FISO Telecon 04-08-15
A CREWED MARS EXPLORATION ARCHITECTURE USING FLYBY AND RETURN TRAJECTORIES
Andrew S.W. Thomas NASA Astronaut, Explora on Branch, Astronaut Office, NASA Johnson Space Center
Cesar A. Ocampo Senior Engineer, Odyssey Space Research LLC., NASA Johnson Space Center
Damon F. Landau Jet Propulsion Laboratory, California Ins tute of Technology
These are part of the results of an internal NASA-JSC study with NASA-JPL collaboration titled The Mars Lite Study Presentation given by: C. Ocampo and D. Landau This presentation is not a stand-alone presentation document. It requires narration.
© 2015 All rights reserved 1 Inspira on Mars Founda on
Aims to launch a manned mission to fly by Mars in by 2021
Founda on claims that space explora on provides a catalyst for growth, na onal prosperity, knowledge and global leadership.
By taking advantage of this window of opportunity, the Inspira on Mars Founda on intends to revitalize interest in science, technology, engineering and mathema cs (STEM) educa on. h p://www.inspira onmars.org/
2 Figure Only: EME-Inspiration Mars Foundation. (in case next slide video does not work for some)
3 Video: EME-Inspiration Mars Foundation. Click center of screen once to start.
4 Figure Only: EME-Inspiration Mars Foundation Fly Around. (in case next slide video does not work for some)
5 Video: EME-Inspiration Mars Foundation Fly Around. Click center of screen once to start.
6 Single Flyby Mission: fast in-and-out
Ballistic single flyby Pass.
dip in and out Δv Speed up Δv Catch up
Δv
7 Figure Only: Single Flyby Mission: fast in-and-out: (in case next slide video does not work for some)
8 Video: Single Flyby Mission: fast in-and-out: Click center of screen once to start.
9 Solu on: Use Low Energy Flyby and Return Trajectories with Two Flyby Events Inherit natural abort op on
The two flyby events separated by months
Place massive transit habitat(s) on these trajectories eliminate inser on and departure of massive assets into and out of Mars Orbit
1st flyby event is used to drop off a crew taxi 2nd flyby event picks-up and uses a hyperbolic rendezvous for Earth return Assume Mars Stay Habitat has been Pre-deployed at Mars
Favor launch, en-route maneuvers, Earth arrival speeds over transit mes. Assume no new major technology development. 10
Work summarized and presented as paper AAS 15-372 at the 25th AAS/AIAA Space Flight Mechanics Mee ng, Williamsburg, VA, January 2015
11 Mars Free Returns…
Damon Landau
12 Broad Search of Mars Free-Returns
Search parameters Launch 2015–2052 Maximum flight me: 1200 days
Maximum Launch V∞: 7 km/s
Maximum Arrival V∞: 9 km/s Minimum Mars flyby al tude: 300 km Heliocentric revolu ons between encounters: 0 or 1 Number of gravity assists: 1 or 2 Parameters specific to “Star” algorithm Time step for encounter dates: 3 days Maximum ΔV at flyby: 20 m/s
V∞ step for 180° transfers: 20 m/s 13 Trajectory Search Methodology
Launch Mars Flyby Earth 1. Grid up Earth, Mars, and Earth Dates ΔV < 20 m/s Return encounter mes V∞ < 7 km/s Alt > 300 km V∞ < 9 km/s 2. Calculate outbound & inbound legs 2015 independently
3. Filter on low ΔV to match in & out V∞ at Mars 3-day Turns a 3-D search into two 2-D searches increments • 720M sequences considered with only 7.3M trajectory computa ons (Lambert fits) • 44,725 trajectories met all constraints 2052
Flight time < 1200 d
V∞ constraint violated
Time node deleted 14 Double-Flyby Free-Returns
• EMME, EMVE, EVME Launch Mars or Mars or Earth Dates Venus Venus Return sequences in single run V∞ < 7 km/s ΔV < 20 m/s ΔV < 20 m/s V∞ < 9 km/s • Transform 4-D search 2015 into three 2-D searches • 280B sequences 3-day assessed with only increments 27M trajectory fits • 1,425 trajectories met all constraints 2052 Flight time < 1200 d
15 Building Mul ple Flybys
Flyby ΔV calcula on builds trajectory segments with three encounters: departure body to flyby body (incoming leg) and flyby body to arrival body (outgoing leg). The outgoing legs for one trajectory segment match with the incoming legs to another trajectory segment. Launch Mars or Mars or Dates Venus Venus Launch Mars or Mars or Earth Dates Venus Venus Return = Earth + Return
16 Flight Times
Trajectories in black also satisfy Trans-Mars Injection ΔV < 4.5 km/s and Earth entry < 12.5 km/s 17 Launch Opportuni es
Trajectories in black also satisfy Trans-Mars Injection ΔV < 4.5 km/s and Earth entry < 12.5 km/s 18 3:2 Resonance Free Returns
19 2:1 Resonance Free Returns
20 Short Flight Time
21 Double Mars Flyby
22 Venus Flybys
23 …con nue
Using Free Returns for extended Human Mars Explora on missions
24 Determine how to use 2 flyby events
?
