Atlas 2E missile, San Diego Aerospace Museum
|Function||Intercontinental Ballistic Missile (ICBM)|
|Country of origin||United States|
|Height||75 ft 10 in (23.11 m)|
85 ft 6 in (26.06 m) in ICBM configuration
|Diameter||10 ft (3.0 m)|
|Width||16 ft (4.9 m)|
|Mass||260,000 lb (117,900 kg)|
|Status||Retired April 1965|
|First flight||6 June 1957|
|Last flight||24 August 1959|
|Thrust||300,000 lbf (1,300 kN)|
|Total thrust||360,000 lbf (1,600 kN)|
|Thrust||60,000 lbf (270 kN)|
|Convair X-11 / SM-65 Atlas|
|Place of origin||United States|
|Used by||United States Air Force|
|Mass||255,950 lb (116,100 kg) for Atlas D w/o payload, 260,000 lb (117,900 kg) for Atlas D with Mk 2/3 RV and W49 warhead, 268,000 lb (121,560 kg) for Atlas E&F with Mk 4 RV and W38 warhead|
|Length||75 ft 1 in (22.89 m) with Mk 2 re-entry vehicle, 82 ft 6 in (25.15 m) with Mk 3|
|Width||16 ft 1 in (4.90 m) with Mk 2 re-entry vehicle, 82 ft 6 in (25.15 m) with Mk 3|
|Diameter||10 ft 0 in (3.05 m)|
|Engine||1 × Rocketdyne LR105 rocket engine, 1 × Rocketdyne XLR89 rocket engine with two 150,000 lbf (670 kN) thrust chambers (Atlas D), 2 × Rocketdyne LR101 vernier rocket engines with 1,000 lbf (4.4 kN) of thrust (propellant feed from LR105 sustainer engine turbopumps); 2 × LR89 booster engines (independent turbopumps) with 165,000 lbf (730 kN) (Atlas E&F)|
57,000 lbf (250,000 N) thrust
|Accuracy||CEP 4,600 ft (1,400 m)|
|No. built||350 (all versions)|
Peak deployment level of 129
(30 D, 27 E, 72 F).
|Variants||Atlas A, B/C, D, E/F (ICBMs)|
SLV-3/3A/3C (NASA use)
The SM-65 Atlas was the first operational intercontinental ballistic missile (ICBM) developed by the United States and the first member of the Atlas rocket family. It was built for the U.S. Air Force by the Convair Division of General Dynamics at an assembly plant located in Kearny Mesa, San Diego). Atlas became operational as an ICBM in October 1959 and was quickly obsoleted by new development, being retired as a missile by 1965. The Atlas required extremely long preparation times which made it unsuitable for a quick launch ICBM. However, this was not a requirement for planned space launches, and so Atlas-derived launch vehicles served a long history as space launchers.
Even before its ICBM use ended in 1965, Atlas had placed four Project Mercury astronauts in orbit and was becoming the foundation for a family of successful space launch vehicles, most notably Atlas Agena and Atlas Centaur. Mergers led to the acquisition of the Atlas Centaur line by the United Launch Alliance. Today ULA supports the larger Atlas V, which combines the unique and highly efficient Centaur upper stage with a new booster. Until 2001, many of the retired Atlas ICBMs were refurbished and combined with upper stages to launch satellites.
Atlas was the first US ICBM and one of the first large liquid-fueled rockets. As such, its early development was quite chaotic, with plans changing rapidly as flight tests revealed issues.
Atlas got its start in 1946 with the award of an Army Air Forces research contract to Consolidated Vultee Aircraft (later Convair) for the study of a 1,500-to-5,000-mile (2,400 to 8,000 km) range missile that might at some future date carry a nuclear warhead. This MX-774 project was named for the Atlas of Greek mythology and the contractor's parent Atlas Corporation. At the time, the smallest atomic warheads were all larger than the maximum theoretical payloads of the planned long range missiles, so the contract was canceled in 1947, but the Army Air Forces allowed Convair to launch the three almost-completed research vehicles using the remaining contract funds. The three flights were only partially successful, but did show that balloon tanks and gimbaled rocket engines were valid concepts.
