NASA/TM–2007–214762
Decadal Planning Team Mars Mission Analysis Summary Bret G. Drake National Aeronautics and Space Administration Lyndon B. Johnson Space Center Houston, Texas 77058
Previously released in February 2007 as JSC 63725
July 2007
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NASA/TM–2007–214761
Decadal Planning Team Mars Mission Analysis Summary Bret G. Drake National Aeronautics and Space Administration Lyndon B. Johnson Space Center Houston, Texas 77058
Previously released in February 2007 as JSC 63725
July 2007
Available from: NASA Center for AeroSpace Information 7115 Standard Drive Hanover, MD 21076-1320 301-621-0390
National Technical Information Service 5285 Port Royal Road Springfield, VA 22161 703-605-6000
This report is also available in electronic form at http://ston.jsc.nasa.gov/collections/TRS/
FOREWORD
In June 1999 the NASA Administrator chartered an internal NASA task force, termed the Decadal Planning Team, to create new integrated vision and strategy for space exploration. The efforts of the Decadal Planning Team evolved into the Agency-wide team known as the NASA Exploration Team (NEXT). This team was also instructed to identify technology roadmaps to enable the science-driven exploration vision, established a cross-Enterprise, cross-Center systems engineering team with emphasis focused on revolutionary not evolutionary approaches. The strategy of the DPT and NEXT teams was to “Go Anywhere, Anytime” by conquering key exploration hurdles of space transportation, crew health and safety, human/robotic partnerships, affordable abundant power, and advanced space systems performance. Early emphasis was placed on revolutionary exploration concepts such as rail gun and electromagnetic launchers, propellant depots, retrograde trajectories, nano structures, and gas core nuclear rockets to name a few. Many of these revolutionary concepts turned out to be either not feasible for human exploration missions or well beyond expected technology readiness for near-term implementation. During the DPT and NEXT study cycles, several architectures were analyzed including missions to the Earth-Sun Libration Point (L2), the Earth-Moon Gateway and L1, the lunar surface, Mars (both short and long stays), one-year round trip Mars, and near-Earth asteroids. Common emphasis of these studies included utilization of the Earth-Moon Libration Point (L1) as a staging point for exploration activities, current (Shuttle) and near-term launch capabilities (EELV), advanced propulsion, and robust space power. Although there was much emphasis placed on utilization of existing launch capabilities, the team concluded that missions in near-Earth space are only marginally feasible and human missions to Mars were not feasible without a heavy lift launch capability. In addition, the team concluded that missions in Earth’s neighborhood, such as to the moon, can serve as stepping-stones toward further deep-space missions in terms of proving systems, technologies, and operational concepts. The material contained in this presentation was compiled to capture the work performed by the Mars Sub-Team of the DPT NEXT efforts in the late 1999-2001 timeframe.
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CONTENTS
1.0 2.0
DPT Mars Short-Stay Mission Architecture Status .................................................. 1 DPT Mars Long-Stay Mission Architecture Status................................................. 44
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Exploration Office
DPT Mars Short-Stay Mission Architecture Status Mid-Term (2018) Nuclear Thermal Propulsion System Option
Bret G. Drake NASA/Johnson Space Center July 11, 2000
BGD/Short Stay Architecture 7/11/2000 6
1
Outline Exploration Office
•
Ground Rules and Assumptions
•
Trajectory Options
•
Mission Case Studies
•
Systems Overview – Transit Habitat – Descent / Ascent Vehicle – Interplanetary Transportation
BGD/Short Stay Architecture 7/11/2000 6
•
Technology Needs
•
Architecture Summary
2
Guiding Principles Exploration Office
• Go Anywhere - Go Anytime • Avoid political obstacles - No HLLV • Limit the total mission duration (goal of one-year) • Push advanced technologies – Advanced space transportation - NTR – Advanced materials (factor of 9)
BGD/Short Stay Architecture 7/11/2000 6
3
Mars Short-Stay Ground Rules and Assumptions Exploration Office
• Detailed GR&A provided in the “Mars ‘Short-Mission’ Scenario/Architecture GR&A” document dated 4-10-2000 • Primary DPT GR&A which drive this architecture include: – – – – – – – – –
“Go Anywhere – Go Anytime” Philosophy Short stay on Mars Short total mission duration – goal of one year round-trip First cargo mission 2016, First human mission 2018 Four crew Zero-g transits Technology freeze to TRL 6 by 2011 Factor of nine improvement for primary and secondary structures Transportation Assumptions • EELV-H for cargo delivery to Earth orbit • Bi-Modal Nuclear Thermal Propulsion for interplanetary transits • Long-term cryogenic fluids storage
BGD/Short Stay Architecture 7/11/2000 6
4
Purpose of Architecture Analysis Exploration Office
•
Development of architectures serve as an “Existence Proof” of the various technology options and mission approaches under consideration – Feasibility check – Plausibility
•
Architecture analysis includes detailed end-to-end analysis of – – – – – – – –
Mission goals and objectives Mission sequence Approaches to minimizing risks and maximizing crew safety Vehicles and systems Technology applicability and benefits System drivers Operations concepts Schedules
BGD/Short Stay Architecture 7/11/2000 6
From Earth – to the destination – back to Earth
5
Architecture Study Team Exploration Office
Architecture Architecture Integration Integration (JSC) (JSC)
DPT Transportation (MSFC)
Science/Scenario (HQ, ?)
Cost Analysis (LaRC)
Trajectory Trajectory// Mission MissionAnalysis Analysis
NTR NTRAnalysis Analysis
Crew CrewSystems Systems
Power PowerSystem System
Operations Operations
Aeroassist Aeroassist
Risk RiskAnalysis Analysis
Ground GroundProcessing Processing
(JSC, (JSC,MSFC, MSFC,GRC) GRC)
(JSC) (JSC)
BGD/Short Stay Architecture 7/11/2000 6
(GRC) (GRC)
(LaRC, (LaRC,JSC) JSC)
(JSC) (JSC)
(JSC) (JSC)
(GRC) (GRC)
(KSC) (KSC)
6
Study Process Exploration Office
(JSC) (JSC)
• Transit Habitat • Descent/Ascent Vehicle
Results Resultsand andIssues Issues (Architecture (ArchitectureTeam) Team)
Transportation Transportation Studies Studies (MSFC) (MSFC)
• Abundant Chemical, Tethers, EP, NTR, VASIMR, Pulsed Detonation, M2P2, Beamed MPD, etc.
NTR NTRCase CaseStudy Study Analysis Analysis (GRC) (GRC)
• Feasibility • Initial Mass in LEO • Number of Launches
Payload Payload//Mission Mission Refinement Refinement NTR as an example
Initial InitialPayload Payload Definition Definition
(JSC) (JSC)
• • • •
Trajectory Options Advanced Materials Trip-time sensitivities Vehicle configurations
NTR NTRConcept Concept Initialized Initialized
(Architecture (ArchitectureTeam) Team) • Initialization Package • Case Studies Defined • System Concepts Refined
Architecture Architecture Refinement Refinement
BGD/Short Stay Architecture 7/11/2000 6
7
Trajectory Options Under Consideration Exploration Office
•One-Year Mission – Missions with short Mars surface stays with total mission duration of one year or less SUN
γ
•Opposition Class Mission – Variations of missions with short Mars surface stays and may include Venus swing-by SUN
γ
•Conjunction Class Mission – Variations of missions with long Mars surface stays Outbound Surface Stay Inbound
BGD/Short Stay Architecture 7/11/2000 6
γ
8
Total Mission ∆V vs Earth Departure Date Short-Stay Mars Missions Exploration Office
Total Mission ∆V vs Earth Departure Date 32000 30000 28000 26000
Assumptions - All propulsive mission - Earth parking orbit = 407 km - Mars parking orbit = 500 km - 40 day Mars stay - Figure of merit = Total ∆V (all legs)
468
24000
Mission ∆V (m/s)
Inbound Venus Swingby
497
22000
583
519
20000 453
18000
No Inbound Venus Swingby
494
446
365 Day Mission No Venus Swby
515 527
Local Min ∆ V No Venus
545
585 661
16000
Local Min ∆ V Venus Swby (Return Leg
619
14000
582
12000 10000 8000 Local Min ∆ V One Way Cargo
6000 4000
275 day
01-Jan-15
31-Dec-16
205 31-Dec-18
206 30-Dec-20
347 30-Dec-22
332 29-Dec-24
312 29-Dec-26
300 28-Dec-28
28-Dec-30
27-Dec-32
Earth Departure Date
BGD/Short Stay Architecture 7/11/2000 6
9
Minimum Solar Distance vs. Mission Opportunity Short-Stay Mars Missions Exploration Office
Radiation doses during solar fly-by can increase 2-8 times Earth
1.000 Long-Stay Mission with Fast Transits to-from Mars
Venus
Mercury
Minimum Solar Distance (AU)
0.900 0.800 0.700
O O
x2
(unless indicated)
O O
O
0.600 No inbound Venus swingby
0.500
365 Day Mission No Venus Swby
Inbound Venus swingby
O
Local Min ∆ V No Venus Swby
OO O
Local Min ∆ V Venus Swby
0.400 0.300
x8
0.200 0.100
Assumptions - All propulsive mission - Earth parking orbit = 407 km - Mars parking orbit = 500 km - 40 day Mars stay - Figure of merit = Total ∆ V (all legs) - All minimum solar distances are due to inbound leg(s) unless accompanied by an "O" indicating minimum solar distance due to the outbound leg
(Return Leg Only)
0.000 1-Jan-15
31-Dec-16
31-Dec-18
30-Dec-20
30-Dec-22
29-Dec-24
Earth Departure Date
BGD/Short Stay Architecture 7/11/2000 6
29-Dec-26
28-Dec-28
28-Dec-30
27-Dec-32
G. Condon/JSC/EG
10
Mars Short-Stay Initial Case Studies Exploration Office
• Prior to performing detailed architectural analysis a series of focused case studies were conducted • Primary case study variables included – WORST versus BEST mission opportunity – HIGH versus LOW Mars parking orbit – Pre-deploy LANDER versus pre-deploy LANDER & RETURN VEHICLE
• The results were used to determine the relative benefits and technology needs for the various mission approaches under consideration
BGD/Short Stay Architecture 7/11/2000 6
11
Mars Short-Stay Initial Case Studies Exploration Office
Opportunity
Energy Level
Trip Time
6.1
Worst (2026)
Minimize ∆V
< 650 days
500 x 500 km
Lander
6.2
Worst (2026)
Minimize ∆V
< 650 days
250 x 33,793 km
Lander
6.3
Worst (2026)
Minimize ∆V
< 650 days
500 x 500 km
Lander & Return Vehicle
6.4*
Worst (2026)
Minimize ∆V
< 650 days
250 x 33,793 km
Lander & Return Vehicle
6.5
Best (2018)
Minimize ∆V
< 650 days
500 x 500 km
Lander
6.6*
Best (2018)
Minimize ∆V
< 650 days
250 x 33,793 km
Lander
6.7
Best (2018)
One-Year
< 365 days
500 x 500 km
Lander
6.8
Best (2018)
One-Year
< 365 days
250 x 33,793 km
Lander
6.9
Best (2018)
One-Year
< 365 days
500 x 500 km
Lander & Return Vehicle
6.10
Best (2018)
One-Year
< 365 days
250 x 33,793 km
Lander & Return Vehicle
6.11
Best (2018)
Minimize ∆V
< 650 days
500 x 500 km
Lander & Return Vehicle
6.12
Best (2018)
Minimize DV
< 650 days
250 x 33,793 km
Lander & Return Vehicle
BGD/Short Stay Architecture 7/11/2000 6
Mars Orbit
Pre-Deploy
12
Mars Mission Overview (NTR Option) Exploration Office Earth return vehicle propulsively captures into Mars orbit and remains
Cargo Vehicles Delivered to Low-Earth Orbit via EELV-H Launch Vehicles • Descent-Ascent Lander • Descent-Ascent Lander NTR • Earth Return NTR • Earth Return Propellant • TMI/MOI Propellant
Ascent/Descent Vehicle aerocaptures and remains in Mars orbit for the crew
Crew rendezvous with Descent/Ascent Vehicle and Earth Return Vehicle
30 day Science mission Crew travels to Mars. Propulsively captures into Mars orbit
Earth Return Vehicle remains in Mars orbit
Crew ascends and rendezvous with waiting Earth Return Vehicle
Mars Surface
Crew Vehicles Delivered to Low-Earth Orbit via EELV-H Launch Vehicles • Transit Habitat • Transit Habitat NTR Crew delivered to Mars Vehicle via Shuttle
Earth Orbit
BGD/Short Stay Architecture 7/11/2000 6
Crew returns to Earth with Direct entry at Earth
13
Short-Stay Mission Sequence Exploration Office
Mission 4
Mission 3
Mission 2
Mission 1
Mars Flight
2014
1 Cargo
2015
2016
2017
2018
2019
2020
2021
2022
2023
2024
Return Vehicle
2026
Crew Transits
Arrival
Descent/Ascent
2025
Surface Mission Cargo Outbound Unoccupied Wait
2 Crew
3 Cargo 4 Crew
5 Cargo 6 Crew
7 Cargo 8 Crew
BGD/Short Stay Architecture 7/11/2000 6
Transit Vehicle Departure
Arrival
Return Vehicle Arrival
Descent/Ascent
Transit Vehicle Departure
Arrival
Return Vehicle Arrival
Descent/Ascent
Transit Vehicle Departure
Arrival
Return Vehicle Arrival
Descent/Ascent
Transit Vehicle Departure
Arrival
14
Mars Short-Stay Mission Initial NTR Case Study Results Exploration Office
Worst Opportunity (2026 No Swing-by)
Best Opportunity (2018)
3,000.000
Descent / Ascent Vehicle 2,500.000
Piloted Round-Trip Piloted Earth-Return
Initial Mass in LEO (mt)
Piloted Outbound
ISS at Assembly Complete (470 t)
2,000.000
1,500.000
Long LongStay Stay Mission Mission
1,000.000
500.000
0.000 6.1 2026 6.2 2026 6.3 2026 6.4 2026 6.5 2018 6.6 2018 6.7 2018 6.8 2018 6.9 2018 Min ?V Min ?V Min ?V Min ?V Min ?V Min ?V 1Year 1Year 1Year LMO HMO LMO HMO LMO HMO LMO HMO LMO
BGD/Short Stay Architecture 7/11/2000 6
6.10 2018 1Year
6.11 6.12 2018 Min 2018 Min ?V LMO ?V HMO
Ref. Glenn Research Center
15
EELV-H Launch/Assembly Scenario Best Case (2018) Mission Opportunity Exploration Office
LANDER AND RETURN PROPELLANT
7
4 Vehicle 3 Propellant Tanks
9
2 Vehicle 7 Propellant Tanks
? Cargo Launches Lander Ascent, Descent Aerobrake assembled in LEO
?
