.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 or 4 |
| Capacity | |
| Payload to LEO | |
| 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 | 3 |
| Partial failure | 2 |
| First flight | April 5, 1990 (Pegsat / NavySat) |
| Last flight | June 13, 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 |
| Part of a series on |
| Private spaceflight |
|---|
Pegasus is an air-launched multistage rocket developed by Orbital Sciences Corporation (OSC) and later built and launched by Northrop 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) into low Earth orbit, Pegasus first flew in 1990 and last flew in 2021, but there is one more mission planned for 2026. The vehicle consists of three solid propellant stages and an optional monopropellant 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 attitude control while in the atmosphere. The first stage does not have a thrust vector control (TVC) system.[4]
History
[edit]Pegasus was designed by a team led by Antonio Elias.[5] The Pegasus's three Orion solid motors were developed by Hercules Aerospace (later Alliant 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 by Burt Rutan and his company, Scaled Composites, which manufactured them for Orbital.
- Mass: 18,500 kg (Pegasus), 23,130 kg (Pegasus XL)[4]: 3
- Length: 16.9 m (Pegasus), 17.6 m (Pegasus XL)[4]: 3
- Diameter: 1.27 m
- Wing span: 6.7 m
- Payload: 443 kg (1.18 m diameter, 2.13 m length)
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 the B-52 carrier aircraft on a cost-reimbursable basis during the development (captive carry tests) and the first few flights. Two Orbital internal projects, the Orbcomm communications constellation and the OrbView 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 April 5, 1990, with NASA test pilot and former astronaut Gordon Fullerton in command of the carrier aircraft. Initially, a NASA-owned B-52 Stratofortress NB-008 served as the carrier aircraft. By 1994, Orbital had transitioned to their "Stargazer" L-1011, a converted airliner which was formerly owned by Air Canada. The name "Stargazer" is an homage to the television series Star Trek: The Next Generation: the character Jean-Luc Picard was captain of a ship named Stargazer prior to the events of the series, and his first officer William Riker once served aboard a ship named Pegasus.[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 July 17, 1991, caused the seven USAF microsatellites to be delivered to a lower than planned orbit, significantly reducing the mission lifetime. The last mission failure on November 4, 1996, resulted in the loss of gamma-burst identifying satellite HETE-1 (High Energy Transient Explorer).[11]
Preparations for launch of Pegasus XL carrying the NASA Interstellar Boundary Explorer (IBEX) spacecraft.
The Pegasus XL with fairing removed exposing payload bay and the IBEX satellite.
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 1991 National Medal of Technology by U.S. President George H. W. Bush.
The initial launch price offered was US$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's Ionospheric 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 October 11, 2019.
In July 2019, it was announced that Northrop Grumman had lost the launch contract of the Imaging X-ray Polarimetry Explorer (IXPE) satellite to SpaceX. 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 October 12, 2019, after the launch of ICON) no space launch missions announced for the Pegasus XL rocket. The future (under construction as of 2019) NASA Explorer program mission Polarimeter 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 the PUNCH constellation will be launched as rideshare payloads together with SPHEREx in April 2025 on a SpaceX Falcon 9 rocket.[17][18]
Demand for the Pegasus XL declined sharply by the late 2010s and early 2020s, as most small satellites shifted to lower-cost rideshare opportunities on larger launch vehicles. Between 2016 and 2026, Pegasus XL flew only three times: 2019, 2021, and a launch planned for 2026.[19]
In November 2025, Katalyst Space Technologies selected Pegasus XL to launch a rescue mission for NASA's Neil Gehrels Swift Observatory to prevent an uncontrolled re-entry. The mission required insertion into a specific low-inclination orbit not served by common rideshare launches, and smaller dedicated rockets lacked the necessary performance. The flight will use the last Pegasus XL in Northrop's inventory, likely sold at a discount.[19][20]
Launch profile
[edit]
Orbital's Lockheed L-1011 Stargazer launches Pegasus carrying the three Space Technology 5 satellites, 2006
Pegasus engine fires following release from its host, a Boeing B-52 Stratofortress, 1991
In a Pegasus launch, the carrier aircraft takes off from a runway with support and checkout facilities. Such locations have included Kennedy Space Center / Cape Canaveral Air Force Station, Florida; Vandenberg Air Force Base and Dryden Flight Research Center, California; Wallops Flight Facility, Virginia; Kwajalein Range in the Pacific Ocean, and the Canary Islands in the Atlantic Ocean. Orbital offers launches from Alcantara, 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-degree delta 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 a thrust-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 and hypersonic 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 two axes, 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's Orion 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 least one instance, the spacecraft was built around the HAPS.
