1 00:00:22,039 --> 00:00:28,220 At almost midnight on April 24 at Cape Canaveral’s Launch Complex 34, the scheduled ten hour 2 00:00:28,220 --> 00:00:38,519 long countdown began for the launching of the second Saturn test flight vehicle, SA-2. 3 00:00:38,519 --> 00:00:45,120 All automatic propellant loading and sequencing processes were conducted satisfactorily. 4 00:00:45,120 --> 00:00:52,559 The countdown proceeded without a single technical hold. 5 00:00:52,559 --> 00:00:59,660 One thirty minute range hold was called, however, until a ship could clear the range area. 6 00:00:59,660 --> 00:01:05,040 Shortly after 9:00 A.M. 7 00:01:05,040 --> 00:01:13,750 on April 25, six months after the spectacularly successful first Saturn flight, the countdown 8 00:01:13,750 --> 00:01:19,970 for SA-2 had reached its final seconds. 9 00:01:19,970 --> 00:01:57,710 “Ten, nine, eight, seven, six, five, four, three, two, one, zero.” 10 00:01:57,710 --> 00:02:04,580 Ignition, thrust buildup, and liftoff wee normal. 11 00:02:04,580 --> 00:02:09,420 Objectives of the SA-2 launch included flight testing of the booster stage and operational 12 00:02:09,420 --> 00:02:12,629 testing of associated launch facilities. 13 00:02:12,629 --> 00:02:18,159 Structural integrity of the Block I airframe and aerodynamic characteristics were confirmed 14 00:02:18,159 --> 00:02:21,290 and capabilities of the control system demonstrated. 15 00:02:21,290 --> 00:02:26,569 The propulsion system performed normally throughout powered flight. 16 00:02:26,569 --> 00:02:31,430 All electrical networks and instrumentation functioned properly with very satisfactory 17 00:02:31,430 --> 00:02:42,870 telemetry signals received. 18 00:02:42,870 --> 00:02:56,980 Maximum velocity of over 3,700 miles per hour was attained. 19 00:02:56,980 --> 00:03:02,559 The sloshing effects observed during the SA-1 flight was reduced to an acceptable level. 20 00:03:02,559 --> 00:03:10,519 Cutoff occurred at 110 seconds for inboard engine and 116 for outboard as predicted. 21 00:03:10,519 --> 00:03:19,980 In virtually every respect, the SA-2 flight was successful. 22 00:03:19,980 --> 00:03:42,250 [Sound of Engines Firing] 23 00:03:42,250 --> 00:03:53,730 SA-2 also carried out a secondary, or bonus, scientific experiment known as Project Highwater. 24 00:03:53,730 --> 00:04:00,329 At an altitude of sixty-five miles, the vehicle, whose dummy upper stages carried 23,000 gallons 25 00:04:00,329 --> 00:04:06,489 of water as ballast, was purposely exploded to investigate the optical, ionospheric, and 26 00:04:06,489 --> 00:04:14,010 meteorological effects which water vapor has on the high atmosphere. 27 00:04:14,010 --> 00:04:18,810 About fifteen percent of the water evaporated and the remaining eighty-five tons formed 28 00:04:18,810 --> 00:04:27,419 a cloud of very small ice particles along the remained of the vehicle trajectory. 29 00:04:27,419 --> 00:04:33,139 Prior to SA-2’s flight, laboratory experiments in connection with Project Highwater were 30 00:04:33,139 --> 00:04:36,680 conducted at Marshall Center’s Astrionics Division. 31 00:04:36,680 --> 00:04:40,780 Saturn flight conditions are simulated by using a vacuum chamber. 32 00:04:40,780 --> 00:04:46,630 To facilitate viewing, coloring is added to the water in the test tube. 33 00:04:46,630 --> 00:04:50,470 In this experiment, the tube is suspended in the horizontal position. 34 00:04:50,470 --> 00:04:55,180 A solenoid operated hammer breaks the tip, releasing the water. 35 00:04:55,180 --> 00:04:58,930 Because of the low pressure, the water evaporates rapidly. 36 00:04:58,930 --> 00:05:02,570 Cooling is so fast that ice flakes for immediately. 