Source: http://astronautix.com/a/atlasv.html
Timestamp: 2019-04-25 10:55:32+00:00

Document:
American orbital launch vehicle. The Atlas V launch vehicle system was a completely new design that succeeded the earlier Atlas series. Atlas V vehicles were based on the 3.8-m (12.5-ft) diameter Common Core Booster (CCB) powered by a single Russian RD-180 engine. These could be clustered together, and complemented by a Centaur upper stage, and up to five solid rocket boosters, to achieve a wide range of performance.
Status: Active. Payload: 12,500 kg (27,500 lb). Thrust: 8,590.00 kN (1,931,100 lbf). Gross mass: 546,700 kg (1,205,200 lb). Height: 58.30 m (191.20 ft). Diameter: 3.81 m (12.49 ft). Span: 5.40 m (17.70 ft). Apogee: 185 km (114 mi).
When combined with a standard Atlas payload fairing, the configuration was designated as the Atlas V 400 series. The Atlas V 500 series combined the CCB with a larger 5 m diameter payload fairing derived from that used on the Ariane 5 vehicle The Atlas V 500 series could also tailor performance by incorporating from zero to five solid rocket boosters (SRB).
Both Atlas V 400 and 500 configurations incorporated a stretched version of the Centaur upper stage (CIII), which could be configured as a single-engine Centaur (SEC) or a dual engine Centaur (DEC). The Atlas V family of launch vehicles could be launched from either Cape Canaveral Air Station Launch Complex 41 or Vandenberg Air Force Base Space Launch Complex 3W.
Launch Price $: 138.000 million in 2004 dollars.
Stage 0. 5 x Atlas V SRB. Gross Mass: 40,824 kg (90,001 lb). Empty Mass: 4,000 kg (8,800 lb). Thrust (vac): 1,270.000 kN (285,500 lbf). Isp: 275 sec. Burn time: 94 sec. Isp(sl): 245 sec. Diameter: 1.55 m (5.08 ft). Span: 1.00 m (3.20 ft). Length: 17.70 m (58.00 ft). Propellants: Solid. No Engines: 1. Engine: Aerojet SRB. Status: In production. Comments: New SRB boosters in development for Atlas V. Empty mass, vacuum thrust, sea level Isp estimated.
Stage 1. 1 x Atlas CCB. Gross Mass: 306,914 kg (676,629 lb). Empty Mass: 22,461 kg (49,518 lb). Thrust (vac): 4,151.998 kN (933,406 lbf). Isp: 338 sec. Burn time: 253 sec. Isp(sl): 311 sec. Diameter: 3.81 m (12.49 ft). Span: 3.81 m (12.49 ft). Length: 32.46 m (106.49 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-180. Status: In production. Comments: Common Core Booster uses Glushko RD-180 engine and new isogrid tanks. Used in Atlas IV/USAF EELV, Atlas V. Includes 272 kg booster interstage adapter and 1297 kg Centaur interstage adapter.
Stage 2. 1 x Centaur V1. Gross Mass: 22,825 kg (50,320 lb). Empty Mass: 2,026 kg (4,466 lb). Thrust (vac): 99.194 kN (22,300 lbf). Isp: 451 sec. Burn time: 894 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 12.68 m (41.60 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RL-10A-4-2. Status: In production. Centaur is powered by either one or two Pratt & Whitney RL10A-4-2 turbopump-fed engines burning liquid oxygen and liquid hydrogen. For typical, high-energy mission applications, Centaur will be configured with one RL10 engine. For heavy payload, low earth orbit missions, Centaur will use two RL10 engines to maximize boost phase mission performance. Guidance, tank pressurization, and propellant usage controls for both Atlas and Centaur phases are provided by the inertial navigation unit (INU) located on the Centaur forward equipment module.
Andrews ETOS American orbital launch vehicle. Proposed Earth-to-Orbit Segment booster for Andrews CEV architecture. Consisted of an Atlas V core, two Zenit-2 booster strap-ons, and a new-development LOx/LH2 upper stage.
Atlas V 401 American orbital launch vehicle. Atlas V version with a 4-m diameter payload fairing, single engine Centaur upper stage, and no strap-on solid boosters. Payloads: 7,095 kg (15,642 lb) to sun synchronous orbit; 4,950 kg (10,910 lb) to geosynchronous transfer orbit.
