Single launch complex consisting of 2 launch pads.

• 1966 October 2 10:39 - ESSA 3 Launch Vehicle: Delta E. Thor Delta E 463/D41 Apogee: 1�486 km (923 mi). Environmental Survey Satellite 3; replace ESSA 1. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1966 December 29 12:00 - OPS 1584 Launch Vehicle: Thor Agena D. Thor SLV-2A Agena D 459 / Agena D SS-01B 2731 Apogee: 495 km (307 mi).

• 1967 January 26 17:31 - ESSA 4 Launch Vehicle: Delta E. Thor Delta E 472/D45 Apogee: 1�440 km (890 mi). Replaced ESSA 2. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1967 April 20 11:21 - ESSA 5 Launch Vehicle: Delta E. Thor Delta E 484/D48 Apogee: 1�422 km (883 mi). Replaced ESSA 3. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1967 May 24 14:05 - Explorer 34 Launch Vehicle: Delta E. Thor Delta E1 486/D49 Apogee: 214�379 km (133�208 mi). Radiation, magnetic field data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1967 May 31 09:30 - Calsphere 4 Launch Vehicle: Thor Agena D. Thor SLV-2 Agena D 443 / Agena D SS-01B 2704 Apogee: 834 km (518 mi). Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

• 1967 July 25 03:48 - OPS 1879 Launch Vehicle: Thor Agena D. Thor SLV-2A Agena D 496 / Agena D SS-01B 2732 Apogee: 608 km (377 mi).

• 1967 July 28 14:21 - OGO 4 Launch Vehicle: Thor Agena D. Thor SLV-2A Agena D 478 (TA8) / Agena D SS-01B 680 Apogee: 885 km (549 mi). OGO 4 was a large observatory instrumented with experiments designed to study the interrelationships between the aurora and airglow emissions, energetic particle activity, geomagnetic field variation, ionospheric ionization and recombination, and atmospheric heating which take place during a period of increased solar activity. After the spacecraft achieved orbit and the experiments were deployed into an operating mode, an attitude control problem occurred. This condition was corrected by ground control procedures until complete failure of the tape recording systems in mid-January 1969. At that time, due to the difficulty of maintaining attitude control without the tape recorders, the attitude control system was commanded off, and the spacecraft was placed into a spin-stabilized mode about the axis which was previously maintained vertically. In this mode, seven of the remaining experiments were turned off since no meaningful data could be observed by them. On October 23, 1969, the satellite was turned off. It was reactivated again in January 1970 for 2 months to obtain VLF observations.

• 1967 November 10 17:53 - ESSA 6 Launch Vehicle: Delta E. Thor Delta E1 480/D54 Apogee: 1�485 km (922 mi). Returned cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1968 January 11 16:16 - Explorer 36 Launch Vehicle: Delta E. Thor Delta E1 454/D56 Apogee: 1�574 km (978 mi). The geodetic instrumentation systems included (1) four optical beacons, (2) two C-band radar transponders, (3) a passive radar reflector, (4) a sequential collation of range radio range transponder, (5) a Goddard range and range rate transponder, (6) laser reflectors, and (7) Doppler beacons. Non-geodetic systems included a laser detector and a Minitrack interferometer beacon. The objectives of the spacecraft were to optimise optical station visibility periods and to provide complementary data for inclination-dependent terms established by the Explorer 29 (GEOS 1) gravimetric studies. The spacecraft was placed into a retrograde orbit to accomplish these objectives. Operational problems occurred in the main power system, optical beacon flash system, and the spacecraft clock, and adjustments in scheduling resulted in nominal operations.

• 1968 January 17 10:12 - OPS 1965 Launch Vehicle: Thor Agena D. Thor SLV-2A Agena D 498 / Agena D 2733 Apogee: 536 km (333 mi).

• 1968 May 18 08:23 - Nimbus B Launch Vehicle: Thorad Agena D SLV-2G. Failure. Thorad SLV-2G Agena D 520 (TA9) / Agena D 6221 (TA Launched with Secor 10.

