In the question Why didn't the Space Shuttle have a launch escape system? there was discussion in the commentary about why the Space Shuttle could not safely abort through much of its envelope.

Why could the Space Shuttle not abort? What problems were there?


2 Answers 2


There were four types of intact aborts designed for Shuttle (not counting pad aborts). An intact abort is defined as one that returns the Orbiter intact to a runway.

In order of least to most desirable:

  1. Return to Launch Site (RTLS)
  2. Trans-Atlantic Abort (TAL)
  3. Abort Once Around (AOA)
  4. Abort to Orbit (ATO)

Only the ATO was ever performed in the Shuttle program.

enter image description here

In addition, contingency aborts were designed. A contingency abort is defined as one that allows the crew to bail out, but does not allow for safe return of the Orbiter.

There was a type of contingency abort called East Coast Abort Landing (ECAL) that could have allowed the orbiter to land...but since it was not a certified abort mode, it was still considered contingency.

Aborts could be performed either for performance reasons (failure of, or underperformance of one or more main engines) or systems reasons (cabin leak, loss of cooling, etc).

The aborts overlapped to some degree. Abort selection was based largely on vehicle state at the time of failure and performance. For example, the last possible time to select RTLS ocurred when the vehicle did not have enough propellant remaining to burn its velocity down to zero and then back up high enough to make it to Kennedy Space Center.

This paper gives good detailed information about all I have said.

The reason that the SRBs couldn't be "jettisoned" at any desired time is because the separation system as designed was not powerful enough to safely jettison the boosters if they were delivering a significant amount of thrust. The separation system simply severed the bolts holding the boosters to the External Tank and fired booster-mounted motors to provide clearance between them and the accelerating Orbiter/ET stack. If significant thrust loads had been present, then significant forces and moments would have been applied to the Orbiter/ET stack. It is possible that a more robust system could have been designed, but it wasn't incorporated in the system we had.

Similarly, the ET separation system simply severed the bolts holding the ET to the Orbiter. No separation motors were provided because the system was supposed to be in a low dynamic pressure environment at separation - the Orbiter manoeuvred away using its Reaction Control System jets. In a high dynamic pressure environment with significant propellant sloshing around in the tank, the potential for recontact with the Orbiter was high.

There was some discussion in the other question about the ejection seats used in early Columbia missions. These had limited utility - at a point in ascent the plume expanded out so much that the seat trajectory would pass through it and a "Negative seats" call was made. Similarly, on entry, the vehicle had to be going slow enough that a relatively unshielded ejecting crewmember could slow to a safe velocity.

I deeply wish that a better abort/escape system had been designed in, but that was not the reality of STS.

Edit: I just noticed that the crew training handbooks for intact and contingency aborts are available on Ken Hollis's Rocket Scientists page. These are wonderful references for STS aborts.

  • 1
    $\begingroup$ Super great answer and great links! Lovely manuals, they had an "abort mode rotary switch" on the control panel! My basic takeaway is that it is basically more problematic to separate an orbiter that is mounted on the side, than one that is mounted on the top, of the launcher. $\endgroup$
    – LocalFluff
    Commented Aug 12, 2015 at 5:32
  • $\begingroup$ @LocalFluff They did. See also the photo here. $\endgroup$
    – user
    Commented Aug 12, 2015 at 8:11
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    $\begingroup$ It seems to me, without having done the math, that even if it were possible to jettison a set of burning SRBs during launch, you'd be hard pressed to find a moment in time when doing so would not result in the orbiter passing through the exhaust trail of the SRBs. Sure, the orbiter could be designed to withstand such an abuse, but there's a lot that could be that wasn't... like the better abort/escape system. $\endgroup$
    – user
    Commented Nov 30, 2016 at 21:49

There were many abort modes on the Space Shuttle during launch, and the options changed depending on the specifics of each portion of the flight.

The main issue is that separating from two burning SRB's (Solid Rocket Boosters) producting 2.8 million pounds of thrust each is just plain not going to work. That is, the tiniest asymmetry in the disconnect and you are likely dead.

Thus the Shuttle was stuck for the first 2 minutes and change until the SRB's burned out.

In the hypersonic airflow, the slightest deviation from flight could destroy the Shuttle airframe, which is part of why abort was so difficult.

Once the SRB's were dropped, there was an RTLS (Return to Launch Site) which had been described by astronauts as better than nothing, but not with great confidence.

This would require the Shuttle to retain the External Tank for fuel, gimbal the engines to get high enough, and turn around and fly back towards the launch site (once out of the atmosphere to protect from the airflow) and then drop the tank once it had the energy to glide back to Kennedy.

There were Abort to Orbit modes (Used once I believe). Abort Once Around, and more.

But for much of the flight, with SRB's burning the options are hugely limited, since they cannot be turned off. They can be flight terminated by blowing a linear charge along the length of it, but that would also take out the tank, and thus probably the Orbiter if still attached.

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    $\begingroup$ I can't agree with "since in simulations, it was virtually impossible to succeed. " We flew thousands of successful RTLSs in sims. In fact, you had to do it to be qualified to fly the motion base simulator. $\endgroup$ Commented Aug 11, 2015 at 22:42
  • $\begingroup$ It's also an odd phrase "for much of the flight with SRBs burning". They only burned for 2 minutes of a 2 week mission (or, if you are talking about ascent, 2 minutes of an 8 1/2 minute ascent). $\endgroup$ Commented Aug 11, 2015 at 22:44
  • $\begingroup$ @OrganicMarble 2 of 8 minutes is pretty much 25% of the time. :) $\endgroup$
    – geoffc
    Commented Aug 11, 2015 at 23:11
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    $\begingroup$ @MSalters 5.6 million lbs of thrust. You do not depart from from 5.6 Mlbs of thrust and survive. You wait for them to stop boosting. $\endgroup$
    – geoffc
    Commented Sep 16, 2015 at 15:31
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    $\begingroup$ @MSalters: The orbiter fuel reserve only powered the OMS engines which were just too weak for atmospheric flight. $\endgroup$
    – Joshua
    Commented Feb 15, 2018 at 22:56

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