255,950lb (116,100kg) for Atlas D w/o payload,260,000lb (117,900kg) for Atlas D with Mk 2/3 RV and W49 warhead,268,000lb (121,560kg) for Atlas E&F with Mk 4 RV and W38 warhead
Length
75ft 1in (22.89m) with Mk 2 re-entry vehicle,82ft 6in (25.15m) with Mk 3
Width
16ft 1in (4.90m)
Diameter
10ft 0in (3.05m)
Engine
2 ×Rocketdyne XLR-89 booster rocket engines each 150,000lbf (670kN) sharing one turbopump (Atlas A)
1 ×Rocketdyne LR-105 sustainer rocket engine,2 ×Rocketdyne XLR-89 booster rocket engines each 150,000lbf (670kN) sharing one turbopump (Atlas B,C)
1 ×Rocketdyne LR-105 sustainer rocket engine,2 ×LR89 booster engines with independent turbopumps each 165,000lbf (730kN) (Atlas D,E,F,G)
The development of the Atlas was first begun in 1946,but over the next few years the project underwent several cancellations and re-starts. The deepening of the Cold War and intelligence showing the Soviet Union was working on an ICBM design led to it becoming a crash project in late 1952,along with the creation of several other missile projects to ensure one would enter service as soon as possible. The first test launch was carried out in June 1957,which failed. The first success of the Soviet R-7 Semyorka in August gave the program new urgency,leading to the first successful Atlas A launch in December. Of the eight flights of the A model,only three were successful,but the later models demonstrated increasing reliability and the D model was cleared for use.
Atlas C was declared operational in September 1959. Even at that time it was considered less than ideal[citation needed] as it had to be fuelled immediately before launch and thus had very slow reaction times. The Air Force still saw its strategic bombers as its primary force and considered Atlas as a last-ditch weapon that would ensure a counterattack in the case the Soviets attempted a sneak attack on the US bomber bases. The initial versions were stored at ground level and thus subject to attack by Soviet bombers,which greatly reduced their suitability for this role. Starting with the F models they were stored in underground silos that offered some protection from air attack. New designs,especially the Minuteman,rendered Atlas obsolete and it was retired from the ICBM role by 1965.
These disadvantages had no bearing on its use for space launches,and Atlas-derived launch vehicles served as launchers for NASA for four decades. 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 Centaur upper stage with a new booster. Until 1995,many retired Atlas ICBMs were refurbished and combined with upper stages to launch satellites.[2]
History
Theodore von Kármán,left,is joined by Air Force and NASA officials while inspecting two of the models used in the high velocity,high altitude wind tunnels at Arnold Air Force Base. The missiles are AGARD-B and Atlas Series-B. (1959)
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 began in 1946 with the award of an Army Air Forces research contract to a then AVCO-owned Convair for the study of a 1,500-to-5,000-mile (2,400 to 8,000km) range missile that might at some future date carry a nuclear warhead. This MX-774 project would go on to acquire the name Atlas,a god in Greek mythology,in 1951,from the Atlas Corporation,Convair’s parent since 1947.[3]:70
At the onset of the project,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 use the remaining contract funds to launch the three almost-completed research vehicles. The three flights were only partially successful,but did show that balloon tanks and gimbaled rocket engines were valid concepts.[4]
A second development contract was awarded to Convair on 23 January 1951 for what was then called MX-1593,with a relatively low priority.[3]:68 The initial design completed by Convair in 1953 was larger than the missile that eventually entered service. Estimated warhead weight was lowered from 8,000lb (3,630kg) to 3,000lb (1,360kg) 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. Project Atlas was assigned the highest Air Force development priority on 14 May 1954 by General Thomas D. White.[3]:106
A major development and test contract was awarded to Convair on 14 January 1955 for a 10-foot (3m) diameter missile to weigh about 250,000lb (113,400kg).[5] 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.[6]
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.[7]
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 until the 1990s.[2]
The penetrating lubricant WD-40 found its first use as a corrosion-inhibiting coating for the outer skin of the Atlas missile.[8]
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. The lack of internal structure contributed to dozens of failed launches during its development. After watching Atlas Serial 7Dexplode shortly after its nighttime launch,Mercury astronaut Gus Grissom remarked "Are we really going to get on top of one of those things?"[9] 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 became a more reliable launch vehicle.[citation needed] 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[who?] 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.[citation needed] Some of the repeat failures were also the result of rushed launch schedules and could have been avoided.[citation needed] The last major design hurdle to overcome was unstable engine thrust,which caused three Atlas missiles (Serial 51D and 48D in 1960 and Serial 27E in 1961) to explode on their launching stands.