• 1968 July 4 17:26 - Explorer 38 Launch Vehicle: Delta J. Thor Delta J 476/D57 Apogee: 5�861 km (3�641 mi). Radio Astronomy Explorer; Earth, solar, cosmic radio emission data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1968 August 16 11:24 - ESSA 7 Launch Vehicle: Delta N. Thor Delta N 528/D58 Apogee: 1�473 km (915 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1968 December 15 17:21 - ESSA 8 Launch Vehicle: Delta N. Thor Delta N 532/D62 Apogee: 1�464 km (909 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1969 January 30 06:46 - Isis 1 Launch Vehicle: Delta E. Thor Delta E1 485/D65 Apogee: 3�458 km (2�148 mi). Ionospheric measurements; data correlated with measurements from Alouette 1. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1969 April 14 07:54 - Nimbus 3 Launch Vehicle: Thorad Agena D SLV-2G. Thorad SLV-2G Agena D 543 (TA10) / Agena D 6222 (T Apogee: 1�130 km (700 mi). Primary experiments consisted of a satellite infrared spectrometer (SIRS) for determining the vertical temperature profiles of the atmosphere, an infrared interferometer spectrometer (IRIS) for measuring the emission spectra of the earth-atmosphere system, both high- and medium-resolution infrared radiometers (HRIR and MRIR) for yielding information on the distribution and intensity of infrared radiation emitted and reflected by the earth and its atmosphere, monitor of ultraviolet solar energy (MUSE) for detecting solar UV radiation, image dissector camera system for providing daytime cloudcover pictures in both real-time mode using the real time transmission system and tape recorder mode using the high data rate storage system, radioisotope thermoelectric generator (RTG) SNAP-19 to assess the operational capability of radioisotope power for space applications, and an interrogation, recording and location system (IRLS) experiment designed to locate, interrogate, record, and retransmit meteorological and geophysical data from remote collection stations. Nimbus-3 was successful and performed normally until July 22, 1969, when the IRIS experiment failed. The HRIR and the SIRS experiments were terminated on January 25, 1970, and June 21, 1970, respectively. The remaining experiments continued operation until September 25, 1970, when the rear horizon scanner failed. Without this horizon scanner, it was impossible to maintain proper spacecraft attitude, thus making most experimental observations useless. All spacecraft operations were terminated on January 22, 1972.

• 1969 June 5 14:42 - OGO 6 Launch Vehicle: Thorad Agena D SLV-2H. Thorad SLV-2H Agena D 526 (TA11) / Agena D 6803 (T Apogee: 1�089 km (676 mi). OGO 6 was a large observatory instrumented with 26 experiments designed to study the various interrelationships between, and latitudinal distributions of, high-altitude atmospheric parameters during a period of increased solar activity. On June 22, 1969, the spacecraft potential dropped significantly during sunlight operation and remained so during subsequent sunlight operation. This unexplained shift affected seven experiments which made measurements dependent upon knowledge of the spacecraft plasma sheath. During October 1969, a string of solar cells failed, but the only effect of the decreased power was to cause two experiments to change their mode of operation. Also during October 1969, a combination of manual and automatic attitude control was initiated, which extended the control gas lifetime of the attitude control system. In August 1970, tape recorder (TR) no. 1 operation degraded, so all recorded data were subsequently taken with TR no. 2. By September 1970, power and equipment degradation left 14 experiments operating normally, 3 partially, and 9 off. From October 14, 1970, TR no. 2 was used only on Wednesdays (world days) to conserve power and extend TR operation. In June 1971, the number of 'on' experiments decreased from 13 to 7, and on June 28, 1971, the spacecraft was placed in a spin-stabilized mode about the yaw (Z) axis and turned off due to difficulties with spacecraft power. OGO 6 was turned on again from October 10, 1971, through March 1972, for operation of experiment 25 by The Radio Research Laboratory, Japan.

