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The Atlas-Centaur was a US expendable launch vehicle derived from the SM-65 Atlas D missile. Launches were conducted from Launch Complex 36 at the Cape Canaveral Air Force Station in Florida.

Atlas-Centaur
Surveyor 1 launch.jpg
An Atlas-Centaur launching Surveyor 1
FunctionExpendable launch system
ManufacturerConvair
General Dynamics
Country of originUnited States
Launch history
StatusRetired
Launch sitesLC-36, Cape Canaveral
Total launches197
Successes181
Failures13
Partial failures3
First flightMay 8, 1962
Last flightAugust 31, 2004

Contents

Early developmentEdit

Convair, the manufacturer of the Atlas, developed the Centaur upper stage specifically for that booster, sharing its pressure stabilized tank structure.

TechnicalEdit

Centaur was the first rocket stage to utilize liquid hydrogen (LH2) and liquid oxygen (LOX) as propellants. Despite high performance, LH2 had to be chilled at extremely low temperatures (lower than LOX) and its low density meant that large fuel tanks were needed.

The first attempt at using an LH2/LOX-fueled engine was the Air Force's top-secret Lockheed CL-400 Suntan reconnaissance aircraft program in the mid-1950s. The progress made during the aborted venture was picked up by Convair and others for rocket stage use. Originally, Centaur was conceived of as a purely experimental project to develop experience for larger, more powerful rocket stages so as not to distract Convair's focus on the all-important SM-65 Atlas missile program.

Convair developed a specially-enhanced version of the Atlas D vehicle for mating with Centaur stages; the Atlas was equipped with an uprated propulsion system, the MA-5, which had twin turbopumps on each booster engine, and the structure reinforced for the large upper stage, along with elongated fuel tanks. Centaur development was made somewhat difficult by the insistence on modifying Atlas components rather than developing totally new ones. This was done for time and budget reasons and because it allowed the Centaur to be manufactured on the existing Atlas assembly line at Convair. The engines were manufactured by Pratt and Whitney. There were considerable difficulties integrating the two vehicles, especially because Atlas-Centaur would be almost 30% longer than an Atlas ICBM and there were doubts as to its aerodynamic stability in flight.[citation needed]

ProgramEdit

Although originally under ARPA supervision, Centaur was transferred to NASA in July 1959, eleven months after the program's inception. However, the Air Force retained overall supervision in part because they intended to use Centaur to launch a network of military communications satellites known as ADVENT. A constellation of ten satellites would provide round-the-clock instant communications for the three main branches of the US military. The first three would be launched on an Atlas-Agena, then the remainder on Centaur. ADVENT never got off the drawing board, but Centaur quickly found a use for several NASA planetary probe projects, namely Mariner and Surveyor.

An initial lack of funds caused the project to drag on far longer than intended. Under original timetables, Centaur was to make its first flight in January 1961. In April, NASA Lunar and Planetary Programs director Oran Nicks suggested that it might be necessary to use Atlas-Agena for Mariner instead. In April 1962, a month before Centaur's first test launch, it came out that the rocket stage's lift capacity was about 400 pounds less than anticipated, which meant that Surveyor could not carry as many experiments as originally intended.[citation needed]

R&D flightsEdit

First flightEdit

In October 1961, the first Atlas-Centaur (Vehicle F-1: Atlas 104D and Centaur F-1) arrived at Cape Canaveral and was erected at the newly completed and specifically built LC-36As. Technical problems caused the vehicle to sit on the launch pad for seven months, the most serious being leakage of liquid hydrogen through the intermediate bulkhead separating the propellant tanks combined with numerous lesser maladies with the guidance and propulsion systems. The vehicle was launched on 8 May 1962, with the intention of performing a single burn with a partially fueled Centaur. At T+53 seconds, the Centaur stage ruptured and disintegrated, taking the Atlas with it in a matter of seconds.

It was unclear what had caused the failure at first, as tracking camera footage merely showed a large white cloud enveloping the booster followed by explosion of the entire launch vehicle. Initial assumptions were that Atlas had suffered a LOX tank failure, either from a pressurization problem, rupture of the tank from flying debris, or structural bending/aerodynamic issues caused by the unproven Atlas-Centaur combination, and indeed there had been several previous occurrences of these failure modes on Atlas launches. Scott Carpenter's Mercury flight was only days away, and if the failure were caused by the Atlas, it could mean significant delays for that mission, which used a similar Atlas D derived Atlas LV-3B booster. However, analysis of telemetry data and closer examination of the launch films quickly confirmed the Centaur as the source of trouble.

