Feasibility Analysis for a Manned Mars Free-Return Mission in 2018
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1 Feasibility Analysis for a Manned Mars Free-Return Mission in 2018 Inspiration Mars Dennis Tito, Taber MacCallum, John Carrico, 8 May, 2013
2 Authors Dennis A. Tito Inspiration Mars Foundation Grant Anderson Paragon Space Development Corporation John P. Carrico, Jr. Applied Defense Solutions, Inc. Jonathan Clark, MD Center for Space Medicine Baylor College Of Medicine Barry Finger Paragon Space Development Corporation Gary A Lantz Paragon Space Development Corporation Michel E. Loucks Space Exploration Engineering Corporation Taber MacCallum Paragon Space Development Corporation Jane Poynter Paragon Space Development Corporation Thomas H. Squire Thermal Protection Materials NASA Ames Research Center S. Pete Worden Brig. Gen., USAF, Ret. NASA AMES Research Center Tito, MacCallum, Carrico, Loucks 2
3 Background Worked on first Mars flyby trajectory at JPL: Mariner 4 Presented at the 2 nd Annual AIAA Meeting Started researching trajectories for human deep space missions This research led to the identification of a rare, 501-day, Quick Free-return Mars fly-by launch opportunity in January, 2018 Commissioned feasibility study for publication at IEEE Tito, MacCallum, Carrico, Loucks 3
4 Moonish R. Patel, James M. Longuski, Jon A. Sims, Mars Free Return Trajectories, JOURNAL OF SPACECRAFT AND ROCKETS, Vol. 35, No. 3, May June 1998 Tito, MacCallum, Carrico, Loucks 4
5 Tito, MacCallum, Carrico, Loucks 5
6 A 501-day free-return Mars flyby passing within a hundred miles of the surface Only small correction maneuvers are needed during transit Simple mission architecture lowers risk No entry into Mars atmosphere An exceptionally quick free return occurs twice every 15 years 1.4 years duration vs. 2 to 3.5 years typical Launch Jan 5, 2018, (or 2031) Mars on 20 Aug 2018 (227 days) Earth on 20 May 2019 (274 days) At Mars, Earth is 38,000,000 miles away Trajectory Tito, MacCallum, Carrico, Loucks 6
7 Trajectory Targeting Optimized 2-body/patched-conic trajectory values from Mission Analysis Environment (MAnE, from Space Flight Solutions): Leg Stay Time (days) Depart Arrive Flight Time (days) 1 Earth JAN 5, 2018, hours GMT AUG 20, 2018, hours GMT Mars Julian Date Julian Date Mars AUG 20, 2018, hours GMT MAY 21, 2019, hours GMT Earth Julian Date Julian Date Total Duration Leg V Inf (km/s) V Inf (km/s) Fully numerically integrated trajectory (using JPL 421 Ephemerides) values from STK/Astrogator (From Analytical Graphics, Inc.) Leg Stay Time (days) 1 Earth Mars Depart 5 Jan :00: UTCG 20 Aug :18: UTCG Mars Earth Arrive Flight Time (days) 20 Aug :18: UTCG May :52: UTCG Total Duration Departure Arrival V Inf V peri C3 V Inf V peri C3 Leg (km/s) (km/s) (km 2 /s 2 ) (km/s) (km/s) (km 2 /s 2 ) Tito, MacCallum, Carrico, Loucks 7
8 Tito, MacCallum, Carrico, Loucks 8
9 (4) Trans Mars Injection Burn (3)Low Earth Checkout and Deployment (9) Trans Earth Trajectory Mar s Motion Relative to Trajectory (10) Earth Reentry Sequence (1) Launch Fuel Supply? (2) Launch Human Crew (8) Mars Encounter Exit (11)Land on Earth (7) Mars Proximity Trajectory Events: Launch Fuel Supply: TMI - 1 Months? Launch Human Crew: TMI - < 2 Weeks Trans Mars Injection: TMI Mars Encounter Entrance: TMI + 8 Mo Mars Encounter Exit: TMI + 8 Mo Earth Reentry Sequence: TMI + 8 Mo Land on Earth: TMI + 17 Mo (5) Trans Mars Trajectory Phase (6) Mars Encounter Entrance Phases (Durations): Low Earth Checkout and Deployment: < 2 Weeks Trans Mars Trajectory: 8 Months Mars Proximity: ~ 24 hours Trans Earth Trajectory: 9 Months Earth Reentry Phase: 24 Hours Event Phase
10 Calendar Dec 17 Jan 18 Feb 18 Mar 18 Apr 18 May 18 Jun 18 Jul 18 Aug 18 Sep 18 Oct 18 Ground Network NEN/USN/TDRSS DSN/Other* DSN/Other MPT Phase LEO C&D Trans Mars Trajectory Trans Earth Trajectory Low Earth Orbit Phase: 1) Fuel Supply Launch? 2) Human Crew Launch 3) Crew & Fuel Rendezvous? 4) Systems Checkout 5) Inflatable Deployment 6) Trans Mars Injection Burn NEN begins to transition out DSN/Other/MRO/MAVEN Mars Periareion 20 Aug 2018 MRO 2005 Calendar Ground Network Phase Nov 18 Dec 18 Jan 19 Feb 19 Mar 19 Apr 19 May 19 DSN/Other** NEN/USN ERP Trans Earth Trajectory (Cont d) ** NEN begins to transition in Perihelion - 11 Mar 2019 Earth Reentry Phase: 1) Upper Stage Jettison 2) Inflatable Jettison 3) Entry Interface Attitude Alignment 4) Atmospheric Entry 5) Parachute Deployment 6) Land On Earth MAVEN
11 Trajectory Perspective Miles AU Black = Spacecraft distance from Earth (miles) Green = Spacecraft distance from Mars (miles) Red = Spacecraft distance from the Sun in Astronomical Units (AU)
12 Falcon Heavy Option Graphic courtesy SpaceX First flight scheduled for 2013 Man-rated design 53,000 kg to LEO 10,000 kg to Mars for this mission Free-return trajectory enables upper stage to stay attached for shielding Falcon Heavy Graphic courtesy SpaceX Tito, MacCallum, Carrico, Loucks 12
