.jpg) Pegasus XL launching CYGNSS in 2016 | |
| Function | Small-lift launch vehicle |
|---|---|
| Manufacturer | Northrop Grumman |
| Country of origin | United States |
| Cost per launch | US$40 million[1] |
| Size | |
| Height | 16.9 m (55 ft 5 in) XL: 17.6 m (57 ft 9 in) |
| Diameter | 1.27 m (4 ft 2 in) |
| Mass | 18,500 kg (40,800 lb) XL: 23,130 kg (50,990 lb) |
| Stages | 3 |
| Capacity | |
| Payload toLEO | |
| Altitude | 200 km (120 mi) |
| Orbital inclination | 28.5° |
| Mass | 450 kg (990 lb) |
| Associated rockets | |
| Derivative work | Minotaur-C |
| Comparable | Electron,Vector-H,Falcon 1,LauncherOne |
| Launch history | |
| Status | Active |
| Launch sites | |
| Total launches | 45 |
| Success(es) | 40 |
| Failure(s) | 3 |
| Partial failure(s) | 2 |
| First flight | 5 April 1990 (Pegsat /NavySat) |
| Last flight | 13 June 2021 (TacRL-2 / Odyssey) |
| First stage –Orion 50S | |
| Maximum thrust | 500 kN (110,000 lbf) |
| Burn time | 75.3 seconds |
| Propellant | HTPB /Al |
| First stage (Pegasus XL) –Orion 50SXL | |
| Height | 10.27 m (33 ft 8 in) |
| Diameter | 1.28 m (4 ft 2 in) |
| Empty mass | 1,369 kg (3,018 lb) |
| Gross mass | 16,383 kg (36,118 lb) |
| Propellant mass | 15,014 kg (33,100 lb) |
| Maximum thrust | 726 kN (163,000 lbf) |
| Specific impulse | 295 s (2.89 km/s) |
| Burn time | 68.6 seconds |
| Propellant | HTPB /Al |
| Second stage –Orion 50 | |
| Maximum thrust | 114.6 kN (25,800 lbf) |
| Burn time | 75.6 seconds |
| Propellant | HTPB /Al |
| Second stage (Pegasus XL) –Orion 50XL | |
| Height | 3.07 m (10 ft 1 in) |
| Diameter | 1.28 m (4 ft 2 in) |
| Empty mass | 391 kg (862 lb) |
| Gross mass | 4,306 kg (9,493 lb) |
| Propellant mass | 3,915 kg (8,631 lb) |
| Maximum thrust | 158 kN (36,000 lbf) |
| Specific impulse | 289 s (2.83 km/s) |
| Burn time | 71 seconds |
| Propellant | HTPB /Al |
| Third stage –Orion 38 | |
| Height | 1.34 m (4 ft 5 in) |
| Diameter | 0.97 m (3 ft 2 in) |
| Empty mass | 102.1 kg (225 lb) |
| Gross mass | 872.3 kg (1,923 lb) |
| Propellant mass | 770.2 kg (1,698 lb) |
| Maximum thrust | 32.7 kN (7,400 lbf) |
| Specific impulse | 287 s (2.81 km/s) |
| Burn time | 66.8 seconds |
| Propellant | HTPB /Al |
| Fourth stage (optional) –HAPS | |
| Height | 0.3 m (1 ft 0 in) |
| Diameter | 0.97 m (3 ft 2 in) |
| Propellant mass | 72 kg (159 lb) |
| Powered by | 3 ×MR-107N |
| Maximum thrust | 0.666 kN (150 lbf) |
| Specific impulse | 230.5 s (2.260 km/s) |
| Burn time | 131 + 110 seconds (2 burns) |
| Propellant | N2H4 |
Pegasus is anair-launchedmultistage rocket developed byOrbital Sciences Corporation (OSC) and later built and launched byNorthrop Grumman. Pegasus is the world's first privately developed orbital launch vehicle.[2][3] Capable of carrying small payloads of up to 443 kg (977 lb) intolow Earth orbit, Pegasus first flew in 1990 and remained active as of 2021[update]. The vehicle consists of threesolid propellantstages and an optionalmonopropellant fourth stage. Pegasus is released from its carrier aircraft at approximately 12,000 m (39,000 ft) using a first stage wing and a tail to provide lift and altitude control while in the atmosphere. The first stage does not have athrust vector control (TVC) system.[4]
Pegasus was designed by a team led by Antonio Elias.[5] The Pegasus's three Orion solid motors were developed byHercules Aerospace (laterAlliant Techsystems) specifically for the Pegasus launcher but using advanced carbon fiber, propellant formulation and case insulation technologies originally developed for the terminated USAF Small ICBM program. The wing and fins' structures were designed byBurt Rutan and his company,Scaled Composites, which manufactured them for Orbital.
