The launch of an Antares 110 rocket
|Function||Medium expendable launch system|
|Manufacturer||Orbital ATK (main)
Yuzhnoye Design Bureau (sub)
|Country of origin||United States|
|Project cost||$472 million until 2012|
|Height||110/120: 40.5 m (133 ft)
130: 41.9 m (137 ft)
|Diameter||3.9 m (13 ft)|
|Mass||282,000 kg (622,000 lb)—296,000 kg (653,000 lb)|
|Stages||2 to 3|
|Payload to LEO||6,120 kg (13,490 lb)|
|Launch sites||MARS LP-0A|
|Total launches||5 (110: 2, 120: 2, 130: 1)|
|Successes||4 (110: 2, 120: 2, 130: 0)|
|Failures||1 (130: 1)|
|First flight||110: April 21, 2013
120: January 9, 2014
130: October 28, 2014
|Last flight||110: September 18, 2013
120: July 13, 2014
130: October 28, 2014
|First stage (Antares 100-series)|
|Empty mass||18,700 kg (41,200 lb)|
|Gross mass||260,700 kg (574,700 lb)|
|Thrust||3,265 kN (734,000 lbf)|
|Specific impulse||Sea level: 297s
|Burn time||235 seconds|
|First stage (Antares 200-series)|
|Thrust||3,700 kN (830,000 lbf)|
|Second stage - Castor 30A/B/XL|
|Gross mass||30A: 14,035 kg (30,942 lb)
30B: 13,970 kg (30,800 lb)
30XL:26,300 kg (58,000 lb)
|Propellant mass||30A: 12,815 kg (28,252 lb)
30B: 12,887 kg (28,411 lb)
|Thrust||30A: 259 kN (58,200 lbf)
30B: 293.4 kN (65,960 lbf)
Antares (//), known during early development as Taurus II, is an expendable launch system developed by Orbital Sciences Corporation (now Orbital ATK) to launch the Cygnus spacecraft to the International Space Station as part of NASA's COTS and CRS programs. Able to launch payloads heavier than 5,000 kg (11,000 lb) into low-Earth orbit, Antares is the largest rocket operated by Orbital ATK. Antares launches from the Mid-Atlantic Regional Spaceport and made its inaugural flight on April 21, 2013.
NASA awarded Orbital a Commercial Orbital Transportation Services (COTS) Space Act Agreement (SAA) in 2008 to demonstrate delivery of cargo to the International Space Station. For these COTS missions Orbital intends to use Antares to launch its Cygnus spacecraft. In addition, Antares will compete for small-to-medium missions. Originally designated the Taurus II, Orbital Sciences renamed the vehicle Antares, after the star of the same name, on December 12, 2011.
- 1 Development
- 2 Design
- 3 Configurations and numbering
- 4 Launch history
- 5 List of missions
- 6 Launch sequence
- 7 See also
- 8 References
- 9 External links
The NASA COTS award was for US$171 million and Orbital Sciences expected to invest an additional $150 million, split between $130 million for the booster and $20 million for the spacecraft. A Commercial Resupply Service contract of $1.9 billion for 8 flights was awarded in 2008. As of April 2012, development costs were estimated at $472 million.
On June 10, 2008 it was announced that the Mid-Atlantic Regional Spaceport, formerly part of the Wallops Flight Facility, in Virginia, would be the primary launch site for the rocket. Launch pad 0A (LP-0A), previously used for the failed Conestoga rocket, would be modified to handle Antares. Wallops allows launches which reach the International Space Station's orbit as effectively as those from Cape Canaveral, Florida, while being less crowded. The first Antares flight launched a Cygnus mass simulator.
On December 10, 2009 Alliant Techsystems Inc. (ATK) test fired their Castor 30 motor for use as the second stage of the Antares rocket. In March 2010 Orbital Sciences and Aerojet completed test firings of the NK-33 engines. On February 22, 2013 a hot fire test was successfully performed, the entire first stage being erected on the pad and held down while the engines fired for 29 seconds.
The first stage of Antares burns RP-1 (kerosene) and liquid oxygen (LOX). As Orbital had little experience with large liquid stages and LOX propellant, the first stage core was designed and is manufactured in Ukraine by Yuzhnoye SDO and includes propellant tanks, pressurization tanks, valves, sensors, feed lines, tubing, wiring and other associated hardware. Like the Zenit—also manufactured by Yuzhnoye—the Antares vehicle has a diameter of 3.9 m (150 in) with a matching 3.9 m payload fairing.
The Antares 100-series first stage was powered by two Aerojet AJ26 engines. These began as Kuznetsov NK-33 engines built in the Soviet Union in the late 1960s and early 1970s, 43 of which were purchased by Aerojet in the 1990s. 20 of these were refurbished into AJ26 engines for Antares. Modifications included equipping the engines for gimballing, adding US electronics, and qualifying the engines to fire for twice as long as designed and to operate at 108% of their original thrust. Together they produced 3,265 kilonewtons (734,000 lbf) of thrust at sea level and 3,630 kN (816,100 lbf) in vacuum.
