Deimos Rendezvous

8/12/2019 Deimos Rendezvous

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Mitigating Long Duration Biomedical Constraints

With Innovative Mission Architecture

James S. Logan, M.D.Group Manager, Human Test Support

Clinical Services Branch/SD3NASA Johnson Space Center

[email protected]

A Design Reference Mission Suite


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Mitigating Long Duration Biomedical Constraints

With Innovative Mission Architecture

Dan AdamoIndependent Astrodynamics Consultant

[email protected]

Special Acknowledgment


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> 270 Missions

> 500 People

> 100 Person-years

2011 Will Be Year 50 of human spaceflight!!

What are the implications of the EVIDENCE?


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Potential Lunar Long Duration Showstoppers*

Lunar Dust Wild Card Wild Card

RadiationEVA Hab

Surface

(EVA)Depth

Surface

(EVA)Depth

Hypogravity Nonstarter Nonstarter

SynergisticEffects

Element Sortie Outpost Settlement Frontier

* Assuming current technology and goal of civilization


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From Apollo Experience Report Protection Against Radiation

NASA TN D-7080 (1973)


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Risk of Exposure Induced Death

REID is a statistical approach pegged to a single radiation effect:

DEATH from cancer directly attributable to the exposure

In 1989 NASA accepted National Committee on Radiation Protection

(NCRP) recommendation of career dose limits corresponding to a

lifetime increase of 3% in cancer mortality

In 2000, NCRP kept that same 3% recommendation but alsosignificantly reduced the dose expected to reach the 3% lifetime risk.

45 y.o. male astronauts 10 year 3% career limit went from

325 rem in 1989 to 150 rem in 2000

35 y.o. female astronauts 10 year 3% career limit went from

175 rem in 1989 to 60 rem in 2000

This is NOT being more conservative, this is a realization that

radiation is more harmful than predicted


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New Radiation Protection Scale

RP100 Same radiation protection as Earth at sea level(1030 g/cm2 radiation shield equivalent or 100%)

RP50 Radiation shield equivalent to 18,000 ft altitude

RP2 Best ISS locations ~ 2% Earth protection

RP0.005 Radiation protection equivalent of space suit

(one-half of 1% Earth equivalent)


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X


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X X


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Implications

Moon/Mars may never more than sortie destinations*

Habitats must be shielded or underground Repeat EVAs (same crew) will be severely constrained

Robotic precursor missions must scout destinations

and prepare sites for human presence

Must determine Gravity Prescription for people,

plants, animals and multiple generations

*At least not without significant new investments

in research and enabling technology


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We need to stop this obsessive

preoccupation with spherical bodies at

the bottom of gravity wells with basicallyno atmosphere and no magnetic field.

These places just arent good for us - - at

least not as settlement, frontier orcivilization destinations.

James S. Logan, MD


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The Perfect Place

Low Delta-V

Lots of RESOURCES!

Little or No GRAVITY WELL

At or Near Earth Normal GRAVITY for

People, Plants and Animals

Natural RADIATION Protection

Permit Large Redundant Ecosystem(s)

Staging Area for Exploration and Expansion


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Round-Trip v To SomeNearby Destinations

Daniel R. Adamo 23 May 2010 21


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Accessible NEOs On 1 March 2010

Daniel R. Adamo 23 May 2010 22


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33 by 13 Km; 2,900 Cubic Kilometers

3% metals (gold, aluminum, platinum,zinc., iridium, etc.)

$20,000,000,000,000


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Virtues of DEIMOSThird Largest NEO (12.6 km mean diameter)

Less Delta-V than Moon, Phobos, Eros

(escape velocity of 12.5 mph (5.6 m/s; 20 km/h)!!