STS Crew involvement TBD
Cargo Launches NTR cargo vehicle & crew return vehicle launched & assembled
Placeholder for NTR Graphic
STS Crew involvement TBD
PILOTED VEHICLE
4
2 Vehicle 2 Propellant Tanks
? STS Transit Habitat, Earth Return Capsule BGD/Short Stay Architecture 7/11/2000 6
Cargo Launches NTR piloted vehicle launched & assembled
STS Crew involvement TBD
Placeholder for NTR Graphic STS Crew Delivery 16
Mars Short-Stay Launch Strategy EELV-H Option (Best Opportunity Example) Exploration Office
Best Opportunity (2018) Pre-Deploy Lander and Return Vehicle
2018 Crew
• Evolved commercial EELV, heavy lift option, with exploration unique upper stage • Large shroud assumed (8 x 30 m) • 35 mt lift capacity due east (assumed performance - no data yet) • Only mission hardware considered (need for on-orbit infrastructure not yet determined) • Crew support for on-orbit assembly, outfitting, and checkout not yet addressed • Launch rate shown does not support continuous exploration (cargo launches must be supported in the 2018 launch opportunity) • Detailed analysis not yet complete
2016 Cargo
Assumptions:
Launch # 1 2 3 4 5 6 7
Descent / Ascent Vehicle Ascent Stage Aerobrake / Deorbit Descent Stage Propellants NTR Core Stage NTR Structure Assembly NTR Propellant Tank NTR Propellant Tank
Vehicle Type Delta IV-H Delta IV-H Delta IV-H Delta IV-H Delta IV-H Delta IV-H Delta IV-M
8 9 10 11 12 13 14 15 16
Earth Return Vehicle NTR Core Stage NTR Structure Assembly NTR Propellant Tank NTR Propellant Tank NTR Propellant Tank NTR Propellant Tank NTR Propellant Tank NTR Propellant Tank NTR Propellant Tank
Delta IV-H Delta IV-H Delta IV-H Delta IV-H Delta IV-H Delta IV-M Delta IV-H Delta IV-H Delta IV-M
17 18 19 20 21 22 23 24
Transit Habitat Transit Habitat Habitat Consumables / ERC / Shadow Shield NTR Core Stage NTR Structure Assembly NTR Tank Set 2 NTR Tank Set 3 Checkout Crew Flight Crew
Delta IV-H Shuttle Delta IV-H Delta IV-H Delta IV-H Delta IV-H Shuttle Shuttle
Cargo launches for next mission BGD/Short Stay Architecture 7/11/2000 6
17
“Shuttle Compatible” Launch/Assembly Scenario Best Case (2018) Mission Opportunity Exploration Office
LANDER AND RETURN PROPELLANT
6
2
2 Vehicle 4 Propellant Tanks
? Cargo Launches Descent/ Ascent Vehicle
Cargo Launches NTR cargo vehicle & crew return vehicle launched & assembled
STS No Crew involvement
Placeholder for NTR Graphic
STS Crew involvement TBD
PILOTED VEHICLE
1
1 Vehicle
Placeholder for NTR Graphic STS Transit Habitat, Earth Return Capsule BGD/Short Stay Architecture 7/11/2000 6
Cargo Launches NTR piloted vehicle launched
STS Crew Delivery 18
EELV-H Launch/Assembly Scenario Worst Case (2026) Mission Opportunity Exploration Office
LANDER AND RETURN PROPELLANT
5
23
4 Vehicle 19 Propellant Tanks
? Cargo Launches Assembly platform Lander, Aerobrake assembled in LEO
?
STS Crew involvement TBD
Cargo Launches NTR cargo vehicle & crew return vehicle launched & assembled
Placeholder for NTR Graphic
STS Crew involvement TBD
PILOTED VEHICLE
26
2 Vehicle 24 Propellant Tanks
? STS Transit Habitat, Earth Return Capsule BGD/Short Stay Architecture 7/11/2000 6
Cargo Launches NTR piloted vehicle launched & assembled
STS Crew involvement TBD
Placeholder for NTR Graphic STS Crew Delivery 19
“Shuttle Compatible” Launch/Assembly Scenario Worst Case (2026) Mission Opportunity Exploration Office
LANDER AND RETURN PROPELLANT 3 Vehicle 7 Propellant Tanks
10
1
? Cargo Launches Descent/ Ascent Vehicle
STS No Crew involvement
Cargo Launches NTR cargo vehicle & crew return vehicle launched & assembled
Placeholder for NTR Graphic
STS Crew involvement TBD
PILOTED VEHICLE
11
2 Vehicle 9 Propellant Tanks
? STS Transit Habitat, Earth Return Capsule BGD/Short Stay Architecture 7/11/2000 6
Cargo Launches NTR piloted vehicle launched & assembled
STS Crew involvement TBD
Placeholder for NTR Graphic STS Crew Delivery 20
Initial Mars Short-Stay NTR Case Study Findings Non-Venus Swing-by Option Exploration Office
•
It is the consensus of the architecture team that the only way to perform the short-stay, nonVenus swing-by missions in the harder opportunities is to pre-deploy both the lander and return propellant – Lowers mission mass by approximately 36% (return propellant pre-deployed on minimum energy transfers) – Increases risk: Rendezvous in Mars orbit must be performed for crew survival (return) – Increases operating time of crew systems by 114% (as compared to non pre-deploy missions)
•
Number of launches required poses a significant challenge – # of EELV-H launches = 54 (1 launch every 2 weeks) – # of 80 mt Shuttle Compatible launches = 22 (1 launch every 4 weeks ) – Neither of these launch rates can be sustained • No margin for launch failure • No margin for launch delay • Current production/launch rate for Delta-IV is 14 per year (x 4 current capacity) – Probability of mission success significantly decreases with increased launch rate
“Go Anywhere / Go Anytime” + Small Launch Vehicle
BGD/Short Stay Architecture 7/11/2000 6
Launch LaunchVehicle VehicleSize Size/ / Number NumberofofLaunches Launches
Launch LaunchVehicle Vehicle Reliability Reliability
Probability Probabilityofof Successful SuccessfulLaunches Launches
EELV-H EELV-H/ /54 54 EELV-H/ EELV-H/54 54 “Shuttle Comp.” “Shuttle Comp.” / /22 22 “Shuttle Comp.” / 22 “Shuttle Comp.” / 22
94% 94% 99% 99% 94% 94% 99% 99%
4% 4% 58% 58% 26% 26% 80% 80%
Current Industry Launch Success Rate 94%
21
Utility of Venus Swing-by Trajectories Exploration Office
• • • •
•
•
Venus swing-by trajectories can significantly decrease mission mass Characterized by one short leg combined with a long Venus swing-by leg Swing-by occurs on either outbound or inbound leg Desired to constrain the swing-by to the inbound leg – Short outbound leg maximizes crew health at Mars – Crew will have Earth support at end of mission – Can save up to 39% delta-V Allowing the Venus swing-by on either leg – Outbound legs can be up to 310 days long – Can save up to 42% delta-V Issues of solar distance during swing-by need to be addressed – Radiation dose to the crew – Thermal environment Outbound SUN
γ
Mars Stay Inbound
BGD/Short Stay Architecture 7/11/2000 6
22
Trajectory Characteristics Comparison Exploration Office
Parameter
1-Year
Opposition
Conjunction
21,700-31,200
14,800-25,800
5,600-6,700
5.9 – 16.8
2.7 – 9.3
1.0 – 1.1
Mission Duration (months)
12
15-22
30-32
Surface Stay
1
1
16-21
One-Way Transits
4-9
6-13
6-7
Total Transit Time
11
14-21
8-13
0.57-0.72
0.35 -0.72
1.0
% Time in Zero-g Space
92%
93-96%
38-44%
% Time on Mars Surface
8%
7-4%
56-62%
Interplanetary Delta-V (m/s) Normalized Mass Ratio (for NTR)
Health Concerns Sun Closest Approach (AU)
7
1
4
Transit Times (months)
One-Year Round-Trip
Outbound Surface
6
6
BGD/Short Stay Architecture 7/11/2000 6
1
12
Return
Typical Opposition Class 18
6
Typical Conjunction Class 23
Total Mission ∆V vs Earth Departure Date Short-Stay Mars Missions Exploration Office
Total Mission ∆V vs Earth Departure Date 32000 30000 28000 26000
Assumptions - All propulsive mission - Earth parking orbit = 407 km - Mars parking orbit = 500 km - 40 day Mars stay - Figure of merit = Total ∆V (all legs)
468
24000
Mission ∆V (m/s)
Inbound Venus Swingby
497
22000
583
519
20000 453
18000
No Inbound Venus Swingby
494
446
527
Local Min ∆ V No Venus
545
585 661
16000
Local Min ∆ V Venus Swby (Return Leg
619
14000
582
12000
475 603
10000
612
8000
Local Min ∆ V Venus Swby Where Appropriate Local Min ∆ V One Way Cargo
6000 4000
365 Day Mission No Venus Swby
515
275 day
01-Jan-15
31-Dec-16
205 31-Dec-18
206 30-Dec-20
347 30-Dec-22
332 29-Dec-24
312 29-Dec-26
300 28-Dec-28
28-Dec-30
27-Dec-32
Earth Departure Date
BGD/Short Stay Architecture 7/11/2000 6
24
Comparison of Mission Trajectories Initial Mass and NTR Vehicle Complexity Exploration Office
1,800 (5)
1,600
156
(21)
Total Mission Mass (t)
1,400
(29+STS)
1,200
Pre-Deployed Mars Lander Pre-Deployed Crew Return Vehicle Piloted Mars Outbound Vehicle Note: Vehicles are 50-75% propellant (H2)
610 (5)
1,000
(11)
800 (7+STS)
600 158 (5)
897
400
156
200
125 115
0
(5)
298
(4+STS)
138
No Venus Swing-by
Representative Venus Swing-by
One-Year Round-Trip
2026 (Worst Case) 460 Days (180-40-240) Pre-Deploy Lander and Return Vehicle
2016 Launch Opportunity 479 Days (179-40-250) Pre-Deploy Lander and Return Vehicle
2018 (only) 365 Days (109-40-216) Pre-Deploy Lander and Return Vehicle
BGD/Short Stay Architecture 7/11/2000 6
Ref. Glenn Research Center
25
Technology Driven Capabilities Exploration Office Lunar L1 Habitat
Deep-Space L2 Habitat
Mars Transit Mars Transit Habitat Habitat
Lunar Surface Habitat
Mars Surface Mars Surface Habitat Habitat
Advanced Habitation • • • •
Radiation Protection Closed-loop Life Support Large Volume Advanced Health Care Lunar L1 SEP
Deep-Space L2 SEP
Electric Propulsion
Mars SEP
? Mars NEP
?
