Atlas I

Launch of the maiden flight of the Atlas I, with theCRRES satellite
Function	Expendable launch system
Manufacturer	General Dynamics
Country of origin	United States
Size
Height	43.90m (144.00 ft)
Diameter	3.05m (10 ft)
Mass	164,300kg (362,200 lb)
Stages	2.5
Capacity
Payload to 185 km (115 mi)LEO
Mass	5,900 kg (13,000 lb)[1]
Payload toGTO
Mass	2,375 kg (5,236 lb)[2]
Associated rockets
Family	Atlas
Launch history
Status	Retired
Launch sites	LC-36B,Cape Canaveral
Total launches	11
Success(es)	8
Failure	3
First flight	July 25, 1990
Last flight	April 25, 1997
Boosters – MA-5[3]
No. boosters	1
Powered by	2 LR-89-7
Maximum thrust	1,901.6 kN (427,500 lbf)[3]
Specific impulse	293.4 s (2.877 km/s)
Burn time	155 seconds[2]
Propellant	RP-1 /LOX
First stage
Powered by	1LR-105-7
Maximum thrust	386.4 kN (86,900 lbf)[3]
Specific impulse	316 s (3.10 km/s)
Burn time	266 seconds[2]
Propellant	RP-1 /LOX
Second stage –Centaur
Powered by	2RL-10A
Maximum thrust	147 kN (33,000 lbf)
Specific impulse	449 s (4.40 km/s)
Burn time	410 seconds[2]
Propellant	LH2 /LOX
[edit on Wikidata]

TheAtlas I was a USexpendable launch system manufactured byGeneral Dynamics in the 1990s to launch a variety of satellites. It was largely a commercial rebrand of theAtlas G (although it did fly multiple government payloads), but did feature several electrical and guidance improvements.^[4] Atlas I did not feature any major payload capacity improvements over its predecessor^[1] but did offer a larger payload fairing option.^[2] Eleven launches took place, with three failures.

Atlas I would be further developed and improved upon to produce the highly successfulAtlas II rocket.^[2]

The production line ofAtlas G, the predecessor to Atlas I, was wound down and eventually mothballed in the 1980s as theSpace Shuttle came online. The Shuttle's promise of a rapid launch cadence and lower launch costs resulted in dwindling demand for Atlas, and expendable rockets as a whole. However, theSpace Shuttle Challenger disaster in January 1986 caused second-guessing of the Shuttle's ability, and renewed interest in uncrewed expendable launch vehicles. Atlas G production would now be restarted, under the name Atlas I, sporting guidance upgrades.^[5] In June 1987, General Dynamics committed $100M to acquire long-lead procurement items to support the build of 18 vehicles for sale commercially.^[6]

The "I" in "Atlas I" can cause confusion, as all previous Atlas rockets were designated using letters, ending with theAtlas H. However, subsequent rockets were designated using Roman numerals, starting with theAtlas II. Officially, the "I" is the Roman numeral "1".

Atlas I was the last use of the classic Atlas design with three engines, a jettisonable booster section, and two vernier engines. While retaining most of those features,Atlas II replaced the verniers with ahydrazine roll control system.^[2]

The first stage of the Atlas I was essentially a copy of the first stage of theAtlas G.^[2] It featured 2 LR-89-7 booster engines, one LR-105-7 sustainer engine, and 2 LR-101 vernier engines for roll control. The structure of the first stage consisted of stainless steel balloon tanks, much like earlier Atlas rockets. The sustainer and vernier engines were mounted onto this tank structure. The two booster engines, however, were mounted to their own cylindrical skirt structure attached to the bottom of the tanks. Each LR-89-7 had its own turbopump to feed propellants into the combustion chamber, but the two engines shared a single common gas generator.^[3] The complete sustainer and booster engine assembly was referred to as theMA-5.

The booster engines, along with their support structure and plumbing, would drop away in one piece during flight. As the sustainer engine was more efficient than the booster engines, dropping the booster engines increased the stage's performance.^[3] The LR-105-7 sustainer engine and LR-101 vernier engines shut down when all propellant in the first stage tanks was depleted, around four and a half minutes after liftoff. Toward the end of the first stage burn, the payload fairing was jettisoned.^[2]

Atlas I featured the same first-stage engines as the Atlas G. They would later be replaced on theAtlas II with better-performing engines derived from theRS-27.^[3]

The upper stage of the Atlas I was the Centaur I stage, derived from earlier models ofCentaur that also flew atop Atlas boosters. Centaur I featured two RL-10-A-3A engines burning liquid hydrogen and liquid oxygen, making the stage extremely efficient. To help slow the boiloff of liquid hydrogen in the tanks, Centaur featured fiberglass insulation panels that were jettisoned 25 seconds after the first stage booster engines were jettisoned.^[4] Centaur I was the last version of the stage to feature separating insulation panels.

Centaur could be reignited to propel payloads to a geostationary transfer orbit, which was by far the most common flight profile on Atlas I.^[1] The maximum coast time of Centaur (essentially the stage's mission lifetime on orbit) was around 90 minutes when the stage was equipped with a long-coast kit. This kit included a larger battery, increased helium storage, additional shielding on the stage, and an extra bottle for hydrazine.^[2]

General Dynamics offered an optionalStar 48B third stage for Earth-departure launches. This small solid rocket motor would help give payloads a final push away from Earth shortly after separating from Centaur. Although Star motors flew on other Atlas rockets, they never flew on Atlas I.^[2]

Two fairing models were available for the Atlas I:^[2]

• Medium, with a diameter of 3.3 m (11 ft), a height of 10.4 m (34 ft), and a mass of 1,409 kg (3,106 lb)
• Large, with a diameter of 4.2 m (14 ft), a height of 12.2 m (40 ft), and a mass of 2,087 kg (4,601 lb)

Both fairing models were also offered on theAtlas II series of rockets,^[2] and the Large model continued to fly until 2022 on theAtlas V.^[7]

The payload mass numbers for Atlas I were based on vehicles flying with a 4.2 m (14 ft)-diameter Large fairing. If a vehicle flew using a Medium fairing, the lower mass of the fairing would enable an approximately 135 kg (298 lb) increase in payload capacity to a geostationary transfer orbit.^[2]

• Comparison of orbital launchers families
• Atlas G
• Atlas H
• Atlas II
• Atlas (rocket family)

• Atlas (rocket family)

• Articles with short description
• Short description matches Wikidata
• Use mdy dates from October 2018