New Mars Forums

Official discussion forum of The Mars Society and MarsNews.com

You are not logged in.

Announcement

Announcement: We've recently made changes to our user database and have removed inactive and spam users. If you can not login, please re-register.

#51 2020-01-11 22:45:03

SpaceNut
Administrator
From: New Hampshire
Registered: 2004-07-22
Posts: 17,778

Re: Reuseable Mars Lander, surface to orbit and back

With mars and even for the moon the fuel you used to get there is the fuel you will need to go home.

The large 599 page document
Mav is a 2 stage drop tanks on ascent design I think has 3 engines
stage 1 we have LCH4 2,298 kg and LOx 7,841 kg for tank mass
stage 2 it has LCH4 1,191 kg and LOx 3,523 kg for tank mass

MAV requires 6,978kg liquid methane and 22.728kg of liquid oxygen

better defining details are on pg 364

https://pdfs.semanticscholar.org/3d46/c … a3a780.pdf
Development of a Two-Stage Mars Ascent Vehicle Using In-Situ Propellant Production

Offline

#52 2020-01-12 10:56:49

SpaceNut
Administrator
From: New Hampshire
Registered: 2004-07-22
Posts: 17,778

Re: Reuseable Mars Lander, surface to orbit and back

This is from the DRM 5 designs
https://commons.wikimedia.org/wiki/File … A-5-A2.png
https://www.nasa.gov/sites/default/file … 6-ADD2.pdf

pg 364
stage 1 for ascent will have 4 engines and 2 tanks
stage 2 for ascent will have the cabin, 1 engine and 2 tanks

the descent will have all 4 tanks and 5 engines between the stages for landing with a base platform.

Stage 2
Ascent Module Dry Mass 5 engines w/No Crew 5,129 kg    Crew*(6)* 591 kg    *Sample*Return*Package* 261kg*
Ascent*Module*Mass*w/CH4*&*LOX* 5,129kg*  crew and payload return max 6,668kg * wet total 37,331 kg*
2 tanks CH4 Propellant  7,131kg
2 tanks Inert'Mass' 1,629'
2 tanks LOX Propellant 23,532kg
2 tanks Inert'Mass' 1,345'
Ascent*Module*Mass*(2nd*Stage)* 2 tanks and 4 engines removed basic 3,875kg*  5,038kg* 5,038kg*
ascent module Docked*Mass* 1 engine remains basic 4,727kg*  max 5,893kg* wet total 5,257kg *
stage 1 consists of attachment members and 2 tanks with 4 engines
total launch mass 38,076kg

descent has only a partial tank fuel loading
'LCH4'Propellant' 2,917
'LOX'Propellant' 4,214' *table location error
landing TOTALS''' 13,536

continued on pg 368
Design'Constraints/Parameters'
• Ascent'rendezvous'loca#on:''High''
Mars'Orbit'
• Ascent'Dura#on:'43'hours'(max.)'
• Samples'returned'from'surface:'250'kg'
• ISRU'assump#on:''LOX'for'ascent'
• MAV'Opera#onal'Life:'2'days'
• MAV'Total'Service'Life:'~1669'days'
• MAV'Surface'Exposure:'~1344'days'
• Total'Reserve:'30%'(20%'Growth,'10%'PMR'on'inert'mass)
'Crew'Cabin'
• Crew'Capacity:'6'
• Pressurized'Volume:'18'm3'
Two'Propulsion'Stages'
• Stage'1'#'Main'Engines:'4''
• Stage'2'#'Main'Engines:'1'
• “Nested”'Propellant'Tanks'
• Main'Engine'and'RCS'Propellants:'LO2/CH4'
• Main'Engine'Isp'(100%):'360'sec'
• Main'Engine'Thrust'(100%):'100'kN'ea'
• Total'Thrust'(100%):'500'kN'

Crew'Cabin' 3,431' 4,438'
''C&DH 265 265
''GN&C 75 75
''C&T 82 82
''Power 371 371
''Thermal 217 217
''ECLS 364 364
''EVA 110 165
''Structures'&' Mechanisms 1,700 1,700
''Human'Factors 47 82
''Crew'&'Crew;Worn 0 787
''Cargo' 0' 250'
''Non;Prop.'Fluids 200 80

Offline

#53 2020-01-12 22:58:38

SpaceNut
Administrator
From: New Hampshire
Registered: 2004-07-22
Posts: 17,778

Re: Reuseable Mars Lander, surface to orbit and back

The Comparison of oxygen liquefaction methods for use on the Martian surface

one issue is the getting of the oxygen to be able to condense and liquify it for the trip home starts with either the mars air or from the mars soils for the source to which the oxygen is gained. Each has a mass and energy penalty that must be within payload capability to and for manned missins for mars.

http://systemarchitect.mit.edu/docs/hofstetter05b.pdf
Affordable Human Moon and Mars Exploration through Hardware Commonality

Offline

Board footer

Powered by FluxBB