Nuclear Thermal Propulsion
Mars NTR Mars NTR
Lunar LTV
Deep-Space L2 LTV
Mars Taxi Vehicle
Near Earth Transportation • • • •
Radiation Protection Closed-loop Life Support Large Volume Advanced Health Care
BGD/Short Stay Architecture 7/11/2000 6
26
Mars Short-Stay Transit Habitat Exploration Office TRANSIT HABITAT
Need Need graphic graphic
Transit Mass (4 Crew, 650 total days)
Mass (kg)
1.0 2.0 3.0 4.0 5.0 6.0 7.0
2362.6 287.0 3948.9 1257.3 3396.1 879.9 817.3 2426.4 372.0 2600.0 2600.0 0.0 20947.5
Stowed Vol. (M3) 0.000 0.140 19.133 5.260 21.235 3.653 0.000 9.884 ----9.043 9.043 0.000 77.392
4270.6
0.000
Power System Avionics Environmental Control & Life Support Thermal Management System Crew Accommodations EVA Systems Structure Margin (20%) Crew Food (Return Trip) Food (Outbound Trip) Food (Contingency) Total Transit Habitat Mass Earth Return Vehicle Total Mass
• • • • • • • • •
25218.1
Supports mission crew of four for up to 365-650-days round-trip missions to and from Mars Crew consumables and support systems tailored for mission duration Zero-g configuration with integrated deep-space radiation protection Power generation provided by the bi-modal NTR vehicle Closed-loop (air and water) life support system Advanced health care systems Advanced materials for primary and secondary structures Advanced MEMS / wireless avionics for increased reliability and redundancy Earth return vehicle for crew return
BGD/Short Stay Architecture 7/11/2000 6
Ref. Johnson Space Center
27
Mars Descent / Ascent Vehicle Exploration Office
• •
Small shroud of the EELV-H has significant impact on the Descent / Ascent Vehicle Vertical lander configuration is not viable for small launch shrouds – – – – – –
Packaging and volume problems High center of gravity increases landing stability problems Assembled vehicles have larger c.g. uncertainty – increases aerocapture and aeroentry precision Ingress / Egress difficulties Launch vehicle shroud cannot be used as the Mars aerobrake or aeroentry shield Parachute deployment speeds: Parachutes cannot be used due to high deployment speeds (M=4.5) due to high ballistic coefficient – Aerobrarke on-orbit assembly and checkout required or other concepts which utilize deployed systems are needed
•
Large 8 x 30 m shroud assumed for vehicle elements Parachute deployment speeds
7.6
6 m Delta-IV H (Not Standard) BGD/Short Stay Architecture 7/11/2000 6
8 m Diameter Shroud
M ach No. at 10 K m Altitude - ND
4.5
Current Estimate
4
3.5
3
2.5
Current Mach number parachute deployment limits
2 1.50
2.00
2.50
3.00
3.50
4.00
Aeroshell Length to D iameter R atio - N D
28
Short-Stay Mars Descent / Ascent Vehicle Exploration Office
High Mars Orbit Option
Cargo Bays
LO2/CH4 Descent Engines (4)
• • • • • •
Airlock
LO2/CH4 Ascent Engines (2)
Transports four crew from Mars orbit to the surface and return to Mars orbit Vehicle supports crew for 30-days Two-stage design for high Mars orbit staging Regenerative air, open water life support system Advanced EVA and mobility Crew health and maintenance, including exercise equipment, for adaptation to martian gravity
BGD/Short Stay Architecture 7/11/2000 6
Payloads and Systems 1.0 Power System 2.0 Avionics 3.0 Environmental Control & Life Support 4.0 Thermal Management System 5.0 Crew Accommodations 6.0 EVA Systems 7.0 In-Situ Resource Utilization 8.0 Mobility 9.0 Science 10.0 Structure Margin (20%) Food Crew
DESCENT/ASCENT LANDER Stowed Vol. Mass (kg) (M3) 13276.4 36.640 4226.0 0.000 153.0 0.279 1037.6 3.983 527.4 2.350 727.7 5.776 1073.9 7.539 0.0 0.000 1350.4 8.171 301.2 1.600 1339.8 0.000 1807.4 5.689 360.0 1.252 372.0 -----
Ascent Stage (Two Stage) Crew Module Stage Propulsion Propellants
31442.7 1617.5 161.3 4675.6 24988.2
1.000 1.000 0.000 0.000 0.000
Descent Stage (Payload Down) Stage Propulsion Propellants
17237.2 44719.1 1242.3 4658.9 11336.0
0.000 ----0.000 0.000 0.000
Aerobrake
10184.1
0.000
Total Mass
72140.4
Ref. Johnson Space Center
29
“Bimodal” NTR Transfer Vehicles for Mars Cargo and Piloted Missions Exploration Office
Graphics Shown : One-year round-trip mission (2018) utilizing 80 mt launch vehicle
Cargo CargoMission Mission11 Descent Descent/ /Ascent AscentLander Lander IMLEO IMLEO==123 123--157 157mt mt
Cargo CargoMission Mission22 Crew CrewReturn ReturnVehicle Vehicle IMLEO IMLEO==250 250--612 612mt mt
Piloted PilotedMission Mission Crew CrewTransfer TransferVehicle Vehicle IMLEO IMLEO==104 104--896 896mt mt BGD/Short Stay Architecture 7/11/2000 6
Ref. Glenn Research Center
30
Architecture Unique Technology Needs Short-Stay Mars Mission Exploration Office
• Human Support – Advanced health care systems for long periods away from Earth (22 months)
• Advanced Space Transportation – Advanced interplanetary propulsion: Options include: • Bi-Modal Nuclear Thermal Propulsion (925 sec Isp, 15 kWe) • High Power Nuclear Electric (Ion, MPD, or VASMIR at multi-MW power levels) ? – Large volume / large mass Earth-to-Orbit transportation – Very high rate payload and launch vehicle processing land launch capability – Advanced LEO automated rendezvous, assembly, checkout, and verification facilities and techniques – Long-term storage of hydrogen in space
• Advanced Space Power – Nuclear power reactor 15-30 kWe for high-latitude scientific investigations
• Miscellaneous – Integrated vehicle health maintenance for vehicles unattended for long periods (21-22 months) – Advanced reliability for long vehicle operations (up to 44 months excluding LEO assembly ops) BGD/Short Stay Architecture 7/11/2000 6
31
Architecture Comparison Criteria Short-Stay Mars Mission Exploration Office
Criteria Criteria
BGD/Short Stay Architecture 7/11/2000 6
Value Value
Architecture ArchitectureEvolution EvolutionPotential Potential Architecture ArchitectureCommonality Commonality
Focus Focuson onshort shortstay staylimits limitsevolution evolution Very Verylittle littlepropulsion propulsionsystem systemcommonality commonality
Initial InitialMass MassininLow-Earth Low-EarthOrbit Orbit Mass MasstotoMars MarsSurface Surface
522-1665 522-1665mt mt 13 13mt mt
Number NumberofofCrew Crew Number NumberofofCargo CargoLaunches Launches
44 17-55 17-55
On-orbit On-orbitAssembly AssemblyRequired? Required? Number NumberofofCrew CrewLaunches Launches
Yes Yes tbd tbd
Architecture ArchitectureRedundancy Redundancy Architecture ArchitectureComplexity Complexity
No Nooverlapping overlappingofofresources resources Very Verycomplex complexLEO LEOmission mission
Architecture ArchitectureSensitivity Sensitivity Crew CrewHazards Hazards
High High Mars Marsorbit orbitrendezvous, rendezvous,365-650-day 365-650-daylong longmission mission
Time TimeininInterplanetary InterplanetarySpace Space Time Timeon onSurface Surface
620 620total totaldays days 30 30total totaldays days 32
Mars-Short Stay Mission Architecture Summary Strengths •
One-year mission is possible in some opportunities
Exploration Office
Weaknesses •
Large initial mass in LEO
•
Large variation in mass; large sensitivity to mass, level of redundancy, and technology changes
•
Shorter total mission reduces reliability requirements
•
Accomplish mission events quicker allowing crew return phase to begin sooner
•
Science return is local “focus” oriented (10 km)
•
No overlap of mission/vehicle resources
•
Shorter mission reduces crew time spent beyond Earth orbit (365-650 total days)
•
•
Minimizes surface infrastructure
Launch facilities and launch rate impacts as well as on-orbit assembly and checkout issues
•
Majority of mission is spent in zero-g radiation environment (95%)
•
Close sun passage increases radiation dose to the crew (0.35-0.7 AU)
•
Short surface stay allows less time for contingencies and re-planning (30 days)
BGD/Short Stay Architecture 7/11/2000 6
33
Architecture Issues and Follow-on Work Exploration Office
•
Results are due to the short-stay mission constraints and are not due to the NTR system performance. The trends of these results will be similar for all advanced propulsion options.