Started in the spring of 1987,[6] the development project was funded by Orbital Sciences Corporation and Hercules Aerospace, and did not receive any government funding. Government funding was received to support operational testing.[7]NASA did provide the use of theB-52 carrier aircraft on a cost-reimbursable basis during the development (captive carry tests) and the first few flights. Two Orbital internal projects, theOrbcomm communications constellation and theOrbView observation satellites, served as anchor customers to help justify the private funding.[8]
There were no Pegasus test launches prior to the first operational launch on 5 April 1990 with NASA test pilot and formerastronautGordon Fullerton in command of the carrier aircraft. Initially, a NASA-ownedB-52 StratofortressNB-008 served as the carrier aircraft. By 1994, Orbital had transitioned to their "Stargazer"L-1011, a converted airliner which was formerly owned byAir Canada. The name "Stargazer" is an homage to thetelevision seriesStar Trek: The Next Generation: the characterJean-Luc Picard was captain of a ship namedStargazer prior to the events of the series, and his first officerWilliam Riker once served aboard a ship namedPegasus.[9]
During its 45-launch history, the Pegasus program had three mission failures (STEP-1, STEP-2 and HETI/SAC-B), and two partial failures, (USAF Microsat and STEP-2) followed by 30 consecutive successful flights for a total program success rate of 89 percent.[10] The first partial failure on 17 July 1991 caused the seven USAFmicrosatellites to be delivered to a lower than planned orbit, significantly reducing the mission lifetime. The last mission failure on 4 November 1996 resulted in the loss of gamma-burst identifying satellite HETE (High Energy Transient Explorer).[11]
The Pegasus XL, introduced in 1994 has lengthened stages to increase payload performance.[12] In the Pegasus XL, the first and second stages are lengthened into the Orion 50SXL and Orion 50XL, respectively. Higher stages are unchanged; flight operations are similar. The wing is strengthened slightly to handle the higher weight. The standard Pegasus has been discontinued; the Pegasus XL is still active as of 2019. Pegasus has flown 44 missions in both configurations, launching 91 satellites as of October 12, 2019.[13][14]
Dual payloads can be launched, with a canister that encloses the lower spacecraft and mounts the upper spacecraft. The upper spacecraft deploys, the canister opens, then the lower spacecraft separates from the third-stage adapter. Since the fairing is unchanged for cost and aerodynamic reasons, each of the two payloads must be relatively compact. Other multiple-satellite launches involve "self-stacking" configurations, such as the ORBCOMM spacecraft.
For their work in developing the rocket, the Pegasus team led by Antonio Elias was awarded the 1991National Medal of Technology by U.S. President George H. W. Bush.