Guidance is via a 32-bit computer and an IMU. A GPS 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 are ballistic, and their guidance is derived from a Space Shuttle algorithm.[citation needed]
Carrier aircraft
[edit]The carrier aircraft (initially a NASA B-52, now an L-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 with Stratolaunch Systems to launch Pegasus-XL rockets from the giant Scaled Composites Stratolaunch, which could launch up to three Pegasus-XL rockets on a single flight.[21]
Related projects
[edit]
Pegasus XL at the Steven F. Udvar-Hazy Center
Pegasus components have also been the basis of other Orbital Sciences Corporation launchers.[22] The ground-launched Taurus rocket places the Pegasus stages and a larger fairing atop a Castor 120 first stage, derived from the first stage of the MX Peacekeeper missile. Initial launches used refurbished MX first stages.
The Minotaur I, also ground-launched, is a combination of stages from Taurus launchers and Minuteman missiles, hence the name. The first two stages are from a Minuteman 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 dubbed Minotaur IV despite containing no Minuteman stages. It consists of a refurbished MX with an Orion 38 added as a fourth stage.
The NASA X-43A hypersonic test vehicles were boosted by Pegasus first stages. The upper stages were replaced by exposed models of a scramjet-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 the Ground-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.
Launch statistics
[edit]Launch sites
[edit]- Edwards
- Kennedy
- Cape Canaveral
- Vandenberg
- Gando
- Wallops
- Kwajalein
Launch outcomes
[edit]- Failure
- Partial failure
- Success
- Planned
Carrier airplane
[edit]- B-52
- L-1011
Launch history
[edit]Pegasus has flown 45 missions between 1990 and 2021, with a final mission planned for 2026.[13]
| Flight No. | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Target Orbit[23] | Actual Orbit[23] | Customer | Launch outcome |
|---|---|---|---|---|---|---|---|---|---|
| 1 | April 5, 1990 19:10:17 |
Standard (B‑52) | Edwards | Pegsat, NavySat | 320 x 360 km @ 94° | 273 x 370 km @ 94.15° | Success | ||
| 2 | July 17, 1991 17:33:53 |
Standard w/ HAPS (B‑52) | Edwards | Microsats (7 satellites) | 389 x 389 km @ 82° | 192.4 x 245.5 km @ 82.04° | Partial failure | ||
| Orbit too low, spacecraft reentered after 6 months instead of planned 3-years lifetime. | |||||||||
| 3 | February 9, 1993 14:30:34 |
Standard (B‑52) | Kennedy | SCD-1 | 405 x 405 km @ 25° | 393 x 427 km @ 24.97° | Success | ||
| In the final minute of the launch sequence an abort was called by NASA's Range Safety Officer (RSO). Despite the abort call, the launch was reinitiated by then operator Orbital Sciences Corporation's test conductor without coordination with other launch participants.[24][25] Launch was completed without further issue. In an investigation led by the National Transportation Safety Board (NTSB) found that: fatigue; lack of clear command, control, and communication roles were factors that led to the incident.[25] | |||||||||
| 4 | April 25, 1993 13:56:00 |
Standard (B‑52) | Edwards | ALEXIS – Array of Low Energy X-ray Imaging Sensors | 400 x 400 km @ 70° | 404 x 450.5 km @ 69.92° | Success | ||
| 5 | May 19, 1994 17:03 |