Atlas V 402 American orbital launch vehicle. Atlas V version with a 4-m diameter payload fairing, dual engine Centaur upper stage, and no strap-on solid boosters.
Atlas V 411 American orbital launch vehicle. Atlas V with 4-m diameter payload fairing, single engine Centaur upper stage, and one strap-on solid booster. Payloads: 8,763 kg (19,320 lb) to sun synchronous orbit; 6,075 kg (13,393 lb) to geosynchronous transfer orbit.
Atlas V 412 American orbital launch vehicle. Atlas V version with a 4-m diameter payload fairing, single engine Centaur upper stage, and two strap-on solid boosters.
Atlas V 421 American orbital launch vehicle. Atlas V with 4-m diameter payload fairing, single engine Centaur upper stage, and two strap-on solid boosters. Payloads: 10,168 kg (22,416 lb) to sun synchronous orbit; 7,000 kg (15,432 lb) to geosynchronous transfer orbit.
Atlas V 422 American orbital launch vehicle. Atlas V version with a 4-m diameter payload fairing, dual engine Centaur upper stage, and two strap-on solid boosters.
Atlas V 431 American orbital launch vehicle. Atlas V with 4-m diameter payload fairing, single engine Centaur upper stage, and three strap-on solid boosters. Payloads: 11,547 kg (25,458 lb) to sun synchronous orbit; 7,800 kg (17,196 lb) to geosynchronous transfer orbit.
Atlas V 501 Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and no strap-on solid boosters. Payloads: 6,319 kg (13,931 lb) to sun synchronous orbit; 3,970 kg (8,752 lb) to geosynchronous transfer orbit.
Atlas V 502 American orbital launch vehicle. Atlas V version with a 5-m diameter payload fairing, dual engine Centaur upper stage, and no strap-on solid boosters.
Atlas V 511 American orbital launch vehicle. Atlas V version with a 5-m diameter payload fairing, single engine Centaur upper stage, and one strap-on solid booster.
Atlas V 512 American orbital launch vehicle. Atlas V version with a 5-m diameter payload fairing, dual engine Centaur upper stage, and one strap-on solid booster.
Atlas V 521 American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and two strap-on solid boosters. Payloads: 10,161 kg (22,401 lb) to sun synchronous orbit; 6,485 kg (14,297 lb) to geosynchronous transfer orbit.
Atlas V 522 American orbital launch vehicle variant.
Atlas V 531 American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and three strap-on solid boosters.
Atlas V 532 American orbital launch vehicle. Atlas V version with a 5-m diameter payload fairing, dual engine Centaur upper stage, and three strap-on solid boosters.
Atlas V 541 American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and four strap-on solid boosters.
Atlas V 542 American orbital launch vehicle. Atlas V version with a 5-m diameter payload fairing, dual engine Centaur upper stage, and four strap-on solid boosters.
Atlas V 551 American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and five strap-on solid boosters. Payloads: 20,520 kg (45,238 lb) to sun synchronous orbit; 8,700 kg (19,180 lb) to geosynchronous transfer orbit.
Atlas V 552 American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, dual engine Centaur upper stage, and five strap-on solid boosters.
Atlas V Growth Phase 1 American orbital launch vehicle. Proposed growth variant of the heavy-lift version of the Atlas V launch vehicle with three parallel 3.8-m-diameter Common Core Boosters (CCB), a 5-m-diameter wide body version of the Centaur upper stage with a single-engine, and a 5 m diameter payload fairing. Another variant would use a stretched wide body version of the Centaur upper stage with 2 or 4 motors, allowing payloads of up to 13,500 kg to be lofted to earth escape velocity.
Atlas V Growth Phase 2 American orbital launch vehicle. Proposed growth variant of the heavy-lift version of the Atlas V launch vehicle with three parallel 5-m-diameter wide-body Common Core Boosters (CCB), each with 1 or 2 RD-180 engines; a 5-m-diameter new LOx/LH2 stage with 2 or 4 engines with a total thrust of 180,000 kgf; and a 5 m diameter payload fairing.
Atlas V Growth Phase 3 American orbital launch vehicle. Proposed Saturn-V class variant of the heavy-lift version of the Atlas V launch vehicle with five parallel 5-m-diameter wide-body Common Core Boosters (CCB), each with 1 or 2 RD-180 engines; a 7-m-diameter new LOx/LH2 stage; and a 7 m diameter payload fairing.
