mission to mars piecescanada.marssociety.org/winnipeg/files/raftery_5-14-14.pdf · 2016-05-25 ·...

Copyright © 2010 Boeing. All rights reserved.

Mission to Mars in Six (not so easy) Pieces May 14, 2014


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Copyright © 2010 Boeing. All rights reserved. 2

Mars Mission Studies

National Aeronaut ics and

Space Admi nistration

Report of the 90-Day Study

on Human Exploration

of the Moon and Mars

November 1989

1960s 1970s 1980s 1990s 2000s

http://en.wikipedia.org/wiki/File:WernherVonBraunDasMarsprojekt.jpg


Mars Mission IMLEO (NASA Studies)

0

200

400

600

800

1000

1200

1400

1600

1 2 3 4 5 6 7 8 9 10 11 12

1 1988 Mars Expedition (Chem A/B)

2 1989 Mars Evolution (Chem A/B)

3 1990 90-Day Study (NTR)

4 1991 Synthesis Group (NTR)

5 1995 DRM 1 Long Stay (NTR)

6 1997 DRM 3 Refinement (NTR)

7 1998 DRM 4 Refinement (NTR or SEP)

8 1999 Dual Landers (SEP)

9 2000 DPT/NEXT (NTR or SEP)

10 2009 DRA 5 (NTR Option)

11 2009 DRA 5 (Chemical Option)

12 2013 DRA 5 Addendum (SEP Hybrid)

ISS IMLEO = 2800t


1998 1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012

88 96 101 98 105 112

106

92

97

102 108 113

100 110

104 111

114 121 117 122 126 128 131 134

115 118 123 119 129 132 135

116 120 124 127 130 133

FGB 1R

8P

2P 1P

2S 3S

3P

4P

5P 7P 9P

6P

4S 5S

11P 14P 16P

10P 12P

6S 7S 8S 9S 10S 11S 12S 13S

13P 15P 17P 19P 21P

18P 20P 22P

2R

23P 25P 27P

24P

14S 15S 16S 17S

26P 28P 30P

18S

19S

20S

29P 31P 33P 35P 37P

32P 34P 36P 38P 40P 42P

39P 41P 43P

44P 46P

45P 47P

48P

22S 24S 26S

21S 23S 25S 27S

28S 30S

29S 31S ATV1

HTV1 HTV2 HTV3

ATV2 ATV3

49P

SpXD SpX1

5R

4R

Building & Operating ISS


Injected Mass to Low Earth Orbit (IMLEO)

ISS

Assembly

Complete


Six (not so easy) Pieces for Mars

Orion

Space Launch System

Transit Habitat

Mars Lander

Mars Ascent Vehicle

SEP Tug


Element Phasing

Orion

Space Launch System

Transit Habitat

Mars Lander

Mars Ascent Vehicle

SEP Tug

Phase 1 – Earth’s

Gravity Well

Phase 2 – In-Space

Elements

Phase 3 – Mars

Gravity Well

Humans 2 Mars Drake Webinar

A trip to Mars with a return back to Earth is a double rendezvous problem

— Mars round-trip missions are flown in heliocentric space

— Relative planetary alignment is a key driver in the mission duration and propulsion required

Mars Trajectory Classes

8

EARTH DEPARTURE

MARS ARRIVAL

g

MARS DEPARTURE

VENUS SWING-BY

SUN

EARTH RETURN

EARTH DEPARTURE

MARS ARRIVAL

g

MARS DEPARTURE

SUN

EARTH RETURN

Example “Short-Stay” Opposition Class Mission

Example “Long-Stay” Conjunction Class Mission


Timing for a Mission to Mars

CREDIT: Lockheed Martin Corp.


