[FIRST APOLLO LAUNCH ESCAPE SYSTEM TEST NOVEMBER 7, 1963 WHITE SANDS, NEW MEXICO]

Year Published: 1963

Description: This film shows the first test of the Apollo launch escape system (LES) which took place on Nov. 7, 1963, at the White Sands Missile Range. A safety system connected to the Command Module, the LES was designed to protect the life of the crew in the event of a critical emergency at launch. 00:00: Man with high speed movie camera with large telephoto lens on a stand near launch site 00:20: Dignitaries and engineers, and possibly some astronauts, stand by for the tests 00:45: Everyone on the viewing stand for the test 1:16: Gus Grissom talks to an unknown man 1:36: Command Module test article seen after the test (this is out of sequence) 2:11: Panel briefs the viewers as to what they are about to see 2:36: Parachute provides shade for the viewers 3:23: NASA logo on control building at the range 5:04: shot of the smoke trail from the test (out of sequence) 6:21: Slate indicating 7 November 1963 at White Sands. 6:49: Launch sequence 7:24: Command module descends via parachute The Apollo launch escape system (LES) was designed to provide a positive means of crew escape if booster failure occurred during the initial phase of launch. The system had to achieve sufficient altitude for deployment of the command module (CM) parachutes and to ensure safe lateral separation. Lateral separation was achieved by firing simultaneously the pitch-control motor and the launch-escape motor for low altitude aborts. The pitch-control motor was not required for high-altitude aborts. The system is no longer required after second-stage ignition and is jettisoned after verification of ignition. The Apollo launch escape propulsion subsystem contained three solid-propellant rocket motors: the launch-escape motor, the tower-jettison motor, and the pitch-control motor. The launch-escape motor, the main motor in the launch escape system, had a thrust of 155,000 pounds and was capable of moving the command module away from and out of the path of the remaining portions of the launch vehicle if a launch-vehicle malfunction occurred and an abort was required. The tower-jettison-motor function was to separate the launch escape system from the command module before deployment of the command module parachutes if an abort occurred. The tower-jettison motor also was used to remove the launch escape system away from and out of the path of a normally functioning launch vehicle. The pitch-control motor was essential to establish a safe trajectory of the activated launch escape system. The design, qualification, and testing of the launch escape system components were completed during the years 1961 to 1966.

Complete Record: This film shows the first test of the Apollo launch escape system (LES) which took place on Nov. 7, 1963, at the White Sands Missile Range. A safety system connected to the Command Module, the LES was designed to protect the life of the crew in the event of a critical emergency at launch. 00:00: Man with high speed movie camera with large telephoto lens on a stand near launch site 00:20: Dignitaries and engineers, and possibly some astronauts, stand by for the tests 00:45: Everyone on the viewing stand for the test 1:16: Gus Grissom talks to an unknown man 1:36: Command Module test article seen after the test (this is out of sequence) 2:11: Panel briefs the viewers as to what they are about to see 2:36: Parachute provides shade for the viewers 3:23: NASA logo on control building at the range 5:04: shot of the smoke trail from the test (out of sequence) 6:21: Slate indicating 7 November 1963 at White Sands. 6:49: Launch sequence 7:24: Command module descends via parachute The Apollo launch escape system (LES) was designed to provide a positive means of crew escape if booster failure occurred during the initial phase of launch. The system had to achieve sufficient altitude for deployment of the command module (CM) parachutes and to ensure safe lateral separation. Lateral separation was achieved by firing simultaneously the pitch-control motor and the launch-escape motor for low altitude aborts. The pitch-control motor was not required for high-altitude aborts. The system is no longer required after second-stage ignition and is jettisoned after verification of ignition. The Apollo launch escape propulsion subsystem contained three solid-propellant rocket motors: the launch-escape motor, the tower-jettison motor, and the pitch-control motor. The launch-escape motor, the main motor in the launch escape system, had a thrust of 155,000 pounds and was capable of moving the command module away from and out of the path of the remaining portions of the launch vehicle if a launch-vehicle malfunction occurred and an abort was required. The tower-jettison-motor function was to separate the launch escape system from the command module before deployment of the command module parachutes if an abort occurred. The tower-jettison motor also was used to remove the launch escape system away from and out of the path of a normally functioning launch vehicle. The pitch-control motor was essential to establish a safe trajectory of the activated launch escape system. The design, qualification, and testing of the launch escape system components were completed during the years 1961 to 1966.