Atlas V Heavy American orbital launch vehicle. Heavy-lift version of the Atlas V launch vehicle system with three parallel 3.8-m-diameter Common Core Boosters (CCB), and a stretched version of the Centaur upper stage (CIII), which could be configured as a single-engine Centaur (SEC) or a dual engine Centaur (DEC), and a 5 m diameter payload fairing. As of 2004 no work had been authorized to build Atlas V Heavy facilities at either Cape Canaveral or Vandenberg AFB.
Family: orbital launch vehicle. Country: USA. Spacecraft: MMS, Astro-200, BCP-5000, Intruder, Juno, LRO, MAVEN, PAN, Quasar, RBSP, Topaz, Trumpet Follow-on, Eurostar 2000, FS-1300, HS 601, Mercury ELINT, MicroSat-100, Spacebus 3000, AS 2100, LM 700, DMSP Block 5D-3, HS 702, FalconSat, SA-200, SDS-3, X-37, NOSS-3, Cubesat, Eurostar 3000, Mars Reconnaissance Orbiter, New Horizons, Jumpseat-2, Midstar, Orbital Express Astro, RS-300, STPSat, SSTL-150, SDO, GPS Block 2F, MSL. Agency: Martin. Bibliography: 2, 278, 416, 42, 552, 554, 61, 8174.
2005 March 11 - . 21:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 431.
Inmarsat-4 F1 - . Payload: Inmarsat 4A / Eurostar 3000GM. Mass: 5,959 kg (13,137 lb). Nation: International. Agency: Inmarsat. Manufacturer: EADS Astrium. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 3000. USAF Sat Cat: 28628 . COSPAR: 2005-009A. Apogee: 36,011 km (22,376 mi). Perigee: 35,562 km (22,097 mi). Inclination: 3.00 deg. Period: 1,436.10 min.
Heaviest single payload to geosynchronous transfer orbit to that date. Delayed from October 2004, February 27, March 10, 2005. The satellite was to provide L-band mobile communications and wideband data transmission for Inmarsat's global network. As of 2007 Mar 11 located at 63.82E drifting at 0.000E degrees per day.
2006 January 19 - . 19:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
New Horizons - . Mass: 478 kg (1,053 lb). Nation: USA. Agency: JPL, NASA. Manufacturer: APL. Class: Outer planets. Type: Outer planets probe. Spacecraft: New Horizons. USAF Sat Cat: 28928 . COSPAR: 2006-001A.
Last robotic mission to an unexplored planet in our solar system. New Horizons was due to receive a gravity boost from Jupiter in February 2007, then fly by Pluto in 2015. During launch toward Jupiter it reached a higher velocity than any manmade object, and was the first to be boosted directly to solar escape velocity. The trajectory had a perihelion of 0.98 AU, an inclination of 0.87 deg and an eccentricity of 1.03. After the Jupiter encounter it was to have a perihelion of 2.2 AU, an inclination of 2.3 deg and an eccentricity of 1.40. At encounter with Pluto on July 14, 2015, the spacecraft would be 1.1 AU above the ecliptic plane and 32.9 AU from the Sun, leaving the solar system toward the star Xi Sgr.
2007 October 11 - . 00:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 421.
USA 195 - . Payload: WGS 1. Mass: 5,987 kg (13,199 lb). Nation: USA. Agency: Martin. Class: Communications. Type: Military communications satellite. Spacecraft: HS 702. USAF Sat Cat: 32258 . COSPAR: 2007-046A. Apogee: 39,016 km (24,243 mi). Perigee: 32,586 km (20,247 mi). Inclination: 0.20 deg. Period: 1,436.80 min. First USAF Wideband Global Satcom satellite, designed to replace the DSCS series, was placed by the Atlas booster in an initial 477 km x 66,847 km x 20.1 deg geosynchronous transfer orbit. The satellite carried X-band and Ka-band communications payloads..
2008 April 14 - . 20:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 421.
ICO G1 - . Mass: 6,600 kg (14,500 lb). Nation: USA. Agency: Martin. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 32763 . COSPAR: 2008-016A. Apogee: 35,800 km (22,200 mi). Perigee: 35,774 km (22,228 mi). Inclination: 6.00 deg. Period: 1,436.10 min. The satellite was to provide mobile communications services for ICO Global Communications, a successor company to Teledesic..
