Thrust | 147 kN (41,592 lbf) |
Specific impulse | 449 sec |
Burn time | 392 seconds |
Fuel | LH2 / LOX |
Third stage - IABS (optional) | |
Engines | 1 R-4D |
Thrust | 980N (220 lbf) |
Specific impulse | 312 sec |
Burn time | 60 seconds |
Fuel | N 2O 4 / MMH |
Atlas II was a member of the Atlas family of launch vehicles, which evolved from the successful Atlas missile program of the 1950s. It was designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. Sixty-three launches of the Atlas II, IIA and IIAS models were carried out between 1991 and 2004; all sixty-three launches were successes, making the Atlas II the most reliable launch system in history. The Atlas line was continued by the Atlas III, used between 2000 and 2005, and the Atlas V which is still in use.
- 2Versions
Design[edit]
Atlas II provided higher performance than the earlier Atlas I by using engines with greater thrust and longer fuel tanks for both stages. LR-89 and LR-105 were replaced by the RS-56, derived from the RS-27. The total thrust capability of the Atlas II of 490,000 pounds force (2,200 kN) enabled the booster to lift payloads of 6,100 pounds (2,767 kg) into geosynchronous transfer orbit (GTO) of 22,000 miles (35,000 km) or more. Atlas II was the last Atlas to use a three engine, 'stage-and-a-half' design: two of its three engines were jettisoned during ascent, but its fuel tanks and other structural elements were retained. The two booster engines, RS-56-OBAs, were integrated into a single unit called the MA-5A and shared a common gas generator. They burned for 164 seconds before being jettisoned. The central sustainer engine, an RS-56-OSA, would burn for an additional 125 seconds.[2] The Vernier engines on the first stage of the Atlas I were replaced by a hydrazine fueled roll control system.[3]
This series used an improved Centaur upper stage, the world's first cryogenic propellant stage, to increase its payload capability. Atlas II also had lower-cost electronics,[4] an improved flight computer[4] and longer propellant tanks than its predecessor, Atlas I.[4]
Versions[edit]
Atlas II[edit]
The original Atlas II was based on the Atlas I and its predecessors. This version flew between 1991 and 1998.[3]
Atlas IIA[edit]
Atlas IIA was a derivative designed to service the commercial launch market. The main improvement was the switch from the RL10A-3-3A to RL10A-4 engine on the Centaur upper stage.[5] The IIA version flew between 1992 and 2002.[6]
Atlas IIAS[edit]
Atlas IIAS was largely identical to IIA, but added four Castor 4A solid rocket boosters to increase performance. These boosters were ignited in pairs, with one pair igniting on the ground, and the second igniting in the air shortly after the first pair separated. The half-stage booster section would then drop off as usual.[5] IIAS was used between 1993 and 2004, concurrently with IIA.[7]
Background[edit]
In May 1988, the Air Force chose General Dynamics (now Lockheed-Martin) to develop the Atlas II vehicle, primarily to launch Defense Satellite Communications System payloads and for commercial users as a result of Atlas I launch failures in the late 1980s. Led by lead engineer Samuel Wagner, the Atlas II was crucial to the continued development of the United States' space program.
Atlas IIs were launched from Cape Canaveral Air Force Station, Fla., by the 45th Space Wing. The final West Coast Atlas II launch was accomplished December 2003 by the 30th Space Wing, Vandenberg AFB, California.
Specifications[edit]
- General Characteristics[8]
- Primary function: Launch vehicle
- Primary contractor: Lockheed Martin – airframe, assembly, avionics, test and systems integration
- Principal subcontractors: Rocketdyne (Atlas engine, MA-5); Pratt & Whitney (Centaur engine, RL-10) and Honeywell & Teledyne (avionics)
- Power Plant: Three MA-5A (RS-56) Rocketdyne engines, two Pratt & Whitney RL10A-4 Centaur engines
- Thrust: 494,500 lbf (2,200 kN)
- Length: Up to 156 ft (47.54 m); 16 ft (4.87 m) high engine cluster
- Core Diameter: 10 feet (3.04 m)
- Gross Liftoff Weight: 414,000 lb (204,300 kg)
- First Launch: February 10, 1992
- Models: II, IIA, and IIAS
- Launch Site: Cape Canaveral AFS, Florida
See also[edit]
References[edit]
- ^ abTariq Malik 'Final Atlas 2 Rocket Orbits Classified U.S. Satellite', Space News, August 31, 2004 (Accessed September 24, 2014)
- ^'Atlas IIA(S) Data Sheet'. Space Launch Report. Retrieved January 9, 2016.
- ^ ab'Atlas II'. Astronautix. Retrieved January 9, 2016.
- ^ abc'Atlas II Factsheet'. au.af.mil.
- ^ ab'Atlas Launch System Payload Planner's Guide'(PDF). Lockheed Martin. Archived from the original(PDF) on April 21, 2015. Retrieved January 9, 2016.
- ^'Atlas IIA'. Astronautix. Retrieved January 9, 2016.
- ^'Atlas IIAS'. Astronautix. Retrieved January 9, 2016.
- ^Spaceflight Now, Atlas IIAS (accessed September 24, 2014)