Tomorrow, if all goes well, more than 120,000 pounds (54,430 kg) of thrust will rock Space Launch Complex (SLC)-40 at Cape Canaveral Air Force Station, Fla., as SpaceX stages the long-awaited Pad Abort Test of its crewed Dragon spacecraft. The test, which is part of the Commercial Crew integrated Capability (CCiCap) contract with NASA and comes only months after SpaceX was awarded a slice of the $6.8 billion Commercial Crew transportation Capability (CCtCap) “pie,” will see eight side-mounted SuperDraco thrusters boost the soon-to-be-piloted capsule to an altitude of 5,000 feet (1,500 meters) and about 6,000 feet (1,800 meters) eastwards, after which Dragon will execute a parachute-guided splashdown in the Atlantic Ocean. Wednesday’s test will be dramatic, indeed, and represents a critical milestone as SpaceX aims to deliver U.S. astronauts to the International Space Station (ISS), aboard a U.S. spacecraft, and from U.S. soil, by mid-2017. Yet it is actually the latest in a long line of pad abort tests over more than five decades, which have served to prove the safety and flightworthiness of U.S. crewed vehicles.
If all goes according to plan on Wednesday morning—and SpaceX has already explained that “Winds above 25 knots and Phase II Lightning are the primary Range weather constraints”—the Pad Abort Test will get underway at 7 a.m., about 22 minutes after local sunrise. “Winds have become gusty out of the east and will remain so for the next couple of days as a low-pressure area develops south-east of Central Florida,” it was highlighted by the 45th Weather Squadron in an update on Monday. “The increase in winds also increases the threat of showers along the Space Coast. Showers will be most prevalent in the morning hours and typically diminish after noon. On Wednesday, the low-pressure area will drift north and east, relaxing the pressure gradient, which will result in lower wind speeds over the Spaceport.” Maximum winds to 5,000 feet (1,500 meters) are expected to be easterly at 20 knots, producing a 70-percent likelihood of acceptable conditions on Wednesday. That probability is expected to improve to 80-percent favourable on the backup day on Thursday, as the low-pressure region continues to move north-west and winds continue to weaken. In the event of a 24-hour scrub, the maximum winds to 5,000 feet (1,500 meters) on Thursday will be north-easterly at 17 knots.
BOOKMARK our “Launch and Events Tracker” for regular updates and LIVE COVERAGE of the SpaceX Crew Dragon PAT Wednesday.
Although the test will occur from SLC-40, which is the same site as used last week for the TurkmenÄlem52E/MonacoSat launch, several key modifications were performed on Thursday, 30 April. Notably, the high-level catenary lines for lightning protection have been removed and a truss structure to support the Dragon vehicle at ground level was installed over the SLC-40 flame trench.
At T-0, the eight hypergolic SuperDraco thrusters, built into the sides of the Dragon, will roar to life and ramp up to their maximum 120,000 pounds (54,430 kg) of thrust. This impetus will propel the vehicle away from SLC-40. “After half a second of vertical flight, Crew Dragon pitches toward the ocean and continues its controlled burn,” SpaceX reported Monday, 4 May. “The SuperDraco engines throttle to control the trajectory, based on real-time measurements from the vehicle’s sensors.” Two seconds into the ascent, the spacecraft will have already attained an altitude of 328 feet (100 meters) and will hit 1,640 feet (500 meters) at five seconds. “The abort burn is terminated once all propellant is consumed,” it was continued, “and Dragon coasts for just over 15 seconds to its highest point about 0.93 miles (1,500 meters) above the launch pad.”
The unpressurized “trunk” will be jettisoned at T+21 seconds and the Dragon capsule will commence a slow rotation, with its base heat shield positioned towards the ground. Four seconds later, the drogue parachutes will be deployed, within a 4-6 second window, stabilizing the vehicle in advance of the unfurling of the three main canopies at T+35 seconds. Current expectations are that the Dragon capsule will hit the waters of the Atlantic Ocean at T+107 seconds, with the impact point predicted about 1.4 miles (2,200 meters) downrange of SLC-40.