A second development contract was awarded to Convair on 16 January 1951 for what was then called MX-1593, with a relatively low priority. The initial design completed by Convair in 1953 was larger than the missile that eventually entered service. Estimated warhead weight was lowered from 8,000 lb (3,630 kg) to 3,000 lb (1,360 kg) based on highly favorable U.S. nuclear warhead tests in early 1954. This, in addition to the Soviet Union's 1953 Joe 4 dry fuel thermonuclear weapon test and the CIA learning that the Soviet ICBM program was making progress, led to the project being dramatically accelerated. Atlas became a crash program of the highest national importance on 14 May 1954.
A major development and test contract was awarded to Convair on 14 January 1955 for a 10-foot (3 m) diameter missile to weigh about 250,000 lb (113,400 kg). Atlas development was tightly controlled by the Air Force's Western Development Division, WDD, later part of the Air Force Ballistic Missile Division. Contracts for warhead, guidance and propulsion were handled separately by WDD. The first successful flight of a highly instrumented Atlas missile to full range occurred 28 November 1958. Atlas ICBMs were deployed operationally from 31 October 1959 to 12 April 1965.
The missile was originally designated as the XB-65 experimental bomber; in 1955 it was redesignated SM-65 ("Strategic Missile 65") and, from 1962, it became CGM-16. This letter "C" stood for "coffin" or "Container", the rocket being stored in a semi-hardened container; it was prepared for launch by being raised and fueled in the open. The Atlas-F (HGM-16) was stored vertically underground, but launched after being lifted to the surface.
By 1965, with the second-generation Titan II having reached operational status, the Atlas was obsolete as a missile system and had been phased out of military use. Many of the retired Atlas D, E, and F missiles were used for space launches into the 1990s.
The Atlas's complicated, unconventional design proved difficult to debug compared with rocket families such as Thor and Titan which used conventional aircraft-style structures and two stage setups and there were dozens of failed launches during the early years. After watching an Atlas ICBM explode shortly after launch, Mercury astronaut Gus Grissom remarked "Are we really going to get on top of one of those things?" The numerous failures led to Atlas being dubbed an "Inter County Ballistic Missile" by missile technicians, but by 1965 most of the problems had been worked out and it was a reliable launch vehicle. Nearly every component in the Atlas managed to fail at some point during test flights, from the engine combustion chambers to the tank pressurization system to the flight control system, but Convair engineers noted with some pride that there had never been a repeat of the same failure more than three times, and every component malfunction on an Atlas flight was figured out and resolved. The last major design hurdle to overcome was unstable engine thrust, which caused three Atlas missiles to explode on their launching stands. It was solved with the use of baffled injectors and other modifications which would prove vital to the Saturn V program, as it used a first stage engine that was loosely derived from the Atlas booster engines.
Atlas was unusual in its use of balloon tanks for fuel, made of very thin stainless steel with minimal or no rigid support structures. Pressure in the tanks provides the structural rigidity required for flight. An Atlas rocket would collapse under its own weight if not kept pressurized, and had to have 5 psi (34 kPa) nitrogen in the tank even when not fueled. The only other known use of balloon tanks at the time of writing is the Centaur high-energy upper stage, although some rockets (such as the Falcon series) use partially pressure-supported tanks. The rocket had two small thrust chambers on the sides of the tank called vernier rockets. These provided fine adjustment of velocity and steering after the sustainer engine shut down.
Atlas was informally classified as a "stage-and-a-half" rocket, with a central sustainer engine and set of two booster engines that were all started at launch, each drawing from a single set of propellant tanks. Most multistage rockets drop both engines and fuel tanks simultaneously before firing the next stage's engines. However, when the Atlas missile was being developed, there was doubt as to whether a rocket engine could be air-started. Therefore, the decision was made to ignite all of the Atlas' engines at launch; the booster engines would be discarded, while the sustainer continued to burn. A "stage" of a liquid propellant rocket normally consists of both propellant tanks and engines, so jettisoning one or more engines only is equivalent to "half a stage". At staging, the booster engines would be shut off and a series of mechanical and hydraulic mechanisms would close the plumbing lines to them. The booster section would then be released by a series of hydraulic clamps (aside from the early test model Atlas B, which used explosive bolts) and slide off the missile. From there on, the sustainer and verniers would operate by themselves. Booster staging took place at roughly two minutes into launch, although the exact timing could vary considerably depending on the model of Atlas as well as the particular mission being flown. This "stage-and-a-half" design was made possible by the extremely light weight of the balloon tanks. The tanks made up such a small percentage of the total booster weight that the mass penalty of lifting them to orbit was less than the technical and mass penalty required to throw half of them away mid-flight. However, technology advanced quickly and not long after design work on Atlas was completed, Convair rival Martin proposed a solution to the air-starting problem. Their Titan I missile, developed as an Atlas backup, had a conventional two stage design.