The initial launch price offered wasUS$6 million, without options or a HAPS (Hydrazine Auxiliary Propulsion System) maneuvering stage. With the enlargement to Pegasus XL and the associated improvements to the vehicle, baseline prices increased. In addition, customers usually purchase additional services, such as extra testing, design and analysis, and launch-site support.[15]
As of 2015, the most recent Pegasus XL to be purchased — a planned June 2017 launch of NASA'sIonospheric Connection Explorer (ICON) mission — had a total cost of US$56.3 million, which NASA notes includes "firm-fixed launch service costs, spacecraft processing, payload integration, tracking, data and telemetry and other launch support requirements".[15] A series of technical problems delayed this launch, which finally took place on 11 October 2019.
In July 2019, it was announced thatNorthrop Grumman had lost the launch contract of theImaging X-ray Polarimetry Explorer (IXPE) satellite toSpaceX. IXPE had been planned to be launched by a Pegasus XL rocket, and had been designed so as to fit within the Pegasus XL rocket constraints. With the IXPE launch removed from the Pegasus XL rocket, there are currently (as of 12 October 2019, after the launch of ICON) no space launch missions announced for the Pegasus XL rocket. The future (under construction as of 2019) NASAExplorer program missionPolarimeter to Unify the Corona and Heliosphere (PUNCH) was planned to be launched by Pegasus XL; but then NASA decided to merge the launches of PUNCH and another Explorer mission,Tandem Reconnection and Cusp Electrodynamics Reconnaissance Satellites (TRACERS) (also under construction as of 2019). These two space missions, consisting of 6 satellites in total, are to be launched by one launch vehicle. It is expected that a larger launcher will be chosen for this dual mission launch.[16] In August 2022 NASA announced that the 4 microsatellites of thePUNCH constellation will be launched as rideshare payloads together withSPHEREx in April 2025 on aSpaceXFalcon 9 rocket.[17][18]
Northrop has one Pegasus XL remaining in its inventory. It is looking for customers for those rockets. Northrop does not plan on retiring the Pegasus XL rocket as of October 2019.[19]
In a Pegasus launch, the carrier aircraft takes off from a runway with support and checkout facilities. Such locations have includedKennedy Space Center /Cape Canaveral Air Force Station, Florida;Vandenberg Air Force Base andDryden Flight Research Center,California;Wallops Flight Facility,Virginia;Kwajalein Range in thePacific Ocean, and theCanary Islands in theAtlantic Ocean. Orbital offers launches fromAlcantara,Brazil, but no known customers have performed any.
Upon reaching a predetermined staging time, location, and velocity the aircraft releases the Pegasus. After five seconds of free-fall, the first stage ignites and the vehicle pitches up. The 45-degreedelta wing (of carbon composite construction and double-wedge airfoil) aids pitch-up and provides some lift. The tail fins provide steering for first-stage flight, as the Orion 50S motor does not have athrust-vectoring nozzle.
Approximately 1 minute and 17 seconds later, the Orion 50S motor burns out. The vehicle is at over 200,000 feet (61 km) in altitude andhypersonic speed. The first stage falls away, taking the wing and tail surfaces, and the second stage ignites. The Orion 50 burns for approximately 1 minute and 18 seconds. Attitude control is by thrust vectoring the Orion 50 motor around twoaxes, pitch and yaw; roll control is provided by nitrogen thrusters on the third stage.[citation needed]
Midway through second-stage flight, the launcher has reached a near-vacuum altitude. The fairing splits and falls away, uncovering the payload and third stage. Upon burnout of the second-stage motor, the stack coasts until reaching a suitable point in its trajectory, depending on mission. Then the Orion 50 is discarded, and the third stage'sOrion 38 motor ignites. It too has a thrust-vectoring nozzle, assisted by the nitrogen thrusters for roll. After approximately 64 seconds, the third stage burns out.[citation needed]
A fourth stage is sometimes added for a higher altitude, finer altitude accuracy, or more complex maneuvers. The HAPS (Hydrazine Auxiliary Propulsion System) is powered by three restartable,monopropellant hydrazine thrusters. As with dual launches, the HAPS cuts into the fixed volume available for payload. In at leastone instance, the spacecraft was built around the HAPS.