37 00:05:02,570 --> 00:05:11,470 With the tube in this position, water boil off is slow and sporadic. 38 00:05:11,470 --> 00:05:17,070 In a second experiment, a vial is suspended vertically, the tip is broken, and a boiling 39 00:05:17,070 --> 00:05:18,760 reaction occurs. 40 00:05:18,760 --> 00:05:22,200 With the vial vertical, water boil off is constant. 41 00:05:22,200 --> 00:05:28,380 In both experiments, pressure is so low that the ice which is formed has an unusually low 42 00:05:28,380 --> 00:05:29,380 temperature. 43 00:05:29,380 --> 00:05:42,990 Ice maintained at this temperature is very hard and elastic. 44 00:05:42,990 --> 00:05:59,490 Three static test firings of the third Saturn flight vehicle, SA-3, were held at Marshall 45 00:05:59,490 --> 00:06:06,030 this quarter, two of thirty seconds duration and the final one running 119 seconds. 46 00:06:06,030 --> 00:06:11,360 Defective bearings and main shafts resulted in excessive turbopump vibration in the first 47 00:06:11,360 --> 00:06:12,360 test. 48 00:06:12,360 --> 00:06:17,630 Defective parts were replaced and pumps and engines were satisfactorily retested before 49 00:06:17,630 --> 00:06:19,930 the engines were reinstalled. 50 00:06:19,930 --> 00:06:29,780 Later firings encountered no difficulty. 51 00:06:29,780 --> 00:06:35,210 Assembly of the booster for the fourth Saturn flight test vehicle, SA-4, was completed on 52 00:06:35,210 --> 00:06:43,280 May 28, and the stage is now undergoing pre static test checkout. 53 00:06:43,280 --> 00:06:47,960 Fabrication of components and subassemblies, such as this thrust frame barrel assembly 54 00:06:47,960 --> 00:06:53,870 for the fifth Saturn flight booster, SA-5, first of the Block II series, was carried 55 00:06:53,870 --> 00:06:59,240 out this quarter by Marshall’s Manufacturing Engineering Division. 56 00:06:59,240 --> 00:07:07,150 A number of new fabrication fixtures, such as this one for making Saturn spider beam 57 00:07:07,150 --> 00:07:15,120 assemblies, have been placed into service for Block II booster fabrication. 58 00:07:15,120 --> 00:07:20,389 Looking toward future fabrication techniques for Saturn or other space vehicles, Marshall 59 00:07:20,389 --> 00:07:26,700 engineers are investigating exploding bridgewires in a fluid media as a means of forming and 60 00:07:26,700 --> 00:07:29,660 working metals. 61 00:07:29,660 --> 00:07:37,020 In this test, a piece of flat stock aluminum is loaded onto a female die and securely mounted. 62 00:07:37,020 --> 00:07:43,930 A crane hoists the die and stock into the forming tank, which is filled with water and 63 00:07:43,930 --> 00:07:50,710 the exploding bridgewire is properly positioned. 64 00:07:50,710 --> 00:07:57,870 The ultra-fast discharge of a large capacitor bank explodes the bridgewire, creating a high 65 00:07:57,870 --> 00:08:00,310 energy shockwave in the water. 66 00:08:00,310 --> 00:08:06,280 This shockwave, along with hydrodynamic pressure pulses, forms the metal into the previously 67 00:08:06,280 --> 00:08:08,270 evacuated die. 68 00:08:08,270 --> 00:08:13,270 Advantages of forming materials by this method lie in the control of forming and relative 69 00:08:13,270 --> 00:08:25,020 ease of operation. 70 00:08:25,020 --> 00:08:31,800 Hayes International Incorporated in Birmingham is fabricating several Block II booster components, 71 00:08:31,800 --> 00:08:36,140 including fins, lower shrouds, and engine skirts. 72 00:08:36,140 --> 00:08:42,550 Fin design utilizes the spar, rib, and skin-type structure, which provides a high degree of 73 00:08:42,550 --> 00:08:44,639 structural reliability. 74 00:08:44,639 --> 00:08:47,450 Three basic fin configurations are used. 75 00:08:47,450 --> 00:08:53,399 Four large fins will be located at ninety degree intervals around the booster. 