During Wednesday’s test, SpaceX hopes to acquire significant data in the areas of Sequencing, Closed-Loop Control, Trajectory and External and Internal Environments. It will demonstrate the proper sequencing of the pad-abort timeline, serving to validate the execution of multiple critical commands in a very short period, as well as testing as many as eight SuperDracos in unison for the first time. It will obtain trajectory data for both maximum altitude and downrange distance from the pad and will gather data on “various internal and external factors to Crew Dragon to help ensure safe conditions for crew transport.” Interestingly, SpaceX also noted that the crash test dummy is actually not nicknamed “Buster”, despite media reports to the contrary and SpaceX Vice President of Mission Assurance Hans Koenigsmann referring to the dummy as such during last Friday’s press briefing. “Buster the Dummy already works for a great show you may have heard of, called MythBusters,” SpaceX said in a press statement Monday. “Our dummy prefers to remain anonymous for the time being.”
However, Wednesday’s Pad Abort Test is the latest in a long series of such exercises to validate pad systems, booster systems and spacecraft systems, ahead of piloted flights. As described in yesterday’s AmericaSpace article, the Little Joe booster advanced U.S. knowledge of the intricacies of high-altitude abort events in readiness for Project Mercury, and its immediate descendent (the “Little Joe II”) was employed between August 1963 and January 1966 for five unmanned tests of the escape system for the Apollo Command and Service Module (CSM), as America strove to plant human bootprints on the Moon before the decade’s end. Early studies for Little Joe II (initially dubbed “Little Joe Senior”) got underway in mid-1961, not long after the completion of Little Joe’s involvement with Project Mercury. It would be required to support two launches in 1963 for tests in the Max Q region—an area of maximum aerodynamic turbulence upon a launch vehicle’s flight surfaces, typically encountered about a minute into ascent—followed by two very-high-altitude atmospheric aborts and finally a “Confirming Max Q Abort.” In May 1962, General Dynamics/Convair won the contract to develop the Little Joe II vehicle, with White Sands Missile Range, near Alamagordo, N.M., chosen as the launch site.
As preparation work got underway, Aerojet-General’s Algol-1D solid-fueled rocket engine—capable of 98,916 pounds (44,870 kg) of propulsive yield—was selected as the main “sustainer” motor, supplemented by a clustered arrangement of six Recruit engines, producing a total thrust of 228,000 pounds (103,420 kg). Resized to accommodate the much larger Apollo CSM, the Little Joe II stood 33.1 feet (10.1 meters) tall—rising to 85.9 feet (26.2 meters), with the payload affixed—and 12.8 feet (3.9 meters) in diameter, with a span across the four aerodynamic stabilization fins at its base of 28.5 feet (8.7 meters). The stack was then topped by the launch escape apparatus, a truncated rectangular pyramid which acted as an intermediate structure between the CSM and the four solid-propellant tower-jettison motors, which produced 155,000 pounds (70,000 kg) of thrust to pull the spacecraft away from a failed booster.
It was agreed that the maiden voyage of the Little Joe II would be for qualification purposes, and in the meantime, by March 1963, the first booster had emerged from production and was delivered to White Sands at the end of April. The Qualification Test Vehicle (QTV) followed in mid-July and was successfully fired from Army Launch Area (ALA)-3 on 28 August, carrying a dummy aluminum shell in the basic shape of the Apollo CSM and an inert launch escape system. In spite of failing to destruct when commanded, due to an improperly installed primacord, the Little Joe II reached a maximum altitude of 4.5 miles (7.3 km), covered a distance of 8.7 miles (14 km) and accomplished its test objectives to determine base pressures and heating on the vehicle.
Six months later, in February 1964, the second Little Joe II arrived at White Sands, and a boilerplate Apollo CSM was installed at the end of March, prior to the “A-001” flight on 13 May. With the six Recruit motors firing for 1.5 seconds and the Algol-1D sustainer operating for 42 seconds, the flight attained an altitude of 3.1 miles (5 km) and at 44 seconds accomplished the first successful abort with a “live” launch escape system. The landing sequence of the spacecraft also ran normally, with the exception of a failure of one of the mortar-deployed main parachutes, which produced a faster than intended landing. A third (“A-002”) mission took place on 8 December and evaluated the effectiveness of the launch escape system at equivalent pressures and stresses to those expected during a Saturn IB or Saturn V ascent.
On 19 May 1965, the fourth (“A-003”) mission failed in spectacular fashion when one of the Little Joe II’s four stabilizing fins failed, inducing an uncontrollable roll and precipitating the disintegration of the vehicle. A subsequent NASA-General Dynamics/Convair investigation revealed that the No. IV fin inadvertently moved into a “hard-over” position, about a second after liftoff, due to an internal mechanical failure. By 2.5 seconds into the flight, the fin had reached a fully deflected position, where it remained until the vehicle disintegrated. Consequently—and a little ironically—what should have been an abort test turned into a real abort situation, although it was executed at low altitude, rather than the intended higher altitude.