Guidance is via a 32-bit computer and anIMU. AGPS receiver gives additional information. Due to the air launch and wing lift, the first-stage flight algorithm is custom-designed. The second- and third-stage trajectories areballistic, and their guidance is derived from a Space Shuttle algorithm.[citation needed]
The carrier aircraft (initially a NASAB-52, now anL-1011 owned by Northrop Grumman) serves as a booster to increase payloads at reduced cost. 12,000 m (39,000 ft) is only about 4% of a low Earth orbital altitude, and the subsonic aircraft reaches only about 3% of orbital velocity, yet by delivering the launch vehicle to this speed and altitude, the reusable aircraft replaces a costly first-stage booster.
In October 2016,Orbital ATK announced a partnership withStratolaunch Systems to launch Pegasus-XL rockets from the giantScaled Composites Stratolaunch, which could launch up to three Pegasus-XL rockets on a single flight.[20]
Pegasus components have also been the basis of other Orbital Sciences Corporation launchers.[21] The ground-launchedTaurus rocket places the Pegasus stages and a larger fairing atop aCastor 120 first stage, derived from the first stage of theMXPeacekeeper missile. Initial launches used refurbished MX first stages.
TheMinotaur I, also ground-launched, is a combination of stages from Taurus launchers and Minuteman missiles, hence the name. The first two stages are from aMinuteman II; the upper stages are Orion 50XL and 38. Due to the use of surplus military rocket motors, it is only used for U.S. Government and government-sponsored payloads.[why?]
A third vehicle is dubbedMinotaur IV despite containing no Minuteman stages. It consists of a refurbished MX with an Orion 38 added as a fourth stage.
The NASAX-43A hypersonic test vehicles were boosted by Pegasus first stages. The upper stages were replaced by exposed models of ascramjet-powered vehicle. The Orion stages boosted the X-43 to its ignition speed and altitude, and were discarded. After firing the scramjet and gathering flight data, the test vehicles also fell into the Pacific.
The most numerous derivative of Pegasus is the booster for theGround-based Midcourse Defense (GBMD) interceptor, basically a vertical (silo) launched Pegasus minus wing and fins, and with the first stage modified by addition of a Thrust Vector Control (TVC) system.
Pegasus has flown 45 missions between 1990 and 2021.[13]
| Flight No. | Date / time (UTC) | Rocket, Configuration | Launch site | Payload | Payload mass | Target Orbit[22] | Actual Orbit[22] | Customer | Launch outcome |
|---|---|---|---|---|---|---|---|---|---|
| 1 | 5 April 1990 19:10:17 | Standard (B-52) | Edwards AFB | Pegsat,NavySat | 320.0 x 360.0 km @ 94.00° i | 273.0 x 370.0 km @ 94.15° i | Success | ||
| 2 | 17 July 1991 17:33:53 | Standard w/ HAPS (B-52) | Edwards AFB | Microsats (7 satellites) | 389.0 x 389.0 km @ 82.00° i | 192.4 x 245.5 km @ 82.04° i | Partial failure | ||