25 Solu on 1: Dual Habitat Concept
Sketch credited to Ryan Whitley (JSC) OTH = Outbound Transit Habitat RTH = Return Transit Habitat 26 Solu on 2: Loiter Habitat Concept
Sketch credited to Ryan Whitley (JSC) 27 Used… Copernicus: A Generalized Trajectory Design and Op miza on System
Developed jointly between the University of Texas and the NASA Johnson Space Center (2001-present) Hosted at NASA-JSC
Current Development at JSC Current Lead Developer: Jacob Williams, ERC-NASA- JSC, Houston, Texas
http://www.nasa.gov/centers/johnson/copernicus/ 28 Impulsive Gravity Assist to Real Flyby Conversion
29 Impulsive Gravity Assist to Real Flyby Conversion
30 Figure Only: Initial Guess for An Earth-Venus-Mars-Earth Free Return. Animation on next slide. Earth Depart
Mars Flyby
Venus Flyby
Earth Arrive
31 Video: EVME Trajectory Construction Iteration Sequence. Click center of screen once to start.
32 Dual Habitat Model
Uses an Earth-Mars conjunc on class trajectory for the Outbound Habitat and an Earth-Mars-Earth Flyby and Return Trajectory for the Return Habitat
Crew Taxi 1-Sol Orbit Drop-off and Departure and Transfer to a Hyperbolic 1-Sol Orbit Rendezvous with Return Habitat
Low energy conjunc on class 3:2 Resonant Earth-Mars-Earth Free Return Trajectory Earth-Mars (Habitat orbits Sun twice while the Earth orbits Sun 3 mes 33 33 2039 2040 2041 2042 2043 Earth Mars Earth Dep. Fly by Arr. RTH Crew at Mars
OTH Earth Mars Dep. Fly by RTH Mars Flyby 10/21/2041
RTH E-M-E Trajectory (3:2 Resonant w/Earth)
OTH Earth Departure OTH 10/13/2039 Mars Arrival 06/21/2040
RTH Earth Departure 06/04/2039
RTH Earth Arrival 05/13/2042
34 Figure Only: Dual Habitat Model RTH Mars Flyby Pickup, Hyperbolic Animation on next slide Rendezvous
OTH Mars Arrive OTH Earth Depart
RTH Earth Arrive
RTH Earth Depart 35 Video: Dual Habitat Model Animation. Click center of screen once to start.
36 Dual Habitat Model 37 Loiter Habitat Model
Uses an Earth-Mars-Mars-Earth Flyby and Return Trajectory
Mars Flyby 1 to Mars Flyby 2
“Loiter Leg”
Crew Taxi 1-Sol Orbit Drop-off and Departure and Transfer to a Hyperbolic 1-Sol Orbit Rendezvous with Loiter Habitat
38 In live discussion point out the key features/pros/cons 39 39 Video: Loiter Hab Mars Centered Iteration Sequence. Click center of screen once to start.
