Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. A Mars Heavy Transport.

Slides:

Advertisements

Similar presentations

Concept Overview for 2 mt Case “2 mt case”: integrated payloads of no more than 2 mt can be landed on the surface of Mars; extension of current Mars EDL.

Advertisements

Larry Phillips MAY 13th-17th, 2002 Micro Arcsecond Xray Imaging Mission: Pathfinder (MAXIM-PF) Launch Vehicle Information Final Version.

MAE 4262: ROCKETS AND MISSION ANALYSIS Orbital Mechanics and Hohmann Transfer Orbit Summary Mechanical and Aerospace Engineering Department Florida Institute.

A GenCorp Company High Thrust In-Space Propulsion Technology Development R. Joseph Cassady Aerojet 22 March 2011.

Comparative Assessment of Human Missions to Mars Damon F. Landau Ph. D. Preliminary Exam September 13, 2005.

 Falcon 9 Heavy › To carry crew capsule and propellant required to rendezvous with transit vehicle Image Credit:

“Mars To Go” Based Missions Donovan Chipman David Allred, Ph.D.

Mission To Mars In Kerbal Space Program, Where distances are 1/9 real world values.

Lessons from Apollo * Data from NASA Apollo 11 Press Kit Shows spacecraft weight delivered to LEO (Low Earth Orbit) Shows weights for each portion of Apollo.

Minimalist Mars Mission Establishing a Human Toehold on the Red Planet January 2011 Review DevelopSpace MinMars Team.

Minimalist Human Mars Mission Surface infrastructure discussion July 26 th, 2008.

AAE450 Spring 2009 Propellant Choice and Mass Estimates for the Translunar OTV Week 2 Presentation Thursday, Jan 22, 2009 Brad Appel Propulsion Group.

The Lander is at a 25 km Lunar altitude and an orbital period of approximately 110 minutes. After separation occurs the Lander is completely self sufficient.

AAE450 Spring 2009 Slide 1 of 8 Orbital Transfer Vehicle (OTV) Masses and Costs Ian Meginnis March 12, 2009 Group Leader - Power Systems Phase Leader -

Project X pedition Spacecraft Senior Design – Spring 2009

AAE450 Spring 2009 Translunar OTV (Orbital Transfer Vehicle) : Chemical Propulsion System Refined estimates: OTV WET Mass, Propellant Volume & Propellant.

Spacecraft Propulsion Dr Andrew Ketsdever Lesson 13 MAE 5595.

Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration Vehicle Michael Seibert University of Colorado at Boulder.

THE FUTURE PLANS OF NASA FOR HUMAN SPACE FLIGHT; MISSIONS, LAUNCH VEHICLES.

Launch System Launch Vehicle Launch Complex Orbit Insertion Orbit Maneuvers.

Jet Propulsion Laboratory California Institute of Technology National Aeronautics and Space Administration National Aeronautics and Space Administration.

Samara State Aerospace University (SSAU) Samara 2015 SELECTION OF DESIGN PARAMETERS AND OPTIMIZATION TRAJECTORY OF MOTION OF ELECTRIC PROPULSION SPACECRAFT.

Background The Apollo program sent 12 Americans to the lunar surface between 1969 and 1972, but humans have not set foot on the moon since then. In January.

The Return to Space Exploration Constellation. NASA Authorization Act of 2005 The Administrator shall establish a program to develop a sustained human.

A3 Altitude Test Facility

Oh, Thank Heaven for 7-Eleven: Fueling Up in Space with In-Situ Resource Utilization ASTE-527 Final Presentation Riley Garrett.

Dynamic Design: Launch and Propulsion Genesis Launch Vehicle: The Delta Rocket Student Text Supplement.

Ryan Mayes Duarte Ho Jason Laing Bryan Giglio. Requirements  Overall: Launch 10,000 mt of cargo (including crew vehicle) per year Work with a $5M fixed.

“BUILDING SUCCESS WITH S..T..E..M” (S CIENCE, T ECHNOLOGY, E NGINEERING & M ATH ) Presented by Scientist Wardell Huff And Sharon Huff April 2014.

Team PM8 Eventus Slide 1. Commercial spaceflight has seen increased activity as more privately owned companies invest in the venture. To avoid a catastrophic.

LUNAR MISSION TO CELEBRATE THE 50 TH ANNIVERSARY OF THE APOLLO 11 LANDING 01October2015.

What to do with Space Station Poo 1. 2 David Heck Advanced Manufacturing Research & Development Boeing – Phantom Works, St. Louis, Mo SEND IT TO THE MOON.

Advanced Space Exploration LEO Propellant Depot: Space Transportation Impedance Matching Space Access 2010 April 8-10, 2010 Dallas Bienhoff Manager, In-Space.

AAE 450- Propulsion LV Stephen Hanna Critical Design Review 02/27/01.