| Orbit too low, spacecraft reentered after 6 months instead of planned 3-years lifetime. | |||||||||
| 3 | 9 February 1993 14:30:34 | Standard (B-52) | Kennedy Space Center | SCD-1 | 405.0 x 405.0 km @ 25.00° i | 393.0 x 427.0 km @ 24.97° i | Success | ||
| In the final minute of the launch sequence an abort was called by NASA'sRange Safety Officer (RSO). Despite the abort call, the launch was reinitiated by then operatorOrbital Sciences Corporation's test conductor without coordination with other launch participants.[23][24] Launch was completed without further issue. In an investigation led by theNational Transportation Safety Board (NTSB) found that: fatigue; lack of clear command, control, and communication roles were factors that led to the incident.[24] | |||||||||
| 4 | 25 April 1993 13:56:00 | Standard (B-52) | Edwards AFB | ALEXIS – Array of Low Energy X-ray Imaging Sensors | 400.0 x 400.0 km @ 70.00° i | 404.0 x 450.5 km @ 69.92° i | Success | ||
| 5 | 19 May 1994 17:03 | Standard w/ HAPS (B-52) | Edwards AFB | STEP-2 (Space Test Experiments Platform/Mission 2/SIDEX) | 450.0 x 450.0 km @ 82.00° i | 325.0 x 443.0 km @ 81.95° i | Partial failure | ||
| Orbit slightly low | |||||||||
| 6 | 27 June 1994 21:15 | XL (L-1011) | Vandenberg AFB | STEP-1 (Space Test Experiments Platform/Mission 1) | - | - | Failure | ||
| Loss of vehicle control 35 seconds into flight, flight terminated. | |||||||||
| 7 | 3 August 1994 14:38 | Standard (B-52) | Edwards AFB | APEX | 195.0 x >1000 km @ 70.02° i | 195.5 x 1372.0 km @ 69.97° i | Success | ||
| 8 | 3 April 1995 13:48 | Hybrid (L-1011)[a] | Vandenberg AFB | Orbcomm (2 satellites),OrbView 1 | 398.0 x 404.0 km @ 70.00° i | 395.0 x 411.0 km @ 70.03° i | Success | ||
| 9 | 22 June 1995 19:58 | XL (L-1011) | Vandenberg AFB | STEP-3 (Space Test Experiments Platform/Mission 3) | - | - | Failure | ||
| Destroyed during second-stage flight | |||||||||
| 10 | 9 March 1996 01:33 | XL (L-1011) | Vandenberg AFB | REX II | 450.0 x 443.0 km @ 90.00° i | 450.9 x 434.3 km @ 89.96° i | Success | ||
| 11 | 17 May 1996 02:44 | Hybrid (L-1011) | Vandenberg AFB | MSTI-3 | 298.0 x 394.0 km @ 97.13° i | 293.0 x 363.0 km @ 97.09° i | Success | ||
| 12 | 2 July 1996 07:48 | XL (L-1011) | Vandenberg AFB | TOMS-EP | 340.0 x 955.0 km @ 97.40° i | 341.2 x 942.9 km @ 97.37° i | Success | ||
| 13 | 21 August 1996 09:47:26 | XL (L-1011) | Vandenberg AFB | FAST (Fast Auroral Snapshot Explorer) | 350.0 x 4200.0 km @ 83.00° i | 350.4 x 4169.6 km @ 82.98° i | Success | ||
| 14 | 4 November 1996 17:08:56 | XL (L-1011) | Wallops Flight Facility | HETE,SAC-B | 510.0 x 550.0 km @ 38.00° i | 488.1 x 555.4 km @ 37.98° i | Failure | ||
| Satellites not ejected from third stage | |||||||||