•
Small launch vehicle constraints force large levels of on-orbit assembly and checkout in low-Earth orbit which significantly increases mission complexity, mission risk, and cost.
•
Separating crew from their return vehicle increases risk to the crew (survival).
•
Requirements of the short stay mission poses a significant mission, design, assembly, and risk challenge for minimal return.
•
Additional analysis is required to determine feasibility. – – – –
Finalize trajectory options Update vehicle concepts Launch/assembly impacts Operations concepts
BGD/Short Stay Architecture 7/11/2000 6
– – – –
Risk analysis Crew health and performance Parking orbit analysis Power strategy
34
Mars Short-Stay Architecture Analysis Remaining Work Exploration Office
•
Finalize Mars Short-Stay Mission Trajectory Options – Variation and sensitivity across the entire synodic cycle – Vehicle and crew impacts of heliocentric passage – Parking orbit arrival/departure constraints for short Mars vicinity stay
•
Launch Vehicle / Assembly Assessments – Launch vehicle impacts – On-orbit assembly / checkout concepts – Vehicle support concepts (fuel depot?)
• •
Probabilistic Risk Assessments for leading architecture concepts Operations Concepts – Launch operations, vehicle, and payload processing – Flight and surface mission – Abort concepts
•
Crew Health and Performance Assessments – Radiation and zero-g for various total mission durations – Crew health and countermeasures for long-outbound transits
•
Power System Strategy – Strategy to meet high latitude, mobility, and science requirements
•
Update Vehicle Concepts – Mars Descent / Ascent Vehicle – NTR Piloted Vehicles
BGD/Short Stay Architecture 7/11/2000 6
35
Exploration Office
Backup
BGD/Short Stay Architecture 7/11/2000 6
36
Short-Stay Mars Mission Implications Exploration Office
• Large energy requirements increases mission vehicle size dictates need for advanced propulsion technology • Significant variation of propulsion requirements for the Short-Stay mission across synodic cycle (100%) – Significant impacts to vehicle design and certification due to wide variation of vehicle size
• Short stay in the vicinity of Mars compromises mission return and crew safety – Limited time for gravity-acclimation – Limited time for contingencies or dust storms – Majority of time spent in deep space (zero-gravity & deep space radiation)
• Total mission duration for the Short-Stay Mission on the order of 12-22 months – System reliability still critical to crew survival – Life support system reliability – Short (one-year) missions are possible, but limited to single opportunities over the 15-year synodic cycle (2018)
• Venus swing-by’s can reduce propulsive requirement (and thus mission mass) – Pass within 0.35-0.72 AU of the sun (increases radiation and thermal load) – Longer total mission duration in interplanetary space environment BGD/Short Stay Architecture 7/11/2000 6
BGD-LS-98-006 37
Normalized Mass Ratio Exploration Office
• •
Provides a top-level comparison of the relative initial mass in LEO Derived from the rocket equation M Final Mass (kg) f
Mf Mi
=
∆V g * Isp
Mi
Initial Mass (kg)
∆V
Velocity Change (m/s)
g
Gravitational Acceleration (m/s2)
Isp
Specific Impulse (s)
30
Chemical
Normalized Mass Ratio
25
20
NTR 15
10
5
0 0
5000
10000
15000
20000
25000
30000
35000
Delta-V (m/s) BGD/Short Stay Architecture 7/11/2000 6
38
Short-Stay Operational Considerstions Exploration Office
• Need to maintain abort gap closure for all interplanetary propulsion options considered • A separate Earth Return Vehicle (ERV) remains an important safety and mission success asset, and should be retained in this architecture • Mars orbital operations (capture, rendezvous, phasing for departure, etc.) needs further assessment • Short-stay surface adaptation story is mixed: – Short-stay allows for simpler surface spacecraft, but – will generate pressure to get on with the exploration phase early (adaptation issues) – Initial operations (g-transition, vehicle safing, appendage deployments) must occur without crew exertion
• Entry, Descent, and Landing (EDL) precision for this mission is primarily for mission success (along with rendezvous with pre-deployed robotic systems) • 10 km radius has been established as a reasonable traverse radius about the landing zone (walkback). Unpressurized rover(s) is assumed to be used during this mission due to the short-stay • Surface mission likely similar to an extended and very complex ISS assembly mission • Shorter exposure window to radiation and dust storm events on the surface, but due to visibility restrictions, the crew may get to Mars and be NO GO to land due to dust storms in the landing zone. • Initial timeline assessment: 21 EVAs of 6.5 hour duration are supported: • 5 local area (acclimation, area science, rover assembly) • 5 rover-assisted traverses • 11 Core drills at three different sites (Core A is assumed to take only 3 EVAs, the others require 4 each) • This timeline is considered optimistic
BGD/Short Stay Architecture 7/11/2000 6
39
Variation of Daylight Hours High Latitude Landing Sites Exploration Office
Variation VariationininDaylight DaylightHours HoursDuring DuringaaMartian MartianYear Year for Mid to High (+/40, 50, & 60 deg) Latitudes for Mid to High (+/- 40, 50, & 60 deg) Latitudes
Arrival (7/18/20) Arrival (7/18/20) Departure (8/27/20) Departure (8/27/20)
21 21 N Summer Solstice N Summer Solstice
20 20
Arrival (8/01/29) Arrival (8/01/29)
19 19 18 18
S Summer Solstice S Summer Solstice
Arrival (9/28/18), Arrival (9/28/18), (7/17/22) (7/17/22) Departure (11/17/18) Departure (11/17/18) (8/26/22) (8/26/22) Arrival (7/27/24) Arrival (7/27/24) Departure (9/5/24) Departure (9/5/24) Arrival (9/13/26) Arrival (9/13/26)
Departure Departure (9/10/29) (9/10/29)
17 H 17 H o 16 o u 16 u r 15 r 15 s s 14 14 o o f 13 f 13 D 1212 D a a y 1111 y l l i 1010 i g g 9 h 9 h t t 8 8 7 6 5
60 N 60 N 50 N 50 N Equinox (N Spring, S Fall) Equinox (N Spring, S Fall)
40 N 40 N
Equinox (N Fall, S Spring) Equinox (N Fall, S Spring)
60 S 60 S
Mission MissionDate Dateand andLanding LandingSite Site Location Significantly Influence Location Significantly Influence Length Lengthof ofOperational Operational“Day” “Day”
50 S 50 S 40 S 40 S
Science ScienceLanding LandingRequirements Requirements 55ººSStoto65 65ººNN
Highest Highest Probability of Probability of Global Dust Global Dust Storms Storms
7 6 5
S Winter Solstice S Winter Solstice
4
4 0 0 Departure Departure (10/23/26) (10/23/26) BGD/Short Stay Architecture 7/11/2000 6
43 43
86 86
129 129
172 172
N Winter Solstice N Winter Solstice
215 258 301 344 387 430 473 215 258 301 344 387 430 473 Days From Mars' Northern Vernal Equinox (0 - 688) Days From Mars' Northern Vernal Equinox (0 - 688)
516 516
559 559
602 602
645 645
688 688
40
Variation of Daylight Hours Low Latitude Landing Sites Exploration Office
Variation VariationininDaylight DaylightHours HoursDuring DuringaaMartian MartianYear Year for Low (+/10, 20, & 30 deg) Latitudes for Low (+/- 10, 20, & 30 deg) Latitudes 15 15
Arrival (8/01/29) Arrival (8/01/29) N Summer Solstice Departure N Summer Solstice Departure (9/10/29) (9/10/29)
Arrival (7/18/20) Arrival (7/18/20) Departure (8/27/20) Departure (8/27/20)
S Summer Solstice S Summer Solstice Arrival (9/28/18) Arrival (9/28/18) (7/17/22) (7/17/22) Departure (11/17/18) Departure (11/17/18) (8/26/22) (8/26/22) Arrival (7/27/24) Arrival (7/27/24) Departure (9/5/24) Departure (9/5/24) Arrival (9/13/26) Arrival (9/13/26)
14 14 H H o o u u r r s s13 13 o o f f
30 N 30 N 20 N 20 N Equinox (N Spring, S Fall) Equinox (N Spring, S Fall)
D D a a y 12 y l 12 l i i g g h h t t
10 N 10 N
Equinox (N Fall, S Spring) Equinox (N Fall, S Spring)
30 S 30 S 20 S 20 S 10 S 10 S
Highest Highest Probability of Probability of Global Dust Global Dust Storms Storms
11 11 Departure Departure (10/23/26) (10/23/26)
10 10 0
S Winter Solstice S Winter Solstice 0
BGD/Short Stay Architecture 7/11/2000 6
43 43
86 86
129 129
172 172
N Winter Solstice N Winter Solstice
215 258 301 344 387 430 473 215 258 301 344 387 430 473 Days From Mars' Northern Vernal Equinox (0 - 688) Days From Mars' Northern Vernal Equinox (0 - 688)
516 516
559 559
602 602
645 645
688 688
41
Mars Transit Habitat Exploration Office
HATCH DOORS
LEVEL 4 Pressurized Tunnel
INFLATABLE SHELL
LEVEL 3 Crew Health Care Area
SOFT STOWAGE ARRAY
ERGOMETER
CENTRAL STRUCTURAL CORE TREADMILL
LEVEL 2 Crew Quarters & Mech Rm
INFLATABLE OUTFITTING COMPRESSION RING
INTEGRATED WATER TANK / STORM SHELTER
LEVEL 1: Galley / Wardroom Area
20" WINDOW (2)
BGD/Short Stay Architecture 7/11/2000 6
Ref. Johnson Space Center
42
Modular “Bimodal” NTR Transfer Vehicle Designs Developed for Mars Cargo and Piloted Missions Exploration Office
Bimodal NTR:
High thrust, high Isp propulsion system utilizing U235 produces thermal energy for propellant heating and electric power generation enhancing vehicle capability
Bimodal NTR Stage
Engine Characteristics • • • •
Three 15 klbf tricarbide engines Each bimodal NTR produces 25 kWe Utilizes proven Brayton technology Variable thrust & Isp optional with “LOXafterburner” nozzle (LANTR)
Vehicle Characteristics TransHab
• • • •
Versatile design “Bimodal” stage produces 50 kWe Power supports active refrigeration of LH2 New “saddle” truss design allows easy jettisoning of “in-line” LH2 tank & contingency consumables • Propulsive Mars capture and departure on piloted mission • Fewest mission elements, simple space operations & reduced crew risk Crew Transfer Vehicle
BGD/Short Stay Architecture 7/11/2000 6
Ref. Glenn Research Center
43
Exploration Office
DPT Mars Long-Stay Mission Architecture Status Mid-Term (2018) Nuclear Thermal Propulsion and Solar Electric Propulsion System Options
Bret G. Drake NASA/Johnson Space Center July 11, 2000
BGD/Short Stay Architecture 7/11/2000 6
44
Outline Exploration Office
• • • • •
Architecture Overview Ground Rules and Assumptions Detailed Mission by Phase Capability Evolution Systems – – – – –
• • •
BGD/Short Stay Architecture 7/11/2000 6
Transit Habitat Surface Habitat Descent / Ascent Vehicle Interplanetary Transportation Launch Vehicle
Architecture Features Technology Needs Architecture Summary
45
Evolution of the Long-Stay Mission Philosophy Exploration Office
1988: Case Studies • Short Surface Stay • Chemical / Aerobrake • Split Sprint Missions
∗∗ Short-stay Short-staymissions missionsare areenergy energyintensive intensive ∗∗ On-orbit assembly increases mission On-orbit assembly increases missioncomplexity complexity ∗∗ Large Largemasses/volumes masses/volumesrequire requirelarge largelaunch launchvehicle vehicle
1989: Case Studies • Short Surface Stay • Chemical / Aerobrake • All-up Mission Profile
∗∗ “Free-Return “Free-Returntrajectories trajectoriesnot notbeneficial beneficial ∗∗ Crew acclimation for short stay Crew acclimation for short staymissions missionsneeds needs further investigation further investigation ∗∗ Large Largemasses/volumes masses/volumesrequire requirelarge largelaunch launchvehicle vehicle
1990: 90-day Study • Short Surface Stay • Split Sprint Missions • Various propulsion options
∗∗ NTR NTRpropulsion, propulsion,Aerobraking Aerobrakingand andISRU ISRU are promising technologies to pursue are promising technologies to pursue ∗∗ Large Largemasses/volumes masses/volumesrequire requirelarge large launch vehicle launch vehicle
1991: Synthesis Group ∗∗ ∗∗
“Key” “Key”Technologies Technologiesidentified identified Large masses/volumes Large masses/volumesrequire require large launch vehicle large launch vehicle
• Short Surface Stay • Nuclear Thermal Propulsion • Heavy lift launch vehicle
1997: DRM 1.0 ∗∗ ∗∗ ∗∗
• Long Surface Stay • Nuclear Thermal Propulsion • Heavy lift launch vehicle
Crew Crewexposure exposuretotointerplanetary interplanetaryspace spacelimited limited Large masses/volumes require large launch Large masses/volumes require large launchvehicle vehicle Functional redundancy maximized Functional redundancy maximized
1999: Dual Landers ∗∗ Lowest Lowestmass massapproach approach ∗∗ Crew exposure Crew exposurelimited limited ∗∗ Science return maximized Science return maximized ∗∗ “Shuttle Compatible” launch vehicle “Shuttle BGD/Short Stay Architecture 7/11/2000 6Compatible” launch vehicle
• Long Surface Stay • NTR or SEP • Enabled Global Access 46
Mars Long-Stay Mission Significant Features Exploration Office
•
Balances technical, programmatic, mission, and safety risks
•
Lowest number of launches per human mission
•
Simple LEO operations – automated rendezvous and docking of two elements
•
High scientific return (500+ days on Mars) with continuous collaboration with colleagues on Earth
•
Minimizes exposure of crew to interplanetary environment (zero-g and deepspace radiation)
•
Maximizes reuse of mission elements: SEP and surface habitat (if desired)
•
Vehicle design independent of mission opportunity (Small variation (10%) in vehicle size for every Mars opportunity)
•
Enables global surface access if desired
BGD/Short Stay Architecture 7/11/2000 6
47
High Earth Orbit Staging Mission Scenarios Exploration Office
Mars
Space Station Orbit (LEO) Rendezvous
Earth
Crew Transfer via Crew Taxi
Elliptical Parking Orbit (EPO)
Mars Aerocapture
Chem Transfer EP Transfer
Chemical Injection Burn Near Earth Asteroids Libration Points 48
Mars Mission Overview (SEP Option) Exploration Office Surface Habitat and exploration gear aerocaptures into Mars orbit. Ascent/Descent Vehicle aerocaptures and remains in Mars orbit for the crew. Habitat Lander and Ascent/Descent Vehicles delivered to Low Earth Orbit with “Shuttle Class” launcher. Solar Electric Propulsion stage spirals cargo to High Earth Orbit. Chemical injection used at perigee. SEP spirals back to LEO for reuse.