Solar System Velocity Map

Reference: http://en.wikibooks.org/wiki/Space_Transport_and_Engineering_Methods/Orbital_Mechanics

http://en.wikibooks.org/wiki/Space_Transport_and_Engineering_Methods/Orbital_Mechanics


DV & Propellant Requirements for Mars

Earth

Launch

2

1

3

4

5

6

7

8

9

De

lta

Ve

loc

ity (

Km

/s)

HEO

Boost

TMI

Boost

Mars

Capture

Mars

EDL

Mars

Launch

HMO

Boost

10

11

12

20

10

30

40

50

60

70

80

90

100

110

120

EML2

Capture

Earth

EDL

Pro

pe

lla

nt

ma

ss

(M

t)

Red text denotes Aero-assisted Entry

6900* 210 * Three Block 2 SLS

Launches

Mars Ascent is

One of the Key

Architecture

Drivers


Stepping Stone Approach to Mars

• Understanding the Destination – Robotic Precursors

• Operations “Beyond the Belts” – Testing the waters

• Building the Spacecraft – Assembly and departure options

• Early Scouting – Free return trajectory options

• Proving the Pieces – Deimos and/or Phobos precursor missions

• First Landing – Flags, Footprints, & Follow-through

• Recurring Operations – Incremental Improvements

We need an incremental plan for developing and maturing

the six (not so easy) pieces


Mission Objectives and Trades

1. Deliver the crew safely to the surface of Mars and return them

safely to the Earth

2. Provide a good balance of mission risks to ensure a reasonable

(>90%) probability of accomplishing objective #1

Top Level Objectives:

• Crew size (3,4,5,6)

• Cost of the mission

• Cost to repeat the mission

• International participation

• Timing of the mission

• Mode of transportation

• Propulsion technology

• Aerobraking technology

Tradable parameters:

• Duration of surface stay

• Surface landing site

• Surface mobility

• Quantity and quality of science

• Quantity of sample returns

• In-situ propellant production

• Radiation protection


Mission Description Approach

Working Backwards:

• With Mars as the objective, first describe a full-up human landing

mission to Mars and then determine the precursor activities that can

best lead to and support this landing

• Provide a cadence of launches (no more than 2 per year) that could

reasonably be supported by an extrapolation of existing budgets

• Be mindful that significant elements on the critical path will need to

be provided by International Partners; Seek element roles that fit

well with these Partners


First Landing Campaign



Six Main Elements for Mars

Orion

Space Launch System

Transit Habitat

Mars Lander

Mars Ascent Vehicle

SEP Tug


Transit to Mars

18

Initial Mars Landing Campaign

Cargo Lander

on Mars

(July 2034)

2030 2031 2032 2033 2034 2035 2036 2037 2038 2039

Assembly at EML2

Spiral to EML2

Humans Land

on Mars

(May 2036)

Assy at EML2

Surface Ops

EML2

Transit

Crew Home

Feb 2038

Spiral to EML2

Transit

454 days

936 days

204 days 256 days 515 days


Cargo Launch to LEO

19


Spiral out to EML2

20


Spiral out to EML2

21


Arrival at EML2 Gateway

22


TransHab / Kickstage Launch

23


Arrival at EML2 Gateway

24


Cargo Departure for Mars

25


2013 Mars Design Reference Architecture – Departure with no kick-stage

– Krypton Propellant

– 4600s Isp (high efficiency)

– Cargo Outbound Total Prop: 24.8t

– Duration to Mars: 510 days

2033 Cargo Outbound Trajectory

Depart EML2:

1/7/2033

Thrust Segment 1:

48.7 days @ 4.2t prop

Coast Segment:

49.5 days

Thrust Segment 2:

326.9 days @ 17.3t

prop

Mars Capture 17K km:

89 days @ 3.3t prop

6/6/2034


Arriving at Mars

27


Cargo Lander Preparing for Entry

28


Cargo Lander during Aero Descent

29


Altitude Zone

Opportunity

(2003)

Viking 2

(1975)

Spirit

(2003)

Phoenix

(2008)

Mars 3

(1971)

Viking 1

(1975)

Mars

Pathfinder

(1996)

Historical Landing Sites

Curiosity

(2013)

+45 deg

-45 deg


Cargo Lander during Terminal Phase

31


Cargo Lander on the Surface

32


SEP Tug Climbs to 17,000 Km Orbit

33


Launch of the Crew Lander

34


Crew Cabin Configuration

35


Spiral out to EML2

36


Crew Lander at EML2 Gateway

37


Second Transhab Launch

38


Human Mission Elements at Gateway

39


Crew Launch

40


Crew Capture of Fuel Module

41


Orion Lunar Fly-by

42


Expedition Crew Arrives at Gateway

43


Expedition Crew Arrives at Gateway

44


SEP Refuel

45


Expedition Crew Departing for Mars


2013 Mars Design Reference Architecture – Departure with Earth Swing-By


– 3000s Isp (increased thrust)