• 1969 June 21 08:47 - Explorer 41 Launch Vehicle: Delta E. Thor Delta E1 482/D69 Apogee: 98�159 km (60�993 mi). Cislunar radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1970 January 23 11:31 - ITOS 1 Launch Vehicle: Delta N. Thor Delta N6 542/D76 Apogee: 1�479 km (919 mi). Improved TIROS Operational Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1970 February 4 02:59 - SERT 2 Launch Vehicle: Thorad Agena D SLV-2G. Thorad SLV-2G Agena D 534 (TA12) / Agena D (TA12) Apogee: 1�046 km (649 mi). Space Electric Rocket Test; the ion engines aboard were operated until 1981. The SERT 2 development program started in 1966 and included thruster ground tests of 6742 hours and 5169 hours duration. A prototype version of the SERT 2 spacecraft was ground-tested for a period of 2400 hours with an operating ion engine. In addition to diagnostic equipment and related ion engine hardware, the spacecraft had two identical 15 cm diameter, mercury ion engines. Flight objectives included in-space operation for a period of 6 months, measurement of thrust, and demonstration of electromagnetic compatibility. The thruster maximum power level was 0.85 kW, and this provided operation at a 28 mN thrust level at 4200 s specific impulse. Flight data were obtained from 1970 to 1981 with an ion engine operating intermittently in one of three different modes, namely, HV ion extraction, discharge chamber operation only, or just neutralizer operation. Major results were that two mercury engines thrusted for periods of 3781 hours and 2011 hours. Test duration was limited due to shorts in the ion optical system. Thrust measured in space and on the ground agreed within the measurement uncertainties. Up to 300 thruster restarts were demonstrated. One power-processing unit accumulated nearly 17,900 hours during the course of the mission. Additionally, the ion propulsion system was electromagnetically compatible with all other spacecraft systems.

• 1970 April 8 08:17 - Nimbus 4 Launch Vehicle: Thorad Agena D SLV-2G. Thorad SLV-2G Agena D 553 (TA13) / Agena D 6223 (T Apogee: 1�099 km (682 mi). Environmental research. Primary experiments consisted of an image dissector camera system for providing daytime cloudcover pictures both in real-time and recorded modes, temperature-humidity infrared radiometer (THIR) for measuring daytime and nighttime surface and cloudtop temperatures as well as the water vapor content of the upper atmosphere, infrared interferometer spectrometer (IRIS) for measuring the emission spectra of the earth/atmosphere system, satellite infrared spectrometer (SIRS) for determining the vertical profiles of temperature and water vapor in the atmosphere, a monitor of ultraviolet solar energy (MUSE) for detecting solar UV radiation, a backscatter ultraviolet (BUV) detector for monitoring the vertical distribution and total amount of atmospheric ozone on a global scale, a filter wedge spectrometer (FWS) for accurate measurement of IR radiance as a function of wavelength from the earth/atmosphere system, a selective chopper radiometer (SCR) for determining the temperatures of six successive 10-km layers in the atmosphere from absorption measurements in the 15-micrometer CO2 band, and an interrogation, recording, and location system (IRLS) for locating, interrogating, recording, and retransmitting meteorological and geophysical data from remote collection stations. The spacecraft performed well until April 14, 1971, when attitude problems started. The experiments then operated on a limited time basis until September 30, 1980.

• 1970 December 11 11:35 - NOAA 1 Launch Vehicle: Delta N. Thor Delta N6 546/D81 Apogee: 1�473 km (915 mi). Built for NASA; operated by NOAA. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1971 April 1 02:57 - Isis 2 Launch Vehicle: Delta E. Thor Delta E1 491/D84 Apogee: 1�424 km (884 mi). Ionospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1971 October 21 11:32 - ITOS B Launch Vehicle: Delta N. Failure.. Thor Delta N6 572/D86 Apogee: 1�483 km (921 mi). Unusable orbit.

• 1972 January 31 17:20 - HEOS 2 Launch Vehicle: Delta L. Thor Delta L 564/D87 Apogee: 240�164 km (149�230 mi). Highly Eccentric Orbiting Satellite; particles and fields data. Fifth satellite of ESRO. Also registered as US object 1972-05A in A/AC.105/INF.248 with orbit 7835.4 min, 439 x 248160 km x 90.2 deg, category B.

• 1972 March 12 01:55 - TD-1A; Thor Delta 1A Launch Vehicle: Delta N. Thor Delta N 573/D88 Apogee: 550 km (340 mi). Sixth satellite of ESRO. Also registered as US object 1972-14A in A/AC.105/INF.255 with orbit 95.3 min, 525 x 548 km x 97.5 deg, category B.

