FISO Telecon 04-08-15 A CREWED MARS EXPLORATION ARCHITECTURE USING FLYBY AND RETURN TRAJECTORIES Andrew S.W. ThomAs NASA Astronaut, Exploraon 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 Ins1tute 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 Inspiraon Mars Foundaon Aims to launch a manned mission to fly By Mars in By 2021 Foundaon 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 Inspiraon Mars Foundaon intends to revitalize interest in science, technology, engineering and mathema+cs (STEM) educa+on. hPp://www.inspiraonmars.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 Soluon: Use Low Energy FlyBy and Return Trajectories with Two FlyBy Events Inherit natural abort opon The two flyby events separated By months Place massive transit habitat(s) on these trajectories eliminAte inseron 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 Mee1ng, WilliamsBurg, VA, January 2015 11 Mars Free Returns… Damon Landau 12 Broad Search of Mars Free-Returns Search parameters Launch 2015–2052 Maximum flight 1me: 1200 days Maximum Launch V∞: 7 km/s Maximum Arrival V∞: 9 km/s Minimum Mars flyBy al1tude: 300 km Heliocentric revolu1ons 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 1mes 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 computaons (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 Mul1ple FlyBys Flyby ΔV calculaon 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 Opportuni1es 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 …connue Using Free Returns for extended Human Mars Exploraon missions 24 Determine how to use 2 flyBy events ? 25 Solu1on 1: Dual Habitat Concept Sketch credited to Ryan Whitley (JSC) OTH = Outbound Transit Habitat RTH = Return Transit Habitat 26 Solu1on 2: Loiter Habitat Concept Sketch credited to Ryan Whitley (JSC) 27 Used… Copernicus: A GenerAlized Trajectory Design and Opmizaon 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 conjunc1on 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 conjunc1on class 3:2 Resonant Earth-Mars-Earth Free Return Trajectory Earth-Mars (Habitat orBits Sun twice while the Earth orBits Sun 3 1mes 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 op1mal 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 Soluons) 53 Figure Only: Mars centered transfers, iteration sequence.