The R-7 Semyorka was the first Soviet ICBM and similarly started all engines before launch to avoid igniting a large liquid fuel engine at high altitudes. However, the R-7 had a central sustainer section, with four boosters attached to its sides. The large side boosters required use of an expensive launch pad and prevented launching the rocket from a silo. Like the Atlas, the use of cryogenic liquid oxygen meant that the missile could not be kept in the state of flight readiness indefinitely and was largely useless for its intended purpose.
The booster engine consisted of two large thrust chambers. On the Atlas A/B/C, one turbopump assembly powered both booster engines. On the Atlas D, the booster engines had separate pump assemblies. On the Atlas E/F, each booster turbopump also got its own gas generator. Later space launcher variants of the Atlas used the MA-5 propulsion system with twin turbopumps on each booster engine, driven by a common gas generator. The boosters were more powerful than the sustainer engine and did most of the lifting for the first two minutes of flight. In addition to pitch and yaw control, they could also perform roll control in the event of a vernier failure. The sustainer engine on all Atlas variants consisted of a single thrust chamber with its own turbopump and gas generator, and two small pressure-fed vernier engines. The verniers provided roll control and final velocity trim. The total sea level thrust of all five thrust chambers was 360,000 lbf (1,600 kN) for a standard Atlas D. Atlas E/F had 375,000 pounds of thrust. Total sea level thrust for these three-engine Atlas Es and Fs was 389,000 lbf (1,730 kN). Space launcher variants of the Atlas often had performance enhancements to the engines.
The Atlas missiles A through D used radio guidance: the missile sent information from its inertial system to a ground station by radio, and received course correction information in return. The Atlas E and F had completely autonomous inertial guidance systems.
The warhead of the Atlas D was originally the G.E. Mk 2 "heat sink" re-entry vehicle (RV) with a W49 thermonuclear weapon, combined weight 3,700 lb (1,680 kg) and yield of 1.44 megatons (Mt). The W49 was later placed in a Mk 3 ablative RV, combined weight 2,420 lb (1,100 kg). The Atlas E and F had an AVCO Mk 4 RV containing a W38 thermonuclear bomb with a yield of 3.75 Mt which was fuzed for either air burst or contact burst. The Mk 4 RV also deployed penetration aids in the form of mylar balloons which replicated the radar signature of the Mk 4 RV. The Mk 4 plus W-38 had a combined weight of 4,050 lb (1,840 kg). The Atlas missile's warhead was over 100 times more powerful than the bomb dropped over Nagasaki in 1945.
The Convair X-11/SM-65A Atlas/Atlas A was the first full-scale prototype of the Atlas missile, first flying on 11 June 1957. It was a test model designed to verify the structure and propulsion system, and had no sustainer engine or separable stages. The first three Atlas A launches used an early Rocketdyne engine design with conical thrust chambers and only 135,000 pounds of thrust. By the fourth Atlas test, they were replaced by an improved engine design that had bell-shaped thrust chambers and 150,000 pounds of thrust.
The Atlas A conducted eight test flights in 1957-1958, of which four were successful. All test flights were conducted from Cape Canaveral Air Force Station, at either Launch Complex 12 or Launch Complex 14. Atlas A flights were powered by a single engine consisting of two large thrust chambers fed by a single set of turbopumps.
The Convair X-12/SM-65B was the second, more advanced testbed for the Atlas rocket program. The SM-65B pioneered the use of the stage and a half rocket engines that became a hallmark of the Atlas rocket program and was also the first rocket to achieve a flight distance that could be considered intercontinental when it flew 6,325 miles (10,180 km).
This was followed by the Atlas B and C in 1958-1959. The B had full engines and booster engine staging capability. The MA-1 engine system, used on both the Atlas B and Atlas C, consisted of the booster engine used on the predecessor X-11 plus a sustainer engine. MA-1 was the direct predecessor of the MA-2 engine system of Atlas D which in turn was the direct predecessor of the MA-5 engine system used in Atlas Agena and Atlas Centaur launch vehicles.
The Atlas B was first flown on 19 July 1958, with ten total flights. Nine of these were sub-orbital test flights of the Atlas as an Intercontinental Ballistic Missile, with five successful missions and four failures. All launches were conducted from Cape Canaveral Air Force Station, at Launch Complexes 11, 13 and 14.