76 00:08:53,399 --> 00:08:58,449 Two configurations of stub fins will be located at right angles to each other between the 77 00:08:58,449 --> 00:08:59,899 large fins. 78 00:08:59,899 --> 00:09:04,610 Three of these have provisions for venting liquid hydrogen from the vehicle’s second 79 00:09:04,610 --> 00:09:05,610 stage. 80 00:09:05,610 --> 00:09:10,500 In addition to providing flight stability, these eight fins have vehicle support and 81 00:09:10,500 --> 00:09:11,500 hold down fittings. 82 00:09:11,500 --> 00:09:20,149 The lower shroud, which Hayes makes for Saturn 83 00:09:20,149 --> 00:09:26,180 Block II boosters, is basically a corrugated skin structure with continuous rings supporting 84 00:09:26,180 --> 00:09:31,360 the entire unit. 85 00:09:31,360 --> 00:09:36,920 Republic Aviation Corporation of Long Island, New York, is another prime example of industry 86 00:09:36,920 --> 00:09:40,939 at work for Saturn. 87 00:09:40,939 --> 00:09:45,779 One of the world’s largest banks of numerical control machines, which operate from taped 88 00:09:45,779 --> 00:09:52,339 manufacturing instructions, is being put to use by Republic Aviation for fabrication of 89 00:09:52,339 --> 00:09:59,670 various Saturn components. 90 00:09:59,670 --> 00:10:05,319 The first of the Saturn LOX and fuel tanks manufactured by Ling-Temco-Vought near Dallas, 91 00:10:05,319 --> 00:10:09,029 Texas, were delivered to the Marshall Center this quarter. 92 00:10:09,029 --> 00:10:17,860 During transportation, the tanks are protected from damage by a custom made shipping container. 93 00:10:17,860 --> 00:10:22,680 Marshall personnel thoroughly inspect each tank prior to acceptance. 94 00:10:22,680 --> 00:10:28,329 Tanks are subjected to an air pressure leak test with Freon used as a tracer gas. 95 00:10:28,329 --> 00:10:36,550 If leakage exists, an electronic instrument detects the area of escaping gas. 96 00:10:36,550 --> 00:10:43,459 Delivery of the H-1 engines, both inboard and outboard, for the SA-5 booster was accomplished 97 00:10:43,459 --> 00:10:51,309 early in April by the contractor, Rocketdyne Division of North American Aviation Company. 98 00:10:51,309 --> 00:10:56,999 Small model rocket engines, such as the 500 pound thrust H-1 model are being fabricated 99 00:10:56,999 --> 00:11:06,279 by the Marshall Center’s Test Division for use in gathering data about their real counterparts. 100 00:11:06,279 --> 00:11:11,910 One-tenth scale models of the C-I Saturn’s booster and S-IV stage have been tested in 101 00:11:11,910 --> 00:11:16,889 the high altitude chamber to study interstage separation problems. 102 00:11:16,889 --> 00:11:20,569 [Sound of Engines Firing] 103 00:11:20,569 --> 00:11:26,399 Test objectives were to obtain data on pressure versus interstage separation distances and 104 00:11:26,399 --> 00:11:33,129 to determine the effect of a modified conical flow deflector on the hot gas back lag. 105 00:11:33,129 --> 00:11:39,699 A one-twentieth scale model of a Block II Saturn booster was tested in conjunction with 106 00:11:39,699 --> 00:11:45,459 a model flame deflector of the type intended for use on the launch pedestal of Launch Complex 107 00:11:45,459 --> 00:11:50,439 37, now under construction at Cape Canaveral. 108 00:11:50,439 --> 00:12:01,180 [Sound of Engines Firing] 109 00:12:01,180 --> 00:12:06,559 This test program enables engineers to study base region environmental pressures, temperatures 110 00:12:06,559 --> 00:12:13,279 and heating rates, as well as flame deflector effectiveness under hot firing conditions. 