Pressure stabilized tanks
Atlas was unusual in its use of balloon tanks for the propellants,made of very thin stainless steel with minimal or no rigid support structures,as already pioneered by the Soviet R-5 first launched in 1953.[10] 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 5psi (34kPa) nitrogen in the tank even when not fueled.[11] 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.
'Stage-and-a-half'
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.[12][13] 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.[12] 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 on two tracks. 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 balloon tanks.[13] 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.[14]
Engines
The booster engine consisted of two large thrust chambers. The Atlas A/B/C/D had a single turbopump assembly and gas generator driving both booster engines;the A/B/C had an interim engine with lower thrust while the D-series had the full-up engines delivering 303,000 pounds of thrust.[13] On the Atlas E/F,each booster engine had a separate pump and 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.[12] 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,which also powered two small pressure-fed vernier engines.[13] The verniers provided roll control and final velocity trim. The total sea level thrust of all five thrust chambers was 360,000lbf (1,600kN) 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 389,000lbf (1,730kN).[15]Launcher variants of the Atlas often had performance enhancements to the engines.[13]
Guidance
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 ground based guidance computer was a key part of the missile system,until guidance computers were miniaturized enough to be installed inside the missile. Isaac L. Auerbach designed the Burroughs guidance computer for the Atlas ICBM missiles. The Burroughs guidance computer was one of the first transistor computers. It processed 24-bit data using 18-bit instructions. A total of 17 of these ground computers were delivered. These same ground computers were later used for Atlas-Able,Project Mercury,and other early spacecraft.[16]
Warhead
The warhead of the Atlas D was originally the G.E. Mk 2 "heat sink" re-entry vehicle (RV)[17] with a W49thermonuclear weapon,combined weight 3,700lb (1,680kg) and yield of 1.44 megatons (Mt). The W49 was later placed in a Mk 3 ablative RV,combined weight 2,420lb (1,100kg). The Atlas E and F had an AVCO Mk 4 RV containing a W38thermonuclear warhead with a yield of 3.75Mt[18] 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 4,050lb (1,840kg). All of the warheads deployed in the Atlas were over 100 times more powerful than the bomb dropped over Nagasaki in 1945.[19]
Comparison with R-7
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 cryogenicliquid oxygen meant that the missile could not be kept in the state of flight readiness indefinitely,was largely useless as a strategic weapon,and was similarly developed into a space launch vehicle,initially delivering Sputnik and Vostok into orbit. The Soyuz rocket is descended from the R-7 and remains in use today.[20]
Atlas,test number 449,Air Force Missile Test Center.
The ConvairX-11/SM-65A Atlas/Atlas A was the first full-scale prototype of the Atlas missile,first flying on 11 June 1957.[21] 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 Convair X-12/SM-65B was the second prototype version,introducing the stage and a half system that was a hallmark of the Atlas rocket program. This version was the first American rocket to achieve a flight distance that could be considered intercontinental when it flew 6,325 miles (10,180km).[22]
The SM-65C Atlas,or Atlas C was the third prototype Atlas version,a more refined model with improved,lighter-weight components. a bigger LOX tank,and a smaller fuel tank. First flown on 24 December 1958,it was the final development version. 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.[23] Six flights were made,all sub-orbital ballistic test flights of the Atlas,with three tests succeeding,and three failing.[24] All launches were conducted from Cape Canaveral Air Force Station,at Launch Complex 12.[25]
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.[26] Atlas D weighed 255,950lb (116,100kg) (without payload) and had an empty weight of only 11,894lb (5,395kg);the other 95.35% was propellant. Dropping the 6,720lb (3,048kg) booster engine and fairing reduced the dry weight to 5,174lb (2,347kg),a mere 2.02% of the initial gross weight of the vehicle (still excluding payload). This very low dry weight gave Atlas D a range of up to 9,000 miles (14,500km),or to orbit payloads without requiring an upper stage.[27] 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.[28] They remained on alert until 1 May 1964.[29]
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.[30]
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 nine missiles assigned to the squadron.[15]
Convair SM-65F Atlas 532 550 SMS Site 02 Abilene KS.