“The faster the rocket went up, the faster it spun around,” remembered instrumentation and electronics engineer Gary Johnson in a 2010 NASA oral history, who observed the A-003 failure. “It had six solid-rocket motors … and those six motors all just came apart. We were only a half-mile away from the launch pad and, all of a sudden, these rockets were coming flying in every direction, almost like they were coming back at us, but they weren’t, of course.” However, the launch escape system fired on time and successfully pulled the Apollo CSM away from the blazing booster and it parachuted to safety.
Also watching the ill-fated A-003 ascent was NASA’s Little Joe II Program Manager Milt Silveira and his wife. “The vehicle started to roll, and when it rolled to the point, structurally, [that] it wouldn’t take it, and it blew apart, and then the payload aborted off the launch vehicle,” Silveira told the NASA oral historian in 2005. “So it was a little more realistic than what we thought! It was supposed to go to a hundred miles down, around, and downrange, and it only went about twenty. But it scattered aluminum all over the sky and things like that. It was a very realistic test from that point, even though it wasn’t the planned one.”
“The lesson out of that was the abort system to initiate the abort for the spacecraft and the launch vehicle consisted of the opening-up of the circuit between the spacecraft and the launch vehicle to initiate the abort,” added Gary Johnson in his recollection of the events of that day. “When the launch vehicle came apart, that in itself opened up that wiring and automatically initiated the Launch Escape System. The pyros fired to separate the Command Module from the launch vehicle, the launch escape motor went off, the pitch-control motor went off, and it went through the entire sequence, which consisted of tower jettison, deploying the apex cover, putting out the drogue parachutes, putting out the main parachutes and then safely recovering the vehicle. The lesson there was on any future vehicles, one of the abort sensors should be this wiring that goes down to the launch vehicle such that if it ever opens up due to a launch vehicle blow-up or structural break-up, it would automatically, without any other indication, initiate the abort.”
The final, seven-minute-long Little Joe II test (“A-004”) occurred on 20 January 1966, delivering a production Apollo Block I spacecraft (CSM-002) to a peak altitude of 14 miles (23 km) and demonstrating its twin objectives of proper LES orientation/stabilization and full structural integrity of the escape vehicle.
In the meantime, separate tests were also underway to demonstrate the capacity of the launch escape system to pull the spacecraft away from an exploding booster on the pad. Unlike Little Joe II altitude flights, which sought to demonstrate the system’s capability to boost a spacecraft away from a failing booster in high-dynamic-pressure conditions, a pair of Pad Abort Tests, also at LC-36 at White Sands, saw the launch escape mechanism fired at ground level. On 7 November 1963, Pad Abort Test-1 successfully lifted a boilerplate Apollo CSM and attached Launch Escape System (LES) from LC-36. Fifteen seconds into the abort, the LES separated and the CM successfully parachuted to a safe landing. With the exception of soot deposited on the spacecraft’s exterior surfaces and a less-than-predicted stability, the 165-second test was considered a great success, reaching a peak altitude of 1.7 miles (2.8 km). This was followed by a highly successful Pad Abort Test-2 on 29 June 1965, closing out Little Joe’s final involvement with a soon-to-be-piloted spacecraft.
It would be more than four decades—well into the twilight of the space shuttle era—before a series of pad abort testing of an entirely new U.S. piloted spacecraft took place. Following NASA’s August 2006 announcement that Lockheed Martin would be prime contractor for the Orion spacecraft, the initial contracts were expanded in April of the following year with plans for two tests of a Launch Abort System (LAS). That same month, NASA partnered with the Air Force’s Space Development and Test Wing at Kirtland Air Force Base, near Albuquerque, N.M., to stage a series of tests between 2008-2011 of an mechanism to pull Orion to safety in the event of a launch malfunction. “A total of six tests are planned, pending environmental assessments,” it was reported. “Two will simulate an abort from the launch pad and will not require a booster. The rest will use abort test boosters and simulate aborts at three stressing conditions along the … launch vehicle trajectory.”