Only 20,000 km from Martian surface

Just above aerosynchronous orbit

Launch window every 2.14 years

Visualize all of Mars except extreme polar regions


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Virtues of DEIMOSRound trip light time of 0.13 seconds

Locked orbit around Mars

Couldbe captured carbonaceous chondrite

Low average density (1.471 g/cm2)

Could achieve all Mars surface explorationobjectives via short range human telepresence(ref.NASA Mars Design Reference Architecture [DRA] 5.0,

Section 3: Goals and Objectives)


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Duration of DEIMOS Mission

Outbound Leg : 240 Days (24%)

DEIMOS Stay Time: 469 Days (46.9%)

Return Leg: 249 Days (24%)

Total 949 Days

5.1% Pad (consumables) 1000 Days (100%)

~1000 Days is unacceptable re: RADIATION!

Therefore you must implement an RP100 environment at Deimos.

This will reduce your exposed days by half


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Mission Architecture Elements Series of Robotic Precursor Missions (RPMs) for

reconnaissance and habitat site preparation

Pre-emplacement of stay time, return consumables

as well as return entry vehicle at destination

(i.e. must rendezvous with Deimos)

Earth Parking Orbit (EPO) functions as fuel depot

Incremental build up of Mars Transit Vehicle

Abort To Destination (ATD) only option after TMI No aerobraking for Mars capture KISS principle

Direct entry upon Earth return


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Consumables Mass Estimate Calculations

Method Two (modified Logan method)

NASA Open Loop Life Support and modified ISS experience for

1000 days

Water: 18,000 kg

Oxygen: 2,170

Food: 5,700

Crew Supplies: 2,071Gasses Lost to Space: 2,071

Systems Maintenance 2,071

TOTAL 32,084

Outbound + Pad (Crew Vehicle): 9,336 kg

Preemplacement at DEIMOS: 22,747 kg

TOTAL 32,084


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Innovative Architecture

Elements:RADIATION PROTECTION

Radical redesign of Human Element (HE) vehicle toleverage all infrastructure mass (includingpropellant)

for radiation protection

At least RP5 required during transit (~50g/cm2)

Minimize radiation exposure by reducing Exposed

Days

Habitat site at destination mustprovide RP100

Use of NTM for radiation protection on return leg


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Destination Deimos Mars Transfer Vehicle (MTV)

Assumptions Propulsion stages made up of 15.7% structure

(tankage, plumbing,...)

A launch package is limited to 187.7 mT IMLEO(think Ares V i.e. real Heavy Lift not wimpy Heavy Lift)

Pre-emplace all return consumables at Deimos, including a crewEarth-return vehicle required for direct atmospheric entry

First heavy-lift launch package: Cargo Element #1 (CE1) First half of hypergolic propulsion stage required for Mars orbit

insertion (MOI) and Deimos rendezvous

Payload mass = 50.9 mT; IMLEO = 134.0 mT

Additional payload mass = 21.6 mT available (likely forhypergolic propellant supporting Earth orbit loiter to await laterlaunch packages)

CE2 is identical to CE1 and completes assembly of MOIstage


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Destination Deimos Mars Transfer Vehicle (MTV)

CE3 is unique Inflatable TransHab module (28.1 mT) plus open-loop crew

consumables for 8 months + 5.1% margin (9.4 mT) plus

additional radiation shielding (23.0 mT) to achieve RP5 Payload mass = 60.4 mT; IMLEO = 157.6 mT

Fourth heavy-lift launch package: Human Element (HE)

Cryogenic trans-Mars injection (TMI) stage (46.9 mT) plus crewexploration vehicle (CEV, 18.6 mT)

Payload mass = 65.5 mT; IMLEO = 170.3 mT

Without nuclear propulsion, there are no Earth return optionspost-TMI. Therefore, the CEV nominally undocks from the

MTV after the crew enters TransHab and is GO for TMI.Following successful TMI, the CEV is deorbited.

Total IMLEO = 595.8 mT (current ISS mass = 370.2 mT,

but this is not the IMLEO associated with ISS assembly)


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Mars Orbit Insertion andDeimos Rendezvous

Core Size: 0.460 km by 12 km


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Core Volume: 1.99 km3

Mean Density: 1.471 gm/cm

3

Core Mass: 2,927,290,000,000 kg

1% H2O => 29 Billion Liters





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The Art & Science of BIONEERING:

Turning this

I t thi


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Into this


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Questions?

Documents

Deimos Rendezvous