The failure was determined to be caused by an insulation panel that ripped off the Centaur during ascent, resulting in a surge in tank pressure when the LH2 overheated. The pneumatic system responded by excessive venting of propellant to reduce pressure levels, but eventually they exceeded the LH2 tank's structural strength. It then ruptured, causing flying debris to also rupture the Atlas's LOX tank, followed by complete destruction of the launch vehicle. The panel had been meant to jettison at 50 miles (80 kilometers) up when the air was thinner, but the mechanism holding it in place was designed inadequately, leading to premature separation. The insulation panels had already been suspected during Centaur development of being a potential problem area, and the possibility of a LH2 tank rupture was considered as a failure scenario. Testing was suspended while efforts were made to correct the Centaur's design flaws.

InvestigationEdit

A Congressional investigation in June 1962 called the overall management of the Centaur program "weak," and Wernher von Braun recommended that it be cancelled in favor of a Saturn I with an Agena upper stage for planetary missions. The Congressional committee was headed by Representative Joseph Karth (D-Minnesota), who expressed his opinion that Centaur was a useless project.[citation needed]

In addition, the production Centaur stage had less lift capacity than originally planned, leading to ARPA cancelling Project Advent. NASA transferred Centaur development from MSFC to the Lewis Center in Ohio where a team headed by Abe Silverstein worked to correct the insulation panel problems and various other design flaws.[1]

In November 1962, President Kennedy suggested cancelling Centaur entirely, but was talked out of it on the grounds that the experience gained with liquid hydrogen rocket engines was vital to the success of the Apollo program. In addition, Werner Von Braun's proposed Saturn-Agena was ruled out for cost reasons - Saturn was much too expensive to justify as a launch vehicle for small uncrewed probes. In addition, Agena was proving to be a reliability nightmare in both Air Force and NASA programs.[citation needed]

Eight Atlas-Centaur test missions were scheduled to be completed by the end of 1964, followed by the first Surveyor program launch. Centaur was upgraded to a high priority project because of this direct relation to Apollo.[citation needed]

Meanwhile, the Department of Defense had settled on the Titan family for its heavy lift launching needs and so the Atlas-Centaur would remain a civilian launch vehicle used by NASA to fly scientific and commercial payloads. A conflict between the Air Force, who had primary oversight of the Atlas, and NASA also existed as the Centaur stage required various modifications to the basic Atlas. By 1962, the Air Force had considered the Atlas fully developed and operational and was against any further significant changes to it which might potentially jeopardize the ICBM program. The dispute was ultimately resolved by NASA agreeing to purchase standard Atlas D vehicles which could be custom-modified for Centaur launches. However, when the Atlas ICBM program ended in 1965, Convair replaced all of the earlier variants with a standardized booster for all space launches.[citation needed]

Second flightEdit

More than a year later, AC-2 took place a few days after President Kennedy's assassination. The redesigned Centaur stage functioned without any problems and performed a single burn to geosynchronous transfer orbit, where it remains today. The insulation panels were permanently attached to the stage as the jettison problem had still not been solved. Vibration data proved that the panels would have prematurely detached had they not been bolted down. The ultimate fix to the panel problem added more dry mass to Centaur, further dropping its payload capacity.[citation needed]

Third flightEdit

AC-3 was launched on 30 June 1964. Atlas experienced a slightly LOX-rich engine operation during the first minute of flight, but overall performance was unaffected. Insulation panel and payload shroud jettisons were tested for the first time. Following Centaur staging and engine start, the number two (C-2) engine began to lose roll control. The C-1 engine was able to compensate for a time, but the Centaur eventually lost control and began tumbling. Premature engine shutdown due to propellant starvation occurred at T+496 seconds, and the Centaur impacted in the South Atlantic. Postflight investigation traced the malfunction to a failure of the C-2 engine hydraulic gimbal acutator.[2]

Fourth flightEdit

AC-4 launched on December 11 following two scrubbed attempts due to bad weather. The guidance system was operated closed-loop for the first time and an attempt was made to recover the payload shroud, which was equipped with a balloon designed to release green marker dye into the ocean. The shroud was sighted by recovery crews but sank into the ocean and could not be located. The Atlas phase of the flight and the initial phase of Centaur flight were uneventful. The mission went awry when the Centaur could not be restarted due to an ill-conceived design modification--the ullage rockets were reduced in size to save weight, however they proved insufficient to settle the propellants in the tanks. Subsequently, venting hydrogen caused the vehicle to tumble out of control. After ten orbits, the Centaur reentered over the South Pacific.[3]

Fifth flightEdit

The AC-5 flight on 2 March 1965 was only intended to carry out a single burn of the Centaur, and program officials felt confident. However, this was also the first Atlas-Centaur equipped with the uprated 165,000 lb thrust MA-5 booster engines after previous testing on two Atlas-Agena flights. The booster engines shut down 1.5 seconds after liftoff, and the rocket fell back onto LC-36A and exploded. The damage to LC-36A was not as severe as it looked and repairs were largely completed in three months, but the completion of LC-36B was also accelerated. Most damage was thermal rather than structural, and the upper portion of the umbilical tower, which was in the center of the LH2 blast, had been subjected to temperatures of 6000°F (3315°C).[1] The accident marked the first failure of an Atlas booster in a space launch since Midas 8 in June 1963, a new record at the time of 26 consecutive flights with only malfunctions of the upper stages or payload. This would be the last on-pad explosion at Cape Canaveral until 2016.[citation needed]