111 00:12:13,279 --> 00:12:19,309 The new Block II Saturn booster assembly station was installed during this report period in 112 00:12:19,309 --> 00:12:24,279 Marshall’s recently expanded Saturn assembly building, which now contains over two hundred 113 00:12:24,279 --> 00:12:28,440 thousand square feet of floor space. 114 00:12:28,440 --> 00:12:33,649 The tooling ring for the SA-5 booster has be fabricated and work is scheduled to begin 115 00:12:33,649 --> 00:12:39,839 in July on SA-5 booster assembly. 116 00:12:39,839 --> 00:12:44,480 Selection of International Business Machines, Incorporated of [Wiego,] New York to develop 117 00:12:44,480 --> 00:12:48,550 the guidance computer for Saturn C-I was announced this quarter. 118 00:12:48,550 --> 00:12:54,920 For test purposes, the computer will be aboard the SA-5. 119 00:12:54,920 --> 00:13:00,750 Also slated for initial use on SA-5 is a new camera eject mechanism which will help to 120 00:13:00,750 --> 00:13:04,360 provide a photographic record of vehicle actions. 121 00:13:04,360 --> 00:13:10,320 Along the spider beam of the SA-5 booster, eight movie camera pods and paraballoon recovery 122 00:13:10,320 --> 00:13:17,420 packages will be mounted into ejection cylinders. 123 00:13:17,420 --> 00:13:23,110 In this laboratory test at the Marshall Center, gaseous nitrogen is used as a pressurant. 124 00:13:23,110 --> 00:13:27,990 When sufficient pressure is attained, the firing switch is closed and the camera pod 125 00:13:27,990 --> 00:13:31,820 and recovery package are ejected. 126 00:13:31,820 --> 00:13:38,809 SA-D, the test vehicle which had provided vital dynamic vibration data contributing 127 00:13:38,809 --> 00:13:43,830 to the success of the first two flight vehicles, was removed from Marshall’s Dynamic Test 128 00:13:43,830 --> 00:13:47,480 Stand this quarter, its mission completed. 129 00:13:47,480 --> 00:13:53,870 A new vehicle, SA-D-5, a simulation of SA-5, will be built at Marshall and later installed 130 00:13:53,870 --> 00:13:57,949 in the stand for testing. 131 00:13:57,949 --> 00:14:06,990 Marshall’s Static Test Stand will soon be modified to accommodate two Saturn C-I boosters 132 00:14:06,990 --> 00:14:07,990 simultaneously. 133 00:14:07,990 --> 00:14:12,800 The old test position in which Jupiter and Juno II rockets were once tested has already 134 00:14:12,800 --> 00:14:18,749 been removed in preparation for creating a second Saturn booster test position in its 135 00:14:18,749 --> 00:14:23,819 place. 136 00:14:23,819 --> 00:14:28,559 Several major construction projects are changing the Marshall Center horizon. 137 00:14:28,559 --> 00:14:34,180 The nine story central laboratory and office building, scheduled for completion next January, 138 00:14:34,180 --> 00:14:38,699 will be the center’s tallest building. 139 00:14:38,699 --> 00:14:43,199 Personnel of the Propulsion and Vehicle Engineering Division are due to begin occupying their 140 00:14:43,199 --> 00:14:47,410 new five story addition in July. 141 00:14:47,410 --> 00:14:52,160 And Manufacturing and Engineering Division has already moved into its recently finished 142 00:14:52,160 --> 00:14:54,089 addition. 143 00:14:54,089 --> 00:14:59,779 At any division, a group of Chrysler engineers and technicians are presently receiving orientation 144 00:14:59,779 --> 00:15:06,070 on Saturn fabrication and assembly methods in preparation for Chrysler’s future C-I 145 00:15:06,070 --> 00:15:13,040 booster manufacturing at Marshall’s Michoud Operations Plant near New Orleans. 146 00:15:13,040 --> 00:15:18,389 Twenty miles from Michoud at Slidell, Louisiana, this new $2 million building has been acquired 147 00:15:18,389 --> 00:15:21,490 by NASA from the Federal Aviation Agency. 148 00:15:21,490 --> 00:15:26,489 The building, which contains 53,000 square feet of floor space, is being occupied by 149 00:15:26,489 --> 00:15:39,550 some 500 Chrysler employees in a move to alleviate a critical office space problem at Michoud. 