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 essentially a quick-firing version of the Atlas E,modified to be stored in a vertical position inside underground concrete and steel silos. It was nearly identical to the E version except for interfaces associated with their different basing modes (underground silo for F) and the fuel management system.[31] When stored,the missile sat atop an elevator. If 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,it was fueled with liquid oxygen. Once the liquid oxygen fueling was complete,the elevator raised the missile to the surface for launching.[32]
This method of storage allowed the Atlas F to be launched in about ten minutes,[33] 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.[33]
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.[21]
Strategic Air Command deployed 13 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.[34]:216
Service history
The number of Atlas intercontinental ballistic missiles in service,at the end of each year:[29]:Table 3
Date
CGM-16D (Atlas D)
CGM-16E (Atlas E)
HGM-16F (Atlas F)
1959
6
0
0
1960
12
0
0
1961
30
27
0
1962
30
27
72
1963
20
27
72
1964
0
0
72
Atlas-D deployment
Atlas-D ICBM launching from semi-hardened "coffin" bunker at Vandenberg AFB,California.
In September 1959 the first operational Atlas ICBM squadron went on operational alert at F.E. Warren AFB,[35] 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,[35] were based in above-ground launchers that provided blast protection against over-pressures of only 5 pounds per square inch (34kPa). 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.[34]:218
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 121ft (33 by 37m) with a partial basement. A dispersal technique of spreading the launch complexes were 20 to 30 miles (30 to 50km) apart was also employed to reduce the risk that one powerful nuclear warhead could destroy multiple launch sites.[34]
Atlas-E deployment
The SM-65E Atlas were based in horizontal "semi-hard" or "coffin" facilities that protected the missile against over-pressures up to 25psi (170kPa). 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:[36]
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 100psi (690kPa).[7] These units were:[37]
The Atlas F's employment was dangerous due to the flammability of the stored liquid rocket fuels. Four sites and their missiles were destroyed during propellant loading exercises (known as PLXs) when liquid oxygen leaked and fires ensued. On 1 June 1963 Roswell's site 579-1 was destroyed by explosion and fire. On 13 February 1964 Roswell's site 579-5 was destroyed, and a month later on 9 March 1964 site 579-2 was also destroyed by explosion and fire. Finally, on 14 May 1964 an Altus AFB site, 577-6 in Frederick, Oklahoma, was also destroyed by explosion and fire during a PLX. Fortunately the crews all survived. None of the damaged sites were repaired or returned to service.
Retirement as an ICBM
After the solid-fuelLGM-30 Minuteman had become operational in early 1963, the Atlas became rapidly obsolete.[38] 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.[39]
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.[33]
Atlas-A to -C launch history
SM-65A (Atlas A) variant launch history
1965 graph of Atlas launches, cumulative by month with failures highlighted (pink) along with USAF Titan II and NASA use of ICBM boosters for Projects Mercury and Gemini (blue). Apollo–Saturn history and projections shown as well.
Eight flights of Atlas A occurred during the history of this variant.[40]
HGM-16F Atlas is on display at the National Museum of the United States Air Force in Dayton, Ohio. For years the missile was displayed outside the museum. In 1998 it was removed from display. It was restored by the museum's restoration staff and returned to display in the museum's new Missile Silo Gallery in 2007. The stage is currently in storage at the museum.[43] The white nose cone atop the museum's Atlas is an AVCO IV re-entry vehicle built to contain a nuclear warhead. This nose cone actually stood alert in defense of the United States, as it was initially installed on an Atlas on 2 October 1962 at a Denton Valley launch site near Clyde, Texas.[44]
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