The SM-65C Atlas, or Atlas C was a prototype of the Atlas missile.
The C was a more refined model with improved, lighter-weight components and a bigger LOX tank and smaller fuel tank. First flown on 24 December 1958, it was the final development version of the Atlas rocket, prior to the operational Atlas D. It was originally planned to be used as the first stage of the Atlas-Able rocket, but following an explosion during a static test on 24 September 1959, this was abandoned in favor of the Atlas D. Six flights were made, all sub-orbital test flights of the Atlas as an Intercontinental Ballistic Missile, with three tests succeeding, and three failing. All launches were conducted from Cape Canaveral Air Force Station, at Launch Complex 12.
The SM-65D Atlas, or Atlas D, was the first operational version of the Atlas missile and the basis for all Atlas space launchers, debuting in 1959. Atlas D weighed 255,950 lb (116,100 kg) (without payload) and had an empty weight of only 11,894 lb (5,395 kg), the other 95.35% was propellant. Dropping the 6,720 lb (3,048 kg) booster engine and fairing reduced the dry weight to 5,174 lb (2,347 kg), a mere 2.02% of the initial gross weight of the vehicle (still excluding payload). This very low dry weight allowed Atlas D to send its thermonuclear warhead to ranges as great as 9,000 miles (14,500 km) or orbit payloads without an upper stage.
It first flew on 14 April 1959. To provide the United States with an interim or emergency ICBM capability, in September 1959 the Air Force deployed three SM-65D Atlas missiles on open launch pads at Vandenberg AFB, California, under the operational control of the 576th Strategic Missile Squadron, 704th Strategic Missile Wing. Completely exposed to the elements, the three missiles were serviced by a gantry crane. One missile was on operational alert at all times. They remained on alert until 1 May 1964.
The SM-65E Atlas, or Atlas-E, was the first 3-engine operational variant of the Atlas missile, the third engine resulting from splitting the two booster thrust chambers into separate engines with independent sets of turbopumps. It first flew on 11 October 1960, and was deployed as an operational ICBM from September 1961 until March 1965.
The final variants of the Atlas ICBM were the E and F, introduced in 1960-61. E and F had fully self-contained inertial navigation systems (INS) and were nearly identical to each other except for interfaces associated with their different basing modes (underground silo for F) and the fuel management system.
A major enhancement in the Atlas E was the new all-inertial system that obviated the need for ground control facilities. Since the missiles were no longer tied to a central guidance control facility, the launchers could be dispersed more widely in what was called a 1 × 9 configuration, with one missile silo located at one launch site each for the 9 missiles assigned to the squadron.
Atlas-E launches were conducted from Cape Canaveral Air Force Station, at Launch Complexes 11 and 13, and Vandenberg Air Force Base at Vandenberg AFB Operational Silo Test Facility, Vandenberg AFB Launch Complex 576 and Vandenberg AFB Space Launch Complex 3.
The SM-65F Atlas, or Atlas-F, was the final operational variant of the Atlas missile. It first flew on 8 August 1961, and was deployed as an operational ICBM between September 1962 and April 1965.
The Atlas F was the final and most advanced version of the Atlas ICBM and was essentially a quick-firing version of the Atlas E, modified to be stored in a vertical position inside underground concrete and steel silos. When stored, the Atlas F sat atop an elevator. If a missile was placed on alert, it was fueled with RP-1 (kerosene) liquid fuel, which could be stored inside the missile for extended periods. If a decision was made to launch the missile, it was fueled with liquid oxygen. Once the liquid oxygen fueling was complete, the elevator raised the missile to the surface for launching.
This method of storage allowed the Atlas F to be launched in about ten minutes, a saving of about five minutes over the Atlas D and Atlas E, both of which were stored horizontally and had to be raised to a vertical position before being fueled.
Atlas-F launches were conducted from Cape Canaveral Air Force Station, at Launch Complexes 11 and 13, and Vandenberg Air Force Base at OSTF-2, Vandenberg AFB Launch Complex 576 and Vandenberg AFB Space Launch Complex 3.
Strategic Air Command deployed 11 operational Atlas ICBM squadrons between 1959 and 1962. Each of the three missile variants, the Atlas D, E, and F series, were deployed and based in progressively more secure launchers.