Crew rendezvous with Descent/Ascent Vehicle in Mars Orbit then lands in vicinity of Habitat Lander.
Surface Habitat lands and performs initial setup and checkout - Initial outpost established.
30 days provided to satisfy “longstay” criteria.
Mars Surface
Crew travels to Mars in “fast transit” 180-206 day transfer. Aerobrakes into Mars orbit.
Habitat remains in Mars orbit.
Crew ascends and rendezvous with waiting Transit Habitat.
Transit Habitat vehicle delivered to LEO with “Shuttle Class” launcher. SEP spirals Transit Habitat to High Earth Orbit. Crew delivered to vehicle via crew taxi. SEP spirals back to LEO for reuse.
Earth
BGD/Short Stay Architecture 7/11/2000 6
Crew returns to Earth on “fast transit” 180-206 day transfer. Direct entry at Earth.
49
Mars Mission Overview (NTR Option) Exploration Office Surface Habitat and exploration gear aerocaptures into Mars orbit
Cargo Vehicles Delivered to Low-Earth Orbit via “Shuttle Compatible” Launch Vehicle • Surface Habitat/Lander • Surface Habitat NTR • Descent-Ascent Lander • Descent-Ascent Lander NTR
Ascent/Descent Vehicle aerocaptures and remains in Mars orbit for the crew
Crew rendezvous with Descent/Ascent Vehicle in Mars Orbit then lands in vicinity of Habitat Lander
Surface Habitat lands and performs initial setup and checkout - Initial outpost established
30 days provided to satisfy “longstay” criteria Crew travels to Mars in “fast transit” 180-206 day transfer. Propulsively captures into Mars orbit
Mars Surface
Habitat remains in Mars orbit
Crew ascends and rendezvous with waiting Transit Habitat
Crew Vehicles Delivered to Low-Earth Orbit via “Shuttle Compatible” Launch Vehicle • Transit Habitat/Lander • Transit Habitat NTR Crew delivered to Mars Vehicle via Shuttle
Earth
BGD/Short Stay Architecture 7/11/2000 6
Crew returns to Earth on “fast transit” 180-206 day transfer. Direct entry at Earth
50
Long-Stay Mission Sequence Exploration Office
Mars Flight
2014
2018
2019
2020
2021
2022
2023
2024
Mission 1
2025
2026
Crew Transits Surface Mission Cargo Outbound Overlapping Resources Unoccupied Wait
Transit Vehicle Departure
Arrival
Departure
Arrival
Descent/Ascent Vehicle Surface Habitat
Mission 2 Mission 3
5 Cargo
2017
Surface Habitat
3 Cargo 4 Crew
2016
Descent/Ascent Vehicle
1 Cargo 2 Crew
2015
Transit Vehicle Departure
8 Crew
BGD/Short Stay Architecture 7/11/2000 6
Departure
Arrival
Descent/Ascent Vehicle Surface Habitat
6 Crew
Transit Vehicle Departure
Mission 4
7 Cargo
Arrival
Arrival
Departure
Arrival
Descent/Ascent Vehicle Surface Habitat
Transit Vehicle Departure
Arrival
Departure
51
Surface Architecture Exploration Office
Outpost Missions (Bite Size Chunks)
• Full Mission and augmented systems • Rovers • Power (nuke) • Science (drills) • etc.
BGD/Short Stay Architecture 7/11/2000 6
Basic Survivability (30 Days)
• Short-stay capability (30 days) • Ascent vehicle and propellant (abort-to-orbit) • Contingency science • Common lander design
Full Mission Capability (18 Months)
• Full surface mission support systems • Power • Life Support • Maintenance • Thermal • Crew accommodations • Science • Common lander design 52
Mars Long-Stay Ground Rules and Assumptions Exploration Office
• •
Detailed GR&A provided in the “Mars Long-Mission GR&A” document dated 4-20-2000 Primary DPT GR&A which drive this architecture include: – – – – – – – –
First cargo mission 2016, First human mission 2018 Short transits to/from Mars (180-206 days) with long surface stay Six crew Zero-g transits Technology freeze to TRL 6 by 2011 Factor of nine improvement for primary and secondary structures Advanced mobility and scientific laboratory capability for enhanced science Transportation Assumptions • “Shuttle Compatible” launch vehicle for cargo (80 mt) • Both SEP and NTR investigated • Aerobraking at Mars • Long-term cryogenic fluids storage
BGD/Short Stay Architecture 7/11/2000 6
53
Mission Sequence High Earth Orbit Boost Phase Exploration Office
UNPILOTED VEHICLES
Cargo Launch 2 SEP launched to low Earth orbit
Cargo Launch 3 Descent/Ascent vehicle, aerobrake, and TMI stage launched LEO
Cargo Launch 4 Surface Habitat Lander, aerobrake, and TMI stage launched LEO
SEP vehicles boost Descent/Ascent and Surface Hab landers to High Earth Orbit
STS 4 / Taxi Servicing mission in High Earth Orbit (contingency)
PILOTED VEHICLES
Cargo Launch 1 Transit Habitat launched to low Earth orbit
BGD/Short Stay Architecture 7/11/2000 6
STS 1 & 2 Transit Habitat outfitting missions
Cargo Launch 5 Transit Habitat SEP vehicle launched to low Earth orbit
Cargo Launch 6 SEP vehicle boosts Transit Habitat Transit Habitat to propulsion stages High Earth Orbit launched to low Earth orbit
STS 3 / Taxi Transit Habitat servicing mission in High Earth Orbit (contingency)
54
Mission Sequence Trans-Mars Injection / Mars Arrival Phase Exploration Office
Surface Habitat Lander Surface Habitat performs deorbit, entry, descent, and precision landing on Mars
Descent/ Ascent Vehicle Unpiloted Vehicles injected toward Mars on near minimum energy transfers
Unpiloted vehicles aerocapture into Mars orbit prior to the crew
Transit Habitat performs rendezvous with Descent/Ascent vehicle in Low Mars Orbit. STS 5 / Taxi Flight Crew Delivery to Transit Habitat
BGD/Short Stay Architecture 7/11/2000 6
Transit Habitat TransMars Injection (180-206 day transfers)
Transit habitat aerocaptures into Mars orbit
Crew transfers to Descent/Ascent Vehicle
55
Mission Sequence Surface Mission / Mars Ascent / Return Phases Exploration Office
Crew performs deorbit, entry, descent, and precision landing on Mars in Descent / Ascent Vehicle
Initial Operations 30 days for systems checkout and crew acclimation. Contingency abort-toorbit capability
BGD/Short Stay Architecture 7/11/2000 6
Low-Mars Orbit Wait Transit Habitat remains in low-Mars Orbit during surface mission (unmanned)
Initial Habitat Operations Safe vehicle, habitat inflation, power system deployment, habitat outfitting and systems checkout.
Ascent & Rendezvous Ascent from Mars surface and rendezvous with Transit Habitat in low-Mars orbit
Earth Return Direct Earth entry at end of mission
Surface Exploration Concentrates on the search for life, drilling, geology, and microbiology investigations (up to 18 months long)
56
Solar Electric Vehicle Transportation Concept Exploration Office
2016
2018
2020
Piloted/Cargo Piloted/CargoBoost Boost
Both Bothcargo cargoand andpiloted piloted vehicles are boosted vehicles are boostedtotohigh high Earth Earthdeparture departureorbit orbit
Cargo CargoBoost Boost
SEP-1 SEP-1vehicle vehicleboosts boostscargo cargo vehicles to high Earth vehicles to high Earth departure departureorbit orbit
2 1
2
1 Return Return
Return Return
SEP-1 SEP-1vehicle vehiclereturns returnstoto LEO LEOfor fornew newpropulsion propulsion module and module andmission missionpayload payload BGD/Short Stay Architecture 7/11/2000 6
SEP-2 SEP-2vehicle vehiclereturns returnstoto LEO for new propulsion LEO for new propulsion module moduleand andmission missionpayload payload
57
“Bimodal” NTR Crew Transfer Vehicle (CTV) Mission Scenario
Exploration Office
(optional)
BGD/Short Stay Architecture 7/11/2000 6
58
Technology Driven Capabilities Exploration Office Lunar L1 Habitat
Deep-Space L2 Habitat
Mars Transit Mars Transit Habitat Habitat
Lunar Surface Habitat
Mars Surface Mars Surface Habitat Habitat
Deep-Space L2 SEP
Mars SEP Mars SEP
Advanced Habitation • • • •
Radiation Protection Closed-loop Life Support Large Volume Advanced Health Care Lunar L1 SEP
Electric Propulsion
? Mars NEP Mars NEP
?
