Pad Abort 1 flight test completed

NASA successfully tests Orion launch abort system.Provided by NASA Headquarters, Washington, D.C.
By | Published: May 7, 2010 | Last updated on May 18, 2023
Pad Abort-1
Pad Abort-1 Crew Module post landing scene was captured by an aerial source May 6, 2010 at the White Sands Missile Range in New Mexico.
May 7, 2010
NASA’s Pad Abort 1 flight test, a launch of the abort system designed for the Orion crew vehicle, lifted off May 6 at the U.S. Army’s White Sands Missile Range (WSMR) near Las Cruces, New Mexico. The flight lasted about 135 seconds from launch until the crew module touchdown about 1 mile north of the launch pad.

The flight was the first fully integrated test of this launch abort system design. The information gathered from the test will help refine design and analysis for future launch abort systems, resulting in safer and more reliable crew escape capability during rocket launch emergencies.

“Through hard work and incredible dedication over the past several years, the Orion Pad Abort 1 team has successfully tested the first U.S. designed abort system since Apollo,” said Doug Cooke, associate administrator for the Exploration Systems Mission Directorate at NASA headquarters in Washington, D.C. “This system is much more advanced in capability and technology than any abort system designed in the past. NASA strives to make human spaceflight as safe as possible, and what we learned here today will greatly contribute to that goal.”

The test involved three motors. An abort motor produced a momentary half-million pounds of thrust to propel the crew module away from the pad. It burned for approximately 6 seconds, with the highest impulse in the first 2.5 seconds. The crew module reached a speed of approximately 445 mph (716 km/h) in the first three seconds, with a maximum velocity of 539 mph (867 km/h) in its upward trajectory to about 1.2 miles (1.9 km) high.

The altitute control motor fired simultaneously with the abort motor and steered the vehicle using eight thrusters, producing up to 7,000 pounds of thrust. It provided adjustable thrust to keep the crew module on a controlled flight path and reorient the vehicle as the abort system burned out.

The jettison motor, the only motor of the three that would be used in all nominal rocket launches, pulled the entire launch abort system away from the crew module and cleared the way for parachute deployment and landing. After explosive bolts fired and the jettison motor separated the system from the crew module, the recovery parachute system deployed. The parachutes guided the crew module to touchdown at 16.2 mph (26.1 km/h), about 1 mile from the launch pad.

The Orion Project has begun the process of recovering all of the test articles from the WSMR range, and they will be evaluating all of the data over the coming weeks.

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