The number of Atlas intercontinental ballistic missiles in service, by year: CGM-16D Atlas Intercontinental Ballistic Missiles assigned:
CGM-16E Atlas Intercontinental Ballistic Missiles assigned:
HGM-16F Atlas Intercontinental Ballistic Missiles assigned:
In September 1959 the first operational Atlas ICBM squadron went on operational alert at F.E. Warren AFB, Wyoming equipped with six SM-65D Atlas missiles based in above-ground launchers. Three additional Atlas D squadrons, two near F.E. Warren AFB, Wyoming, and one at Offutt AFB, Nebraska, were based in above-ground launchers that provided blast protection against over-pressures of only 5 pounds per square inch (34 kPa). These units were:
The first site at Warren for the 564th SMS consisted of six launchers grouped together, controlled by two launch operations buildings, and clustered around a central guidance control facility. This was called the 3 × 2 configuration: two launch complexes of three missiles each constituted a squadron.
At the second Warren site for the 565th SMS and at Offutt AFB, Nebraska, for the 549th SMS, the missiles were based in a 3 x 3 configuration: three launchers and one combined guidance control/launch facility constituted a launch complex, and three complexes comprised a squadron. At these later sites the combined guidance and control facility measured 107 by 121 ft (33 by 37 m) with a partial basement. A dispersal technique of spreading the launch complexes were 20 to 30 miles (30 to 50 km) apart was also employed to reduce the risk that one powerful nuclear warhead could destroy multiple launch sites.
The SM-65E Atlas were based in horizontal "semi-hard" or "coffin" facilities that protected the missile against over-pressures up to 25 psi (170 kPa). In this arrangement the missile, its support facilities, and the launch operations building were housed in reinforced concrete structures that were buried underground; only the roofs protruded above ground level. These units were:
The six SM-65F Atlas squadrons were the first ICBMs to be stored vertically in underground silos. Built of heavily reinforced concrete, the huge silos were designed to protect the missiles from over-pressures of up to 100 psi (690 kPa).
After the solid-fuel LGM-30 Minuteman had become operational in early 1963, the Atlas became rapidly obsolete. By October 1964, all Atlas D missiles had been phased out, followed by the Atlas E/F in April 1965. About 350 Atlas ICBMs of all versions were built, with a peak deployment level of 129 (30 D, 27 E, 72 F). Despite its relatively short life span, Atlas served as the proving ground for many new missile technologies. Perhaps more importantly, its development spawned the organization, policies, and procedures that paved the way for all of the later ICBM programs.
After its retirement from operational ICBM service in 1965, the ICBMs were refurbished and used for close to forty years as space launch vehicle boosters.
|1957-06-11||19:37||LC-14||4A||2 km (1.2 mi)||Failure|
|1957-09-25||19:57||LC-14||6A||3 km (1.9 mi)||Failure|
|1957-12-17||17:39||LC-14||12A||120 km (75 mi)||Success|
|1958-01-10||15:48||LC-12||10A||120 km (75 mi)||Success|
|1958-02-07||19:37||LC-14||13A||120 km (75 mi)||Failure|
|1958-02-20||17:46||LC-12||11A||90 km (56 mi)||Failure|
|1958-04-05||17:01||LC-14||15A||100 km (62 mi)||Success|
|1958-06-03||21:28||LC-12||16A||120 km (75 mi)||Success|
|3B||10 km (6.2 mi)||Failure|
|1958-08-02||22:16||LC-13||4B||900 km (560 mi)||Success|
|1958-08-29||04:30||LC-11||5B||900 km (560 mi)||Success|
|1958-09-14||05:24||LC-14||8B||900 km (560 mi)||Success|
|1958-09-18||21:27||LC-13||6B||100 km (62 mi)||Failure|
|1958-11-18||04:00||LC-11||9B||800 km (500 mi)||Failure|
|1958-11-29||02:27||LC-14||12B||900 km (560 mi)||Success||First full-range test flight|
|1958-12-18||22:02||LC-11||10B||N/A||Success||Placed SCORE satellite|
into 185 km (115 mi) x
1,484 km (922 mi) x 32.3° orbit
|1959-01-16||04:00||LC-14||13B||100 km (62 mi)||Failure|
|1959-02-04||08:01||LC-11||11B||900 km (560 mi)||Success|
|3C||900 km (560 mi)||Success|
|4C||900 km (560 mi)||Failure|
|5C||100 km (62 mi)||Failure|
|7C||200 km (120 mi)||Failure|
|8C||900 km (560 mi)||Success|
|11C||900 km (560 mi)||Success|
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