13 Option 1: Launch 1 Atlas 552: includes 18.1 mt useable propellant Launch 2 Atlas 552: with 10.5 mt payload ULA Options Option 2: Launch 2 Atlas 552: with 10.5 mt payload Launch 2 Delta HLV: with 10.5 mt payload Transfer 12 mt of propellant Tito, MacCallum, Carrico, Loucks 13
14 SLS - Orion as an Analytical Reference Point Tito, MacCallum, Carrico, Loucks 14
15 Earth Reentry Overview Atmospheric reentry vehicles require thermal protection systems (TPS) because they are subjected to intense heating The level of the heating is dependent on: Vehicle shape Entry speed and flight trajectory Atmospheric composition TPS material composition & surface properties Reentry heating to the vehicle comes from two primary Sources Convective heating from both the flow of hot gas past the surface of the vehicle and catalytic chemical recombination reactions at the surface Radiation heating from the energetic shock layer in front of the vehicle Tito, MacCallum, Carrico, Loucks 15
16 Looked at Aerocapture initially Tito, MacCallum, Carrico, Loucks 16
17 Reentry Heating Parameters Magnitude of stagnation heating is dependent on a variety of parameters, including reentry speed (V), vehicle effective radius (R), and atmospheric density (ρ) q conv V 3 R 0.5 Convective Heating As reentry speed increases, both convective and radiation heating increase At high speeds, such as 14.2 Km/s, radiation heating can quickly dominate As the effective vehicle radius increases, R convective heating decreases, but radiation heating increases Reentry g-loading is a parameter we 2R are considering q rad V R 0.5 Shock Radiation Heating Tito, MacCallum, Carrico, Loucks 17 V
18 Flight Concept Tito, MacCallum, Carrico, Loucks 18
19 Object Distance From Sun Mars Orbital Track Mars Flyby Spacecraft Trajectory Earth Orbital Track Venus Orbital Track Perihelion (Close to Venus Orbit*) *Venus is not present when the spacecraft is at perihelion
20 Solar Radiation Mars during the flyby is 708 W/m 2 (52% Earth) Closest approach is 2540 W/m 2 (188% of Earth levels) Solar Radiation (W/m2) Distance from Sun (AU) Solar Radiation Distance Dec Apr Jul Oct-18 4-Feb May-19 Mission Date 0 FISO 3 April,
21 ECLSS Launch Mass Legend: Basis System Consumables + Packaging CR /corrected to replace Biomass with additional packaged food Tito, MacCallum, Carrico, Loucks 21
22 Environmental Control and Life Support Tito, MacCallum, Carrico, Loucks 22
23 ECLSS Resources: 2 Person Crew for 501 Days Subsystem Mass 1 (kg) Vol 2 (m) 3 Peak 1 Power (W) Avg Power (W) Air ,626 1,870 Water 2, Food 1, , Thermal Crew Waste Human Accommodations Basic System 2, ,189 2,109 Consumables 3, Total = 5, ,489 2,109 1 Mass and power estimates based on ANSI/AIAA G , Guide for Estimating and Budgeting Weight and Power Contingencies For Spacecraft Systems 2 Volumes are total volume and do not account for packaging factors 3 Errata corrected from paper (estimated food volume is 4 m 3 ) Tito, MacCallum, Carrico, Loucks 23
24 ECLSS Test Facility Tito, MacCallum, Carrico, Loucks 24
25 Inspiration Mars Medical Team Interdisciplinary Team including Academic, Industry, and Government representation Specific Focus on Radiation, Microgravity and Behavioral Health Threats utilizing Personalized Medicine Astro-omeics Approach Tiered Approach involving candidate selection, crew training, as well as mission and post mission support utilizing the highest level of advanced health care delivery
26 Radiation Environment Risk Assessment Mission occurs during solar minimum Expert consensus: risk is manageable Tito, MacCallum, Carrico, Loucks Risk of Exposure-Induced Death 500-d Mars Flyby (GCR + SPEprob) Multiple dose mitigation strategies can be used to reduce the risk Upper stage & propellant residuals Water storage placement Crew selection Dietary/pharmaceuticals 26
27 Psychological and Behavioral Health 27
28 Inspiration Mars Inspire a sea change in the American Space Program Inspire our political leaders today to stop being timid - and fund a piloted Mars program that will get us to the surface. Address technical risks in human deep space exploration Demonstrate the feasibility of human missions to Mars Foster knowledge, experience and momentum for space exploration Validate the program of record Strengthen the U.S. position as a leader in exploration Inspire youth through science, technology, engineering and math (STEM) education and motivation Public participation Tito, MacCallum, Carrico, Loucks 28
29 Conclusion Completed initial conceptual feasibility study Ongoing development includes Schedule & Program Human Health and Radiation Launch (technical assessment) Spacecraft architecture ECLSS TPS assessment Trajectory optimization Expand interaction with NASA, aerospace industry, and academia Tito, MacCallum, Carrico, Loucks 29
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