2009 April 4 - . 08:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 421.
USA 204 - . Payload: WGS 2. Mass: 5,987 kg (13,199 lb). Nation: USA. Agency: Martin. Class: Communications. Type: Military communications satellite. Spacecraft: HS 702. USAF Sat Cat: 34713 . COSPAR: 2009-017A. Apogee: 35,452 km (22,028 mi). Perigee: 35,397 km (21,994 mi). Inclination: 0.10 deg. Period: 1,417.60 min. Wideband Global Satcom; provided communications for the US Dept. of Defense Central Command (CENTCOM)..
2009 November 23 - . 06:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 431.
Intelsat IS-14 - . Mass: 5,663 kg (12,484 lb). Nation: USA. Agency: Martin. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 36097 . COSPAR: 2009-064A. Apogee: 35,800 km (22,200 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Communications satellite to replace IS-1R at 24 deg W over the Atlantic. The Centaur AV-024 upper stage maneuvered and then released the satellite into a 6157 km x 39094 km x 22.5 deg geosynchronous transfer orbit at 08:53 GMT. IS-14 then used its own propulsion to reach its operational orbit. Mass 2517 kg unfuelled.
2010 April 22 - . 23:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 501.
USA 212 - . Payload: X-37B OTV 1. Mass: 5,000 kg (11,000 lb). Nation: USA. Agency: Martin. Class: Manned. Type: Manned spaceplane. Spacecraft: X-37. Duration: 224.39 days. USAF Sat Cat: 36514 . COSPAR: 2010-015A. Reusable unmanned military orbital spaceplane. Landed successfully at Vandenberg at 09:16 GMT on 3 December..
2010 August 14 - . 11:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 531.
USA 214 - . Payload: AEHF 1 / A2100M. Mass: 6,168 kg (13,598 lb). Nation: USA. Agency: Martin. Class: Communications. Type: Military communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 36868 . COSPAR: 2010-039A. Apogee: 35,807 km (22,249 mi). Perigee: 35,774 km (22,228 mi). Inclination: 4.37 deg. Period: 1,436.31 min.
First USAF Advanced EHF communications satellite. Placed in an initial 221 x 50179 km x 22.2 deg geosynchronous transfer orbit by the Atlas Centaur upper stage. However the satellite's main BT-4 engine failed, meaning the secondary hydrazine thrusters were used to much more satellite raise the spacecraft to geosynchronous orbit.
2011 March 5 - . 22:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 501.
USA 226 - . Payload: OTV-2 F1. Mass: 5,000 kg (11,000 lb). Nation: USA. Class: Manned. Type: Manned spaceplane. Spacecraft: X-37. USAF Sat Cat: 37375 . COSPAR: 2011-010A.
Second unmanned Orbital Test Vehicle X-37B reusable spaceplane. Possibly placed in a 400 x 420 km x 40 deg orbit like that used by OTV-1; mission expected to last 9 months with automatic landing at Vandenberg Air Force Base. The Centaur AV-026 upper stage was deorbited over the Indian Ocean on the first orbit.
2011 August 5 - . 16:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
Juno - . Mass: 3,625 kg (7,991 lb). Nation: USA. Class: Outer planets. Type: Outer planets probe. Spacecraft: Juno. USAF Sat Cat: 37773 . COSPAR: 2011-040A.
Jupiter Near-polar Orbiter, accelerated by the AV-029 Centaur to a hyperbolic escape orbit at 17:15 GMT into a 1.0 AU x 2.26 AU x 0.1 deg solar orbit. A 500-km flyby of Earth on 9 October 2013 pumped this orbit towards Jupiter. It is planned to enter Jovian orbit in July 2016, and be commaned to bun up in Jupiter's atmosphere in October 2017. Payloads included magnetometers, plasma and particle instruments, UV auroral imagers and spectrometers, and the JunoCam imager. The probe has a massmof 1593 kg and carries a further 2032 kg of propellant. Its three large solar arrays span around 22 meters; it is the first spacecraft to fly to the outer solar system without radioisotope power sources.
2012 February 24 - . 22:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
MUOS 1 - . Payload: A2100M. Mass: 6,740 kg (14,850 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 38093 . COSPAR: 2012-009A. Apogee: 35,802 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 5.00 deg. Period: 1,436.10 min. US Navy's first Mobile User Objective System launch, providing military UHF communications services. Launch mass 6740 kg; dry mass 3812 kg..
