Engineering:Little Joe 1

Little Joe 1

Little Joe 1 prepares for launch.
Mission type	Max Q abort and escape test
Operator	NASA
Mission duration	20 seconds
Distance travelled	2,000 feet (610 m)
Apogee	2,000 feet (610 m)
Spacecraft properties
Spacecraft type	Mercury boilerplate
Manufacturer	McDonnell Aircraft
Launch mass	1,159 kilograms (2,555 lb)
Start of mission
Launch date	21 August 1959 (1959-08-21) Launch Escape System fired 30 minutes before planned launch
Rocket	Little Joe
Launch site	Wallops LA-1
End of mission
Landing date	21 August 1959 (1959-08-22)
Project Mercury Abort Tests

Little Joe 1 (LJ-1) was a failed launch of a Little Joe by NASA, a solid fuel rocket that was designed for a Max Q abort and launch escape system test for the Mercury capsule. The objective was to determine how well the escape rocket would function under the most severe dynamic loading conditions anticipated during a Mercury-Atlas launching.

On 21 August 1959, LJ-1 was being prepared for launch from the Wallops Flight Facility, Wallops Island, Virginia. At 35 minutes before launch, evacuation of the area had been proceeding on schedule and the batteries for the programmer and destruct system in the test booster were being charged. Suddenly, half an hour before launch time, an explosive flash occurred. When the smoke cleared it was evident that only the capsule-and-tower combination had been launched, on a trajectory similar to an off-the-pad abort. The booster and adapter-clamp ring remained intact on the launcher. Near apogee, at about 610 m, the clamping ring that held tower to capsule released and the little pyro-rocket for jettisoning the tower fired. The flight time was 20 seconds.

The accident report for LJ-1, issued 18 September 1959, blamed the premature firing of the Grand Central escape rocket on an electrical leak, or what missile engineers call transients or ghost voltages in a relay circuit. The fault was found in a coil designed to protect biological specimens from too rapid an abort.

According to the 18 September 1959 accident report, the unexpected triggering of the launch escape system was caused by a transient or electrical leak; analysis showed it to be due to the rapid-abort system being wired directly into the destruct arming busbar. The batteries were shipped from England to the U.S. uncharged and shorted; on charging at the pad, the batteries, when enough charge was reached, actuated the sequencer for the abort system, and sensing insufficient altitude, fired the squibs in the abort motor. Insufficient power in the batteries then failed to initiate the tower jettison motor and capsule parachute recovery charge, and both crashed into the sea.

External links

• This New Ocean: A History of Project Mercury—NASA SP-4201