Standard w/ HAPS (B‑52) | Edwards | STEP-2 (Space Test Experiments Platform/Mission 2/SIDEX) | 450 x 450 km @ 82° | 325 x 443 km @ 81.95° | Partial failure | ||
| Orbit slightly low | |||||||||
| 6 | June 27, 1994 21:15 |
XL (L‑1011) | Vandenberg | STEP-1 (Space Test Experiments Platform/Mission 1) | - | - | Failure | ||
| Loss of vehicle control 35 seconds into flight, flight terminated. | |||||||||
| 7 | August 3, 1994 14:38 |
Standard (B‑52) | Edwards | APEX | 195 x >1000 km @ 70.02° | 195.5 x 1372 km @ 69.97° | Success | ||
| 8 | April 3, 1995 13:48 |
Hybrid (L‑1011)[a] | Vandenberg | Orbcomm (2 satellites), OrbView 1 | 398 x 404 km @ 70° | 395 x 411 km @ 70.03° | Success | ||
| 9 | June 22, 1995 19:58 |
XL (L‑1011) | Vandenberg | STEP-3 (Space Test Experiments Platform/Mission 3) | - | - | Failure | ||
| Destroyed during second-stage flight | |||||||||
| 10 | March 9, 1996 01:33 |
XL (L‑1011) | Vandenberg | REX II | 450 x 443 km @ 90° | 450.9 x 434.3 km @ 89.96° | Success | ||
| 11 | May 17, 1996 02:44 |
Hybrid (L‑1011)[a] | Vandenberg | MSTI-3 | 298 x 394 km @ 97.13° | 293 x 363 km @ 97.09° | Success | ||
| 12 | July 2, 1996 07:48 |
XL (L‑1011) | Vandenberg | TOMS-EP | 340 x 955 km @ 97.40° | 341.2 x 942.9 km @ 97.37° | Success | ||
| 13 | August 21, 1996 09:47:26 |
XL (L‑1011) | Vandenberg | FAST (Fast Auroral Snapshot Explorer) | 350 x 4200 km @ 83° | 350.4 x 4169.6 km @ 82.98° | Success | ||
| 14 | November 4, 1996 17:08:56 |
XL (L‑1011) | Wallops | HETE-1, SAC-B | 510 x 550 km @ 38° | 488.1 x 555.4 km @ 37.98° | Failure | ||
| Satellites not ejected from third stage | |||||||||
| 15 | April 21, 1997 11:59:06 |
XL (L‑1011) | Gando Air Base | Minisat 01, Celestis space burial | 587 x 587 km @ 151.01° | 562.6 x 581.7 km @ 150.97° | Success | ||
| 16 | August 1, 1997 20:20:00 |
XL (L‑1011) | Vandenberg | OrbView-2 | 310 x 400 km @ 98.21° | 300 x 302 km @ 98.28° | Success | ||
| 17 | August 29, 1997 15:02:00 |
XL (L‑1011) | Vandenberg | FORTE | 800 x 800 km @ 70° | 799.9 x 833.4 km @ 69.97° | Success | ||
| 18 | October 22, 1997 13:13:00 |
XL (L‑1011) | Wallops | STEP-4 (Space Test Experiments Platform/Mission 4) | 430 x 510 km @ 45° | 430 x 511 km @ 44.98° | Success | ||
| 19 | December 23, 1997 19:11:00 |
XL w/ HAPS (L‑1011) | Wallops | Orbcomm (8 satellites) | 825 x 825 km @ 45° | 822 x 824 km @ 45.02° | Success | ||
| 20 | February 26, 1998 07:07:00 |
XL (L‑1011) | Vandenberg | SNOE, BATSAT | 580 x 580 km @ 97.75° | 582 x 542 km @ 97.76° | Success | ||
| 21 | April 2, 1998 02:42:00 |
XL (L‑1011) | Vandenberg | TRACE | 600 x 650 km @ 97.88° | 599.9 x 649.2 km @ 97.81° | Success | ||
| 22 | August 2, 1998 16:24:00 |
XL w/ HAPS (L‑1011) | Wallops | Orbcomm (8 satellites) | 818.5 x 818.5 km @ 45.02° | 819.5 x 826 km @ 45.01° | Success | ||
| 23 | September 23, 1998 05:06:00 |
XL w/ HAPS (L‑1011) | Wallops | Orbcomm (8 satellites) | 818.5 x 818.5 km @ 45.02° | 811 x 826 km @ 45.02° | Success | ||
| 24 | October 22, 1998 00:02:00 |
Hybrid (L‑1011)[a] | Cape Canaveral | SCD-2 | 750 x 750 km @ 25° | 750.4 x 767 km @ 24.91° | Success | ||
| 25 | December 6, 1998 00:57:00 |
XL (L‑1011) | Vandenberg | SWAS | 635 x 700 km @ 70 ° | 637.7 x 663.4 km @ 69.91° | Success | ||
| 26 | March 5, 1999 02:56:00 |
XL (L‑1011) | Vandenberg | WIRE – Wide Field Infrared Explorer | 540 x 540 km @ 97.56° | 539 x 598 km @ 97.53° | Success | ||