2012 May 4 - . 18:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 531.
USA 235 - . Payload: AEHF 2 / A2100M. Mass: 6,168 kg (13,598 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 38254 . COSPAR: 2012-019A. Apogee: 46,814 km (29,088 mi). Perigee: 25,572 km (15,889 mi). Inclination: 4.70 deg. Period: 1,456.90 min. US Air Force Advanced EHF communications satellite, providing strategic military EHF communications. First reflight of the bus with the Japanese IHI BT-4 apogee thruster (which had failed on the prior mission) and an electric propulsion system..
2012 December 11 - . 18:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 501.
USA 240 - . Payload: X-37B OTV-3. Mass: 5,400 kg (11,900 lb). Nation: USA. Class: Manned. Type: Manned spaceplane. Spacecraft: X-37. USAF Sat Cat: 39025 . COSPAR: 2012-071A. Apogee: 360 km (220 mi). Perigee: 343 km (213 mi). Inclination: 43.50 deg. X-37B flight vehicle 1 completed its second flight on Oct 17 2014, landing at Vandenberg AFB at 16:24 GMT after 674.9 days in space..
2013 July 19 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
MUOS 2 - . Payload: A2100M. Mass: 6,700 kg (14,700 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 39206 . COSPAR: 2013-036A. Apogee: 35,822 km (22,258 mi). Perigee: 7,847 km (4,875 mi). Inclination: 14.60 deg. Period: 786.00 min. Mobile User Objective System; provides UHF communications links for the US Navy. 3800 kg dry mass..
2013 September 18 - . 08:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 531.
USA 246 - . Payload: AEHF 3 / A2100M. Mass: 6,168 kg (13,598 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 39256 . COSPAR: 2013-050A. Apogee: 35,816 km (22,254 mi). Perigee: 35,756 km (22,217 mi). Inclination: 1.40 deg. Period: 1,436.07 min. Third Advanced EHF communications satellite for the US Air Force. The satellite has a Japanese IHI BT-4 bipropellant thruster and an Aerojet electric propulsion system..
2014 April 10 - . 17:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 541.
USA 250 - . Payload: NROL-67. Mass: 3,600 kg (7,900 lb). Nation: USA. Class: Surveillance. Type: SIGINT. Spacecraft: Mercury ELINT. USAF Sat Cat: 39652 . COSPAR: 2014-020A. Apogee: 35,790 km (22,230 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.00 min. It appeared likely that the Centaur stage made three burns to deploy the USA 250 payload in geosynchronous orbit. The payload was suspected to be a large NRO signals intelligence satellite..
2015 January 21 - . 01:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
MUOS 3 - . Payload: A2100M. Mass: 6,740 kg (14,850 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 40374 . COSPAR: 2015-002A. Apogee: 35,788 km (22,237 mi). Perigee: 5,592 km (3,474 mi). Inclination: 16.70 deg. US Navy communications satellite..
2015 March 13 - . 02:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 421.
MMS 1 - . Mass: 1,400 kg (3,000 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: MMS. USAF Sat Cat: 40482 . COSPAR: 2015-011A. Apogee: 70,094 km (43,554 mi). Perigee: 1,371 km (851 mi). Inclination: 28.86 deg. Period: 1,433.33 min.
MMS 2 - . Mass: 1,400 kg (3,000 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: MMS. USAF Sat Cat: 40483 . COSPAR: 2015-011B. Apogee: 70,110 km (43,560 mi). Perigee: 1,356 km (842 mi). Inclination: 28.84 deg. Period: 1,433.36 min.
MMS 3 - . Mass: 1,400 kg (3,000 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: MMS. USAF Sat Cat: 40484 . COSPAR: 2015-011C. Apogee: 70,228 km (43,637 mi). Perigee: 1,238 km (769 mi). Inclination: 28.84 deg. Period: 1,433.35 min.
MMS 4 - . Mass: 1,400 kg (3,000 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: MMS. USAF Sat Cat: 40485 . COSPAR: 2015-011D. Apogee: 70,094 km (43,554 mi). Perigee: 1,372 km (852 mi). Inclination: 28.85 deg. Period: 1,433.35 min.