Nuclear Thermal Propulsion
Mars NTR Mars NTR
Lunar LTV
Deep-Space L2 LTV
Mars Taxi Mars Taxi (Lunar LTV) (Lunar LTV)
Near Earth Transportation • • • •
Radiation Protection Closed-loop Life Support Large Volume Advanced Health Care
BGD/Short Stay Architecture 7/11/2000 6
59
Mars Transit Habitat Configuration Exploration Office
Communications Docking/Crew Antenna Transfer Tunnel/EVA Airlock
Crew Earth Return Vehicle
Earth Return/Aborts Communications Antenna - Mars Transit
Solar Array (200 m2)
Ellipsled Body-Mounted Radiator (70 m2)
TEI Stage
TMI Stage
BGD/Short Stay Architecture 7/11/2000 6
Double-Sided Radiator (30.5 m2) Mars Circularization Stage
Inflatable TransHab Ref. Johnson Space Center
60
Mars Transit Habitat Exploration Office TRANSIT HABITAT
5834.6 287.0 3948.9 1257.3 4309.9 868.7 896.9 2475.9 558.0 2436.0 2436.0 7320.0 32629.1
Stowed Vol. (M3) 0.000 0.140 19.133 5.260 30.719 2.922 0.000 8.726 ----8.473 8.473 25.461 109.306
3246.5
0.000
14770.6 567.7 1301.6 12901.3
0.000 0.000 0.000 0.000
4848.5
0.000
TEI Stage Stage Propulsion Propellants
51429.8 1286.0 2363.1 47780.7
0.000 0.000 0.000 0.000
TMI Stage Stage Propulsion Propellants
66583.9 1455.1 2518.5 62610.3
0.000 0.000 0.000 0.000
Mass (kg) 1.0 2.0 3.0 4.0 5.0 6.0 7.0
Power System Avionics Environmental Control & Life Support Thermal Management System Crew Accommodations EVA Systems Structure Margin (15%) Crew Food (Return Trip) Food (Outbound Trip) Food (Contingency) Total Transit Habitat Mass Crew Taxi/Earth Return Capsule
• Supports mission crew of six for up to 200-day transits to and from Mars • Provides zero-g countermeasures and deep-space radiation protection • Return propulsion stage integrated with transit system • Provides return-to Earth abort capability for up to 30 hours post-TMI
Circ Stage Stage Propulsion Propellants Aerobrake
INITIAL MASS IN HIGH EARTH ORBIT BGD/Short Stay Architecture 7/11/2000 6
173508.4
Ref. Johnson Space Center
61
Mars Habitat Lander Exploration Office LEO Configuration
HABITAT LANDER
30325.2 5988.0 153.0 3948.9 2912.1 3502.9 1174.4 165.0 0.0 829.9 1861.3 1775.1 6840.0 0.0
Stowed Vol. (M3) 99.996 0.000 0.279 19.133 9.020 26.369 10.124 0.227 0.000 4.215 0.000 6.837 23.791 -----
243.1 110.0 133.1 0.0 0.0
0.000 0.000 0.000 0.000 0.000
12636.3 30568.3 1002.1 3436.0 8198.2
0.000 ----0.000 0.000 0.000
Aerobrake
4656.2
0.000
Circ/Deorbit Stage Stage Propulsion Propellants
9494.0 365.0 1339.5 7789.5
0.000 0.000 0.000 0.000
24357.3 57354.8 686.4 2045.9 21625.1
0.000 ----0.000 0.000 0.000
Mass (kg) Payloads and Systems 1.0 Power System 2.0 Avionics 3.0 Environmental Control & Life Support 4.0 Thermal Management System 5.0 Crew Accommodations 6.0 EVA Systems 7.0 In-Situ Resource Utilization 8.0 Mobility 9.0 Science 10.0 Structure Margin (15%) Food Crew
Inflatable Habitat
Cargo Bays Airlock LO2/CH4 Descent Engines (4)
• • •
Vehicle supports mission crew of six for up to 18 months on the surface of Mars Provides robust exploration and science capabilities Descent vehicle capable of landing 36,000 kg
Ascent Stage Crew Module Stage Propulsion Propellants Descent Stage (Payload Down) Stage Propulsion Propellants
TMI Stage (TMI Payload) Stage Propulsion Propellants
INITIAL MASS IN HIGH EARTH ORBIT BGD/Short Stay Architecture 7/11/2000 6
81712.1
Ref. Johnson Space Center
62
Mars Descent / Ascent Vehicle Exploration Office LEO Configuration
Payloads and Systems 1.0 Power System 2.0 Avionics 3.0 Environmental Control & Life Support 4.0 Thermal Management System 5.0 Crew Accommodations 6.0 EVA Systems 7.0 In-Situ Resource Utilization 8.0 Mobility 9.0 Science 10.0 Structure Margin (15%) Food Crew
Cargo Bays
LO2/CH4 Descent Engines (4)
• • • •
Airlock
LO2/CH4 Ascent Engines (2)
Transports six crew from Mars orbit to the surface and return to Mars orbit Provides contingency abort-to-orbit capability Vehicle supports crew for 30-days Vehicle capable of utilizing locally produced propellants
BGD/Short Stay Architecture 7/11/2000 6
DESCENT/ASCENT LANDER Stowed Vol. Mass (kg) (M3) 13467.2 30.095 4762.0 0.000 153.0 0.279 1037.6 3.983 527.4 2.350 727.7 5.776 1085.0 3.084 0.0 0.000 1200.4 8.171 301.2 1.600 1339.8 0.000 1415.1 3.599 360.0 1.252 558.0 -----
Ascent Stage Crew Module Stage Propulsion Propellants
17779.2 1617.5 471.3 2121.1 13569.3
1.000 1.000 0.000 0.000 0.000
Descent Stage (Payload Down) Stage Propulsion Propellants
12876.5 31246.3 1242.3 3436.0 8198.2
0.000 ----0.000 0.000 0.000
Aerobrake
4656.2
0.000
Circ/Deorbit Stage Stage Propulsion Propellants
9494.0 365.0 1339.5 7789.5
0.000 0.000 0.000 0.000
24357.3 58273.1 686.4 2045.9 21625.1
0.000 ----0.000 0.000 0.000
TMI Stage (TMI Payload) Stage Propulsion Propellants
INITIAL MASS IN HIGH EARTH ORBIT
82630.4
Ref. Johnson Space Center
63
SETV Baseline 3.3B Rev 1 Exploration Office
SETV Deployed with Mars Payload Element Photovoltaic Array Blanket
SETV Bus Module
Articulated Thruster Boom
Inflatable Ribs
Kapton Webbing
Mars Payload
BGD/Short Stay Architecture 7/11/2000 6
SEP Transfer Vehicle SEP Transfer Vehicle
Total Mass (kg) Total Mass (kg)
Reusable SEP Power Module Reusable SEP Power Module Central Bus Central Bus Power System Power System Manipulator Arm Manipulator Arm
27,935 27,935 3,770 3,770 12,370 12,370 11,795 11,795
SEP Propulsion Module SEP Propulsion Module Propulsion Platform Propulsion Platform Propellant Feed System Propellant Feed System
7,730 7,730
Maximum Propellant Load Maximum Propellant Load
64,335 64,335
Ref. Glenn Research Center
3,900 3,900 3,830 3,830
64
“Bimodal” NTR Transfer Vehicles for Mars Cargo and Piloted Missions Exploration Office
(6 Shuttle Compatible Launch Vehicles plus Shuttle for Crew and TransHab Delivery) 2016 Cargo Mission 1 Habitat Lander IMLEO = 131.5 mt
2016 Cargo Mission 2 Optional “In-Line” LH2 Tank (if needed)
Cargo Lander IMLEO = 132.5 mt
2016 Piloted Mission Crew Transfer Vehicle IMLEO = 168.5 mt
BGD/Short Stay Architecture 7/11/2000 6
Ref. Glenn Research Center
65
Launch Vehicle Exploration Office
•
Cost effective delivery of large mass and large payload
•
Maximizes the cost effective use of common Shuttle boosters and launch facilities
•
Shuttle compatible •
Core equal to the diameter of the External Tank (27.6 mt)
•
Common Pad Hold Down System
•
Common Use of ET Handling & Manufacturing Hardware
•
99.00 27.58 dia 17.7 dia
23.64
Same mobile launch platform (modified flame trenches)
•
Common Boosters
•
Similar GLOW: Use of Shuttle Crawlers & MLPs
60.62
29.00
Engine Configuration
BGD/Short Stay Architecture 7/11/2000 6
Ref. Marshall Space Flight Center
66
“Shuttle Compatible” Launch Vehicle RFS Configuration Exploration Office
Booster Separation
“Shuttle Compatible” Launch Vehicle Payload Fairing 92 ft cyl x 25 ft I.D.