• 1972 July 23 18:06 - Landsat 1 Launch Vehicle: Delta 0100. Delta 0900 574/D89 Apogee: 909 km (564 mi). Earth Resources Technology Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1972 October 15 17:19 - NOAA 2 Launch Vehicle: Delta 0100. Delta 0300 575/D91 Apogee: 1�455 km (904 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1972 December 11 07:56 - Nimbus 5 Launch Vehicle: Delta 0100. Delta 0900 577/D93 Apogee: 1�101 km (684 mi). Environmental research. Primary experiments included a temperature-humidity infrared radiometer (THIR) for measuring day and night surface and cloudtop temperatures as well as the water vapor content of the upper atmosphere, electrically scanning microwave radiometer (ESMR) for mapping the microwave radiation from the earth's surface and atmosphere, infrared temperature profile radiometer (ITPR) for obtaining vertical profiles of temperature and moisture, Nimbus E microwave spectrometer (NEMS) for determining tropospheric temperature profiles, atmospheric water vapor abundances, and cloud liquid water contents, selective chopper radiometer (SCR) for observing the global temperature structure of the atmosphere, and a surface composition mapping radiometer (SCMR) for measuring the differences in the thermal emission characteristics of the earth's surface.

• 1973 July 16 17:10 - ITOS E Launch Vehicle: Delta 0100. Second stage failure.. Delta 0300 578/D96 Improved TIROS Operational System.

• 1973 November 6 17:02 - NOAA 3 Launch Vehicle: Delta 0100. Delta 0300 576/D98 Apogee: 1�510 km (930 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1973 December 16 06:18 - Explorer 51 Launch Vehicle: Delta 1000. Delta 1900 585/D99 Apogee: 4�306 km (2�675 mi). Atmospheric Explorer; upper atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1974 November 15 17:11 - NOAA 4 Launch Vehicle: Delta 2000. Delta 2310 592/D104 Apogee: 1�459 km (906 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1975 January 22 17:55 - Landsat 2 Launch Vehicle: Delta 2000. Delta 2910 598/D107 Apogee: 913 km (567 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1975 April 9 23:58 - Geos 3 Launch Vehicle: Delta 1000. Delta 1410 584/D109 Apogee: 848 km (526 mi). Geodynamics Experimental Ocean Satellite. The mission of GEOS 3 (Geodynamics Experimental Ocean Satellite) was to provide the stepping stone between the National Geodetic Satellite Program (NGSP) and the Earth and Ocean Physics Application Program. It provided data to refine the geodetic and geophysical results of the NGSP and served as a test for new systems. A major achievment was the flight of a radar altimeter. Further mission objectives: intercomparison of tracking systems, investigation of solid-earth dynamic phenomena through precision laser tracking, refinement of orbit determination techniques, determination of interdatum ties and gravity models, and support of the calibration and position determination of NASA Spaceflight Tracking and Data Network (STDN) S-band tracking stations.

• 1975 June 12 08:12 - Nimbus 6 Launch Vehicle: Delta 2000. Delta 2910 595/D111 Apogee: 1�114 km (692 mi). Environmental research. The experiments selected for Nimbus-6 were the earth radiation budget (ERB), electrically scanning microwave radiometer (ESMR), high-resolution infrared radiation sounder (HIRS), limb radiance inversion radiometer (LRIR), pressure modulated radiometer (PMR), scanning microwave spectrometer (SCAMS), temperature-humidity infrared radiometer (THIR), tracking and data relay experiment (T+DRE), and the tropical wind energy conversion and reference level experiment (TWERLE). This complement of advanced sensors was capable of mapping tropospheric temperature, water vapor abundance, and cloud water content; providing vertical profiles of temperature, ozone, and water vapor; transmitting real-time data to a geostationary spacecraft (ATS 6); and yielding data on the earth's radiation budget.