– Crew Outbound Total Prop: 29.2t

– Duration to Mars 17K km: 256 days Does not include Earth Swing-By time

Duration trade on-going

2035 Crew Outbound Trajectory

Depart EML2:

8/3/2035

Thrust Segment 1:

211 days @ 25.4t prop

Mars Capture 17K km:

45 days @ 3.8t prop

4/15/2036


2013 Mars Design Reference Architecture – Currently refining crew outbound trajectory in STK/Astrogator

– 2014 goal of integrating Earth swing-by departure with heliocentric trajectory

2035 Crew Outbound Trajectory


Arriving at Mars

49


Crew during Entry

50


Crew Landing

51


Crew on the Surface of Mars

52



53



54



55



56



57



58



59


Crew Departing Mars

60


During Ascent

61


Mars MAV Analysis

Refinement of OTIS trajectory in STK – Use OTIS ephemeris through first stage jettison, then modeled rest of ascent with STK/Astrogator

62


Rendezvous in High Mars Orbit

63


Departing Mars for the Journey Home

64


2013 Mars Design Reference Architecture – Departure with kick-stage

3500Kg Inert

21,000Kg LOX/Methane

Isp 360


– 4600s Isp (high efficiency)

– Crew Return Total Prop: 11.0t

– Duration to EML2: 210.3 days

2037 Crew Return Trajectory

Arrive EML2:

2/2/2038 Thrust Segment 1: 80

days @ 3.8t prop

Coast Segment:

40.4 days

Thrust Segment 2:


Mars Departure 17K

km: 7/13/2037


2013 Mars Design Reference Architecture – Departure with no kick-stage


– 4600s Isp

– Cargo Return Total Prop: 4.4t

– Duration to EML2: 206.6 days

2037 Cargo Return Trajectory

Arrive EML2:

1/29/2038

Thrust Segment 1:


Coast Segment:

124.3 days

Thrust Segment 2:


Mars Departure 17K km:

7 days @ 0.3t prop

7/14/2037


Back at EML2

67


From EML2 to Earth

68


Crew Returns Home

69


Deimos Precursor

Example Mission



Deimos Mission Elements

Orion

Space Launch System

Transit Habitat Mars Ascent Vehicle

SEP Tug

Subscale Robotic

Lander (10t)

Mars Lander

Kick

Stage Sortie

Cab


Deimos Mission Campaign

Mars Surface

Transit to Mars

Crew at

Deimos

Return

Robotic Lander Sample Return

EML2 Ops

Deimos Crew

Arrives Home

Departure for

Mars

EML2 Ops

Spiral out to EML2

Tug arrival at

EML2

620 days

EM-11 EM-10

TH1

KS2

EM-12 EM-14

Orion

Fuel2

Orion

Fuel1

LEO

Translunar

Deep Space Deimos

2030 2031 2032 2033 2029


Deimos Mission Spacecraft

73


Arrival in High Mars Orbit

74


Crew at Deimos

75


Robotic Lander & Rovers

76


Loading Sample Return Cannisters

77


Asteroid Redirect Precursor



Asteroid Mission Elements

Orion

Space Launch System


SEP Tug Mars Lander

Asteroid Redirect

Vehicle (ARV) (50KW)

Block 1B

Exploration Augmentation

Module (EAM)


Exploration Augmentation Module

Crew operations at a redirected asteroid could be significantly enhanced by providing additional systems and EVA capabilities beyond those available from Orion only missions.

Placing an Exploration Augmentation Module (EAM) at the redirected asteroid would :

– Extend mission duration – Reduce EVA and consumables mass requirements on Orion

– Increase capability – Supply additional EVA functions and crew volume

– Reduce risk - Provide an abort location for Orion

80 Three Concepts


Russian SPM-derived EAM Example

81

• International Participation

• Robust Capabilities

*SPM – Science Power Module


ISS Test Campaign



ISS Test Elements

Orion

Space Launch System


SEP Tug Mars Lander

Solar Array Wing Test

Exploration Augmentation

Module (EAM)

High Energy Atmospheric

Entry Test (HEART)

mission to mars piecescanada.marssociety.org/winnipeg/files/raftery_5-14-14.pdf · 2016-05-25 ·...

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