| 27 | May 18, 1999 05:09:00 |
XL w/ HAPS (L‑1011) | Vandenberg | Terriers, MUBLCOM | 550 x 550 km @ 97.75°,
775 x 775 km @ 97.75° |
551 x 557 km @ 97.72°,
774 x 788 km @ 97.72° |
Success | ||
| 28 | December 4, 1999 18:53:00 |
XL w/ HAPS (L‑1011) | Wallops | Orbcomm (7 satellites) | 825 x 825 km @ 45.02° | 826.5 x 829 km @ 45.02° | Success | ||
| 29 | June 7, 2000 13:19:00 |
XL (L‑1011) | Vandenberg | TSX-5 (Tri-Service-Experiments mission 5) | 405 x 1.750 km @ 69° | 409.9 x 1,711.7 km @ 68.95° | Success | ||
| 30 | October 9, 2000 05:38:00 |
Hybrid (L‑1011)[a] | Kwajalein Atoll | HETE-2 | 600 x 650 km @ 2° | 591.9 x 651.9 km @ 1.95° | Success | ||
| 31 | February 5, 2002 20:58:00 |
XL (L‑1011) | Cape Canaveral | RHESSI | 600 x 600 km @ 38° | 586.4 x 602 km @ 38.02° | Success | ||
| 32 | January 25, 2003 20:13:00 |
XL (L‑1011) | Cape Canaveral | SORCE | 645 x 645 km @ 40° | 622.3 x 647.3 km @ 39.999° | Success | ||
| 33 | April 28, 2003 11:59:00 |
XL (L‑1011) | Cape Canaveral | GALEX – Galaxy Evolution Explorer | 690 x 690 km @ 29° | 689.8 x 711.3 km @ 28.99° | Success | ||
| 34 | June 26, 2003 18:53:00 |
XL (L‑1011) | Vandenberg | OrbView-3 | 369 x 470 km @ 97.29° | 367.1 x 440.5 km @ 97.27° | Success | ||
| 35 | August 13, 2003 02:09:00 |
XL (L‑1011) | Vandenberg | SCISAT-1 | 650 x 650 km @ 73.92° | 647.9 x 659.7 km @ 73.95° | Success | ||
| 36 | April 15, 2005 17:26:00 |
XL w/ HAPS (L‑1011) | Vandenberg | DART | 538.7 x 566.7 km @ 97.73° | 541.2 x 548.8 km @ 97.73° | Success | ||
| 37 | March 22, 2006 14:03:00 |
XL (L‑1011) | Vandenberg | ST-5 – Space Technology 5 (3 satellites) | 300 x 4500 km @ 105.6° | 301.1 x 4571 km @ 105.62° | Success | ||
| 38 | April 25, 2007 20:26:00 |
XL (L‑1011) | Vandenberg | AIM – Aeronomy of Ice in the Mesosphere | 197 kg (434 lb)[27] | 600 x600 km @ 97.77° | 601.3 x 596.2 km @ 97.79° | NASA[27] | Success |
| 39 | April 16, 2008 17:02:00 |
XL (L‑1011) | Kwajalein Atoll | C/NOFS | 384 kg (847 lb)[28] | 400 x 850 km @ 13° | 401 x 868 km @ 12.99° | STP / AFRL / DMSG[28] | Success |
| 40 | October 19, 2008 17:47:23 |
XL (L‑1011) | Kwajalein Atoll | IBEX – Interstellar Boundary Explorer | 107 kg (236 lb)[29] | 207 x 412 km @11° | 206.4 x 445 km @ 10.99° | NASA | Success |
| 41 | June 13, 2012 16:00:00 |
XL (L‑1011) | Kwajalein Atoll | NuSTAR – Nuclear Spectroscopic Telescope Array | 350 kg (770 lb)[30] | ≥530 x ≤660 km @ 5 – 7° | 621.2 x 638.5 km @ 6.024° | NASA / JPL | Success[31] |
| 42 | June 28, 2013 02:27:46[32] |
XL (L‑1011) | Vandenberg | IRIS – Interface Region Imaging Spectrograph SMEX | 183 kg (403 lb)[33] | ≥620 x ≤670 km @97.89° | 622.9 x 669.3 km @ 97.894° | NASA | Success[33] |
| 43 | December 15, 2016 13:37:00 |
XL (L‑1011) | Cape Canaveral | Cyclone Global Navigation Satellite System (CYGNSS)[34] | 345.6 kg (762 lb)[35] | 510 x 6888 km @ 35° | 511.5 x 6908.1 km @ 34.97° | NASA | Success[36] |
| 44 | October 11, 2019 01:59:05 |
XL (L‑1011) | Cape Canaveral | Ionospheric Connection Explorer (ICON) | 281 kg (619 lb)[37][38] | 590 × 607 km (367 × 377 mi)[38] | 608.4 × 571.6 km (378.0 × 355.2 mi) @ 26.98° | UC Berkeley SSL / NASA | Success[39] |
| 45 | June 13, 2021 08:11[40][41] |
XL (L‑1011) | Vandenberg | TacRL-2 (Odyssey) | 325 kg (717 lb) | U.S. Space Force | Success[42] | ||
