1 00:00:00,000 --> 00:00:03,550 Mission Control Announcer: 11...10...9... 2 00:00:03,570 --> 00:00:05,800 Ignition Sequence Start... 3 00:00:05,820 --> 00:00:07,810 Narrator: NASA's Ames Research Center played a 4 00:00:07,830 --> 00:00:10,570 critical role in the development and preparation 5 00:00:10,590 --> 00:00:13,340 for the flight test of NASA's new spacecraft 6 00:00:13,360 --> 00:00:15,570 called Orion. 7 00:00:15,590 --> 00:00:20,100 Designated Exploration Flight Test-1, or EFT-1, 8 00:00:20,120 --> 00:00:22,390 the mission will provide critical data that will 9 00:00:22,410 --> 00:00:25,700 enable engineers to improve Orion's design and 10 00:00:25,720 --> 00:00:27,800 reduce risk for the astronauts 11 00:00:27,820 --> 00:00:30,880 it will eventually carry. 12 00:00:30,900 --> 00:00:33,230 One of the biggest challenges for Orion is that it 13 00:00:33,250 --> 00:00:35,730 will re-enter Earth's atmosphere faster and 14 00:00:35,750 --> 00:00:38,680 encounter more heating than any previously manned 15 00:00:38,700 --> 00:00:42,180 missions including Apollo and the Space Shuttle. 16 00:00:47,320 --> 00:00:45,690 Arc Jet Engineer 1: 5...4...3...2...1... 17 00:00:47,340 --> 00:00:49,540 Narrator: To test Orion's new heat shield made of 18 00:00:49,560 --> 00:00:53,210 a material called Avcoat, Ames used its Arc Jet 19 00:00:53,230 --> 00:00:55,670 facility to simulate the heating and airflow 20 00:00:55,690 --> 00:00:59,700 conditions that occur during atmospheric re-entry. 21 00:00:59,720 --> 00:01:02,410 During these tests, the Avcoat surface reached 22 00:01:02,430 --> 00:01:08,180 temperatures of over 3,000 degrees Fahrenheit. 23 00:01:08,200 --> 00:01:10,600 Ames developed a group of sensors that was built 24 00:01:10,620 --> 00:01:13,250 into in the heat shield itself to monitor how well 25 00:01:13,270 --> 00:01:16,200 it performs during EFT-1. 26 00:01:16,220 --> 00:01:19,660 34 of these sensors will measure the near-surface 27 00:01:19,680 --> 00:01:22,070 and internal temperatures of the heat shield as 28 00:01:22,090 --> 00:01:24,930 Orion re-enters the atmosphere. 29 00:01:24,950 --> 00:01:27,690 This will give engineers a complete data profile 30 00:01:27,710 --> 00:01:30,200 of its performance, allowing them to see what 31 00:01:30,220 --> 00:01:32,830 succeeded and how to make future improvements to 32 00:01:32,850 --> 00:01:37,270 the thermal protection system. 33 00:01:37,290 --> 00:01:40,240 To optimize the design of the Orion Crew Vehicle, 34 00:01:40,260 --> 00:01:42,960 an 8-percent scale model was coated with pressure 35 00:01:42,980 --> 00:01:46,240 sensitive paint and was tested in the Ames 11-foot 36 00:01:46,260 --> 00:01:49,310 Unitary transonic wind tunnel. 37 00:01:49,330 --> 00:01:51,940 This testing simulated airflow and temperature 38 00:01:51,960 --> 00:01:54,950 changes the capsule will experience in flight 39 00:01:54,970 --> 00:01:57,790 after re-entering the atmosphere. 40 00:01:57,810 --> 00:02:00,570 The data collected is also essential to validating 41 00:02:00,590 --> 00:02:03,760 the accuracy of computational models that simulate 42 00:02:03,780 --> 00:02:09,610 the performance of space vehicles during re-entry. 43 00:02:09,630 --> 00:02:12,640 The Orion Launch Abort System required testing in 44 00:02:12,660 --> 00:02:15,110 the wind tunnels at Ames to better understand the 45 00:02:15,130 --> 00:02:18,850 behavior of the system during a complex variety 46 00:02:18,870 --> 00:02:20,080 of launch conditions. 47 00:02:20,100 --> 00:02:22,370 The focus of the study was to determine the 48 00:02:22,390 --> 00:02:25,300 interaction between the plume from the jets with 49 00:02:25,320 --> 00:02:29,140 the airflow effects of separation from the rocket. 50 00:02:29,160 --> 00:02:32,110 Another test used a 6-percent scale model of the 51 00:02:32,130 --> 00:02:34,990 Launch Abort System in the 11-foot wind tunnel to 52 00:02:35,010 --> 00:02:37,890 find ways of minimizing how loud the system would 53 00:02:37,910 --> 00:02:42,710 be, during an actual flight. 54 00:02:42,730 --> 00:02:45,210 Built in the 1960's to support the Apollo 55 00:02:45,230 --> 00:02:48,680 missions, Ames' Horizontal Free Flight Facility 56 00:02:48,700 --> 00:02:51,500 can fire models through a 75-foot-long test 57 00:02:51,520 --> 00:02:55,770 chamber at speeds ranging from 500 to 18,000 58 00:02:55,790 --> 00:02:57,590 miles per hour. 59 00:02:57,610 --> 00:02:59,830 (Bang of gun firing) 60 00:02:59,850 --> 00:03:02,460 Tests of the Orion capsule were essential to 61 00:03:02,480 --> 00:03:04,730 understanding how well the vehicle will fly 62 00:03:04,750 --> 00:03:07,290 through the air after re-entering the atmosphere, 63 00:03:07,310 --> 00:03:12,720 but before the critical parachute deployment. 64 00:03:12,740 --> 00:03:15,680 Ames also specializes in the use of computer 65 00:03:15,700 --> 00:03:19,070 modeling simulations referred to as computational 66 00:03:19,090 --> 00:03:23,270 fluid dynamics or CFD. 67 00:03:23,290 --> 00:03:26,070 This work has been important to understanding the 68 00:03:26,090 --> 00:03:29,460 turbulent wake behind the Orion capsule as it 69 00:03:29,480 --> 00:03:33,000 slows down enough to deploy its parachutes. 70 00:03:33,020 --> 00:03:35,940 Studies have also been conducted to optimize the 71 00:03:35,960 --> 00:03:38,880 thermal heating performance of Orion by using an 72 00:03:38,900 --> 00:03:41,180 Ames-developed software tool called 73 00:03:41,200 --> 00:03:45,100 Data Parallel Line Relaxation or DPLR. 74 00:03:45,120 --> 00:03:47,840 Engineers will compare their predicted results 75 00:03:47,860 --> 00:03:50,880 with actual data from the Arc Jet tests and data 76 00:03:50,900 --> 00:03:53,930 collected from the EFT-1 flight to improve the 77 00:03:53,950 --> 00:03:59,650 DPLR code for future spacecraft design. 78 00:03:59,670 --> 00:04:02,690 The scientists, engineers and researchers at Ames 79 00:04:02,710 --> 00:04:04,990 are proud to have played a critical role in the 80 00:04:05,010 --> 00:04:08,440 EFT-1 flight test as NASA continues to move 81 00:04:08,460 --> 00:04:10,980 forward on its human journey to asteroids and 82 00:04:11,000 --> 00:04:12,680 eventually to Mars. 83 00:04:12,700 --> 00:04:15,500 (Roar of rocket engine)