1 00:00:00,000 --> 00:00:04,354 MUSIC. 2 00:00:04,554 --> 00:00:05,819 So what we have right here is the 3 00:00:06,019 --> 00:00:07,187 Launch Vehicle Stage Adapter which 4 00:00:07,387 --> 00:00:09,347 is the initial adapter above the 5 00:00:09,547 --> 00:00:11,523 launch vehicle and that also holds 6 00:00:11,723 --> 00:00:14,556 the upper stage that is nestled 7 00:00:14,756 --> 00:00:16,056 inside of there so when we get in 8 00:00:16,256 --> 00:00:17,994 to orbit it will separate and come 9 00:00:18,194 --> 00:00:19,794 out of the Launch Vehicle Stage 10 00:00:19,994 --> 00:00:21,675 Adapter and again put the Orion 11 00:00:21,875 --> 00:00:23,083 Crew Capsule on its orbit. 12 00:00:23,283 --> 00:00:24,479 Now we’re very proud of that 13 00:00:24,679 --> 00:00:25,987 adapter along with the Orion 14 00:00:26,187 --> 00:00:27,939 Stage Adapter…we built both of 15 00:00:28,139 --> 00:00:29,283 those adapters here at Marshall 16 00:00:29,483 --> 00:00:30,500 Space Flight Center using some 17 00:00:30,700 --> 00:00:32,532 friction stir welding capability 18 00:00:32,732 --> 00:00:35,435 that we have. So the panels were 19 00:00:35,635 --> 00:00:37,052 made out in California. They are 20 00:00:37,252 --> 00:00:38,523 a lightweight aluminum alloy. 21 00:00:38,723 --> 00:00:40,179 And then they’re shipped here to 22 00:00:40,379 --> 00:00:41,035 Marshall Space Flight Center. 23 00:00:41,235 --> 00:00:43,035 Then we weld eight panels on the 24 00:00:43,235 --> 00:00:44,579 aft cone, eight panels on the 25 00:00:44,779 --> 00:00:45,842 forward cone and then we weld 26 00:00:46,042 --> 00:00:47,707 the two cones together. And then 27 00:00:47,907 --> 00:00:49,795 we go through an analysis phase. 28 00:00:49,995 --> 00:00:51,420 But then we want to make sure 29 00:00:51,620 --> 00:00:52,908 that analysis is accurate so 30 00:00:53,108 --> 00:00:53,955 that’s why we perform these 31 00:00:54,155 --> 00:00:56,051 structural test articles, so we 32 00:00:56,251 --> 00:00:58,354 can actually apply loads, greater 33 00:00:58,554 --> 00:01:00,027 than what we expect to see during 34 00:01:00,227 --> 00:01:01,787 the mission, to prove that we have 35 00:01:01,987 --> 00:01:03,475 sufficient margin to assure mission 36 00:01:03,675 --> 00:01:04,963 success. We have been doing 37 00:01:05,163 --> 00:01:06,195 instrumentation for about three months 38 00:01:06,395 --> 00:01:08,348 on this Launch Vehicle Stage Adapter 39 00:01:08,548 --> 00:01:10,162 and now we are getting ready to lift 40 00:01:10,362 --> 00:01:12,547 it and put it on the KMAG and transport 41 00:01:12,747 --> 00:01:14,555 it to the test stand. So once we get it 42 00:01:14,755 --> 00:01:16,690 to the test area we will have to de-mate 43 00:01:16,890 --> 00:01:19,233 it from the KMAGS and then we will begin 44 00:01:19,433 --> 00:01:22,074 the process of attaching the 300 ton 45 00:01:22,274 --> 00:01:24,154 mobile crane and lifting it and putting 46 00:01:24,354 --> 00:01:27,346 it into 4699 test stack. And then we 47 00:01:27,546 --> 00:01:29,274 will apply all the loads that are required 48 00:01:29,474 --> 00:01:31,539 of us and collect all the data. Then we 49 00:01:31,739 --> 00:01:33,787 will turn all that data over to the stress 50 00:01:33,987 --> 00:01:37,747 analysts, which is NASA, Teledyne Brown 51 00:01:37,947 --> 00:01:40,082 Engineering, United Launch Alliance with 52 00:01:40,282 --> 00:01:41,522 Boeing. So there’s actually several test 53 00:01:41,722 --> 00:01:46,739 requesters for this test that are responsible 54 00:01:46,939 --> 00:01:48,739 for different pieces of the test stack, that