Postflight investigation examined several possible reasons for the booster engine shutdown, with attention quickly centering on closure of the booster fuel prevalves. The low pressure booster fuel ducting was found to have collapsed from a sudden loss of fuel flow, but had not ruptured. The investigation concluded that the fuel prevalves had only opened partially and the propellant flow was enough to push them shut, starving the booster engines of RP-1 and causing a LOX-rich shutdown. Engine start had proceeded normally and all booster systems functioned properly until the prevalves closed, all other launch vehicle systems functioned normally until that point. Bench testing confirmed that there were several possible ways that the prevalves would only open partially, although the exact reason was not determined. This failure mode had never occurred in the 240 Atlas launches prior to AC-5 despite always having been possible.[citation needed]

Until a more permanent solution could be found, a temporary fix was made for Atlas-Agena vehicles by equipping the prevalves with a manual lock that would be enabled during the prelaunch countdown. In addition, an unrelated system malfunction in AC-5 was discovered when examination of telemetry data found that a power failure had occurred in the guidance computer. As a temporary fix for Atlas-Centaur AC-6, 7, and 8, several unused components were removed from the computer in order to reduce system complexity and failure points.[citation needed]

InvestigationEdit

The failure of AC-5 resulted in another Congressional investigation, again headed by Rep. Joseph Karth, who argued that $600 million of taxpayer money had been spent on Centaur so far with little to show for it and that Convair was taking advantage of being the sole supplier of the Atlas-Centaur vehicle. The committee proposed that NASA consider alternate choices for the planetary probe program, such as Titan IIIC, or outsource manufacture of Centaur to other contractors. However, NASA representatives argued that this was impossible as no other aerospace company had the experience or technical capability to manufacture the Centaur's balloon tanks.[citation needed]

Later flightsEdit

LC-36B was hastily brought online, with an entirely successful AC-6 launched on 11 August 1965. Although Centaur appeared flight-ready, the Surveyor program was delayed. Vehicles AC-7 and AC-10 were designated for the first Surveyor missions, with AC-8 to carry out one more test, which took place on 7 April 1966. The Centaur's ullage motors failed again because they did not have enough propellant for the mission. Seven Surveyor probes were launched, all on Atlas-Centaur.[citation needed]

Beginning with AC-13 (Surveyor 5), Atlas-Centaur vehicles switched to the standardized SLV-3 Atlas core.[citation needed]

Operational launchesEdit

Initially, a modified Atlas D designated LV-3C was used as the first stage[4] This was quickly replaced by SLV-3C, and later the SLV-3D, both derived from the standard Atlas SLV-3 rocket. Two spaceflights, with the Pioneer 10 and Pioneer 11 space probes to Jupiter, Saturn and exiting the Solar System, used a spin-stabilized "Star-37E" solid propellant final stage weighing 2473 pounds and contributing 8000 mph to the velocities of the spacecraft.[5]

With the retirement of the Agena stage in 1978, all Atlases flown from that point onward were paired with Centaurs except for a few military flights involving decommissioned Atlas E/F missiles.[citation needed]

Originally designed and built by Convair Division of General Dynamics in San Diego, California, production of Atlas Centaurs at Convair ended in 1995 but was resumed at Lockheed-Martin in Colorado. The list of Atlas Centaur ID numbers began with AC-1 launched on 8 May 1962 and ended with the last Atlas III (Centaur), AC-206, launched on 3 February 2005.[citation needed]

The Rocketdyne-powered Atlas-Centaur was sometimes referred to as a 21/2 stage launch vehicle because the Atlas first stage (in most cases) jettisoned the twin-thrust-chamber booster engine prior to the completion of the first stage burn. Atlas Centaurs with a Rocketdyne-powered first stage were used for 167 launches between 1962 and 2004 by which time they had been superseded by Atlas Vs with a new first stage powered by a much more powerful Russian-designed and built RD-180 twin-chamber engine. (Atlas Vs are not generally referred to as "Atlas Centaurs" and do not share the AC- serial numbers of the original Atlas Centaurs that had the pressure stabilized first stages.)[citation needed]

AC-33 failureEdit

On 20 February 1975, AC-33 launched carrying an Intelsat-4 communications satellite. The flight went awry around the two-minute mark. During booster engine separation, a swivel lanyard designed to pull out an electrical plug supplying power to the booster section failed to detach, causing a voltage spike that reset the Atlas's guidance computer. Control of the booster started to fail and Range Safety sent the destruct signal at around 403 seconds into launch. Investigation showed that the lanyard was not only inadequately designed, it was an off-the-shelf component designed for marine equipment and not rockets or aircraft. Atlas vehicles had been flying with them for years without anyone noticing or considering this potential failure mode. The backup Intelsat was launched successfully on AC-35 the following May.[citation needed]