STRATEGIES FOR MARS NETWORK MISSIONS VIA AN ALTERNATIVE ENTRY, DESCENT, AND LANDING ARCHITECTURE 10 TH INTERNATIONAL PLANETARY PROBE WORKSHOP June,

MIT : NED : Mission to Mars Presentation of proposed mission plan

RASC-AL 2010 Topics. TECHNOLOGY-ENABLED HUMAN MARS MISSION NASA is interested in eventual human mission to the Martian surface. Current Mars design reference.

Minimalist Mars Mission Establishing a Human Toehold on the Red Planet Executive Summary DevelopSpace MinMars Team.

Mars Today 1 An immediate and inexpensive program for manned Mars visitation.

Introduction to the Altair Project

MAE 4262: ROCKETS AND MISSION ANALYSIS

ERV - 1 End of Semester Presentation Brad Buchanan – Group Leader Dominic Amaturo.

Universal Chassis for Modular Ground Vehicles University of Michigan Mars Rover Team Presented by Eric Nytko August 6, 2005 The 2 nd Mars Expedition Planning.

NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM DANIEL MCCAFFERY JEFF ROBINSON KYLE SMITH JASON TANG BRAD THOMPSON.

Structural Practices Principles of Space Systems Design U N I V E R S I T Y O F MARYLAND Structural Design Practices Payload interfaces to launch vehicles.

Unit 6 Lesson 1 Explanation. In 2004, President Bush set the following goal for the NASA constellation program, “this vision… is a sustainable and affordable.

Human Exploration of Mars Design Reference Architecture 5

LEO Propellant Depot: A Commercial Opportunity? LEAG Private Sector Involvement October 1 - 5, 2007 Houston, Texas LEAG Private Sector Involvement October.

Rocket Performance Principles of Space Systems Design U N I V E R S I T Y O F MARYLAND Parametric Design The Design Process Regression Analysis Level I.

Review of Past and Proposed Mars EDL Systems. Past and Proposed Mars EDL Systems MinMars Mars entry body design is derived from JPL Austere Mars entry.

Launch Structure Challenge - Background Humans landed on the moon in 1969 – Apollo 11 space flight. In 2003, NASA started a new program (Ares) to send.

Orbital Aggregation & Space Infrastructure Systems (OASIS) Background Develop robust and cost effective concepts in support of future space commercialization.

Nuclear Thermal Propulsion for Robotic and Piloted Titan Missions Brice Cassenti University of Connecticut.

An Earth – Moon Transportation System Patrick Zeitouni Space Technology.

The Future of Human Spaceflight *** A Journey to Mars

Callisto Mission LaRC Option

Space Tug Propellant Options AIAA 2016-vvvv

1. Launch Mother Ship to LEO

Propellant Depot Bernard Kutter United Launch Alliance

Development and Principles of Rocketry

Deputy, Washington Operations

Mars Sustainability Workshop Kennedy Space Center February 8, 2018

Attitude, Lunar Transfer Phase

Robert Zubrin Pioneer Astronautics W. 8th Ave. unit A

Lunar Base Preliminary Design Study

Sustainable Space Development

Derivation of the FSOA in Ariane 6 Specifications

Introduction to the Altair Project

Robert Zubrin Pioneer Astronautics W. 8th Ave. unit A

Team A Propulsion 1/16/01.

Presentation transcript:

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. A Mars Heavy Transport Architecture Using Existing Launchers and Technology

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Existing « throw capacity » to a direct Trans Mars Injection (C3 = 10 km 2 /s 2 ) Delta-IV HeavyAriane VProton / cryo[1][1]Proton/ Briz[2][2] Payload after TMI:8,000[3][3]5,900[4][4]5’800[5][5]4,580[6][6]Kg [1][1] Assumes developing a new cryogenic upper stage for the Proton, with same dry mass as the Briz-M. [2][2] Using the 327s isp Briz-M upper stage [3][3] Delta IV Heavy Demo brochure [4][4] Derived from GTO payload data [5][5] Derived from Briz-M payload data [6][6] Proton Launch System Mission Planner’s Guide, page 2-23

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Potential payload to Trans Mars Injection using a space tug for orbit raising from 400 x 400 km orbit to 400 x 300,000 km departure orbit (C3 = 10 km 2 /s 2 ) Delta-IV HeavyAriane VProton / cryoProton / Briz Payload after TMI:17,600[1][1]16,400 16’000[1][1] 14,600[1][1] kg [1][1] Additional air drag due to increased payload fairing to 5.4m diameter

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Standard Delta-IV Fairing Proposed configuration

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Standard Delta-IV Fairing Proposed configuration Mars entry aeroshell Payload adaptor and cryogenic cooling system Upper stage modified for cryogenic cooling of propellants

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Orbital Transfer Tug 3,500 m2 SLASR solar arrays Propulsion Module equiped with several NEXT ion drives (13.3 tons) Jettisoneable Propellant Tank (7.1 tons)

