Some sources point out that the shuttle cabin stayed intact following the solid rocket booster explosion, and that in fact, it is likely the crew died upon the cabin impact into the ocean.

Challenger's crew cabin after the explosion

The space shuttle was probably not designed for such scenario, but could the crew have survived if the cabin was equipped with parachutes, just like the cabins used for moon landings from the Apollo era? (To be clear: I mean parachutes attached to the cabin, not for crew members!)

The fact that the cabin part of the shuttle stayed intact at least demonstrates that the shuttle was designed in such a way that upon some catastrophic scenario, the very cabin of the shuttle was durable enough to "break off intact". The shape of the cabin (visible in the footage immediately following the explosion) does seem (at least remotely) similar to the shape of the moon-landing Apollo-era cabins. So in hindsight, I am thinking that it could have been designed as a "last resort survival cabin", should the shuttle catastrophically fail, and could have been equipped with parachutes, so that the cabin could descend on parachutes into the ocean?

  • $\begingroup$ I find it unlikely that post-breakup crew members would've been able to unstrap themselves, grab parachutes, and jump. Likely they were all unconscious or severely injured from the accelerations. That said, early designs of the shuttle (or at least the Buran) had eject seats for the two test pilots. $\endgroup$
    – Dragongeek
    Commented Sep 22, 2020 at 8:14
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    $\begingroup$ I meant parachutes attached to the cabin, not parachutes for the crew. I.e. when cabins from the moon era re-entered the atmosphere, they would parachute to the ocean... $\endgroup$ Commented Sep 22, 2020 at 8:16
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    $\begingroup$ For one thing, Apollo was a complete unit, as opposed to the cabin which wasn't made to be a complete unit. Also - if something had happened to Apollo after the escape tower jettison, they would have been in the same situation as Challenger, the re-entry parachutes weren't designed to operate as launch escape chutes. $\endgroup$
    – NKCampbell
    Commented Sep 22, 2020 at 17:25
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    $\begingroup$ @NKCampbell No. Apollo had viable abort modes throughout ascent. After LES jettison the whole CSM could sep off. en.wikipedia.org/wiki/Apollo_abort_modes $\endgroup$ Commented Sep 22, 2020 at 17:31
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    $\begingroup$ awesome - thanks for the info! @OrganicMarble :D $\endgroup$
    – NKCampbell
    Commented Sep 22, 2020 at 17:52

2 Answers 2


One of the major errors in the Space Transportation System (STS) design was the lack of a crew escape system usable from launch to landing.

Escape systems are costly, take up mass allowance that can be used for payload, and can cause problems on their own. The STS designers had an idée fixe that STS would be an "airliner to space" and would operate with airliner levels of safety. They concluded no escape system would be required due to what they considered a completely safe design.

Note that SpaceX's proposed Starship has no escape system, using similar rationale.

After the failure of STS-51L which destroyed the Challenger Orbiter and killed its crew, the rationale for not including such an escape system was heavily scrutinized by the press, public, and government. Studies were done regarding retrofitting escape systems into the existing Orbiter. Much of this work is mentioned in the NASA report IMPLEMENTATION OF THE PRESIDENTIAL COMMISSION RECOMMENDATIONS which summarized the work done after the STS-51L failure to return the STS to flight operations.

Note that the Rogers Commission recommendation re: escape was only...

Make all efforts to provide a crew escape system for use during controlled gliding flight.

...which was a 'softball'. However, a recommendation to provide a launch to landing escape system would have shut down the program, which at the time was supposed to be the sole US launcher of payloads...

The study, completed in September 1986, considered ejection seats, tractor rocket extraction of seated crew members, bottom bail-out, and tractor rocket extraction through the side hatch. Each option considered the crew size, the required orbiter modifications, and the implementation schedule. These options are summarized in the following paragraphs.

An ejection seat concept that would extract up to five astronauts was assessed. During operation, this concept would jettison the tops of both the crew module and the forward fuselage before propelling the crew out of the opening in individual ejection seats. The addition of ejection seats would require major structural modification of the overhead consoles, flight deck floor, crew module structure, and forward fuselage structure.

A new ejection seat design would be required because the ejection seats used during the orbital flight test program are very large, and installation of five seats would affect orbiter aft flight deck payload station usage. The estimated first availability of the ejection seat concept is mid-1990. This concept is not being pursued because of late availability, extensive vehicle modifications, and crew size limitations.

Another extraction concept investigated was a tractor rocket system that would extract up to six seated crew members. Once activated, this system would jettison the tops of the crew module and forward fuselage and extract the crew using tractor rockets. This concept would require modification of the crew module and forward fuselage structure, the flight deck floor, and overhead consoles, and would affect payload station usage. The earliest availability of this modification is mid-1990. This configuration is no longer being pursued because of late availability, vehicle modification requirements, and crew size limitations.

A bottom bail-out concept that would provide safe egress for up to eight crew members was also assessed. In this concept, a panel would be opened on the bottom of the orbiter to deploy a guide chute, permitting the astronauts to exit the orbiter through the chute. This concept would require extensive structural modifications, including installation of a deployable panel and pyrotechnic devices to open the panel, design and installation of the chute, and relocation of some subsystem components. Modifications could potentially be completed and certified by 1989, but the concept is not being considered because of the highly complex vehicle changes required.

The final concept evaluated was escape through the side hatch using tractor rockets to propel the astronauts out of the orbiter. This method, which could safely extract up to eight astronauts, would require early venting of the crew module to equalize the crew module internal pressure with the external pressure. After venting is completed, the side hatch would be jettisoned. The crew members would then exit sequentially by using the tractor rockets. Required orbiter changes include addition of a cabin vent capability, modification of the side hatch structure to allow for hatch jettison, addition of pyrotechnic devices to jettison the hatch, and installation of the tractor rocket system.