AC-43 failureEdit

Two years later on 29 September 1977, another attempted launch of an Intelsat communications satellite took place on AC-43. Shortly after liftoff, abnormal temperatures were detected in the Atlas's thrust section and continued to rise as the booster ascended. A visible thrust section fire could be seen starting at T+33 seconds and sustainer thrust vector control hydraulic pressure was lost at T+55 seconds, causing total loss of vehicle control. The payload fairing and satellite were stripped from the booster, followed by the Atlas exploding as the thrust section fire touched off the propellant tanks at T+60 seconds. The Centaur flew free until being destructed by the Range Safety Officer a few seconds later. NASA and Air Force officials, already busy investigating the launch failure of a Delta booster three weeks earlier, dredged the Atlas's engines from the ocean floor and sent them to Convair for examination. It was concluded that a gas generator leak caused by improper brazing of a pipe led to overheating and fire in the thrust section of the Atlas. The pipe also suffered corrosion from six years of sitting in a warehouse in the salty air along the Florida coast and the damage was in an area not visible during preflight examination. The Atlas used on this flight had been delivered to the Cape in 1971 and kept in storage since then, an unusually long time. In the aftermath of the accident, NASA inspected their inventory of Atlas vehicles and found several more improperly brazed pipes which needed replacement.[citation needed]

AC-67 failureEdit

On 26 March 1987, AC-67 failed to launch a Navy FLTSATCOM satellite. Weather conditions were extremely poor that day, with thick clouds and heavy precipitation. Although engineers objected to launching, the NASA program directors gave the go-ahead anyway. The Atlas disappeared into the cloud cover shortly after liftoff and was struck by lightning around 38 seconds into launch. Control of the booster started to fail and it broke apart from structural loads at T+50 seconds. Range Safety sent the destruct command, but there was no evidence that the booster ever received it. Debris rained out of the clouds onto the pad area, the shoreline, or in shallow water just off of it and was easily recovered. A section of the payload fairing was found to have multiple small holes burned in it due to repeated lightning strikes. The key piece of evidence was the Atlas's flight computer, which was recovered intact and examined. It was discovered that the last command issued was a signal to gimbal the booster engines hard to right, caused apparently by a lightning bolt altering a single word in the guidance program.[citation needed]

This accident was the culmination in the string of disasters that had befallen the US space program since the Titan 34D failure of August 1985 and caused significant reappraisals of weather guidelines at Cape Canaveral.[citation needed]

VariantsEdit

Name First launch Last launch Launches Successes Failures Partial failures Remarks
Atlas D derived Atlas Centaurs
Atlas LV-3C Centaur-A 1962-05-08 1 0 1 0
Atlas LV-3C Centaur-B 1963-11-27 1 1 0 0
Atlas LV-3C Centaur-C 1964-06-30 1965-03-03 3 0 2 1
Atlas LV-3C Centaur-D 1965-08-11 1967-07-14 7 7 0 0
Atlas SLV-3C Centaur-D 1967-09-08 1972-08-21 17 14 3 0 One flight with Star-37E upper stage
Atlas SLV-3D Centaur-D1A 1973-04-06 1975-05-22 6 5 1 0 One flight with Star-37E upper stage
Atlas SLV-3D Centaur-D1AR 1975-09-26 1983-05-19 26 24 1 1
Designations for evolved Atlas Centaur versions
Atlas G 1984-06-09 1989-09-25 7 5 2 0 (Atlas G Centaur-D1AR)
Atlas I 1990-07-25 1997-04-25 11 8 3 0
Atlas IIA/IIAS 1991-12-07 2004-08-31 63 63 0 0
Designations for RD-180 powered Atlases with Centaur 2nd stage
Atlas III 2000-05-24 2005-02-03 6 6 0 0
Atlas V 2002-08-21 Active 49 48 0 1

ReferencesEdit

  1. ^ a b Kyle, Ed (May 28, 2005). "Atlas Centaur LV-3C Development". www.spacelaunchreport.com. Retrieved April 15, 2016.
  2. ^ "Postflight Evaluation Report, Atlas-Centaur AC-3 Lewis Research Center"
  3. ^ "Postflight Evaluation Report, Atlas-Centaur AC-4 Lewis Research Center"
  4. ^ Krebs, Gunter Dirk. "Atlas Centaur". Gunter's Space Page. Retrieved April 15, 2016.
  5. ^ "STAR Performance and Summary Chart". Thiokol Propulsion. 2000. Archived from the original on August 16, 2000.