• 1975 August 9 01:48 - COS-B; COS B Launch Vehicle: Delta 2000. Delta 2913 602/D113 Apogee: 99�002 km (61�516 mi). Eighth CERS/ESRO satellite, first European Space Agency satellite. Launch time 0147:59 GMT. Argument of perigee 344.7 deg. Also registered by the United States in A/AC.105/INF.331 as 1975-72A, category B satellite with orbit 2203.9 min, 442 x 99002 km x 9 0.3 deg.

• 1975 October 6 09:00 - Explorer 54 Launch Vehicle: Delta 2000. Delta 2910 600/D115 Apogee: 3�819 km (2�373 mi). Atmospheric Explorer; atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1976 May 4 08:00 - Lageos Launch Vehicle: Delta 2000. Delta 2913 609/D123 Apogee: 5�947 km (3�695 mi). LAGEOS (Laser Geodetic Satellite) was a very dense (high mass-to-area ratio) laser retroreflector satellite which provided a permanent reference point in a very stable orbit for such precision earth-dynamics measurements as crustal motions, regional strains, fault motions, polar motion and earth-rotation variations, solid earth tides, and other kinematic and dynamic parameters associated with earthquake assessment and alleviation. The performance in orbit of LAGEOS was limited only by degradation of the retroreflectors, so many decades of useful life can be expected. The high mass-to-area ratio and the precise, stable (attitude-independent) geometry of the spacecraft, together with the orbit, made this satellite the most precise position reference available. Because it is visible in all parts of the world and has an extended operation life in orbit, LAGEOS can serve as a fundamental standard for decades.

• 1976 July 29 17:07 - NOAA 5 Launch Vehicle: Delta 2000. Delta 2310 605/D126 Apogee: 1�523 km (946 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1978 March 5 17:54 - Landsat 3 Launch Vehicle: Delta 2000. Delta 2910 621/D139 Apogee: 915 km (568 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1978 October 24 08:15 - Nimbus 7 Launch Vehicle: Delta 2000. Delta 2910 630/D145 Apogee: 957 km (594 mi). Environmental research. The experiments carried were a limb infrared monitoring of the stratosphere (LIMS), stratospheric and mesopheric sounder (SAMS), coastal-zone color scanner (CZCS), stratospheric aerosol measurement (SAM II), earth radiation budget (ERB), scanning multichannel microwave radiometer (SMMR), solar backscatter UV and total ozone mapping spectrometer (SBUV/TOMS), and temperature-humidity infrared radiometer (THIR). These sensors were capable of observing several parameters at and below the mesospheric levels. After 11 years in orbit, three experiments, SAM II, SBUV/TOMS, and ERB, were still functioning successfully.

• 1981 August 3 09:56 - Dynamics Explorer 1 Launch Vehicle: Delta 3000. Partial Failure.. Delta 3913 642/D155 Apogee: 23�232 km (14�435 mi). Dynamics Explorer 1.

• 1981 October 6 11:27 - SME Launch Vehicle: Delta 2000. Delta 2310 639/D157 Apogee: 337 km (209 mi). Solar Mesosphere Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1982 July 16 17:59 - Landsat 4 Launch Vehicle: Delta 3000. Delta 3920 648/D163 Apogee: 705 km (438 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1983 January 26 02:17 - IRAS Launch Vehicle: Delta 3000. Delta 3910 650/D166 Apogee: 903 km (561 mi). All-sky survey of astronomical IR bodies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1983 May 26 15:18 - Exosat Launch Vehicle: Delta 3000. Delta 3914 D169 Apogee: 191�878 km (119�227 mi). X-ray experiments. Launch time 1518 UT. Launching agency ESA. EXOSAT is a space research satellite of the European Space Agency. The scientific objectives of the EXOSAT mission are to measure the position, structural features, spectral and temporal characteristics of cosmic X-ray sources in the energy range from less than 0.1 keV to greater than 50 keV.

• 1984 March 1 17:59 - Landsat 5 Launch Vehicle: Delta 3000. Delta 3920 D174 Apogee: 703 km (436 mi). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• 1989 November 18 14:34 - COBE Launch Vehicle: Delta 5000. Delta 5920-8 D189 Apogee: 886 km (550 mi). Cosmic Background Explorer; measured background galactic infrared radiation. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

• 1995 November 4 14:22 - Radarsat Launch Vehicle: Delta 7000. Delta 7920-10 D229 Apogee: 793 km (492 mi). Earth imaging with synthetic aperture radar.