Following the catastrophic failure of an AJ26 during testing at Stennis Space Center in May 2014 and the Orb-3 launch failure in October 2014, likely caused by an engine turbopump, the Antares 100-series was retired.
Due to concerns over corrosion, aging, and the limited supply of AJ26 engines, Orbital had already selected new first stage engines prior to the October 2014 Antares failure. The new engines were planned to debut in 2017 and allow Orbital to bid on a second major long-term contract for cargo resupply of the ISS. Less than one month after the loss of the Antares rocket in October 2014, Orbital announced that it would no longer fly Antares with AJ26 engines, and the first flight of Antares with new first stage engines would be moved up to 2016. As of March 2016[update], the first flight of the re-engined Antares 230 configuration is anticipated for June 24, 2016, carrying the Cygnus CRS OA-5 cargo to the ISS.
In late October 2014, the Russian news agency TASS reported that Orbital Sciences had preliminarily selected the Energomash RD-193 to power the second version of the Antares first stage, and in December 2014 Orbital Sciences announced that the RD-181—a modified version of the RD-191—would replace the AJ26 on the Antares 200-series. The first engines are scheduled to arrive from Energomash in summer 2015, where an on-pad 29-second static fire test is projected to occur in fall 2015.
The Antares 200 and 300 first stages will be powered by two RD-181 engines, which will provide 440 kilonewtons (100,000 lbf) more thrust than the dual AJ26 engines used on the Antares 100. Orbital plans to adapt the existing core stage to accommodate the increased performance in the 200 Series, allowing Antares to deliver up to 7,000 kilograms (15,000 lb) to low Earth orbit. The excess performance of the Antares 200-series will allow Orbital to fulfill its ISS resupply contract in only four additional flights, rather than the five that would have been required with the Antares 100-series.
While the 200 series uses the RD-181 by adapting the originally ordered 100 Series stages (KB Yuzhnoye/Yuzhmash, Zenit derived), it requires under throttling the RD-181 engines, which reduces performance. Thus, the 300 series will use a new first stage core designed for the full thrust and performance of the RD-181 engine.
The second stage is an Orbital ATK Castor 30-series solid-fuel rocket, developed as a derivative of the Castor 120 solid motor used as Minotaur-C's first stage. The first two flights of Antares used a Castor 30A, which was replaced by the enhanced Castor 30B for subsequent flights. The Castor 30B produces 293.4 kN (65,960 lbf) average and 395.7 kN (88,960 lbf) maximum thrust, and uses electromechanical thrust vector control. For increased performance, the larger Castor 30XL is available and will be used on ISS resupply flights to allow Antares to carry the Enhanced Cygnus.
Antares offers two optional third stages, the Bi-Propellant Third Stage (BTS) and a Star 48-based third stage. BTS is derived from Orbital Sciences' GEOStar spacecraft bus and uses nitrogen tetroxide and hydrazine for propellant; it is intended to precisely place payloads into their final orbits. The Star 48-based stage uses a Star 48BV solid rocket motor and would be used for higher energy orbits.
The 3.9-meter (13 ft) diameter, 9.9-meter (32 ft) high fairing is manufactured by Applied Aerospace Structures Corporation of Stockton, California, which also builds other composite structures for the vehicle, including the fairing adaptor, stage 2 motor adaptor, stage 2 interstage, payload adaptor, and avionics cylinder.
Configurations and numbering
The first two test flights used a Castor 30A second stage. All subsequent flights will use either a Castor 30B or Castor 30XL. The rocket's configuration is indicated by a three-digit number, the first number representing the first stage, the second the type of second stage, and the third the type of third stage.
|Number||First digit||Second digit||Third digit|
|(First stage)||(Second stage)||(Third stage)|
|0||N/A||N/A||No third stage|
|1||Block 1 first stage
(2 × AJ26-62)
N/A after Block 1
(3 × IHI BT-4)
|2||Block 1 first stage (Adapted to RD-181)
(2 × RD-181)
|Castor 30B||Star 48BV|
|3||Block 2 first stage
Originally scheduled for 2012, the first Antares launch, designated A-ONE was conducted on April 21, 2013, carrying the Cygnus Mass Simulator (a boilerplate Cygnus spacecraft) and four CubeSats contracted by Spaceflight Incorporated: Dove 1 for Cosmogia Incorporated (now Planet Labs) and three PhoneSat satellites – Alexander, Graham and Bell for NASA.
Prior to the launch, a 27-second test firing of the rocket's AJ26 engines was conducted successfully on February 22, 2013, following an attempt on February 13 which was abandoned before ignition.
A-ONE used the Antares 110 configuration, with a Castor 30A second stage and no third stage. The launch took place from Pad 0A of the Mid-Atlantic Regional Spaceport on Wallops Island, Virginia. LP-0A was a former Conestoga launch complex which had only been used once before, in 1995, for the Conestoga's only orbital launch attempt. Antares became the largest — and first — liquid-fuelled rocket to fly from Wallops Island, as well as the largest rocket launched by Orbital Sciences.
