1 00:00:58,880 --> 00:01:02,720 low thrust propulsion is essential for 2 00:01:02,720 --> 00:01:02,730 low thrust propulsion is essential for 3 00:01:02,730 --> 00:01:06,500 low thrust propulsion is essential for all space missions and NASA's Lewis 4 00:01:06,500 --> 00:01:06,510 all space missions and NASA's Lewis 5 00:01:06,510 --> 00:01:08,630 all space missions and NASA's Lewis Research Center is conducting programs 6 00:01:08,630 --> 00:01:08,640 Research Center is conducting programs 7 00:01:08,640 --> 00:01:11,750 Research Center is conducting programs to provide a broad range of low thrust 8 00:01:11,750 --> 00:01:11,760 to provide a broad range of low thrust 9 00:01:11,760 --> 00:01:14,930 to provide a broad range of low thrust propulsion concepts for both auxiliary 10 00:01:14,930 --> 00:01:14,940 propulsion concepts for both auxiliary 11 00:01:14,940 --> 00:01:18,650 propulsion concepts for both auxiliary and primary functions auxiliary 12 00:01:18,650 --> 00:01:18,660 and primary functions auxiliary 13 00:01:18,660 --> 00:01:20,960 and primary functions auxiliary propulsion is used for keeping space 14 00:01:20,960 --> 00:01:20,970 propulsion is used for keeping space 15 00:01:20,970 --> 00:01:24,230 propulsion is used for keeping space systems in desired locations or for 16 00:01:24,230 --> 00:01:24,240 systems in desired locations or for 17 00:01:24,240 --> 00:01:28,580 systems in desired locations or for orientation typical examples are the 18 00:01:28,580 --> 00:01:28,590 orientation typical examples are the 19 00:01:28,590 --> 00:01:31,340 orientation typical examples are the reaction control system for earth to 20 00:01:31,340 --> 00:01:31,350 reaction control system for earth to 21 00:01:31,350 --> 00:01:35,359 reaction control system for earth to orbit vehicles drag makeup and attitude 22 00:01:35,359 --> 00:01:35,369 orbit vehicles drag makeup and attitude 23 00:01:35,369 --> 00:01:38,330 orbit vehicles drag makeup and attitude control for low Earth orbit systems such 24 00:01:38,330 --> 00:01:38,340 control for low Earth orbit systems such 25 00:01:38,340 --> 00:01:41,810 control for low Earth orbit systems such as Space Station freedom station-keeping 26 00:01:41,810 --> 00:01:41,820 as Space Station freedom station-keeping 27 00:01:41,820 --> 00:01:44,180 as Space Station freedom station-keeping for higher orbit systems such as 28 00:01:44,180 --> 00:01:44,190 for higher orbit systems such as 29 00:01:44,190 --> 00:01:47,859 for higher orbit systems such as geosynchronous satellites and finally 30 00:01:47,859 --> 00:01:47,869 geosynchronous satellites and finally 31 00:01:47,869 --> 00:01:51,410 geosynchronous satellites and finally retropropulsion functions near planetary 32 00:01:51,410 --> 00:01:51,420 retropropulsion functions near planetary 33 00:01:51,420 --> 00:01:55,340 retropropulsion functions near planetary bodies primary propulsion functions 34 00:01:55,340 --> 00:01:55,350 bodies primary propulsion functions 35 00:01:55,350 --> 00:01:57,680 bodies primary propulsion functions include the moving of space vehicles 36 00:01:57,680 --> 00:01:57,690 include the moving of space vehicles 37 00:01:57,690 --> 00:02:00,290 include the moving of space vehicles from point to point in earth space as 38 00:02:00,290 --> 00:02:00,300 from point to point in earth space as 39 00:02:00,300 --> 00:02:03,020 from point to point in earth space as well as propulsion between Earth space 40 00:02:03,020 --> 00:02:03,030 well as propulsion between Earth space 41 00:02:03,030 --> 00:02:07,640 well as propulsion between Earth space and various planetary bodies to 42 00:02:07,640 --> 00:02:07,650 and various planetary bodies to 43 00:02:07,650 --> 00:02:09,919 and various planetary bodies to understand these various propulsion 44 00:02:09,919 --> 00:02:09,929 understand these various propulsion 45 00:02:09,929 --> 00:02:13,070 understand these various propulsion applications specific auxiliary and 46 