• 220 NMI/ 28.5 Degrees • P/L: 80 mt • P/L: 25 ft Dia X 92 ft
Circularization Stage LO2 Tank
Launch Pad (Shuttle)
Liquid Flyback Booster (2)
Payload / Stage Adapter
LH2 Tank Fwd Booster Attach
Aft Booster Attach Thrust Structure
BGD/Short Stay Architecture 7/11/2000 6
RS 68 Engines (2)
Ref. Marshall Space Flight Center
67
Baseline Processing Option Exploration Office
MARS PROCESING FLOW LFBB
VAB
LFBB PROCESSING FACILITY
MLT (NEW) LCC
MAGNUM CORE VEHICLE
ET / CORE 1.5 STAGE
O&C
MAGNUM CORE DELIVERY
MARS ENCAPSULATED PAYLOAD
KICKSTAGE
LC-39A OR B (MODIFIED)
SSPF
TMI STAGE TO LOW BAY ISRU
Miscellaneous Science Eqiuipment
MARS PAYLOAD ELEMENTS
BGD/Short Stay Architecture 7/11/2000 6
VPF
TMI DELIVERY
KICKSTAGE DELIVERY
Ref. Kennedy Space Center
68
Baseline Payload Processing Option Exploration Office
MARS PAYLOAD PROCESING VAB
TEI STAGE MARS CARGO DESCENT
PHSF
MARS TRANSHAB DESCENT NPP
MARS TRANSHAB DESCENT NPP TEI STAGE
MARS TRANSHAB DESCENT
MARS ENCAPSULATED PAYLOADS
SSPF
CARGO VEHICLE MARS ASCENT STAGE ISPP RETURN HAB INFLATABLE HAB
LOGISTICS ITEMS ECRV
MPPF
TRANS HAB ISPP INFLATABLE HAB
BGD/Short Stay Architecture 7/11/2000 6
Ref. Kennedy Space Center
69
KSC Facility Modifications Exploration Office
The KSC Operations Assessment team has developed a processing concept that requires an additional Mobile Launcher Platform but does not require construction of new facilities
Minor modifications to existing infrastructure can adequately accommodate the processing of the maximum inventory of flight hardware to support the launch campaign
Mobile Launch Platform Two Mobile Launcher Platforms (MLPs) will be required to support the “Shuttle Compatible” and not interfere with the Space Shuttle Program New MLP Modify existing MLP 1
Pad Modifications One pad will require modifications for both Shuttle and “Shuttle-Compatible” Launches New crawlerway
Operations and Checkout Building No modifications required
Vehicle Assembly Building Only platform modifications are required
BGD/Short Stay Architecture 7/11/2000 6
Ref. Kennedy Space Center
70
Low-Earth Orbit Rendezvous and Docking Exploration Office
•
Utilizing a large volume, large mass launch vehicle requires only automated rendezvous and docking
•
Both Earth surface and LEO based navigation and control infrastructure utilized to enable LEO operations
•
Dual launch sequence: – Mars payload launched first to LEO – Injection stage launched second – Mars payload acts as primary control vehicle during rendezvous and docking maneuver
•
Vehicles remotely checked out in LEO prior to initiating Trans-Mars Injection maneuver
BGD/Short Stay Architecture 7/11/2000 6
71
The Forward Deployment Strategy Exploration Office
Outbound
Prior to Crew Arrival
Crew Arrival
Cargo Missions Primary Use
Crew Mission Depart Earth
Forward ForwardDeployment Deployment Provides Providesthe theCrew Crew Dual DualAbort AbortPaths Paths
Depart Mars
Arrive Earth
Architectural/Functional Backup
Cargo Missions
BGD/Short Stay Architecture 7/11/2000 6
Arrive Mars
Architectural Backup for Crew # 1
72
Example Power System Redundancy Exploration Office
First Human Mission Elements Primary Primary Power Power •• •• ••
Nuclear Nuclear Spare Spare Engine Engine Spare Spare Radiator Radiator
Emergency Emergency Backup Backup
••Solar/Regenerative Solar/Regenerative Fuel Fuel Cell Cell
Emergency Emergency Backup Backup
Second Human Mission Elements Primary Primary Power Power •• •• ••
Nuclear Nuclear Spare Spare Engine Engine Spare Spare Radiator Radiator
••ISRU ISRU Fuel Fuel Cell Cell Reactants Reactants
Emergency Emergency Backup Backup
Emergency Emergency Backup Backup
••Solar/Regenerative Solar/Regenerative Fuel Fuel Cell Cell
••Surface Surface Mobile Mobile Power Power Systems Systems
Emergency Emergency Backup Backup
Abort to Orbit
BGD/Short Stay Architecture 7/11/2000 6
••Surface Surface Mobile Mobile Power Power Systems Systems 73
Example Life Support System Redundancy Exploration Office
Second Human Mission Elements First Human Mission Elements
Life Life Support Support System System •Bioregenerative •Bioregenerative
Life Life Support Support System System ••Bioregenerative Bioregenerative
Emergency Emergency Backup Backup ••Physical/Chemical Physical/Chemical
Emergency Emergency Backup Backup ••Physical/Chemical Physical/Chemical
Long-Term Long-Term Backup Backup ••ISRU ISRU Water/ Water/ O O22 Cache Cache
Long-Term Long-Term Backup Backup ••ISRU ISRU Water/ Water/ O O22 Cache Cache
Abort to Orbit BGD/Short Stay Architecture 7/11/2000 6
74
Earth Vicinity Abort Scenarios (SEP Architecture) Exploration Office
Post-Trans-Mars Injection Aborts: Transit Habitat
Earth Return Vehicle
Trans-Earth Injection Stage
Trans-Earth Injection stage can be used to return the crew from an offnominal TMI burn
Post-Trans-Mars Injection Abort Options c Long Return Option (within 8 hrs of TMI) y Crew lives in Transit Habitat after abort declaration y Crew returned to Earth in the Earth Return Vehicle up to 30 days later
d Quick Return Option (within 30 hrs of TMI) y Crew returned in the Earth Return Vehicle y Return transit time 1-2 days
e Heliocentric Aborts (1-2 months after TMI) y Return transit times range from 360-570 days y Crew lives in the Transit Habitat during return - direct Earth entry via Earth Return Vehicle y Can perform this abort only for some (3 of 7) opportunities (2014, 2016, 2018) with the current TEI size (33% increase to cover all opportunities) BGD/Short Stay Architecture 7/11/2000 6
75
Mars Vicinity Abort Options Exploration Office
System Pre-Deployment
Initial Operations (30 days)
Full Surface Mission (600 days)
Habitat Pre-Deployment
First 30 Days
600-Day Surface Mission
– – –
Surface habitat pre-deployed prior to crew landing. Initial habitat safing, checkout, and verification Risk to crew is reduced since crew does not commit to the landing phase until all habitat systems are operational.
– –
–
–
BGD/Short Stay Architecture 7/11/2000 6
Crew lands in separate vehicle 30-day initial operations for crew acclimation, initial science Once acclimated, crew performs habitat system initialization, checkout and verification. Contingency abort-to-orbit capability provided
– – – –
Crew transition to surface habitat complete Long-stay criteria met Ascent Vehicle placed in stand-by mode Contingency abort-to-orbit in Ascent Vehicle if required. Must wait in Mars orbit until TransEarth Injection window opens.
76
Mars-Long Stay Launch Strategy Shuttle Compatible Launch Vehicle Option Exploration Office
BGD/Short Stay Architecture 7/11/2000 6
2018 Crew 2018 Cargo
• Cargo launch concept based on Shuttle compatible systems • 80 mt lift capacity due east • Shroud 8 x 30 m • Rendezvous and docking of two exploration elements • Launch rate shown does not support continuous exploration (cargo launches must be supported in the 2018 launch opportunity) • Detailed analysis of payload processing, payload and vehicle flows, facility impacts and modifications, schedule impacts, and cost assessments complete.
2016 Cargo
Assumptions: Launch #
Descent / Ascent Vehicle
Vehicle Type
1
Wet Descent / Ascent Vehicle
Shuttle Compatible
2
Wet NTR Stage
Shuttle Compatible
Habitat Lander 3
Wet Habitat Lander
Shuttle Compatible
4
Wet NTR Stage
Shuttle Compatible
Transit Habitat 5
Transit Habitat
Shuttle
6
Habitat Consumables / NTR Core
Shuttle Compatible
7
NTR Tank Set
Shuttle Compatible
8
Checkout Crew
Shuttle
9
Flight Crew
Shuttle
Cargo launches for next mission
77
Mars-Long Stay Launch Strategy EELV-H Option Exploration Office Launch #
BGD/Short Stay Architecture 7/11/2000 6
Vehicle Type
1
Ascent Stage
Delta IV-H
2
Aerobrake / Deorbit Descent Stage
Delta IV-H
3
NTR Core Stage
Delta IV-H
4
NTR Propellant Tank
Delta IV-H
5
NTR Propellant Tank
Delta IV-M
Habitat Lander 6
Ascent Stage
Delta IV-H
7
Aerobrake / Deorbit Descent Stage
Delta IV-H
8
NTR Core Stage
Delta IV-H
9
NTR Propellant Tank
Delta IV-H
10
NTR Propellant Tank
Delta IV-M
2018 Crew
Transit Habitat
2018
• Evolved commercial EELV • Heavy lift option with exploration unique upper stage • 35 mt lift capacity due east (assumed performance - no data yet) • Non-standard large shroud (8 x 30 m) • Only hardware and volume launch considered thus far • Crew support for on-orbit assembly, outfitting, and checkout not yet taken into account. • Launch rate shown does not support continuous exploration (cargo launches must be supported in the 2018 launch opportunity) • Detailed analysis not yet complete
2016 Cargo
Assumptions:
Descent / Ascent Vehicle
11
Transit Habitat
Delta IV-H
12
Habitat Consumables / ERC / Shadow Shield
13
NTR Core Stage
Delta IV-H
14
NTR Tank Set 1
Delta IV-H
15
NTR Tank Set 2
Delta IV-H
16
NTR Tank Set 3
Delta IV-H
17
Checkout Crew
Shuttle
18
Flight Crew
Shuttle
Shuttle
Cargo launches for next mission
78
Human Exploration of Mars Evolution of Common Capabilities L1/L2 Gateways
Mars Habitats
Long duration support of mission crew in interplanetary environment with limited resupply capabilities
L1/L2 Transfer Vehicle
Mars SEP Taxi
Transports mission crew from low-Earth orbit to mission destinations and high-Earth staging orbits
BGD/Short Stay Architecture 7/11/2000 6
L1/L2 SEP
Exploration Office
Mars SEP
Transports mission payloads from low-Earth orbit to mission destination and return
Lunar EVA
Mars EVA
Enables routine access to the planetary surface and expands the range of access for exploration
79
Architecture Unique Technology Needs Long-Stay Mars Mission Exploration Office
• Human Support – Advanced surface mobility and EVA: suitable for robust surface exploration (dexterity, mobility, maintainability) – Advanced health care systems for long periods away from Earth (30 months)
• Advanced Space Transportation – Advanced interplanetary propulsion: Options include: • Solar Electric Propulsion (1.7 Mwe, 18 % efficiency thin film solar) • Bi-Modal Nuclear Thermal Propulsion (925 sec Isp, 25 kWe) – Large volume / large mass Earth-to-Orbit transportation – In-situ consumable production for EVA system breathing oxygen and ECLSS backup – Automated rendezvous and docking of exploration payloads (2) in Earth orbit
• Advanced Space Power – Nuclear power reactor 15-30 kWe for high latitude science investigations
• Miscellaneous – Integrated vehicle health maintenance for vehicles unattended for long periods (22-42 months) – Advanced reliability for long vehicle operations (up to 32-51 months) BGD/Short Stay Architecture 7/11/2000 6
80
Architecture Comparison Criteria Long-Stay Mars Mission Exploration Office
Criteria Criteria
Value Value
Architecture ArchitectureEvolution EvolutionPotential Potential Architecture ArchitectureCommonality Commonality
Long-stay Long-stayhuman humanexpansion expansion High Highpropulsion propulsionsystem systemcommonality commonality(SEP) (SEP)
Initial InitialMass MassininLow-Earth Low-EarthOrbit Orbit Mass MasstotoMars MarsSurface Surface
430 430mt mt 33 33mt mt
Number NumberofofCrew Crew Number NumberofofCargo CargoLaunches Launches
66 66
Number NumberofofCrew CrewLaunches Launches On-Orbit On-OrbitAssembly AssemblyRequired? Required?
11 No No
Architecture ArchitectureRedundancy Redundancy Architecture ArchitectureComplexity Complexity
Full Fullarchitectural architecturalredundancy redundancy(vehicle (vehicleoverlap) overlap) Long Longsurface surfacemission mission
Architecture ArchitectureSensitivity Sensitivity Crew CrewHazards Hazards
Low Low Surface Surfacemission, mission,900-day 900-daylong longmission mission
Time TimeininInterplanetary InterplanetarySpace Space Time Timeon onSurface Surface
360-380 360-380total totaldays days 540 540total totaldays days
BGD/Short Stay Architecture 7/11/2000 6
81
Mars-Long Stay Mission Architecture Summary Strengths
Exploration Office
Weaknesses
•
Low initial mass in LEO (430 mt)
•
•
Small variation in mass; less sensitive to mass, level of redundancy, and technology changes
Long mission requires high reliability (30 months)
•
Long surface mission (18 months)
•
Many unknowns and crew health issues of long surface mission and surface environment (radiation, dust, gravity, etc.)
