“Pad Abort Test-2 (Apollo)” (PA-2) - the 15th launch under the Apollo program , the 2nd launch without a launch rocket, to test the Emergency Rescue System (CAC) , took place on June 29, 1965 .
| Pad Abort Test-2 (Apollo) | |
|---|---|
 | |
| General information | |
| Ship flight data | |
| Ship name | PA-1 (Apollo) |
| Launch pad | Polygon White Sands |
| Launch | June 29, 1965 13:00:01 UTC |
| Ship landing | June 29, 1965 13:01:54 UTC |
| Flight duration | 1 min 52.6 sec |
| Apogee | 2.82 km |
| Weight | kg |
| Crew flight data | |
| Associated Expeditions | |
Content
Background
The PA-2 launch tested the ability of the emergency rescue system (CAC) to provide a safe soft landing for the Apollo crew in a booster accident. This launch was the second (after PA-1 ) test of SAS from ground level.
The SAS was equipped with flat stabilizer plates in the upper part of its body to orient the command module (KM) with a heat shield down to the moment the SAS was shot and the parachutes were released. The KM prototype (BP No. 23A) had a protective coating, it was made of cardboard and was previously used in flight A-002 . After restoration and refinement, the layout more closely corresponded to the regular CM in size, weight and other characteristics. Landing pattern was the same as in flight A-003 .
Flight
The flight began on June 29, 1965 at 6:00:01 local time (13:00:01 UTC) from launch pad No. 36. The main and diverting SAS engines started simultaneously, taking the command module along the planned path. Already at the start, a moderate rotation of the CM around the vertical axis was manifested due to the aerodynamic asymmetry of the command module, which did not affect the success of the test.
The plane of the stabilizers was revealed and deployed KM in the position necessary for the release of brake parachutes. CAS body and heat shield were shot regularly. The protective coating applied to the conical surface of the KM remained intact. The protective cone (under the SAS farm), as expected, collapsed due to the pressure drop during the shooting from the command module, which, however, could not affect the successful opening of the parachutes.
Although one of the lines of the parachute was twisted, the landing went fine. Brake parachutes deployed and stabilized the command module, the main parachutes came out, providing a satisfactory vertical speed of descent. The maximum height reached was 2.82 km - 0.2 km more than the calculated one. The command module landed 2.32 km from the launch pad, 0.6 km further than planned. Four glass windows were installed on the KM layout. No soot appeared on them, but on three they found oil drips. It was decided that these leaks would not cause excessive deterioration in visibility during descent and splashdown. The test was very successful, all the planned goals were achieved.