2015 May 20 - . 15:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Atlas V. Launch Vehicle: Atlas V 501.
USA 261 - . Payload: X-37B OTV-4. Mass: 5,400 kg (11,900 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: X-37. USAF Sat Cat: 40651 . COSPAR: 2015-025A. Apogee: 332 km (206 mi). Perigee: 309 km (192 mi). Inclination: 38.00 deg.
Classified mission of the winged, recoverable X-37B Orbital Test Vehicle. Publicly stated to be carrying an AFRL ion engine test and a NASA materials exposure experiment. After releasing the X-37B the Centaur AV-054 rocket stage reignited to reach a 355 km x 700 km x 55-57 deg orbit and at around 17:00 GMT released a set of 9 cubesats. Centaur then made a third burn to deorbit itself over the Indian Ocean.
USS Langley - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 40652 . COSPAR: 2015-025B. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. 3U cubesat from the US Naval Academy (UNSA) testing out an IP link to the satellite's computer which hosts a Unix webserver..
PSat-1 - . Payload: PARKINSONSAT (PSAT). Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: Cubesat. USAF Sat Cat: 40654 . COSPAR: 2015-025D. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. 1.5U cubesat from the US Naval Academy (UNSA) hosting the USN SCP/ODTML buoy communications payload and an amateur radio payload..
BRICSat-P - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 40655 . COSPAR: 2015-025E. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. 1.5U cubesat from the US Naval Academy (UNSA), built in collaboration with George Washington University, testing an electric micropropulsion system..
GEARRS-2 - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: Cubesat. USAF Sat Cat: 40657 . COSPAR: 2015-025G. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. Second 3U Globalstar Risk Reduction satellite from startup Near Space Launch (a Taylor University spinoff), with AFRL, to demo cubesat data relay via the Globalstar system..
Aerocube-8a - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 40659 . COSPAR: 2015-025J. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. Aerospace Corporation 1.5U cubesat testing an ion-electrospray propulsion system..
Aerocube-8b - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 40660 . COSPAR: 2015-025K. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. Aerospace Corporation 1.5U cubesat testing carbon nanotube materials..
O/C-1 - . Payload: OPTICUBE 01. Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Surveillance. Type: Radar calibration target. Spacecraft: Cubesat. USAF Sat Cat: 40653 . COSPAR: 2015-025C. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. 3U Optical Cubesat sponsored by NRO and built by Cal Poly as targets for space surveillance calibration..
O/C-2 - . Payload: OPTICUBE 02. Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Surveillance. Type: Radar calibration target. Spacecraft: Cubesat. USAF Sat Cat: 40656 . COSPAR: 2015-025F. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. 3U Optical Cubesat sponsored by NRO and built by Cal Poly as targets for space surveillance calibration..
O/C-3 - . Payload: OPTICUBE 03. Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Surveillance. Type: Radar calibration target. Spacecraft: Cubesat. USAF Sat Cat: 40658 . COSPAR: 2015-025H. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg. 3U Optical Cubesat sponsored by NRO and built by Cal Poly as targets for space surveillance calibration..
LightSail-A - . Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 40661 . COSPAR: 2015-025L. Apogee: 700 km (430 mi). Perigee: 350 km (210 mi). Inclination: 55.00 deg.
Planetary Society's 3U cubesat with a solar sail deployment experiment. The cubesat went into safe mode a few days after launch but rebooted on May 30. Its solar panels were deployed on June 3 and the solar sail was unfurled on June 7 at 19:47 GMT. The satellite reentered on June 14.
2015 September 2 - . 10:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
MUOS 4 - . Payload: A2100M. Mass: 6,700 kg (14,700 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 40887 . COSPAR: 2015-044A. Apogee: 35,786 km (22,236 mi). Perigee: 3,802 km (2,362 mi). Inclination: 19.10 deg.
MUOS (Multiple User Objective System), US Navy UHF-band communications satellite,was launched into a geotransfer orbit. The Centaur upper stage made three burns, to 167 km x 630 km, 194 km x 34,447 km, and 3,802 km x 35,786 km orbits, before releasing the satellite. The satellite used its BT-4 liquid engine to raise its orbit to geosynchronous altitue.
2016 June 24 - . 14:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
MUOS 5 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 41622 . COSPAR: 2016-041A. Apogee: 35,670 km (22,160 mi). Perigee: 3,880 km (2,410 mi). Inclination: 19.10 deg.