00:02:13,070 --> 00:02:13,080 applications specific auxiliary and 47 00:02:13,080 --> 00:02:16,220 applications specific auxiliary and primary missions will be discussed on 48 00:02:16,220 --> 00:02:16,230 primary missions will be discussed on 49 00:02:16,230 --> 00:02:18,860 primary missions will be discussed on earth to orbit vehicles such as the 50 00:02:18,860 --> 00:02:18,870 earth to orbit vehicles such as the 51 00:02:18,870 --> 00:02:21,920 earth to orbit vehicles such as the shuttle orbiter Auxiliary low thrust 52 00:02:21,920 --> 00:02:21,930 shuttle orbiter Auxiliary low thrust 53 00:02:21,930 --> 00:02:24,100 shuttle orbiter Auxiliary low thrust propulsion systems are used to control 54 00:02:24,100 --> 00:02:24,110 propulsion systems are used to control 55 00:02:24,110 --> 00:02:28,009 propulsion systems are used to control vehicle orientation or to perform small 56 00:02:28,009 --> 00:02:28,019 vehicle orientation or to perform small 57 00:02:28,019 --> 00:02:33,650 vehicle orientation or to perform small orbit changes examples are orientation 58 00:02:33,650 --> 00:02:33,660 orbit changes examples are orientation 59 00:02:33,660 --> 00:02:35,870 orbit changes examples are orientation of the shuttle orbiter to face the Sun 60 00:02:35,870 --> 00:02:35,880 of the shuttle orbiter to face the Sun 61 00:02:35,880 --> 00:02:39,080 of the shuttle orbiter to face the Sun and rendezvous with low Earth orbit 62 00:02:39,080 --> 00:02:39,090 and rendezvous with low Earth orbit 63 00:02:39,090 --> 00:02:41,030 and rendezvous with low Earth orbit systems such as the long-duration 64 00:02:41,030 --> 00:02:41,040 systems such as the long-duration 65 00:02:41,040 --> 00:02:46,370 systems such as the long-duration exposure facility led F the low thrust 66 00:02:46,370 --> 00:02:46,380 exposure facility led F the low thrust 67 00:02:46,380 --> 00:02:48,470 exposure facility led F the low thrust devices for these applications are 68 00:02:48,470 --> 00:02:48,480 devices for these applications are 69 00:02:48,480 --> 00:02:51,410 devices for these applications are called reaction control systems which 70 00:02:51,410 --> 00:02:51,420 called reaction control systems which 71 00:02:51,420 --> 00:02:53,690 called reaction control systems which generally operate at thrust levels from 72 00:02:53,690 --> 00:02:53,700 generally operate at thrust levels from 73 00:02:53,700 --> 00:02:58,400 generally operate at thrust levels from 25 to a few hundred pounds space station 74 00:02:58,400 --> 00:02:58,410 25 to a few hundred pounds space station 75 00:02:58,410 --> 00:03:01,009 25 to a few hundred pounds space station freedom requires low thrust propulsion 76 00:03:01,009 --> 00:03:01,019 freedom requires low thrust propulsion 77 00:03:01,019 --> 00:03:04,330 freedom requires low thrust propulsion for both orbit and attitude control 78 00:03:04,330 --> 00:03:04,340 for both orbit and attitude control 79 00:03:04,340 --> 00:03:07,300 for both orbit and attitude control orbit control includes atmosphere drag 80 00:03:07,300 --> 00:03:07,310 orbit control includes atmosphere drag 81 00:03:07,310 --> 00:03:11,170 orbit control includes atmosphere drag makeup and collision avoidance attitude 82 00:03:11,170 --> 00:03:11,180 makeup and collision avoidance attitude 83 00:03:11,180 --> 00:03:13,630 makeup and collision avoidance attitude control includes damping of disturbances 84 00:03:13,630 --> 00:03:13,640 control includes damping of disturbances 85 00:03:13,640 --> 00:03:16,900 control includes damping of disturbances such as shuttle docking and momentum 86 00:03:16,900 --> 00:03:16,910 such as shuttle docking and momentum 87 00:03:16,910 --> 00:03:20,910 such as shuttle docking and momentum management small electric rockets called 88 00:03:20,910 --> 00:03:20,920 management small electric rockets called 89 00:03:20,920 --> 00:03:22,240 management small electric rockets called resistojet 90 00:03:22,240 --> 00:03:22,250 resistojet 