| 15 | 21 April 1997 11:59:06 | XL (L-1011) | Gando Air Base, Gran Canaria, Spain | Minisat 01,Celestis space burial | 587.0 x 587.0 km @ 151.01° i | 562.6 x 581.7 km @ 150.97° i | Success | ||
| 16 | August 1, 1997 20:20:00 | XL (L-1011) | Vandenberg AFB | OrbView-2 | 310.0 x 400.0 km @ 98.21° i | 300.0 x 302.0 km @ 98.28° i | Success | ||
| On the line with partial success | |||||||||
| 17 | August 29, 1997 15:02:00 | XL (L-1011) | Vandenberg AFB | FORTE | 800.0 x 800.0 km @ 70.00° i | 799.9 x 833.4 km @ 69.97° i | Success | ||
| 18 | October 22, 1997 13:13:00 | XL (L-1011) | Wallops Flight Facility | STEP-4 (Space Test Experiments Platform/Mission 4) | 430.0 x 510.0 km @ 45.00° i | 430.0 x 511.0 km @ 44.98° i | Success | ||
| 19 | December 23, 1997 19:11:00 | XL w/ HAPS (L-1011) | Wallops Flight Facility | Orbcomm (8 satellites) | 825.0 x 825.0 km @ 45.00° i | 822.0 x 824.0 km @ 45.02° i | Success | ||
| 20 | February 26, 1998 07:07:00 | XL (L-1011) | Vandenberg AFB | SNOE,BATSAT | 580.0 x 580.0 km @ 97.75° i | 582.0 x 542.0 km @ 97.76° i | Success | ||
| 21 | April 2, 1998 02:42:00 | XL (L-1011) | Vandenberg AFB | TRACE | 600.0 x 650.0 km @ 97.88° i | 599.9 x 649.2 km @ 97.81° i | Success | ||
| 22 | August 2, 1998 16:24:00 | XL w/ HAPS (L-1011) | Wallops Flight Facility | Orbcomm (8 satellites) | 818.5 x 818.5 km @ 45.02° i | 819.5 x 826.0 km @ 45.01° i | Success | ||
| 23 | September 23, 1998 05:06:00 | XL w/ HAPS (L-1011) | Wallops Flight Facility | Orbcomm (8 satellites) | 818.5 x 818.5 km @ 45.02° i | 811.0 x 826.0 km @ 45.02° i | Success | ||
| 24 | October 22, 1998 00:02:00 | Hybrid (L-1011) | Cape Canaveral | SCD-2 | 750.0 x 750.0 km @ 25.00° i | 750.4 x 767.0 km @ 24.91° i | Success | ||
| 25 | December 6, 1998 00:57:00 | XL (L-1011) | Vandenberg AFB | SWAS | 635.0 x 700.0 km @ 70.00 ° i | 637.7 x 663.4 km @ 69.91° i | Success | ||
| 26 | March 5, 1999 02:56:00 | XL (L-1011) | Vandenberg AFB | WIRE – Wide Field Infrared Explorer | 540.0 x 540.0 km @ 97.56° i | 539.0 x 598.0 km @ 97.53° i | Success | ||
| 27 | May 18, 1999 05:09:00 | XL w/ HAPS (L-1011) | Vandenberg AFB | Terriers,MUBLCOM | 550.0 x 550.0 km @ 97.75° i, 775.0 x 775.0 km @ 97.75° i | 551.0 x 557.0 km @ 97.72° i, 774.0 x 788.0 km @ 97.72° i | Success | ||
| 28 | December 4, 1999 18:53:00 | XL w/ HAPS (L-1011) | Wallops Flight Facility | Orbcomm (7 satellites) | 825.0 x 825.0 km @ 45.02° i | 826.5 x 829.0 km @ 45.02° i | Success | ||
| 29 | June 7, 2000 13:19:00 | XL (L-1011) | Vandenberg AFB | TSX-5 (Tri-Service-Experiments mission 5) | 405.0 x 1.750.0 km @ 69.00° i | 409.9 x 1,711.7 km @ 68.95° i | Success | ||
| 30 | October 9, 2000 05:38:00 | Hybrid (L-1011) | Kwajalein Atoll | HETE 2 | 600.0 x 650.0 km @ 2.00° i | 591.9 x 651.9 km @ 1.95° i | Success | ||
| 31 | February 5, 2002 20:58:00 | XL (L-1011) | Cape Canaveral | RHESSI | 600.0 x 600.0 km @ 38.00° i | 586.4 x 602.0 km @ 38.02° i | Success | ||
