Timeline for Could the SS520 be used to return a payload from Mars to Earth?
Current License: CC BY-SA 4.0
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| Feb 22, 2022 at 22:26 | answer | added | Mark | timeline score: 2 | |
| Feb 21, 2022 at 15:37 | comment | added | BrendanLuke15 | Previous US Earth entry vehicles (Stardust, Genesis, OSIRIS-REx) all used a ~45 kg, 60° sphere cone design, MSR currently looks to be evolving to a new generation entry vehicle (no parachute!), and similar weight (iirc). Hayabusa(& -2) used a smaller ~19 kg entry vehicle so existing designs are still a ways away from ~5 kg, if that number maths out for the Mars case. | |
| Dec 13, 2020 at 23:15 | history | edited | uhoh |
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| Dec 13, 2020 at 23:15 | comment | added | uhoh | Different but related: How do spherical SRB's compare to long skinny ones? What do their thrust curves look like? | |
| Aug 11, 2020 at 15:00 | history | tweeted | twitter.com/StackSpaceExp/status/1293200520845328384 | ||
| Aug 11, 2020 at 13:03 | history | edited | Christopher James Huff | CC BY-SA 4.0 |
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| Aug 11, 2020 at 12:57 | comment | added | Heopps | About the rocket - I suppose there are at least two problems. First - to deliver the rocket to Mars. It weights over 2600 kg, and also long and thin - not the best shape for atmospheric reentry. (altough the latter can be redesigned). Second - it should be usable at Martian temperatures. For Mars Sample Return mission a special cover for thermal conditioning is planned AFAIK. | |
| Aug 11, 2020 at 12:00 | history | asked | Steve Linton | CC BY-SA 4.0 |