91 00:03:22,250 --> 00:03:25,770 resistojet with thrust levels less than a pound and 92 00:03:25,770 --> 00:03:25,780 with thrust levels less than a pound and 93 00:03:25,780 --> 00:03:29,350 with thrust levels less than a pound and 25 to 100 pound chemical rockets are 94 00:03:29,350 --> 00:03:29,360 25 to 100 pound chemical rockets are 95 00:03:29,360 --> 00:03:32,350 25 to 100 pound chemical rockets are being considered for orbit and attitude 96 00:03:32,350 --> 00:03:32,360 being considered for orbit and attitude 97 00:03:32,360 --> 00:03:36,750 being considered for orbit and attitude control for Space Station freedom 98 00:03:36,750 --> 00:03:36,760 99 00:03:36,760 --> 00:03:39,250 communication satellites are usually 100 00:03:39,250 --> 00:03:39,260 communication satellites are usually 101 00:03:39,260 --> 00:03:40,900 communication satellites are usually first placed in a geosynchronous 102 00:03:40,900 --> 00:03:40,910 first placed in a geosynchronous 103 00:03:40,910 --> 00:03:44,650 first placed in a geosynchronous transfer orbit or GTO 104 00:03:44,650 --> 00:03:44,660 transfer orbit or GTO 105 00:03:44,660 --> 00:03:48,550 transfer orbit or GTO a 100 to 200 pound thrust apogee 106 00:03:48,550 --> 00:03:48,560 a 100 to 200 pound thrust apogee 107 00:03:48,560 --> 00:03:51,460 a 100 to 200 pound thrust apogee propulsion system is used to change the 108 00:03:51,460 --> 00:03:51,470 propulsion system is used to change the 109 00:03:51,470 --> 00:03:54,759 propulsion system is used to change the gto to a circular geosynchronous orbit 110 00:03:54,759 --> 00:03:54,769 gto to a circular geosynchronous orbit 111 00:03:54,769 --> 00:03:58,470 gto to a circular geosynchronous orbit at an altitude of about 20 2,300 miles 112 00:03:58,470 --> 00:03:58,480 at an altitude of about 20 2,300 miles 113 00:03:58,480 --> 00:04:01,900 at an altitude of about 20 2,300 miles in the geosynchronous orbit small 114 00:04:01,900 --> 00:04:01,910 in the geosynchronous orbit small 115 00:04:01,910 --> 00:04:04,270 in the geosynchronous orbit small station-keeping Rockets are used to 116 00:04:04,270 --> 00:04:04,280 station-keeping Rockets are used to 117 00:04:04,280 --> 00:04:06,670 station-keeping Rockets are used to overcome gravitational forces from the 118 00:04:06,670 --> 00:04:06,680 overcome gravitational forces from the 119 00:04:06,680 --> 00:04:10,539 overcome gravitational forces from the Sun Moon and Earth to maintain the 120 00:04:10,539 --> 00:04:10,549 Sun Moon and Earth to maintain the 121 00:04:10,549 --> 00:04:14,580 Sun Moon and Earth to maintain the satellite in the desired position a 122 00:04:14,580 --> 00:04:14,590 satellite in the desired position a 123 00:04:14,590 --> 00:04:17,590 satellite in the desired position a final example of auxiliary propulsion is 124 00:04:17,590 --> 00:04:17,600 final example of auxiliary propulsion is 125 00:04:17,600 --> 00:04:20,920 final example of auxiliary propulsion is the use of 100 to 500 pound retro 126 00:04:20,920 --> 00:04:20,930 the use of 100 to 500 pound retro 127 00:04:20,930 --> 00:04:24,580 the use of 100 to 500 pound retro rockets for orbit change or capture of 128 00:04:24,580 --> 00:04:24,590 rockets for orbit change or capture of 129 00:04:24,590 --> 00:04:29,529 rockets for orbit change or capture of satellites near planetary bodies low 130 00:04:29,529 --> 00:04:29,539 satellites near planetary bodies low 131 00:04:29,539 --> 00:04:31,570 satellites near planetary bodies low thrust systems are also useful for 132 00:04:31,570 --> 00:04:31,580 thrust systems are also useful for 133 00:04:31,580 --> 00:04:34,659 thrust systems are also useful for primary propulsion applications for 134 00:04:34,659 --> 00:04:34,669 primary propulsion applications for 135 00:04:34,669 --> 00:04:38,460 primary propulsion applications for Earth orbit and planetary missions 136 00:04:38,460 --> 00:04:38,470 Earth orbit and planetary missions 137 00:04:38,470 --> 