150 00:15:39,550 --> 00:15:45,180 At the Mississippi Test Facility site, negotiations are now underway with some 200 land owners 151 00:15:45,180 --> 00:15:46,950 in the construction area. 152 00:15:46,950 --> 00:15:56,149 The government schedule calls for outright acquisition of title to the area by July 31. 153 00:15:56,149 --> 00:16:01,510 Construction of Saturn Launch Complex 37 continued at Cape Canaveral during this report period. 154 00:16:01,510 --> 00:16:07,279 Work includes construction of the mobile 3,500 ton steel service structure, 155 00:16:07,279 --> 00:16:13,600 268 foot high umbilical tower and steel launch pedestal, 156 00:16:13,600 --> 00:16:16,799 circular concrete blockhouse, 157 00:16:16,799 --> 00:16:21,709 LOX and fuel storage facilities, and servicing facilities. 158 00:16:21,709 --> 00:16:27,060 Construction of major items is about sixty percent complete and progressing on schedule. 159 00:16:27,060 --> 00:16:33,259 When finished, complex 37 will have two Saturn launch positions, utilizing a single control 160 00:16:33,259 --> 00:16:36,249 center and service tower. 161 00:16:36,249 --> 00:16:41,829 At Douglas Aircraft Company, contractor for Saturn’s S-IV stage, cold flow tests have 162 00:16:41,829 --> 00:16:48,249 been successfully completed at the Sacramento test facility using a single RL-10 liquid 163 00:16:48,249 --> 00:16:51,610 hydrogen-liquid oxygen engine. 164 00:16:51,610 --> 00:16:55,410 Five additional engines were received this quarter from Pratt & Whitney. 165 00:16:55,410 --> 00:16:59,910 After acceptance checking at Santa Monica, the engines were shipped to Sacramento and 166 00:16:59,910 --> 00:17:04,920 installed in the battleship test vehicle in preparation for the second phase of the Battleship 167 00:17:04,920 --> 00:17:11,860 Test Program. 168 00:17:11,860 --> 00:17:16,930 Modification of test stand Number 2, which will be used for the all systems testing, 169 00:17:16,930 --> 00:17:19,980 continued on schedule. 170 00:17:19,980 --> 00:17:25,100 The steam system was being installed during this report period and other necessary hardware 171 00:17:25,100 --> 00:17:31,920 is now available for completion of the stand. 172 00:17:31,920 --> 00:17:36,570 Cornell Aeronautical Laboratory, Buffalo, New York, has been conducting a series of 173 00:17:36,570 --> 00:17:41,870 tests with a S-IV model in an altitude chamber, looking toward solution of problems which 174 00:17:41,870 --> 00:17:47,260 occur when a portion of the engine’s hot exhaust gas escapes from the exhaust plume 175 00:17:47,260 --> 00:17:52,760 and flows into the base region. 176 00:17:52,760 --> 00:18:02,260 During this test, which lasts for only five-thousandths of a second, pressure and temperature measurements 177 00:18:02,260 --> 00:18:07,540 are taken on the base plate of the model using miniature, highly sensitive instruments. 178 00:18:07,540 --> 00:18:13,420 By ESO electric pressure transducers are mounted behind orifices in the base plate at locations 179 00:18:13,420 --> 00:18:19,280 where pressure is to be read. 180 00:18:19,280 --> 00:18:25,410 Fragile thermometers consist of a thin film of metallic paint applied to a quartz button. 181 00:18:25,410 --> 00:18:29,740 When the surface of the button is heated by the gas, the electrical resistance of the 182 00:18:29,740 --> 00:18:31,490 metallic film changes. 183 00:18:31,490 --> 00:18:37,030 Then, the output voltage signal of the thermometer denotes the instantaneous temperature of the 184 00:18:37,030 --> 00:18:45,900 particular location under survey. 