# Crew Dragon Launch Abort System

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Spacecraft launch-escape system

Crew Dragon Launch Abort System Crew Dragon prototype DragonFly[1] performing a pad abort demonstration. Manufacturer SpaceX Country of origin United States Launch history Status Operational Crew Dragon Launch Abort System Powered by 8 × SuperDraco (4 × pairs of 2)[2] Maximum thrust 71 kN Burn time 25 seconds Propellant N2O4 / CH6N2

The **Crew Dragon Launch Abort System** is designed to propel the [SpaceX Crew Dragon spacecraft](/source/Crew_Dragon) away from a failing launch vehicle. It is equipped with 8 [SuperDraco](/source/SuperDraco) engines, each capable of generating 71 [kN](/source/Kilonewton) of thrust.[3][4]

The abort system has several modes, or procedures for performing an abort in different phases of flight, including a pad abort, an in-flight abort, and the ability to use the abort system to fly into a lower than expected orbit should a failure occur late in flight.

## Design

A figure showing the Apollo spacecraft's launch abort system.

A diagram showing the configuration of Crew Dragon *[Endeavor](/source/Crew_Dragon_Endeavour)* during the [Demo-2 mission](/source/Crew_Dragon_Demo-2).

Traditionally, spacecraft like [Apollo](/source/Apollo_(spacecraft)) and [Soyuz](/source/Soyuz_(spacecraft)) have utilized [solid-fueled](/source/Solid-propellant_rocket) "puller" launch escape systems, with the main spacecraft beneath a protective fairing attached to the escape system. Once in space, the escape system and the fairing are jettisoned, with the spacecraft's mode of abort switched to using its orbital maneuvering thrusters or upper stages.[5][6] Crew Dragon, however, has its abort system permanently attached to the sides of the spacecraft.[3]

Part of the reasoning behind this design is that it was originally planned to land dragon propulsively using the launch abort system.[7] These plans were dropped after skepticism from [NASA](/source/NASA) and the cancellation of [SpaceX](/source/SpaceX)'s [Red Dragon](/source/SpaceX_Red_Dragon) capsule.[8] However, the capability was introduced on Crew-8, though only in the event of a parachute failure.[9] Additionally, the ability to keep the abort system attached to the rocket throughout the entire ascent rather than jettisoning the launch escape system after stage separation allows for an abort capability in all stages of flight, increasing crew safety.[10]

Crew Dragon's "trunk", or cargo bay, also plays an important role in the abort sequence. Rather than leaving the trunk with the rocket like [Apollo](/source/Apollo_(spacecraft)) or [Soyuz](/source/Soyuz_(spacecraft)), Dragon keeps the trunk attached during an abort for aerodynamic stability.[11]

## History

### Pad Explosion

On 20 April 2019, [Crew Dragon C204](/source/Crew_Dragon_C204) was destroyed in an incident while testing its [SuperDraco](/source/SuperDraco) engines. A video leaked shortly after the incident shows the capsule exploding on a launch mount.[12][13] [NASA](/source/NASA) and [SpaceX](/source/SpaceX) confirmed the explosion and stated that there were no injuries.[14]

A diagram demonstrating a [check valve](/source/Check_valve).

Following an investigation, SpaceX stated that the explosion was the result of a faulty valve. During a nominal ignition sequence, valves keeping helium inside [COPVs (Composite Overwrapped Pressure Vessels)](/source/COPV) are opened, causing the helium to flow through [one-way check valves](/source/One_way_valve) into the propellant tanks, pushing the fuel into the [combustion chamber](/source/Combustion_chamber).[15]

See also: [Pressure-fed engine](/source/Pressure-fed_engine)

In this incident, however, the one-way oxidizer valve had allowed [nitrogen tetroxide (NTO)](/source/Nitrogen_tetroxide) to leak back through the helium tube.[16] When the helium valve was opened, the "blobs" of NTO inside the helium line were accelerated at high speeds, slamming into and nearly instantaneously destroying the one-way oxidizer valve. The internal titanium components of the destroyed valve were then exposed to the NTO, resulting in combustion and the loss of the vehicle.[17][18]

### In-Flight Abort Test

A video of the in-flight abort test.

Main article: [Crew Dragon In-Flight Abort Test](/source/Crew_Dragon_In-Flight_Abort_Test)

On 19 January 2020, [SpaceX](/source/SpaceX) conducted a test of Crew Dragon's launch abort system.[19]

After a successful liftoff, the launch abort sequence was initiated 1 minute and 26 seconds into flight. [Crew Dragon C205](/source/Crew_Dragon_C205) successfully separated with the [Falcon 9](/source/Falcon_9) rocket, with the rocket breaking up seconds later under the intense aerodynamic forces of [max-q](/source/Max_q).[20]

After separating the trunk, Crew Dragon reached an [apogee](/source/Apogee) of 42 kilometers before splashing down in the [Atlantic Ocean](/source/Atlantic_Ocean).[21][22]

## Abort modes

The Crew Dragon has multiple abort modes for different phases of flight, each with its own landing zones and procedures. As the flight progresses, SpaceX [mission control](/source/Mission_control_center) calls out switches between abort modes.

For typical launches, recovery zones are placed along the 51.64-degree [inclination](/source/Orbital_inclination)[23] of the [ISS](/source/International_Space_Station), and can be targeted with higher levels of precision than spacecraft such as [Orion](/source/Orion_(spacecraft))[24] and [Shenzhou](/source/Shenzhou_(spacecraft)) due to the throttling abilities of the [SuperDraco](/source/SuperDraco) engines. The recovery areas for a 2a type abort are along the East Coast of the United States and [The Maritimes](/source/The_Maritimes) on Canada's Atlantic coast, with a 2b abort landing the Crew Dragon capsule near [Nova Scotia](/source/Nova_Scotia) and the 2c and 2d abort modes resulting in a landing in [Western Ireland](/source/Western_Ireland).[25] 1a and 1b aborts result in landings near the [American East Coast](/source/East_Coast_of_the_United_States).

Time Phase Recovery zone[25][26] T − 37 minutes Pad abort Launch abort armed; recovery zone in Florida coast T + 00 minutes 00 seconds Stage 1a Recovery zones from Florida coast to North Carolina T + 01 minutes 15 seconds Stage 1b Recovery zones along Virginia coast T + 02 minutes 32 seconds Stage 2a Stage separation; recovery zones along North American east coast T + 08 minutes 05 seconds Stage 2b Retrograde burn to land near Nova Scotia T + 08 minutes 28 seconds Stage 2c Prograde burn to land west of Ireland T + 08 minutes 38 seconds Stage 2d Retrograde burn to land west of Ireland T + 08 minutes 44 seconds Stage 2e Uses SuperDracos and Dracos to abort to orbit

## See also

- [Crew Dragon in-flight abort test](/source/Crew_Dragon_In-Flight_Abort_Test), a post-launch abort test of the SpaceX Crew Dragon spacecraft

- [Crew Dragon pad abort test](/source/Crew_Dragon_Pad_Abort_Test), a test of Dragon's abort system while on the launch pad

- [SpaceX Dragon](/source/SpaceX_Dragon), a family of SpaceX spacecraft

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Adapted from the Wikipedia article [Crew Dragon Launch Abort System](https://en.wikipedia.org/wiki/Crew_Dragon_Launch_Abort_System) by Wikipedia contributors ([contributor history](https://en.wikipedia.org/wiki/Crew_Dragon_Launch_Abort_System?action=history)). Available under [Creative Commons Attribution-ShareAlike 4.0 International](https://creativecommons.org/licenses/by-sa/4.0/). Changes may have been made.