00:04:41,050 Earth orbit and planetary missions examples in Earth space include the 138 00:04:41,050 --> 00:04:41,060 examples in Earth space include the 139 00:04:41,060 --> 00:04:43,210 examples in Earth space include the transport of communication satellites 140 00:04:43,210 --> 00:04:43,220 transport of communication satellites 141 00:04:43,220 --> 00:04:46,180 transport of communication satellites from low-earth orbit into geosynchronous 142 00:04:46,180 --> 00:04:46,190 from low-earth orbit into geosynchronous 143 00:04:46,190 --> 00:04:48,790 from low-earth orbit into geosynchronous orbit and the placement of weather 144 00:04:48,790 --> 00:04:48,800 orbit and the placement of weather 145 00:04:48,800 --> 00:04:51,460 orbit and the placement of weather satellites in polar orbits for earth 146 00:04:51,460 --> 00:04:51,470 satellites in polar orbits for earth 147 00:04:51,470 --> 00:04:55,719 satellites in polar orbits for earth observations planetary missions include 148 00:04:55,719 --> 00:04:55,729 observations planetary missions include 149 00:04:55,729 --> 00:04:58,000 observations planetary missions include transferring of systems beyond earth 150 00:04:58,000 --> 00:04:58,010 transferring of systems beyond earth 151 00:04:58,010 --> 00:05:03,900 transferring of systems beyond earth space to planets comets and asteroids 152 00:05:03,900 --> 00:05:03,910 153 00:05:03,910 --> 00:05:06,570 low thrust electric propulsion is 154 00:05:06,570 --> 00:05:06,580 low thrust electric propulsion is 155 00:05:06,580 --> 00:05:09,390 low thrust electric propulsion is particularly valuable for very energetic 156 00:05:09,390 --> 00:05:09,400 particularly valuable for very energetic 157 00:05:09,400 --> 00:05:12,390 particularly valuable for very energetic planetary applications such as cargo 158 00:05:12,390 --> 00:05:12,400 planetary applications such as cargo 159 00:05:12,400 --> 00:05:16,130 planetary applications such as cargo vehicles for major moon Mars missions 160 00:05:16,130 --> 00:05:16,140 vehicles for major moon Mars missions 161 00:05:16,140 --> 00:05:18,870 vehicles for major moon Mars missions the Lewis Research Center is developing 162 00:05:18,870 --> 00:05:18,880 the Lewis Research Center is developing 163 00:05:18,880 --> 00:05:21,420 the Lewis Research Center is developing low thrust chemical and electric 164 00:05:21,420 --> 00:05:21,430 low thrust chemical and electric 165 00:05:21,430 --> 00:05:25,010 low thrust chemical and electric propulsion systems chemical propulsion 166 00:05:25,010 --> 00:05:25,020 propulsion systems chemical propulsion 167 00:05:25,020 --> 00:05:27,960 propulsion systems chemical propulsion includes rockets which use hydrogen 168 00:05:27,960 --> 00:05:27,970 includes rockets which use hydrogen 169 00:05:27,970 --> 00:05:32,010 includes rockets which use hydrogen oxygen and storable propellants although 170 00:05:32,010 --> 00:05:32,020 oxygen and storable propellants although 171 00:05:32,020 --> 00:05:34,110 oxygen and storable propellants although chemical rockets use various propellants 172 00:05:34,110 --> 00:05:34,120 chemical rockets use various propellants 173 00:05:34,120 --> 00:05:36,930 chemical rockets use various propellants all involved heating the propellant and 174 00:05:36,930 --> 00:05:36,940 all involved heating the propellant and 175 00:05:36,940 --> 00:05:39,540 all involved heating the propellant and its subsequent expansion through a 176 00:05:39,540 --> 00:05:39,550 its subsequent expansion through a 177 00:05:39,550 --> 00:05:44,490 its subsequent expansion through a nozzle to produce thrust chemical 178 00:05:44,490 --> 00:05:44,500 nozzle to produce thrust chemical 179 00:05:44,500 --> 00:05:47,280 nozzle to produce thrust chemical rockets using gaseous hydrogen oxygen 180 00:05:47,280 --> 00:05:47,290 rockets using gaseous hydrogen oxygen 181 00:05:47,290 --> 00:05:50,220 rockets using gaseous hydrogen oxygen have been developed for possible