•
Long-range roving capabilities for regional science (1000 km desired)
•
Development of new 80-mt launch vehicle
•
Crew productivity and challenges during long mission
•
Science return is regional “discovery” oriented
•
Crew time spent in free space zerog/radiation environment is minimized (360 days total)
•
Potential for reuse of surface mission assets
•
Functional overlap of mission resources
•
Paced architecture allows for contingencies and re-planning
•
Rendezvous and docking of two elements in low-Earth orbit
BGD/Short Stay Architecture 7/11/2000 6
82
Exploration Office
Backup
BGD/Short Stay Architecture 7/11/2000 6
83
Mars Long-Stay Mission Objectives Exploration Office
•
Balance technical, programmatic, mission, and safety risks
•
Provide an operationally simple mission approach emphasizing the judicious use of common systems
•
Provide a flexible implementation strategy
•
Limit the length of time that the crew is continuously exposed to the interplanetary space environment
•
Define a robust planetary surface exploration capacity capable of safely and productively supporting crews on the surface of Mars for 500-600 days each mission
•
Enable the capability to live off of the land
•
Design systems capable of performing in each launch opportunity
•
Examine at least three human mission to Mars
BGD/Short Stay Architecture 7/11/2000 6
84
Mars Transit Habitat Exploration Office
HATCH DOORS
LEVEL 4 Pressurized Tunnel
INFLATABLE SHELL
LEVEL 3 Crew Health Care Area
SOFT STOWAGE ARRAY
ERGOMETER
CENTRAL STRUCTURAL CORE TREADMILL
LEVEL 2 Crew Quarters & Mech Rm
INFLATABLE OUTFITTING COMPRESSION RING
INTEGRATED WATER TANK / STORM SHELTER
LEVEL 1: Galley / Wardroom Area
20" WINDOW (2)
BGD/Short Stay Architecture 7/11/2000 6
Ref. Johnson Space Center
85
Crew Taxi Vehicle for the SEP Architecture Exploration Office
• “Requirements” – Launch and recovery in Space Shuttle or Based at ISS – Utilizes space storable propellants – Crew of 6 with ∆V capability of >3100 m/s – Ten day upper limit for orbit phasing, rendezvous, and missed rendezvous – Aerocapture maneuvers at lunar return speeds to ISS orbit
Crew Module Space Radiators
Propellant
• Preliminary Concept – Lifting body for crew g reduction – Integral LOX/CH4 propulsion system – Lightweight docking system Fuel Cell Reactants Water Jacket / Storm Shelter
BGD/Short Stay Architecture 7/11/2000 6
Ref. Johnson Space Center
86
Dual Lander Configurations Exploration Office
Surface Habitat
Descent / Ascent Vehicle
Ellipsled Aerobrake Descent / Ascent Vehicle
Hab Lander (Deflated)
Circ. Stage
Circ. Stage TMI Stage
BGD/Short Stay Architecture 7/11/2000 6
TMI Stage
Ref. Johnson Space Center
87
SETV Baseline 3.4B Rev 1 Exploration Office
SETV Resupply Proximity Operations Inflatable Ribs PV Array Sectors
Folded Articulated Thruster Boom HET Thruster Platform
SETV Bus Module Xenon Tank Electric Propulsion Module
Payload Docking Interface
EPM Docking Interface
TMI Stage Mars Payload BGD/Short Stay Architecture 7/11/2000 6
Ref. Glenn Research Center
88
Emerging Solar Array Technology Exploration Office
Four Arched Lenses
Folding Hinge Composite Sheet
• • •
Current SEP concept assumes thin film arrays Loose pointing requirements Requires 14,700 m2
BGD/Short Stay Architecture 7/11/2000 6
•
• •
8.5X Geometric Concentration Ratio
Tandem Cells
In the near term, lab demonstrations of 300 W/m2 for flexible concentrators Tight pointing requirements Area reduced to 6700 m2
89
Modular “Bimodal” NTR Transfer Vehicle Designs Developed for Mars Cargo and Piloted Missions Exploration Office
Bimodal NTR:
High thrust, high Isp propulsion system utilizing U235 produces thermal energy for propellant heating and electric power generation enhancing vehicle capability
Bimodal NTR Stage
Engine Characteristics • • • •
Three 15 klbf tricarbide engines Each bimodal NTR produces 25 kWe Utilizes proven Brayton technology Variable thrust & Isp optional with “LOXafterburner” nozzle (LANTR)
Vehicle Characteristics • • • • • • • •
Versatile design “Bimodal” stage produces 50 kWe Power supports active refrigeration of LH2 New “saddle” truss design allows easy jettisoning of “in-line” LH2 tank & contingency consumables Vehicle rotation (w ≤ 4 rpm) can provide Mars gravity to crew outbound and inbound (available option) Propulsive Mars capture and departure on piloted mission Fewest mission elements, simple space operations & reduced crew risk Bimodal NTR vehicles easily adapted to Moon & NEA missions
BGD/Short Stay Architecture 7/11/2000 6
TransHab
Crew Transfer Vehicle
Ref. Glenn Research Center
90
“Shuttle Compatible” Launch Vehicle Configurations Large Payload Missions to LEO
Exploration Office
Space Based Laser (SBL) Delivery
(HMM w/ Expendable Shroud)
HMM with Integrated Shroud/Aerobrake
SBL
322 ft.
327 ft.
272 ft. U S A
Payload = 188 klb (to 220 nmi circ @ 28.5°)
BGD/Short Stay Architecture 7/11/2000 6
U S A
Payload = 197 klb (to 220 nmi circ @ 28.5°)
U S A
Payload = 139 klb (to 700 nmi circ @ 40°)
Ref. Marshall Space Flight Center
91
Payload/Vehicle Processing Exploration Office ID 1
Task Name Magnum #1
2
Magnum #1
3
Magnum Stack
4
Kick Stage Mate
5
Payload Mate
October 11 18 25
1
November 8 15 22 29
December 6 13 20 27
3
January February 10 17 24 31 7 14 21 28
7
March 14 21 28
4
April 11 18 25
2
May 9 16 23 30
6
June 13 20 27
4
July 11 18 25
1
Magnum #2
8
Magnum #2
9
Magnum Stack
10
Kick Stage Mate
11
Payload Mate Pad Ops
12 13
4
Pad Ops
6 7
27
Magnum #3
14 15
Magnum Stack
16
Kick Stage Mate
17
Payload Mate Pad Ops
18 19
Magnum #4
20
Magnum #4
21
Magnum Stack
22
Kick Stage Mate
23
Payload Mate
23
Payload Mate Pad Ops
24 25
Magnum #5
26
Magnum #5
27
Magnum Stack
28
Kick Stage Mate
29
Payload Mate Pad Ops
30 31
Magnum #6
32
Magnum #6
33
Magnum Stack
34
Kick Stage Mate
35
Payload Mate
36
Pad Ops
BGD/Short Stay Architecture 7/11/2000 6
Ref. Kennedy Space Center
92
Mars Long-Stay Mission Risk Reduction and Functional Redundancy
Exploration Office
• Reliability and survivability of critical systems will be a major challenge for all Mars missions – Long-duration missions – No capability for resupply – Limited abort capabilities
• Risk reduction achieved by several techniques – Architectural redundancies through mission design – Functional redundancy by dis-similar means to accomplish same end result – Early development and implementation of systems (time on systems) – Proper systems designs
• Selection of proper technique(s) requires cost/benefit analysis
BGD/Short Stay Architecture 7/11/2000 6
93
Hierarchy Process Exploration Office
c Mission Design – Forward deployment (overlapping of mission resources) – Verification and checkout prior to crew departure – Mission mission approaches
d Resource Sharing and Technologies – Advanced technologies (unique products and robust capabilities) provides crossstrapping of resources between systems
e Operational Concepts – – – – –
Conservation of resources (power, consumables, etc.) Modularity of systems In-flight maintenance and sparing “Hanger Queen” Procedures and concepts
f Systems Designs – – – – –
Flexibility of designs (unanticipated uses) Experience of previous and current programs Reliability Robustness of mission elements and capabilities Dual paths, isolation, interlinking, crossfeeding, etc.
BGD/Short Stay Architecture 7/11/2000 6
94
Resource Sharing Example: Power and Consumables Exploration Office
RFC Reactants (Backup)
Re
e arg h c
(B
ku ac
p)
i erat
Main Main Power Power
Gen
HO 2 , O
Rovers Rovers
O2
2
( Ma keu
p&
Bac kup )
In-Situ In-Situ Resource Resource Utilization Utilization
on
PV/RFC (Backup)
Advanced Advanced Life Life Support Support BGD/Short Stay Architecture 7/11/2000 6
H2O CO2 Removal (Backup)
Extra Extra Vehicular Vehicular Activity Activity 95
Form Approved OMB No. 0704-0188
REPORT DOCUMENTATION PAGE
Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503.
1. AGENCY USE ONLY (Leave Blank)
2. REPORT DATE
July 2007
3. REPORT TYPE AND DATES COVERED
NASA Technical Memorandum
4. TITLE AND SUBTITLE
5. FUNDING NUMBERS
Decadal Planning Team Mars Mission Analysis Summary
6. AUTHOR(S)
Bret G. Drake
7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)
8. PERFORMING ORGANIZATION REPORT NUMBERS
Lyndon B. Johnson Space Center Houston, Texas 77058 y
S-1012
9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)
10. SPONSORING/MONITORING AGENCY REPORT NUMBER
National Aeronautics and Space Administration Washington, DC 20546-0001
TM-2007-214761
11. SUPPLEMENTARY NOTES
12a. DISTRIBUTION/AVAILABILITY STATEMENT
12b. DISTRIBUTION CODE
Unclassified/Unlimited Available from the NASA Center for AeroSpace Information (CASI) 7115 Standard Hanover, MD 21076-1320 Category: 12 13. ABSTRACT (Maximum 200 words)
In June 1999, the NASA Administrator chartered an internal NASA task force, termed the Decadal Planning Team, to create new integrated vision and strategy for space exploration. The efforts of the Decadal Planning Team evolved into the Agency-wide team known as the NASA Exploration Team (NEXT). This team was also instructed to identify technology roadmaps to enable the sciencedriven exploration vision, established a cross-enterprise, cross-center systems engineering team with emphasis focused on revolutionary not evolutionary approaches. The strategy of the DPT and NEXT teams was to “Go Anywhere, Anytime” by conquering key exploration hurdles of space transportation, crew health and safety, human/robotic partnerships, affordable abundant power, and advanced space systems performance. During the DPT and NEXT study cycles, several architectures were analyzed including missions to the Earth-Sun Libration Point, the Earth-Moon Gateway and Earth-Moon Libration Point, the lunar surface, Mars (both short and long stays), one-year round trip Mars, and near-Earth asteroids. Although there was much emphasis placed on utilization of existing launch capabilities, the team concluded that missions in near-Earth space are only marginally feasible and human missions to Mars were not feasible without a heavy lift launch capability. In addition, the team concluded that missions in Earth’s neighborhood, such as to the moon, can serve as stepping-stones toward further deep-space missions in terms of proving systems, technologies, and operational concepts. 14. SUBJECT TERMS
15. NUMBER OF PAGES
Exploration, space flight, lunar exploration, Mars exploration, experimentation, risk contingency spacecraft design, aerospace engineering 17. SECURITY CLASSIFICATION OF REPORT
18. SECURITY CLASSIFICATION OF THIS PAGE
Unclassified
Unclassified
Standard Form 298 (Rev Feb 89) (MS Word Mar 97) Prescribed by ANSI Std. 239-18 298-102
106
19. SECURITY CLASSIFICATION OF ABSTRACT
Unclassified NSN 7540-01-280-5500
16. PRICE CODE
20. LIMITATION OF ABSTRACT
Unlimited