US Navy Multiple User Object System's Space Vehicle 3 was launched as MUOS 5. The Atlas 5 rocket made three burns to 167 x 659 km x 28 deg, 191 x 32930 x 26 deg and then 3802 x 35786 km x 19 deg, and deployed MUOS which will use its Japanese BT-4 thruster to reach GEO over the Indian Ocean as an in-orbit spare for the system, whose 4 operational satellites were over the Atlantic, the Pacific, the Indian Ocean and the Americas. MUOS 5 had problems with its propulsion system and was parked in a 15242 x 35703 km x 9.8 deg intermediate geotransfer orbit.
2016 July 28 - . 12:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 541.
USA 269 - . Payload: QUASAR. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: Quasar. USAF Sat Cat: 41724 . COSPAR: 2016-047A. Apogee: 35,996 km (22,366 mi). Perigee: 35,576 km (22,105 mi). Inclination: 5.00 deg.
NROL-61 mission was launched on Atlas AV-065 into a geostationary transfer orbit. The satellite was thought to be an NRO (National Reconnaissance Office) data relay communications satellite in the QUASAR series, although there was a chance that it instead had a signals intelligence payload. The payload made orbital maneuvers to raise its perigee, and hobbyists tracked the satellite in geostationary orbit at 92 deg E, over the Indian Ocean.
2016 November 19 - . 23:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 541.
GOES 16 - . Payload: GOES R. Nation: USA. Class: Earth. Type: Weather satellite. Spacecraft: AS 2100. USAF Sat Cat: 41866 . COSPAR: 2016-071A. Apogee: 35,269 km (21,915 mi). Perigee: 8,157 km (5,068 mi). Inclination: 10.60 deg.
Geostationary Operational Environmental Satellite R, which became GOES 16 when operational, was the first in a new series of Lockheed-Martin-built GOES weather satellites for NOAA. The satellite mass was 2857 kg dry, 5192 kg when full of propellant. GOES-R carried the Advanced Baseline Imager, a new camera similar in capabilities to those on the Japanese Himawari 8/9 series. Also aboard were the Geostationary Lightning Mapper, a Space Environment suite, a Solar Ultraviolet Imager, an EUV/X-Ray Irradiance Sensor, a Search and Rescue comm payload, and comm payloads to relay weather data.
2016 December 18 - . 19:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 431.
Echostar 19 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 41893 . COSPAR: 2016-079A. Apogee: 65,110 km (40,450 mi). Perigee: 164 km (101 mi). Inclination: 25.60 deg.
2017 October 15 - . 07:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 421.
USA 279 - . Payload: QUASAR 20?. Nation: USA. USAF Sat Cat: 42949 . COSPAR: 2017-066A. See Quasar 21 (SDS-4 2, USA 279, NROL 52) ?. ..
2018 March 1 - . 22:02 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 541.
GOES 17 - . Payload: GOES S. Nation: USA. USAF Sat Cat: 43226 . COSPAR: 2018-022A. Apogee: 35,800 km (22,200 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.0300 deg. Period: 1,436.07 min. See GOES 17 (GOES S). ..
2018 April 14 - . 23:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
USA 283 - . Payload: CBAS SATCOM. Nation: USA. USAF Sat Cat: 43339 . COSPAR: 2018-036A. See CBAS (USA 283, AFSPC 11). ..
USA 284 - . Payload: EAGLE 1. Nation: USA. USAF Sat Cat: 43340 . COSPAR: 2018-036B. See EAGLE (USA 284). ..
USA 285 - . Payload: MYCROFT. Nation: USA. USAF Sat Cat: 43445 . COSPAR: 2018-036E. See Mycroft (USA 285 ?). ..
USA 286 - . Payload: ESPASat 2. Nation: USA. USAF Sat Cat: 43446 . COSPAR: 2018-036F. See USA 286. ..
USA 287 - . Payload: ESPASat 3. Nation: USA. USAF Sat Cat: 43465 . COSPAR: 2018-036G. See USA 287. ..
2018 October 17 - . 04:14 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 551.
USA 288 - . Payload: AEHF SV-4; AEHF 4 (USA 288). Nation: USA. USAF Sat Cat: 43651 . COSPAR: 2018-079A. Apogee: 36,426 km (22,634 mi). Perigee: 33,735 km (20,961 mi). Inclination: 5.12 deg. Period: 1,400.18 min. See AEHF 4 (USA 288). ..

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