The first attempt to launch the rocket, on April 17, 2013, was scrubbed after an umbilical detached from the rocket's second stage, and a second attempt on April 20 was scrubbed due to high altitude winds. At the third attempt on April 21, the rocket lifted off at the beginning of its launch window. The launch window for all three attempts was three hours beginning at 21:00 UTC (17:00 EDT), shortening to two hours at the start of the terminal count, and ten minutes later[clarification needed] in the count.
October 2014 incident
On October 28, 2014, the first stage of an Antares rocket carrying a Cygnus cargo spacecraft on the Orb-3 resupply mission failed catastrophically six seconds after liftoff from Mid-Atlantic Regional Spaceport at Wallops Flight Facility, Virginia. The flight termination system was activated before the rocket hit the ground, and an explosion and fire destroyed the vehicle and cargo. There were no injuries. Orbital Sciences reported that Launch Pad 0A "escaped significant damage," though initial estimates for repairs were in the $20 million range. Orbital Sciences formed an anomaly investigation board shortly after the launch failure to investigate the cause of the incident.
Following the failure, Orbital sought to purchase launch services for its Cygnus spacecraft in order to satisfy its cargo contract with NASA, and on December 9, 2014, Orbital announced that at least one, and possibly two, Cygnus flights would be launched on Atlas V rockets from Cape Canaveral Air Force Station.[full citation needed] As it happened, Cygnus OA-4 and OA-6 were launched with an Atlas V and the Antares 230 is scheduled to take over Cygnus OA-5 and further missions.
List of missions
|#||Launch date, Time (UTC)||Mission||Payload||Cygnus version||Rocket version||Ref.||Outcome|
|1||April 21, 2013. 21:00||Antares A-ONE||Standard (mass simulator)||Antares 110||||Success|
|Antares test flight, using a Castor 30A second stage and no third stage.|
|2||September 18, 2013. 14:58||Orb-D1||G. David Low Cygnus||Standard||Antares 110||||Success|
|Orbital Sciences COTS demonstration flight. First Cygnus mission, first mission to rendezvous with ISS, first mission to berth with ISS, second launch of Antares. The rendezvous between the new Cygnus cargo freighter and the International Space Station was delayed due to a computer data link problem, but the issue was resolved and berthing followed shortly thereafter.|
|3||January 9, 2014. 18:07||CRS Orb-1||C. Gordon Fullerton Cygnus||Standard||Antares 120||||Success|
|First Commercial Resupply Service (CRS) mission for Cygnus, and first Antares launch using the Castor 30B upper stage.|
|4||July 13, 2014. 16:52||CRS Orb-2||Janice Voss Cygnus||Standard||Antares 120||||Success|
|Spacecraft carried 1,664 kg (3,668 lb) of supplies for the ISS, including research equipment, crew provisions, hardware, and science experiments.|
|5||October 28, 2014. 22:22||CRS Orb-3||Deke Slayton Cygnus||Standard||Antares 130||||Failure|
|First Antares launch to use Castor 30XL upper stage. In addition to supplies for the International Space Station, payload included a Planetary Resources Arkyd-3 satellite and a NASA JPL/UT-Austin CubeSat mission named RACE. The Antares rocket encountered an anomaly seconds into the mission leading to the explosion of the rocket and loss of the payload.|
|6||August 2016 TBD||CRS OA-5||Alan G. Poindexter Cygnus||Enhanced||Antares 230||||Planned|
|Planned first launch of Enhanced Cygnus on Orbital's Antares 230|
|7||December 30, 2016
||CRS OA-7||Enhanced||Antares 230||||Planned|
|8||June 12, 2017
||CRS OA-8E||Enhanced||Antares 230||||Planned|
||CRS OA-9E||Enhanced||Antares 230||||Planned|
||CRS OA-10E||Enhanced||Antares 230||||Planned|
|T- 03:50:00||Launch management call to stations||N/A|
|T- 03:05:00||Poll to initiate liquid oxygen loading system chilldown||N/A|
|T- 01:30:00||Poll for readiness to initiate propellant loading||N/A|
|T- 00:15:00||Cygnus/payload switched to internal power||N/A|
|T- 00:12:00||Poll for final countdown and MES medium flow chilldown||N/A|
|T- 00:11:00||Transporter-Erector-Launcher (TEL) armed for rapid retract||N/A|
|T- 00:05:00||Antares avionics switched to internal power||N/A|
|T- 00:03:00||Auto-sequence start (terminal count)||N/A|
|T- 00:02:00||Pressurize propellant tanks||N/A|
|T- 00:00:00||Main engine ignition||N/A|
|T+ 00:03:55||Main engine cut-off (MECO)||102 km (63 mi)|
|T+ 00:04:01||Stage one separation||108 km (67 mi)|
|T+ 00:05:31||Fairing separation||168 km (104 mi)|
|T+ 00:05:36||Interstage separation||170 km (106 mi)|
|T+ 00:05:40||Stage two ignition||171 km (106 mi)|
|T+ 00:07:57||Stage two burnout||202 km (126 mi)|
|T+ 00:09:57||Payload separation||201 km (125 mi)|
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