• 1996 February 24 11:24 - Polar Launch Vehicle: Delta 7000. Delta 7925-10 D233 Apogee: 50�423 km (31�331 mi). HEO. Fields and particles, auroral studies; part of International Solar Terrestrial Physics program.

• 1996 April 24 12:27 - MSX Launch Vehicle: Delta 7000. Delta 7920-10 D235 Apogee: 907 km (563 mi). LEO. Midcourse Space eXperiment; missile detection technology tests; also used for auroral and atmospheric studies

• 1997 May 5 14:55 - Iridium 8 Launch Vehicle: Delta 7000. Delta 7920-10C D242 Apogee: 780 km (480 mi). Plane 4. Ascending node 262.5 degrees.

• 1997 July 9 13:04 - Iridium 15 Launch Vehicle: Delta 7000. Delta 7920-10C D244 Apogee: 778 km (483 mi). Plane 6. Ascending node 325.8 degrees.

• 1997 August 21 00:38 - Iridium 26 Launch Vehicle: Delta 7000. Delta 7920-10C D246 Apogee: 779 km (484 mi). Plane 2. Ascending node 199.4 degrees.

• 1997 September 27 01:23 - Iridium 19 Launch Vehicle: Delta 7000. Delta 7920-10C D248 Apogee: 780 km (480 mi). Plane 4. Ascending node 262.4 degrees.

• 1997 November 9 01:34 - Iridium 43 Launch Vehicle: Delta 7000. Delta 7920-10C D250 Apogee: 779 km (484 mi). Plane 6. Ascending node 325.8 degrees.

• 1997 December 20 13:16 - Iridium 45 Launch Vehicle: Delta 7000. Delta 7920-10C D251 Apogee: 779 km (484 mi). Plane 2. Ascending node 199.4 degrees.

• 1998 February 18 13:58 - Iridium 52 Launch Vehicle: Delta 7000. Delta 7920-10C D254 Apogee: 780 km (480 mi). Plane 5. Ascending node 294.1 degrees.

• 1998 March 30 06:02 - Iridium 55 Launch Vehicle: Delta 7000. Delta 7920-10C D255 Apogee: 780 km (480 mi). Plane 3. Ascending node 230.9 degrees.

• 1998 May 17 21:16 - Iridium 70 Launch Vehicle: Delta 7000. Delta 7920-10C D257 Apogee: 779 km (484 mi). Plane 1. Ascending node 167.8 degrees.

• 1998 September 8 21:13 - Iridium 82 Launch Vehicle: Delta 7000. Delta 7920-10C D260 Apogee: 712 km (442 mi). Plane 6. Ascending node 325.6 degrees. Not in service.

• 1998 November 6 13:37 - Iridium 2 Launch Vehicle: Delta 7000. Delta 7920-10C D262 Apogee: 603 km (374 mi). Plane 5. Ascending node 289.1 degrees. Parking orbit.

• 1999 February 23 10:29 - ARGOS Launch Vehicle: Delta 7000. Delta 7920-10 D267 Apogee: 839 km (521 mi). ARGOS was a USAF Space Test Program P91-1 technology satellite, equipped with an ion engine, ionosphere, x-ray, and dust detectors. Much delayed, it finally was placed into orbit on the eleventh (!) launch attempt.

• 1999 April 15 18:32 - Landsat 7 Launch Vehicle: Delta 7000. Delta 7920-10 D268 Apogee: 703 km (436 mi). The vehicle entered a 175 km x 706 km x 98.2 deg initial orbit. 57 minutes after launch the Delta stage burned again to circularize the orbit at 668 km x 698 km and Landsat 7 separated from the stage. The Delta stage then burned to depletion of its propellant, into a 184 km x 710 km x 107.5 deg orbit that would decay quickly. The Landsat 7 remote sensing satellite was to be operated by NASA/Goddard until October 2000, when operations would be transferred to the US Geological Survey.