| 46 | June 2026[43] | XL (L‑1011) | Kwajalein Atoll | Katalyst Link | ~400 × 400 km (250 × 250 mi) @ 20.6°[43][44] | Katalyst Space Technologies | Planned | ||
| Katalyst Link spacecraft will be used for a rescue mission for NASA's Neil Gehrels Swift Observatory to prevent an uncontrolled re-entry.[19][20] | |||||||||
Launch failures
[edit]- Flight F-6, June 27, 1994: The vehicle lost control 35 seconds into flight, telemetry downlink lost 38 seconds into flight, range safety commanded flight termination 39 seconds into flight. The likely reason for loss of control was improper aerodynamic modelling of the longer (XL) version of which this was the first flight. The Pegasus carried the DoD Space Test Program's satellite - Space Test Experiments Platform, Mission 1 (STEP-1).
- Flight F-9, June 22, 1995: The interstage ring between the 1st and 2nd stages did not separate, constraining movement of the 2nd-stage nozzle. As a result, the rocket deviated from its intended trajectory and was ultimately destroyed by range safety. The Pegasus carried the DoD Space Test Program's satellite - Space Test Experiments Platform, Mission 3 (STEP-3).
- Flight F-14, November 4, 1996: Failed to separate payloads because of a discharged battery intended to start separation pyros. Battery damage during launch was the likely reason. The lost payloads were the High Energy Transient Explorer and Argentina's SAC-B satellite.
Partial successes
[edit]- Flight F-2, July 17, 1991: A faulty pyrotechnic system caused the rocket to veer off course during 1st-stage separation, resulting erratic maneuvers that prevented the rocket reaching the correct orbit, and the mission life, planned for 3 years, was reduced to 6 months.[45]
- Flight F-5, May 19, 1994: A software navigation error caused the HAPS upper stage to shut down early, resulting in a lower than planned orbit. The Pegasus carried the DoD Space Test Program's satellite - Space Test Experiments Platform, Mission 2 (STEP-2).
See also
[edit]
- Air launch to orbit
- Comparison of orbital launchers families
- Comparison of orbital launch systems
- Pegasus II (rocket)
References
[edit]- ^ "Surplus Missile Motors: Sale Price Drives Potential Effects on DOD and Commercial Launch Providers". Government Accountability Office. Retrieved July 7, 2024.
- ^ "Pegasus Rocket". Northrop Grumman. Retrieved July 28, 2020.
- ^ "Pegasus rocket". Oxford Reference. Retrieved March 3, 2023.
- ^ a b c "Pegasus User's Guide" (PDF). Orbital-ATK. October 2015. Archived from the original (PDF) on January 13, 2016.
- ^ Brown, Stuart (May 1989), "Winging it Into Space", The Popular Science Monthly, Popular Science: 128, ISSN 0161-7370, retrieved June 27, 2013
- ^ Thompson, David (2007), An Adventure Begins - Orbital's First 25 Years, Orbital Sciences Corporation
- ^ Mosier, Marty; Harris, Gary; Richards, Bob; Rovner, Dan; Carroll, Brent (1990). "Pegasus First Mission Flight results". Proceedings of the 4th AIAA/USU Conference on Small Satellites. 1. Bibcode:1990aiaa....1.....M.
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External links
[edit]
- Pegasus/ICON website at Northrop Grumman Archived October 24, 2018, at the Wayback Machine
- Pegasus at Encyclopedia Astronautica
- The Pegasus XL Rocket Archived July 21, 2012, at the Wayback Machine