| 32 | January 25, 2003 20:13:00 | XL (L-1011) | Cape Canaveral | SORCE | 645.0 x 645.0 km @ 40.00° i | 622.3 x 647.3 km @ 39.999° i | Success | ||
| 33 | April 28, 2003 11:59:00 | XL (L-1011) | Cape Canaveral | GALEX – Galaxy Evolution Explorer | 690.0 x 690.0 km @ 29.00° i | 689.8 x 711.3 km @ 28.99° i | Success | ||
| 34 | June 26, 2003 18:53:00 | XL (L-1011) | Vandenberg AFB | OrbView-3 | 369.0 x 470.0 km @ 97.29° i | 367.1 x 440.5 km @ 97.27° i | Success | ||
| 35 | August 13, 2003 02:09:00 | XL (L-1011) | Vandenberg AFB | SCISAT-1 | 650.0 x 650.0 km @ 73.92° i | 647.9 x 659.7 km @ 73.95° i | Success | ||
| 36 | April 15, 2005 17:26:00 | XL w/ HAPS (L-1011) | Vandenberg AFB | DART | 538.7 x 566.7 km @ 97.73° i | 541.2 x 548.8 km @ 97.73° i | Success | ||
| 37 | March 22, 2006 14:03:00 | XL (L-1011) | Vandenberg AFB | ST-5 – Space Technology 5 (3 satellites) | 300.0 x 4500.0 km @ 105.6° i | 301.1 x 4571.0 km @ 105.62° i | Success | ||
| 38 | April 25, 2007 20:26:00 | XL (L-1011) | Vandenberg AFB | AIM – Aeronomy of Ice in the Mesosphere | 197 kg (434 lb)[26] | 600.0 x600.0 km @ 97.77° i | 601.3 x 596.2 km @ 97.79° i | NASA[26] | Success |
| 39 | April 16, 2008 17:02:00 | XL (L-1011) | Kwajalein Atoll | C/NOFS | 384 kg (847 lb)[27] | 400.0 x 850.0 km @ 13.0° i | 401.0 x 868.0 km @ 12.99° i | STP /AFRL / DMSG[27] | Success |
| 40 | October 19, 2008 17:47:23 | XL (L-1011) | Kwajalein Atoll | IBEX – Interstellar Boundary Explorer | 107 kg (236 lb)[28] | 207.0 x 412.0 km @11.0° i | 206.4 x 445.0 km @ 10.99° i | NASA | Success |
| 41 | June 13, 2012 16:00:00 | XL (L-1011) | Kwajalein Atoll | NuSTAR – Nuclear Spectroscopic Telescope Array | 350 kg (770 lb)[29] | ≥530.0 x ≤660.0 km @ 5.0 – 7.0° i | 621.2 x 638.5 km @ 6.024° i | NASA /JPL | Success[30] |
| 42 | June 28, 2013 02:27:46[31] | XL (L-1011) | Vandenberg AFB | IRIS – Interface Region Imaging Spectrograph SMEX | 183 kg (403 lb)[32] | ≥620.0 x ≤670.0 km @97.89° i | 622.9 x 669.3 km @ 97.894° i | NASA | Success[32] |
| 43 | December 15, 2016 13:37:00 | XL (L-1011) | Cape Canaveral | Cyclone Global Navigation Satellite System (CYGNSS)[33] | 345.6 kg (762 lb)[34] | 510.0 x 6888.0 km @ 35° i | 511.5 x 6908.1 km @ 34.97° i | NASA | Success[35] |
| 44 | 11 October 2019 01:59:05 | XL (L-1011) | Cape Canaveral | Ionospheric Connection Explorer (ICON) | 281 kg (619 lb)[36][37] | LEO, 590 x 607 km[37] | 608.4 x 571.6 @ 26.98° i | UC BerkeleySSL /NASA | Success[38] |
| 45 | 13 June 2021 08:11[39][40] | XL (L-1011) | Vandenberg Space Force Base | TacRL-2 (Odyssey) | 325 kg (717 lb) | LEO - | U.S. Space Force | Success[41] | |
This article incorporates text from this source, which is in thepublic domain. This article incorporates text from this source, which is in thepublic domain. This article incorporates text from this source, which is in thepublic domain.
