Global InformationNorthrop Grumman Pegasus information
 Pegasus XL | |
| Function | Launch vehicle |
|---|---|
| Manufacturer | Northrop Grumman |
| Country of origin | United States |
| Cost per launch | US$40 million [1] |
| Size | |
| Height | 16.9 m (55 ft) (Pegasus) 17.6 m (58 ft) (Pegasus XL) |
| Diameter | 1.27 m (4 ft 2 in) |
| Mass | 18,500 kg (40,800 lb) (Pegasus) 23,130 kg (50,990 lb) (Pegasus XL) |
| Stages | 3 |
| Capacity | |
| Payload to Low Earth orbit | |
| Mass | 443 kg (977 lb) |
| Associated rockets | |
| Family | Air launch to orbit |
| Derivative work | Minotaur-C |
| Comparable | Electron, Vector-H, Falcon 1, LauncherOne |
| Launch history | |
| Status | Active |
| Launch sites | Air launch to orbit |
| 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 | |
| Powered by | 1 Solid |
| Maximum thrust | 500 kilonewtons (110,000 lbf) |
| Burn time | 75.3 seconds |
| Propellant | Solid |
| First stage – Orion 50SXL (pegasus XL) | |
| Powered by | 1 Solid |
| Maximum thrust | 647.5 kilonewtons (145,600 lbf) |
| Burn time | 69.1 seconds |
| Propellant | Solid |
| Second stage – Orion 50 | |
| Powered by | 1 Solid |
| Maximum thrust | 114.6 kilonewtons (25,800 lbf) |
| Burn time | 75.6 seconds |
| Propellant | Solid |
| Second stage – Orion 50XL (pegasus XL) | |
| Powered by | 1 Solid |
| Maximum thrust | 160.6 kilonewtons (36,100 lbf) |
| Burn time | 69.7 seconds |
| Propellant | Solid |
| Third stage – Orion 38 | |
| Powered by | 1 Solid |
| Maximum thrust | 32.2 kilonewtons (7,200 lbf) |
| Burn time | 67.7 seconds |
| Propellant | Solid |
| Fourth stage – HAPS (optional) | |
| Powered by | MR-107N (3) |
| Maximum thrust | 0.67 kilonewtons (150 lbf) |
| Burn time | 245 seconds |
| Propellant | Hydrazine |
| Part of a series on |
| Private spaceflight |
|---|
 |
| Active companies |
|
| Active vehicles |
|
| Contracts and programs |
|
| Related |
|
|
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.[1][2] Capable of carrying small payloads of up to 443 kg (977 lb) into low Earth orbit, Pegasus first flew in 1990 and remained active as of 2021[update]. 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 altitude control while in the atmosphere. The first stage does not have a thrust vector control (TVC) system.[3]
- ^ "Pegasus Rocket". Northrop Grumman. Retrieved 28 July 2020.
- ^ "Pegasus rocket". Oxford Reference. Retrieved 3 March 2023.
- ^ "Pegasus User's Guide" (PDF). Orbital-ATK. October 2015. Archived from the original (PDF) on 13 January 2016.