• 2000 March 25 20:34 - IMAGE Launch Vehicle: Delta 7000. Delta 7326-9.5 D277 Apogee: 45�461 km (28�248 mi). Imager for Magnetopause to Aurora Global Exploration was a MIDEX (mid-sized Explorer mission) developed by NASA-Goddard and the SWRI (Southwest Research Institute) of San Antonio, Texas. The spin-stabilised spacecraft carried a set of neutral atom and ultraviolet imagers, and antennae to study radio wavelength emissions from the magnetosphere plasma. The RPI radio plasma imager has four long wire antennae which will be deployed to a span of half a kilometre.

• 2000 November 21 - EO-1 Launch Vehicle: Delta 7000. Delta 7320-10 D282 Apogee: 703 km (436 mi). First use of a Delta dual payload attach fitting. The Earth Orbiter 1 satellite was part of NASA's New Millenium Program. Complementing the New Millenium's Deep Space series, EO-1 was a NASA-Goddard satellite which demonstrated technology for the next generation Landsat. It flew in formation with Landsat-7 for comparison purposes, using a hydrazine thruster to adjust its orbit. The satellite used a MIDEX-derived bus built by Swales Aerospace; dry mass was 566 kg. The main instruments were ALI (Advanced Land Imager) and the Hyperion 220-band imaging spectrometer. At 1835 GMT the Delta second stage completed its first burn and entered a 185 x 713 km x 98.2 deg transfer orbit. At 1920 GMT the orbit was circularised and EO-1 separated at 1925 GMT into a 682 x 729 km x 98.2 deg orbit.

• 2001 October 18 18:51 - QuickBird Launch Vehicle: Delta 7000. Delta 7320-10 D288 Apogee: 464 km (288 mi). The QuickBird commercial imaging satellite was owned by DigitalGlobe (formerly EarthWatch) and used a Ball BCP2000 bus with a launch mass of 1028 kg and a dry mass of about 995 kg. The Delta upper stage entered a 185 x 472 km x 98.1 deg orbit at 1902 GMT. At 1948 GMT it reached apogee and fired again to deploy QuickBird into a 461 x 465 km x 97.2 deg orbit. The Delta then made a series of unusual depletion burns, lowering its perigee to 167 km and changing inclination to 108.9 deg.

  Quickbird 2 was to be operational after a few months of calibration and "ground-truth" checkouts to market high resolution images. The 1.0 tonne satellite was reported to be capable of images with a resolution as small as 0.6 meter, though the standard products were to be coarser. Unlike the comparable quality images from IKONOS images, some of which are currently marketed exclusively to the US military, all Quickbird 2 images may be available in the open market.

• 2001 December 7 15:07 - Jason 1 Launch Vehicle: Delta 7000. Delta 7920-10 D289 Apogee: 1�344 km (835 mi). Oceanography satellite, launch delayed from August 10 and September 15. Jason 1 was a joint mission between CNES (the French space agency) and NASA/JPL, following on the Topex satellite which carried the Poseidon sea surface altimeter. Jason carried Poseidon 2, as well as orbital tracking experiments and a microwave radiometer which measured the amount of water vapor, allowing path delay errors to be calibrated. The satellite used the Alcatel Proteus bus and had a dry mass of 472 kg plus 28 kg of hydrazine propellant. The JASON/TIMED mission's Boeing Delta 7920-10C second stage reached an initial orbit of 215 x 1343 km x 66.2 deg at 1517 GMT. A second burn at 1559 GMT circularized at apogee to 1320 x 1330 km x 66.0 deg, and the Jason 1 satellite was ejected at 1602 GMT.

• 2002 February 11 17:43 - Iridium Launch Vehicle: Delta 7000. Delta 7920-10C D290 Apogee: 684 km (425 mi).

• 2002 May 4 09:54 - Aqua Launch Vehicle: Delta 7000. Delta 7920-10L D291 Apogee: 706 km (438 mi). Climatology and environment satellite. Launch delayed from December 20, 2001, and January 30, April 18 and 26, May 2. NASA's Aqua remote sensing satellite was placed in a 185 x 707 km x 98.1 deg transfer orbit at 1006 UTC. A second burn of the second stage of the Delta at 1048:58 UTC put Aqua in a 676 x 687 km x 98.2 deg orbit.