40 Figure only: Converged Solution of previous slide video. 41 Figure: Mars Arrival Flyby-Loiter-Mars Departure Flyby
42 Figure only: Loiter Hab Mode;. (in case next slide video does not work for some)
43 Video: Loiter Hab Model Animation. Click center of screen once to start.
44 Figure Only: Loiter Hab Model Fly Around. (in case next slide video does not work for some)
45 Video: Loiter Hab Model Fly Around. Click center of screen once to start.
46 Loiter Habitat Model 47 Departure Earth Mars Mars Total Earth Mars Mars Earth Total Mars Mars Earth Mission Departure Fly-by1 Fly-by2 Arrival En-route Transit Transit Transit Duration V∞ V∞ V∞ V∞ ∆V
date day day day day km/s km/s km/s km/s km/s
6 Aug 2020 399 325 303 1028 3.794 2.550 3.018 4.714 1.676
8 Sep 2022 380 311 320 1010 3.673 2.573 2.887 3.787 0.621
05 Oct 2024 348 305 325 976 3.335 2.555 2.721 3.018 0.000
27 Nov 2026 280 303 358 941 4.000 2.942 2.989 3.546 0.126
29 Dec 2028 252 305 366 923 4.000 3.746 3.505 4.609 0.205
13 Feb 2031 223 321 379 924 4.000 3.804 3.251 4.317 0.515
31 Mar 2033 218 358 346 922 4.000 3.703 3.108 4.410 1.100
22 Jul 2035 364 346 213 923 4.000 3.100 3.737 3.884 0.856
10 Sep 2037 370 317 234 921 4.000 3.178 3.669 4.118 0.195
3 Oct 2039 367 305 267 939 3.530 2.852 3.041 4.045 0.000
21 Oct 2041 341 302 338 981 3.159 2.635 2.647 3.268 0.000
15 Oct 2043 331 303 381 1016 4.000 2.782 2.666 3.630 0.495
22 Jan 2046 244 315 375 934 4.000 3.762 3.289 4.227 0.477
13 Mar 2048 219 343 360 923 4.000 3.877 3.214 4.453 0.775
7 Jul 2050 347 361 209 917 4.000 3.046 3.606 3.721 1.068 Drop-Off from and Rendezvous with Transi ng (Loiter) Habitat
48 Drop-Off from and Rendezvous with Transi ng (Loiter) Habitat
49 1st maneuver: capture, coast to apoapsis
50 2nd maneuver: plane change, coast to periapsis
51 3rd maneuver: capture into op mal 1-Sol Orbit Mars Stay
52 4th, 5th maneuver: depart and do Hyperbolic Rendezvous
Total “In-and-Out” DV cost = 2.308 km/s (Oct 2039) (this ranges from 2.1 to 3.1 for all 15 Loiter Habitat Solu ons) 53 Figure Only: Mars centered transfers, iteration sequence. (in case next slide video does not work for some)
54 Video: Mars centered transfers, iteration sequence. Click center of screen once to start.
55 All Dual-Habitat, Loiter-Habitat Solu ons require same type of Mars Centered Maneuvering
Note orienta on of the 1-Sol Orbit 56 Figure only: Capture-Departure Geometry Fly Around. (in case next slide video does not work for some)
57 Video: Capture-Departure Geometry Fly Around. Click center of screen once to start.
58 Figure only: Departure, Hyperbolic Rendezvous. (in case next slide video does not work for some)
59 Video: Departure, Hyperbolic Rendezvous. Click center of screen once to start.
60 One chance to catch the train ride home.
(image credit: “The Darjeeling Limited”, Fox Searchlight Pictures)
61 Solu on 3: Hybrid Dual Loitering Habitat Model Four Flyby Events
62 63 Six E-M-M-E Mission Possibili es for the Hybrid Dual-Loitering Habitat Strategy
64 65 Dual Loitering Habitat Model: Maneuver Data and Performance
66 Concluding Remarks...
! Stair-step approach: Flyby-only, orbital, surface access, access to Phobos, Deimos
! Launch vehicle (Space Launch System) requirements (ongoing work, paper TBP August 2015, Whitley et al.)
- Dual Habitat Model: Requires 3 SLS Block 2B Launches
- Loiter Habitat Model: Requires 2 SLS Block 2B Launches
! Inser on-Departure to and from op mal 1-Sol Orbit is feasible
! Pre-deployment of Mars Stay Assets yet to be addressed (ongoing)
! Sensi vity studies of Hyperbolic Rendezvous wrt to delays, off-engine performance (ongoing work, paper TBP August 2015, Jedrey et al.) 67 Thank you…
Thanks also to the other members of the NASA JSC-JPL Mars Lite Study Team John Aitchison Lora Bailey Joe Caram Bret Drake Ricky Jedrey Kent Joosten Stan Love Fay Mckinney Nathan Strange/JPL Brenda Ward Ryan Whitley 68