The CAIB Report chapter 10, paragraph 10.2 Crew Escape and Survival also contains a useful discussion of the situation, recommended for further reading.

I personally remember proposals to incorporate an escape capsule containing the entire crew compartment; this is not mentioned in the report although this newspaper story alludes to them.. Also note that the proposals mentioned would likely be ineffective for ascent.

In summary, a launch-to-landing escape system should have been provided from the beginning; IMHO if the design could not support it, the design should have been reconsidered. Retrofitting a launch-to-landing escape system into the existing vehicle was not practical.

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    $\begingroup$ Thank you so much for this great answer! Really appreciate this enlightening insight: when you say "I personally remember proposal to incorporate an escape capsule containing the entire crew compartment; this is not mentioned in the report.": you mean you were involved with NASA at the time? $\endgroup$ Commented Sep 22, 2020 at 13:34
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    $\begingroup$ @JanStuller I was a NASA contractor at Johnson Space Center working on shuttle from 1983-2011. $\endgroup$ Commented Sep 22, 2020 at 13:35
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    $\begingroup$ Yes, it's a very good answer. I tried to write a complementary one covering some of the rationale. Note that it doesn't really say it wouldn't have floated, just that making it float would require additional mass. Apollo capsules did float, the desire to retrieve them quickly may have been due to crew comfort considerations. $\endgroup$ Commented Sep 22, 2020 at 13:40
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    $\begingroup$ @janStuller, check Organic Marbles profile for other their other answers on similar topics, most are worth a read. Apollo capsules were nominally supposed to float for a couple of days, a lucky team of three got to verify that at sea, cannot find the quote from the results of that tests but apparently a three people in a craft with no keel on open ocean for a couple of days was very unpleasant. Re shuttle cabin floating a look at outcomes for ditched airliners in open water may be informative. $\endgroup$ Commented Sep 22, 2020 at 14:20
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    $\begingroup$ Armstrong and Scott's experience in Gemini also showed they didn't want to float along in the ocean for very long if at all possible @GremlinWranger $\endgroup$
    – NKCampbell
    Commented Sep 22, 2020 at 17:27

Similar systems certainly exist but not at this scale

Some spherical cow approximations - a parachute for a 70kg human weighs 14kg, giving 0.2kg of parachute per kg of payload.

The dry mass of the shuttle was around 165000kg, take 1/4 of that for mass of the crew section minus wings and fuselage for 41250kg gives a very approximate parachute weight of 8,250kg or 8 tonnes.

The space shuttle payload is around 29 tonnes, so there would be some left but this system would be using somewhere between one third and one quarter of the shuttle capacity, and only work if the shuttle suffers an inflight break up in an environment where the parachute helps.

So would not have helped Columbia, would not help for on pad emergencies, probably not help with catastrophic events early in flight and probably would not have helped Challenger since it is highly likely the in flight disintegration would not have left a structure that floated unless further mass added as airbags. Might have given more wiggle room in the Return to Landing Site.

And an incorrect activation of this system at pretty much any point in a normal flight will be quickly lethal, so this is a safety system that adds little and brings exciting failure modes. Designing the system to separate the crew cabin in flight and operate as a crew escape system allows it to perform over a wider range of conditions (deliberately disintegrate the orbiter) but this further increases the mass and adds more really exciting failure modes if say one destruction charge randomly fires.

I suspect if the astronauts had been offered 1/4 of the payload capacity for improved safety they would have happily used it, but probably in a different way to trying to recover the entire cabin. Moose comes to mind as a starting point.

One consequence of eating payload capacity is that more flights might be flown - if only 2/3 of our timeline payload capacity is available 50% more flights are required which means very approximately the program would have seen three major mishaps. If the safety improvement from the payload reduction does not save at least one of the crews then it actually makes things more dangerous over the life of the program.

Designing for safe spaceflight is a hard problem.

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    $\begingroup$ Wow, I never heard of MOOSE before. What a great idea. Also, Wikipedia at its best: "falling from orbit protected by nothing more than a spacesuit and a bag of foam was unlikely to ever become a particularly safe—or enticing—maneuver.[citation needed]" :-) $\endgroup$
    – TooTea
    Commented Sep 22, 2020 at 19:54
  • $\begingroup$ Both you and @OrganicMarble gave such great answers, I don't know which one to accept, as I'd feel awkward "not accepting" the other answer... $\endgroup$ Commented Sep 23, 2020 at 12:51
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    $\begingroup$ Go with OrganicMarble, means the question has an accepted answer and that one will be a better match for most google hits coming here $\endgroup$ Commented Sep 23, 2020 at 13:43
  • $\begingroup$ The tradeoff between escape system and payload is only required if you do not design the vehicle to accomplish both tasks. The easy answer for Administrator Fletcher and the Shuttle design team in 1973 was to design a vehicle with both. That option was available. A five segment instead of four segment SRB was always an option and in fact was considered post Challenger. The five segment SRB used currently by the SLS required small changes and could have been done in 1970's. Imagine a five segment STS with a fully functional B-58 type escape capsule and the same payload capacity. $\endgroup$ Commented Sep 23, 2020 at 14:48
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    $\begingroup$ Also, making up for lost payload capacity with more flights only works on average, it doesn't work for single payloads that are heavier than the reduced payload. I'm not sure how often the STS flew with a single, non-modular payload at its mass limits, but I can imagine some military payloads hitting that. ISS modules probably not, they were large, but mostly empty space. $\endgroup$ Commented Sep 23, 2020 at 16:29

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