185 00:18:45,900 --> 00:18:53,770 By observing the time history of this temperature, the local heating rate is determined. 186 00:18:53,770 --> 00:18:58,830 Fast responding instruments such as these permit Cornell Aeronautical Laboratory scientists 187 00:18:58,830 --> 00:19:04,800 to study rocket base heating problems in short-duration experiments. 188 00:19:04,800 --> 00:19:09,640 Such tests are better controlled and much more economical to perform than conventional 189 00:19:09,640 --> 00:19:13,850 techniques involving continuous operations. 190 00:19:13,850 --> 00:19:19,390 Here is one frame taken from a high-speed Schlieren motion picture film showing shockwaves 191 00:19:19,390 --> 00:19:28,680 created by the combusted gases exhausting into the vacuum chamber. 192 00:19:28,680 --> 00:19:35,350 Preliminary flight rating endurance testing of the S-IV stages RL-10A-3 engine was successfully 193 00:19:35,350 --> 00:19:48,510 completed on June 9 by the engine contractor, Pratt & Whitney, at West Palm Beach, Florida. 194 00:19:48,510 --> 00:19:54,060 Twenty-six PFRT firings totaling 4,096 seconds were conducted. 195 00:19:54,060 --> 00:19:58,710 Initial inspection showed the engine to be in good condition. 196 00:19:58,710 --> 00:20:04,700 A series on non-firing gimbal tests of the RL-10A-3 using Douglas Aircraft Company plumbing 197 00:20:04,700 --> 00:20:08,550 connections was also carried out. 198 00:20:08,550 --> 00:20:13,760 To test engines and hardware for possible structural weakness, a stress coat was applied 199 00:20:13,760 --> 00:20:19,350 on metal surfaces to locate areas of structural yield. 200 00:20:19,350 --> 00:20:23,820 Various gimbal angels and frequencies were applied to the engine to simulate he worst 201 00:20:23,820 --> 00:20:27,420 expected flight conditions. 202 00:20:27,420 --> 00:20:32,990 Both engine and vehicle plumbing withstood the tests satisfactorily. 203 00:20:32,990 --> 00:20:37,320 In support of the engine program, facilities completed at Pratt & Whitney’s Research 204 00:20:37,320 --> 00:20:44,690 and Development Center this quarter included a new vertical single engine test stand and 205 00:20:44,690 --> 00:20:51,100 a 90,000 gallon vacuum jacketed liquid hydrogen spherical storage container. 206 00:20:51,100 --> 00:20:56,360 As progress continued this quarter on the Saturn C-I, shown alongside the Statue of 207 00:20:56,360 --> 00:21:02,000 Liberty in an artist’s conception to dramatize its great size. 208 00:21:02,000 --> 00:21:07,910 Work was also underway on the even larger Advanced, or C-V, version of Saturn. 209 00:21:07,910 --> 00:21:18,050 The C-V will stand about 350 feet tall, as compared to 170 for C-I. 210 00:21:18,050 --> 00:21:24,490 The C-V, shown in model form, will be able to hurl over 200,000 pounds into a 300 mile 211 00:21:24,490 --> 00:21:25,490 orbit. 212 00:21:25,490 --> 00:21:31,120 The vehicle could use two stages for Earth orbit missions and three stages for escape 213 00:21:31,120 --> 00:21:32,120 missions. 214 00:21:32,120 --> 00:21:38,440 Launching of the first C-V is expected in 1965. 215 00:21:38,440 --> 00:21:43,460 At Marshall, construction is proceeding on the Static Test Facility to be used for testing 216 00:21:43,460 --> 00:21:45,380 C-V boosters. 217 00:21:45,380 --> 00:21:51,260 The concrete foundation for the massive stand plunges over forty-five feet into the Earth. 218 00:21:51,260 --> 00:21:59,480 Including its crane, the new test structure will be 405 feet tall. 219 00:21:59,480 --> 00:22:05,380 Over 1,000 employees of the Boeing Company, contractor for the Saturn C-V booster, are 220 00:22:05,380 --> 00:22:07,630 now at work in the Huntsville area. 221 00:22:07,630 --> 00:22:13,940 The company is expected to employ more than 1,500 there during 1962, most of whom will 222 00:22:13,940 --> 00:22:19,140 later be transferred to Marshall’s Michoud Operations where the giant boosters will be 223 00:22:19,140 --> 00:22:23,850 manufactured. 