Groundbreaking operations for the construction of the abort test pads got underway at the Army’s White Sands Missile Range, near Las Cruces, N.M., in November 2007, and the solid-fueled motor to jettison the LAS was static-fired by prime contractor Aerojet in April 2008. The Pad Abort Test-1 took place at White Sands—the very same location from where the Little Joe II launches originated, so many years earlier—on 6 May 2010. An abort motor, with a momentary 500,000 pounds (226,800 kg) of thrust, burned for six seconds to boost Orion away from the pad. It reached a peak velocity of 540 mph (870 km/h). Simultaneously, a 7,000-pound-thrust (3,170 kg) attitude control motor was also ignited to provide steering, whilst a jettison motor pulled the LAS away from the capsule to permit parachute deployment and a safe landing. Overall, Pad Abort-1 lasted 135 seconds and Orion was brought to a touchdown about a mile (1.6 km) north of the pad. At the time of writing, an Orion Ascent Abort Test (AA-2) is planned from Space Launch Complex (SLC)-46 at Cape Canaveral Air Force Station, Fla., in 2018.
With SpaceX’s fellow CCtCap winner, Boeing, expected to conduct its own Pad Abort Test in support of its CST-100 spacecraft, sometime next year, ahead of inaugural unpiloted and manned missions in 2017, the roar of abort engines on Wednesday morning promises to be a significant milestone as these new crew-carrying vehicles draw closer to maturity. As cautioned by NASA’s Jon Cowart and SpaceX’s Hans Koenigsmann in Friday’s press briefing, the Dragon Pad Abort Test is a development test, “not a shiny, well-polished Space Shuttle launch.” Its ascent will be neither slow or sedate; rather, it will blaze to 5,000 feet (1,500 feet) in about six seconds, before the capsule plummets back to an oceanic splashdown. “I can hold my breath the entire time,” quipped Koenigsmann.
However, what we should see on Wednesday morning will draw more than a few uncanny parallels with the Little Joe missions of yesteryear. It will also closely mirror the Beach Abort Test from 9 May 1960, which was described as “a sterling qualification test, but … hardly spectacular to the public.” Speaking back in 1999, Rodney Rose recalled inviting the media to one of the early Little Joe tests. On one occasion, Rose briefed a group of photojournalists about what they were about to behold.
“Well, this is not quite like what you’re used to, guys,” he explained. “This thing goes off pretty fast.”
“No sweat,” came the reply from one of the photojournalists. “We’ll follow that.”
On the morning of the test, however, he zoomed his camera in on the pad … and missed the Little Joe completely, so rapid was its departure and ascent. “Where did it go? Where did it go?” the hapless photojournalist asked Rose. He had failed to appreciate the sheer impetus with which the launch escape system propelled its precious payload away from the booster. “Six G makes a difference,” Rose explained, “because, you know, 1.1 or less G, they take off pretty sedately from the Cape.”
And therein lies the singular lesson of a Pad Abort Test: Whatever happens on Wednesday morning—whether spectacular to the public or not—the lesson is to Watch Carefully.
For one thing is certain: It’ll be fast.
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What a great two part article. I was familiar with the Little Joe, but it’s great to get so much more history to put the upcoming abort tests (not just of Crew Dragon, but CST-100 and Orion as well).
In seeing milestones for CST-100, I’ve only read about a pad abort test and not an in-flight abort, which I would expect would be just as critical. Both Orion and Crew Dragon have plans for in-flight abort. Has NASA given any indication why this won’t be necessary for CST-100?
Great articles Ben,
I have a few qualms about the tests that only came to me after reading the articles. The original abort systems tests in the 50s and 60s had a number of anomalies. It would seem that if Dragon 2 is fully reusable in the lower altitudes, that doing a single pad abort test will leave questions unnecessarily hanging. Questions like (assuming success tomorrow), “Was this a fluke?” What if this or that condition had been present? If it is economically reusable, then several simulated aborts would seem to be desirable.
This is the first flight of a new type of vehicle with new engines that have also never flown. Should the very first flight have so much riding on it? It would seem that a boilerplate unit would have been thoroughly wrung out at McGregor, or possibly Spaceport America.
My predictions is that the test will be successful in that the instrumented dummy will ‘survive’. Further that there will be at least one anomaly for us to argue the seriousness of. That anomaly will not be in any of the systems that we are expecting it from. In about nine hours, you can start “I told you so’s” when I am wrong.
It would seem that I was wrong about the anomaly.
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