use on 182 00:05:50,220 --> 00:05:50,230 have been developed for possible use on 183 00:05:50,230 --> 00:05:53,820 have been developed for possible use on the space station designs ranging from 184 00:05:53,820 --> 00:05:53,830 the space station designs ranging from 185 00:05:53,830 --> 00:05:56,670 the space station designs ranging from 25 to 50 pounds thrust have been built 186 00:05:56,670 --> 00:05:56,680 25 to 50 pounds thrust have been built 187 00:05:56,680 --> 00:06:00,570 25 to 50 pounds thrust have been built and life tested studies indicate that 188 00:06:00,570 --> 00:06:00,580 and life tested studies indicate that 189 00:06:00,580 --> 00:06:02,940 and life tested studies indicate that future launch vehicles would benefit 190 00:06:02,940 --> 00:06:02,950 future launch vehicles would benefit 191 00:06:02,950 --> 00:06:05,430 future launch vehicles would benefit from liquid hydrogen oxygen reaction 192 00:06:05,430 --> 00:06:05,440 from liquid hydrogen oxygen reaction 193 00:06:05,440 --> 00:06:08,670 from liquid hydrogen oxygen reaction control systems and optimal approaches 194 00:06:08,670 --> 00:06:08,680 control systems and optimal approaches 195 00:06:08,680 --> 00:06:12,630 control systems and optimal approaches are being defined a breakthrough in 196 00:06:12,630 --> 00:06:12,640 are being defined a breakthrough in 197 00:06:12,640 --> 00:06:15,120 are being defined a breakthrough in storable chemical propulsion technology 198 00:06:15,120 --> 00:06:15,130 storable chemical propulsion technology 199 00:06:15,130 --> 00:06:19,520 storable chemical propulsion technology has been verified with a 5-pound rocket 200 00:06:19,520 --> 00:06:19,530 has been verified with a 5-pound rocket 201 00:06:19,530 --> 00:06:22,680 has been verified with a 5-pound rocket 100 to 200 pounds storable rockets are 202 00:06:22,680 --> 00:06:22,690 100 to 200 pounds storable rockets are 203 00:06:22,690 --> 00:06:24,870 100 to 200 pounds storable rockets are now under development which will provide 204 00:06:24,870 --> 00:06:24,880 now under development which will provide 205 00:06:24,880 --> 00:06:26,970 now under development which will provide major increases in the life and 206 00:06:26,970 --> 00:06:26,980 major increases in the life and 207 00:06:26,980 --> 00:06:30,600 major increases in the life and performance of Apogee retro and orbit 208 00:06:30,600 --> 00:06:30,610 performance of Apogee retro and orbit 209 00:06:30,610 --> 00:06:34,920 performance of Apogee retro and orbit change propulsion systems specific 210 00:06:34,920 --> 00:06:34,930 change propulsion systems specific 211 00:06:34,930 --> 00:06:36,720 change propulsion systems specific electric rockets have very different 212 00:06:36,720 --> 00:06:36,730 electric rockets have very different 213 00:06:36,730 --> 00:06:39,840 electric rockets have very different operating principles but all electric 214 00:06:39,840 --> 00:06:39,850 operating principles but all electric 215 00:06:39,850 --> 00:06:42,740 operating principles but all electric propulsion systems share many features 216 00:06:42,740 --> 00:06:42,750 propulsion systems share many features 217 00:06:42,750 --> 00:06:45,870 propulsion systems share many features energy is derived from a solar or 218 00:06:45,870 --> 00:06:45,880 energy is derived from a solar or 219 00:06:45,880 --> 00:06:48,960 energy is derived from a solar or nuclear power source and is converted 220 00:06:48,960 --> 00:06:48,970 nuclear power source and is converted 221 00:06:48,970 --> 00:06:51,870 nuclear power source and is converted into electricity and then conditioned 222 00:06:51,870 --> 00:06:51,880 into electricity and then conditioned 223 00:06:51,880 --> 00:06:54,600 into electricity and then conditioned for use by the electric rockets which 224 00:06:54,600 --> 00:06:54,610 for use by the electric rockets which 225 00:06:54,610 --> 00:06:56,930 for use by the electric rockets which use the power in various