Crew Dragon Launch Abort System

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Crew Dragon Launch Abort System
Crew Dragon Pad Abort Test (16814592054).jpg
Crew Dragon prototype DragonFly [1] performing a pad abort demonstration.
Manufacturer SpaceX
Country of origin United States
Launch history
StatusOperational
Crew Dragon Launch Abort System
Powered by8 × SuperDraco (4 × pairs of 2) [2]
Maximum thrust71 kN
Burn time25 seconds
Propellant N2O4 / CH6N2

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

Contents

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. Launch escape system diagram.jpg
A figure showing the Apollo spacecraft's launch abort system.
A diagram showing the configuration of Crew Dragon Endeavor during the Demo-2 mission. Dragon 2 DM-2 03.jpg
A diagram showing the configuration of Crew Dragon Endeavor during the Demo-2 mission.

Traditionally, spacecraft like Apollo and Soyuz have utilized solid-fueled "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 and the cancellation of SpaceX's 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 or Soyuz, Dragon keeps the trunk attached during an abort for aerodynamic stability. [11]

History

Pad Explosion

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

A diagram demonstrating a check valve. Vertical Ball check valve.jpg
A diagram demonstrating a 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) are opened, causing the helium to flow through one-way "check" valves into the propellant tanks, pushing the fuel into the combustion chamber. [15]

In this incident, however, the one-way oxidizer valve had allowed nitrogen tetroxide (NTO) 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.

On 19 January 2020, 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 successfully separated with the Falcon 9 rocket, with the rocket breaking up seconds later under the intense aerodynamic forces of max-q. [20]

After separating the trunk, Crew Dragon reached an apogee of 42 kilometers before splashing down in the 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 calls out switches between abort modes.

For typical launches, recovery zones are placed along the 51.64 degree inclination [23] of the ISS, and can be targeted with higher levels of precision than spacecraft such as Orion [24] and Shenzhou due to the throttling abilities of the SuperDraco engines. The recovery areas for a 2a type abort are along the East Coast of the United States and the Canadian Maritime provinces, with a 2b abort landing the Crew Dragon capsule near Novia Scotia and the 2c and 2d abort modes resulting in a landing in Western Ireland. [25] 1a and 1b aborts result in landings near the American East Coast.

TimePhaseRecovery Zone [26] [25]
T - 37 minutesPad AbortLaunch abort armed; Recovery zone in Florida Coast
T + 00 minutes, 00 secondsStage 1aRecovery zones from Florida Coast to North Carolina
T + 01 minutes, 15 secondsStage 1bRecovery zones along Virginia Coast
T + 02 minutes, 32 secondsStage 2aStage separation; Recovery zones along North American east coast
T + 08 minutes, 05 secondsStage 2bRetrograde burn to land near Novia Scotia
T + 08 minutes, 28 secondsStage 2cPrograde burn to land west of Ireland
T + 08 minutes, 38 secondsStage 2dRetrograde burn to land west of Ireland
T + 08 minutes, 44 secondsStage 2eUses SuperDracos and Dracos to abort to orbit

See also

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