224 00:22:23,850 --> 00:22:29,910 At North American’s Aviation Space and Information Systems Division, contractor for the Saturn 225 00:22:29,910 --> 00:22:36,950 C-V’s S-II, or second, stage, work this quarter included hot flow tests using scale 226 00:22:36,950 --> 00:22:42,070 model engines with a model flame deflector of comparable scale, to determine optimal 227 00:22:42,070 --> 00:22:45,250 engine orientation for the five engine S-II configuration. 228 00:22:45,250 --> 00:22:50,700 [Sound of Engines Firing] Secondary objectives of the tests include determination of various 229 00:22:50,700 --> 00:22:56,980 deflector parameters such as pressure, temperature, and heat flux profiles, plus investigations 230 00:22:56,980 --> 00:23:00,610 of filmed coolant injection methods. 231 00:23:00,610 --> 00:23:04,870 The scale model engines produce a total thrust of 5,000 pounds. 232 00:23:04,870 --> 00:23:09,680 The deflector is coated with zinc chromate paint, which burns away during firings to 233 00:23:09,680 --> 00:23:16,980 reveal areas of probable burn throw. 234 00:23:16,980 --> 00:23:22,010 Fabrication of an S-II stage and transporter model, designed to verify that the booster 235 00:23:22,010 --> 00:23:28,230 transporter will meet all maneuverability requirements, is now complete. 236 00:23:28,230 --> 00:23:34,070 Using a road gauge fabricated to the same dimensions as the S-II transporter, a month-long 237 00:23:34,070 --> 00:23:38,940 survey has been conducted to determine the feasibility of routes proposed for over land 238 00:23:38,940 --> 00:23:44,750 transportation of the stage from Port Hueneme, California to North American’s static test 239 00:23:44,750 --> 00:23:52,630 facility at Santa Susana, a distance of some fifty miles. 240 00:23:52,630 --> 00:23:57,850 A plater model has been made to serve as a tooling aid for constructing a female layup 241 00:23:57,850 --> 00:24:03,130 dye, which will be used to form bulkhead gore segments for the S-II mockup. 242 00:24:03,130 --> 00:24:07,940 The sweeping frame employed in this operation will later be used to sweep the production 243 00:24:07,940 --> 00:24:16,900 tooling master. 244 00:24:16,900 --> 00:24:22,410 Two antenna radiation pattern models of the C-V Saturn have been completed and one has 245 00:24:22,410 --> 00:24:27,410 been shipped to the Los Angeles Division where initial testing will be performed until the 246 00:24:27,410 --> 00:24:30,860 S&ID antenna range is operational. 247 00:24:30,860 --> 00:24:35,790 The program will determine the numbers and types of antennas required for telemetry, 248 00:24:35,790 --> 00:24:42,430 command control, and tracking aids, and will establish specific locations and angular orientation 249 00:24:42,430 --> 00:24:45,600 of antenna types selected. 250 00:24:45,600 --> 00:24:52,010 A highly significant advance in the Saturn program occurred this quarter when the mammoth 251 00:24:52,010 --> 00:24:58,350 F-1 engine, five of which will be clustered for the C-V booster, underwent its first full 252 00:24:58,350 --> 00:25:03,760 duration static tests at full thrust of 1.5 billion pounds. 253 00:25:03,760 --> 00:25:08,890 The test was conducted at the NASA high thrust area at Edwards, California by the F-1’s 254 00:25:08,890 --> 00:25:21,330 developer, Rocketdyne Division of North American Aviation. 255 00:25:21,330 --> 00:25:28,390 The ground test was sustained for 151.8 seconds, approximately flight duration, before being 256 00:25:28,390 --> 00:25:30,390 terminated as programmed.