ways to 226 00:06:56,930 --> 00:06:56,940 use the power in various ways to 227 00:06:56,940 --> 00:06:59,550 use the power in various ways to accelerate the propellant to produce 228 00:06:59,550 --> 00:06:59,560 accelerate the propellant to produce 229 00:06:59,560 --> 00:07:04,380 accelerate the propellant to produce thrust resistojet s' the simplest 230 00:07:04,380 --> 00:07:04,390 thrust resistojet s' the simplest 231 00:07:04,390 --> 00:07:07,230 thrust resistojet s' the simplest electric rockets add energy to a 232 00:07:07,230 --> 00:07:07,240 electric rockets add energy to a 233 00:07:07,240 --> 00:07:10,380 electric rockets add energy to a propellant via heat transfer from an 234 00:07:10,380 --> 00:07:10,390 propellant via heat transfer from an 235 00:07:10,390 --> 00:07:13,530 propellant via heat transfer from an electrically heated resistor 236 00:07:13,530 --> 00:07:13,540 electrically heated resistor 237 00:07:13,540 --> 00:07:17,040 electrically heated resistor a version which uses waste gas from the 238 00:07:17,040 --> 00:07:17,050 a version which uses waste gas from the 239 00:07:17,050 --> 00:07:19,530 a version which uses waste gas from the station modules as the propellant is 240 00:07:19,530 --> 00:07:19,540 station modules as the propellant is 241 00:07:19,540 --> 00:07:22,560 station modules as the propellant is being developed for drag makeup on Space 242 00:07:22,560 --> 00:07:22,570 being developed for drag makeup on Space 243 00:07:22,570 --> 00:07:26,910 being developed for drag makeup on Space Station freedom in our Jets 244 00:07:26,910 --> 00:07:26,920 Station freedom in our Jets 245 00:07:26,920 --> 00:07:29,820 Station freedom in our Jets the propellant is heated by an electric 246 00:07:29,820 --> 00:07:29,830 the propellant is heated by an electric 247 00:07:29,830 --> 00:07:32,370 the propellant is heated by an electric arc and is then expelled through a 248 00:07:32,370 --> 00:07:32,380 arc and is then expelled through a 249 00:07:32,380 --> 00:07:37,080 arc and is then expelled through a nozzle arc Jets which use about one 250 00:07:37,080 --> 00:07:37,090 nozzle arc Jets which use about one 251 00:07:37,090 --> 00:07:39,660 nozzle arc Jets which use about one kilowatt of power and hydrazine 252 00:07:39,660 --> 00:07:39,670 kilowatt of power and hydrazine 253 00:07:39,670 --> 00:07:42,180 kilowatt of power and hydrazine propellant are under intense development 254 00:07:42,180 --> 00:07:42,190 propellant are under intense development 255 00:07:42,190 --> 00:07:44,580 propellant are under intense development for station keeping on commercial 256 00:07:44,580 --> 00:07:44,590 for station keeping on commercial 257 00:07:44,590 --> 00:07:49,050 for station keeping on commercial geosynchronous satellites electrostatic 258 00:07:49,050 --> 00:07:49,060 geosynchronous satellites electrostatic 259 00:07:49,060 --> 00:07:52,640 geosynchronous satellites electrostatic or ion thrusters and magneto plasma 260 00:07:52,640 --> 00:07:52,650 or ion thrusters and magneto plasma 261 00:07:52,650 --> 00:07:55,920 or ion thrusters and magneto plasma dynamics or MPD Rockets are being 262 00:07:55,920 --> 00:07:55,930 dynamics or MPD Rockets are being 263 00:07:55,930 --> 00:07:59,580 dynamics or MPD Rockets are being developed for Earth orbit and planetary 264 00:07:59,580 --> 00:07:59,590 developed for Earth orbit and planetary 265 00:07:59,590 --> 00:08:04,050 developed for Earth orbit and planetary primary propulsion functions ion Rockets 266 00:08:04,050 --> 00:08:04,060 primary propulsion functions ion Rockets 267 00:08:04,060 --> 00:08:07,110 primary propulsion functions ion Rockets first emit electrons from a cathode to 268 00:08:07,110 --> 00:08:07,120 first emit electrons from a cathode to 269 00:08:07,120 --> 00:08:09,750 first emit electrons from a cathode to create positively charged ions in a 270 00:08:09,750 --> 00:08:09,760 create positively charged ions in a 271 00:08:09,760 --> 00:08:12,200 create positively charged ions in a discharge chamber and then 272 00:08:12,200 --> 00:08:12,210 discharge chamber and then 273 00:08:12,210 --> 00:08:14,850 discharge chamber and then electrostatically accelerate those ions 274 00:08:14,850 --> 00:08:14,860 electrostatically accelerate those ions 275 00:08:14,860 --> 00:08:18,480 electrostatically accelerate those ions through two perforated plates called ion 276 00:08:18,480 --> 00:08:18,490 through two perforated plates called ion 277 00:08:18,490 --> 00:08:19,970 through two perforated plates called ion optics 278 00:08:19,970 --> 00:08:19,980 optics 279 00:08:19,980 --> 00:08:22,920 optics this is a typical discharge chamber 280 00:08:22,920 --> 00:08:22,930 this is a typical discharge chamber 281 00:08:22,930 --> 00:08:26,190 this is a typical discharge chamber along with the ion optics which contain 282 00:08:26,190 --> 00:08:26,200 along with the ion optics which contain 283 00:08:26,200 --> 00:08:31,850 along with the ion optics which contain over 20,000 holes to accelerate the ions 284 00:08:31,850 --> 00:08:31,860 285 00:08:31,860 --> 00:08:34,440 this scene shows an ion thruster 286 00:08:34,440 --> 00:08:34,450 this scene shows an ion thruster 287 00:08:34,450 --> 00:08:38,570 this scene shows an ion thruster operating at approximately 10 kilowatts 288 00:08:38,570 --> 00:08:38,580 operating at approximately 10 kilowatts 289 00:08:38,580 --> 00:08:41,730 operating at approximately 10 kilowatts MPD Rockets produce thrust by using an 290 00:08:41,730 --> 00:08:41,740 MPD Rockets produce thrust by using an 291 00:08:41,740 --> 00:08:44,970 MPD Rockets produce thrust by using an electromagnetic field to accelerate a 292 00:08:44,970 --> 00:08:44,980 electromagnetic field to accelerate a 293 00:08:44,980 --> 00:08:49,470 electromagnetic field to accelerate a plasma direct measurements of ion and 294 00:08:49,470 --> 00:08:49,480 plasma direct measurements of ion and 295 00:08:49,480 --> 00:08:52,770 plasma direct measurements of ion and MPD performance and exhaust plumes are 296 00:08:52,770 --> 00:08:52,780 MPD performance and exhaust plumes are 297 00:08:52,780 --> 00:08:56,010 MPD performance and exhaust plumes are necessary these measurements require 298 00:08:56,010 --> 00:08:56,020 necessary these measurements require 299 00:08:56,020 --> 00:08:58,470 necessary these measurements require large frost stands and state-of-the-art 300 00:08:58,470 --> 00:08:58,480 large frost stands and state-of-the-art 301 00:08:58,480 --> 00:09:04,320 large frost stands and state-of-the-art plume Diagnostics ion and MPD Rockets 302 00:09:04,320 --> 00:09:04,330 plume Diagnostics ion and MPD Rockets 303 00:09:04,330 --> 00:09:07,320 plume Diagnostics ion and MPD Rockets both require large space simulation 304 00:09:07,320 --> 00:09:07,330 both require large space simulation 305 00:09:07,330 --> 00:09:10,290 both require large space simulation facilities with high gas pumping speeds 306 00:09:10,290 --> 00:09:10,300 facilities with high gas pumping speeds 307 00:09:10,300 --> 00:09:13,260 facilities with high gas pumping speeds in order to obtain space like vacuums 308 00:09:13,260 --> 00:09:13,270 in order to obtain space like vacuums 309 00:09:13,270 --> 00:09:16,550 in order to obtain space like vacuums during testing 310 00:09:16,550 --> 00:09:16,560 311 00:09:16,560 --> 00:09:19,460 in summary advanced low thrust 312 00:09:19,460 --> 00:09:19,470 in summary advanced low thrust 313 00:09:19,470 --> 00:09:21,829 in summary advanced low thrust propulsion provides benefits for many 314 00:09:21,829 --> 00:09:21,839 propulsion provides benefits for many 315 00:09:21,839 --> 00:09:23,350 propulsion provides benefits for many applications 316 00:09:23,350 --> 00:09:23,360 applications 317 00:09:23,360 --> 00:09:26,090 applications these range from reaction control 318 00:09:26,090 --> 00:09:26,100 these range from reaction control 319 00:09:26,100 --> 