Mission to Mars Piecescanada.marssociety.org/winnipeg/files/Raftery_5-14-14.pdf · 2016-05-25 ·...
Transcript of Mission to Mars Piecescanada.marssociety.org/winnipeg/files/Raftery_5-14-14.pdf · 2016-05-25 ·...
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Copyright © 2010 Boeing. All rights reserved.
Mission to Mars in Six (not so easy) Pieces May 14, 2014
Copyright © 2012 Boeing. All rights reserved.
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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
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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
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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
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Injected Mass to Low Earth Orbit (IMLEO)
ISS
Assembly
Complete
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Six (not so easy) Pieces for Mars
Orion
Space Launch System
Transit Habitat
Mars Lander
Mars Ascent Vehicle
SEP Tug
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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
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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
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Timing for a Mission to Mars
CREDIT: Lockheed Martin Corp.
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Solar System Velocity Map
Reference: http://en.wikibooks.org/wiki/Space_Transport_and_Engineering_Methods/Orbital_Mechanics
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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
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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
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13
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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
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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
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First Landing Campaign
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Six Main Elements for Mars
Orion
Space Launch System
Transit Habitat
Mars Lander
Mars Ascent Vehicle
SEP Tug
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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
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Cargo Launch to LEO
19
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Spiral out to EML2
20
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Spiral out to EML2
21
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Arrival at EML2 Gateway
22
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TransHab / Kickstage Launch
23
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Arrival at EML2 Gateway
24
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Cargo Departure for Mars
25
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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
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Arriving at Mars
27
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Cargo Lander Preparing for Entry
28
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Cargo Lander during Aero Descent
29
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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
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Cargo Lander during Terminal Phase
31
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Cargo Lander on the Surface
32
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SEP Tug Climbs to 17,000 Km Orbit
33
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Launch of the Crew Lander
34
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Crew Cabin Configuration
35
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Spiral out to EML2
36
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Crew Lander at EML2 Gateway
37
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Second Transhab Launch
38
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Human Mission Elements at Gateway
39
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Crew Launch
40
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Crew Capture of Fuel Module
41
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Orion Lunar Fly-by
42
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Expedition Crew Arrives at Gateway
43
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Expedition Crew Arrives at Gateway
44
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SEP Refuel
45
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Expedition Crew Departing for Mars
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2013 Mars Design Reference Architecture – Departure with Earth Swing-By
– Krypton Propellant
– 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
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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
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Arriving at Mars
49
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Crew during Entry
50
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Crew Landing
51
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Crew on the Surface of Mars
52
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Crew on the Surface of Mars
53
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Crew on the Surface of Mars
54
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Crew on the Surface of Mars
55
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Crew on the Surface of Mars
56
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Crew on the Surface of Mars
57
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Crew on the Surface of Mars
58
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Crew on the Surface of Mars
59
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Crew Departing Mars
60
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During Ascent
61
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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
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Rendezvous in High Mars Orbit
63
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Departing Mars for the Journey Home
64
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2013 Mars Design Reference Architecture – Departure with kick-stage
3500Kg Inert
21,000Kg LOX/Methane
Isp 360
– Krypton Propellant
– 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:
89.9 days @ 7.2t prop
Mars Departure 17K
km: 7/13/2037
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2013 Mars Design Reference Architecture – Departure with no kick-stage
– Krypton Propellant
– 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:
52.2 days @ 2.4t prop
Coast Segment:
124.3 days
Thrust Segment 2:
19.1 days @ 1.7t prop
Mars Departure 17K km:
7 days @ 0.3t prop
7/14/2037
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Back at EML2
67
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From EML2 to Earth
68
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Crew Returns Home
69
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Deimos Precursor
Example Mission
Copyright © 2012 Boeing. All rights reserved.
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Deimos Mission Elements
Orion
Space Launch System
Transit Habitat Mars Ascent Vehicle
SEP Tug
Subscale Robotic
Lander (10t)
Mars Lander
Kick
Stage Sortie
Cab
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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
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Deimos Mission Spacecraft
73
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Arrival in High Mars Orbit
74
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Crew at Deimos
75
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Robotic Lander & Rovers
76
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Loading Sample Return Cannisters
77
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Asteroid Redirect Precursor
Copyright © 2012 Boeing. All rights reserved. 78
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Asteroid Mission Elements
Orion
Space Launch System
Transit Habitat Mars Ascent Vehicle
SEP Tug Mars Lander
Asteroid Redirect
Vehicle (ARV) (50KW)
Block 1B
Exploration Augmentation
Module (EAM)
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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
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Russian SPM-derived EAM Example
81
• International Participation
• Robust Capabilities
*SPM – Science Power Module
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ISS Test Campaign
Copyright © 2012 Boeing. All rights reserved. 82
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ISS Test Elements
Orion
Space Launch System
Transit Habitat Mars Ascent Vehicle
SEP Tug Mars Lander
Solar Array Wing Test
Exploration Augmentation
Module (EAM)
High Energy Atmospheric
Entry Test (HEART)
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84