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Low Earth Orbit to Earth Departure Orbit Earth LEO Departure Orbit

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Earth Departure Orbit Direct launch crew transfer capsule

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug Orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug Orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug Orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug Orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug Orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Space tug Orbit lowering by multiple atmospheric passes Earth LEO

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Mars Capture Orbit

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Mars Capture Orbit Mars 1 sol period capture orbit 250 x 33,793 km

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Transfer data: best 180-day opportunities from 2001 to 2039 DateDeparture C3Arrival C3Departure dVArrival dVEntry VTOF (km2/s2) (km/s) (days)

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Payload to LEO (400 x 400 km orbit) Delta-IV HAriane VProton/cryoProton/Briz Payload to LEO 22,560 21,000 22,200 * 21,600kg 5.4m fairing penalty ,118 kg New payload to LEO 22,234 21,000 20,082 19,482kg Payload + upper stage 26,269 25,838 22,849 22,248kg Refrigeration system kg Payload adapter kg => Additional mass 1, kg

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Results: Gross payload mass to MOC including aeroshell DateDelta-IV HAriane VProton/cryoProton/Briz '896 16'731 16'307 14'922kg '766 16'599 16'193 14'775kg '128 14'942 14'769 12'955kg '245 14'050 14'001 11'998kg '366 14'172 14'106 12'128kg '258 15'073 14'882 13'098kg '327 16'154 15'811 14'282kg '841 16'676 16'259 14'861kg '020 16'856 16'414 15'063kg '755 15'575 15'314 13'645kg '469 14'276 14'196 12'239kg '092 13'895 13'868 11'833kg '834 14'644 14'513 12'634kg '783 15'604 15'339 13'677kg '747 16'580 16'177 14'754kg '950 16'786 16'354 14'984kg '469 16'299 15'936 14'442kg '867 14'678 14'542 12'670kg '205 14'009 13'966 11'955kg

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Results: Net mass to MOC without aeroshell mass (~3.5 tons) DateDelta-IV HAriane VProton/cryoProton/Briz '297 13'179 12'771 11'442kg '286 13'158 12'766 11'396kg '664 11'520 11'354 9'605kg '724 10'579 10'532 8'613kg '733 10'597 10'535 8'653kg '551 11'426 11'245 9'550kg '600 12'484 12'158 10'703kg '197 13'082 12'683 11'344kg '514 13'391 12'964 11'659kg '292 12'154 11'902 10'290kg '969 10'823 10'746 8'867kg '492 10'352 10'326 8'388kg '144 11'015 10'891 9'107kg '024 11'906 11'655 10'079kg '054 12'940 12'556 11'197kg '410 13'289 12'873 11'553kg '004 12'873 12'521 11'077kg '399 11'254 11'123 9'320kg '653 10'510 10'468 8'545kg

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Manned mission to Mars orbit Example manned habitat: Destiny with 5 basic racks = 14.5 tons Minimum consumables for 3 persons for 180 days = 2.4 tons Rough estimation for a 3-person habitat to Mars = 17.7 tons Activities in Mars orbit: 1.Explore the Moons of Mars 2.Remote-control surface robots for in situ resource exploitation (prepare base and manned ascent vehicle) 3.Land on the surface

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Getting down to the surface Problem: Ballistic Coefficient is too high (560 kg/m2) Solution: Raise Drag Coefficient, enlarge drag area Standard aeroshell (works only for relatively light payloads) Large heatshield in front of payload Light aeroshell and hypersonic parachute

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Results: Useful payload on the martian surface - Depends on the atmospheric entry solution chosen - Chemical thrust delta-v may vary between 600 m/s and 1,400 m/s depending on the solution - Considering LOX/LH thrusters, final useful surface payload may vary between 30% and 50% of the atmospheric entry mass: Delta-IV HeavyAriane VProton / cryoProton / Briz Useful payload on surface: 5.3 to 8.8 tons4.9 to 8.2 tons4.8 to 8.0 tons 4.4 to 7.3 tons

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Conclusions 1.Light manned missions to Mars orbit can be made possible using existing launchers and technology Requirements: - Modifying upper stages for cryogenic cooling - Developing an ion-driven space tug - Developing a 5.4m Mars aeroshell - Man-rating a heavy launcher to launch the CEV to 400 x 300,000 km 1.Manned missions to the martian surface may be possible using existing launchers provided certain new technologies are developed Further requirements: - Hypersonic parachutes - Highly autonomous robots for surface activity - Practical and lightweight LOX/LH extraction from martian water

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Thank you for your attention

Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. Appendix: Orbital Transfer Tug Variations Delta-v:3.46 km/s Payload:26.3 tons Can be launched with existing launcher PropulsionISP (s)Wet Mass (tons)Dry Mass (tons) NTO/MMH LOX/LH Nuclear Thermal Ion drive