00:09:28,939 these range from reaction control systems for Earth orbit vehicles such as 320 00:09:28,939 --> 00:09:28,949 systems for Earth orbit vehicles such as 321 00:09:28,949 --> 00:09:31,970 systems for Earth orbit vehicles such as the Space Shuttle and drag make up and 322 00:09:31,970 --> 00:09:31,980 the Space Shuttle and drag make up and 323 00:09:31,980 --> 00:09:34,579 the Space Shuttle and drag make up and attitude control devices for large 324 00:09:34,579 --> 00:09:34,589 attitude control devices for large 325 00:09:34,589 --> 00:09:37,759 attitude control devices for large platforms in low-earth orbit such as 326 00:09:37,759 --> 00:09:37,769 platforms in low-earth orbit such as 327 00:09:37,769 --> 00:09:41,420 platforms in low-earth orbit such as Space Station freedom it also includes 328 00:09:41,420 --> 00:09:41,430 Space Station freedom it also includes 329 00:09:41,430 --> 00:09:43,730 Space Station freedom it also includes significantly reducing the propellant 330 00:09:43,730 --> 00:09:43,740 significantly reducing the propellant 331 00:09:43,740 --> 00:09:46,210 significantly reducing the propellant for Apogee propulsion and 332 00:09:46,210 --> 00:09:46,220 for Apogee propulsion and 333 00:09:46,220 --> 00:09:48,679 for Apogee propulsion and station-keeping propulsion for 334 00:09:48,679 --> 00:09:48,689 station-keeping propulsion for 335 00:09:48,689 --> 00:09:53,119 station-keeping propulsion for geosynchronous satellites and then 336 00:09:53,119 --> 00:09:53,129 geosynchronous satellites and then 337 00:09:53,129 --> 00:09:55,960 geosynchronous satellites and then advanced electric propulsion systems 338 00:09:55,960 --> 00:09:55,970 advanced electric propulsion systems 339 00:09:55,970 --> 00:09:58,730 advanced electric propulsion systems enable an order of magnitude reduction 340 00:09:58,730 --> 00:09:58,740 enable an order of magnitude reduction 341 00:09:58,740 --> 00:10:01,819 enable an order of magnitude reduction in the propellant required for primary 342 00:10:01,819 --> 00:10:01,829 in the propellant required for primary 343 00:10:01,829 --> 00:10:04,809 in the propellant required for primary propulsion in both earth orbital and 344 00:10:04,809 --> 00:10:04,819 propulsion in both earth orbital and 345 00:10:04,819 --> 00:10:09,889 propulsion in both earth orbital and planetary missions the lowest Research 346 00:10:09,889 --> 00:10:09,899 planetary missions the lowest Research 347 00:10:09,899 --> 00:10:11,720 planetary missions the lowest Research Center is conducting a low thrust 348 00:10:11,720 --> 00:10:11,730 Center is conducting a low thrust 349 00:10:11,730 --> 00:10:15,429 Center is conducting a low thrust propulsion program utilizing an in-house 350 00:10:15,429 --> 00:10:15,439 propulsion program utilizing an in-house 351 00:10:15,439 --> 00:10:19,790 propulsion program utilizing an in-house university and industrial team this 352 00:10:19,790 --> 00:10:19,800 university and industrial team this 353 00:10:19,800 --> 00:10:22,970 university and industrial team this blend of skills assures that the program 354 00:10:22,970 --> 00:10:22,980 blend of skills assures that the program 355 00:10:22,980 --> 00:10:25,309 blend of skills assures that the program will develop practical devices for 356 00:10:25,309 --> 00:10:25,319 will develop practical devices for 357 00:10:25,319 --> 00:10:28,819 will develop practical devices for near-term applications and also produce 358 00:10:28,819 --> 00:10:28,829 near-term applications and also produce 359 00:10:28,829 --> 00:10:31,549 near-term applications and also produce more advanced concepts for the 360 00:10:31,549 --> 00:10:31,559 more advanced concepts for the 361 00:10:31,559 --> 00:10:35,210 more advanced concepts for the longer-term higher payoff national space 362 00:10:35,210 --> 00:10:35,220 longer-term higher payoff national space 363 00:10:35,220 --> 00:10:37,759 longer-term higher payoff national space missions