Author Topic: Lockheed Martin Orbiting Mars Laboratory discussion thread.  (Read 72553 times)

Offline russianhalo117

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Re: Lockheed Martin Orbiting Mars Laboratory discussion thread.
« Reply #260 on: 06/15/2018 12:10 AM »

5- Like with SpaceX, I hate having a design that has the crew and cargo having to elevator down from several stories up.


Crew, not the big cargo.

From the published PDF in this thread:

Quote
The center section of the aft end, located between the six main engines, is a retractable equipment lift that lowers to give the crew access to the rovers and other equipment for surface science operations.
http://www.lockheedmartin.com/content/dam/lockheed/data/space/photo/mbc/MBC_Updates_IAC_2017.pdf

If you look at page 2 of said PDF, you can see the cylindrical equipment lift that rests below the hydrogen tank and lowers to the ground.

But a cargo version would probably use externally mounted cargo anyways. From LMO, you still get about 30 mT down if you expend 4 km/s to do a propulsive landing(probably can't do hot re-entry with external cargo). On the Moon, you get about 85 mT down with self-ferry back up and 130 mT down one way. Deals with the main problem with this design which is payload volume.


PDF link is dead.

Offline Coastal Ron

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Re: Lockheed Martin Orbiting Mars Laboratory discussion thread.
« Reply #261 on: 06/15/2018 05:53 AM »

5- Like with SpaceX, I hate having a design that has the crew and cargo having to elevator down from several stories up.


Crew, not the big cargo.

From the published PDF in this thread:

Quote
The center section of the aft end, located between the six main engines, is a retractable equipment lift that lowers to give the crew access to the rovers and other equipment for surface science operations.
http://www.lockheedmartin.com/content/dam/lockheed/data/space/photo/mbc/MBC_Updates_IAC_2017.pdf

If you look at page 2 of said PDF, you can see the cylindrical equipment lift that rests below the hydrogen tank and lowers to the ground.

But a cargo version would probably use externally mounted cargo anyways. From LMO, you still get about 30 mT down if you expend 4 km/s to do a propulsive landing(probably can't do hot re-entry with external cargo). On the Moon, you get about 85 mT down with self-ferry back up and 130 mT down one way. Deals with the main problem with this design which is payload volume.
PDF link is dead.

Try:

https://www.lockheedmartin.com/content/dam/lockheed-martin/eo/photo/webt/Mars-Base-Camp-Update-and-New-Concepts.pdf
If we don't continuously lower the cost to access space, how are we ever going to afford to expand humanity out into space?

Online brickmack

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Re: Lockheed Martin Orbiting Mars Laboratory discussion thread.
« Reply #262 on: 09/29/2018 04:37 PM »
Earlier this month, Lockheed presented a paper at the AIAA Space Forum about their MADV. Lots of new information in there on performance numbers, staging orbits, and the propellant transport/depot system

Online TrevorMonty

Earlier this month, Lockheed presented a paper at the AIAA Space Forum about their MADV. Lots of new information in there on performance numbers, staging orbits, and the propellant transport/depot system
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