AVANT-GARDEMars Transfer Vehicle

MissionBrian CarterZarrin Chua

Anthony ConsumanoThomas HornJan Kaniewski Brian WilliamsMike Wolfner

Overview• General Introduction

- Historical Perspective- Current Trends

• Problem Definition- AIAA Request for Proposal (RFP)- Project Requirements & Constraints

• Value System Design- Objective Hierarchy- Objective Priority

• Functional subdivisions• System Hierarchy & Subsystem interaction• Possible approaches• Project Timeline/Future Planning• Summary

Notable Excursions to Mars

A Historical Perspective

Background• Since 1960, there have been 37

missions to Mars• Roughly two-thirds of all missions to

Mars fail: Earth-Mars “Bermuda Triangle”

• Majority of missions are from US or the former Soviet Union, with recent explorations by Europe, Japan, and Canada.

Mariner 4• Performed first fly by of Mars on July

14 and July 15 of 1965• Perform atmospheric scientific

observations; orbital photographs• Measure particle & field

measurements for interplanetary travel

[1]

Soviet Mars Program• Series of unmanned

landers & orbiters launched in the early 1970s

• Each consisted of an orbiter & attached lander

• First human artifacts to land on Mars

• Mars 2 completed 362 orbits and Mars 3 completed only 20

• Combined both probes sent 60 highly detailed photographs of the surface

• Both Mars 2 and Mars 3 were declared lost after a time span of about 20 seconds on the surface

[2]

The Viking Program• Consisted of two unmanned

space missions (Viking 1 and Viking 2) designed to photograph the Martian surface and land a payload to the surface for observational investigations

• Viking 1 was launched on August 20, 1975 and Viking 2 on September 9, 1975

• Most detailed photos to date taken from Viking crafts

• Used as standard Martian information until late 1990s/early 2000s

• Lost contact with Viking 1 orbiter in 1980, lander in 1982; contact lost with Viking 2 orbiter in 1978, lander in 1980

[25]

Mars Global Surveyor

• US Spacecraft to mark return to Mars after 20 year absence

• Launched in 1996 it completed its primary mission in 2001 and has entered into its extended phase through 2008

• Surveyor first spacecraft to use aerobraking to enter Martian orbit

• NASA lost contact with orbiter on November 5, 2006

• Primary mission was to investigate surface and atmosphere with orbital camera, altimeter, thermal emission spectrometer, and magnetometer

[26]

Mars Pathfinder & Mars Odyssey

• Pathfinder launched on December 4, 1996 intended for ancient flood plain in northern hemisphere

• Pathfinder’s rover Sojourner traveled few meters around lander to photograph & investigate surroundings

• Final transmission sent in September 1997 totaling 16,500 images from lander & 550 from Sojourner

• Odyssey launched on April 7, 2001 with the primary mission to search for evidence of past or present water as well as volcanic activity

• Primary mission has been extended until 2008 and Odyssey currently acts as the primary relay between Earth and the rovers Spirit & Opportunity

[27]

The Mars Rovers

• Launched in June & July of 2003, the rovers Spirit and Opportunity’s primary mission is to investigate Martian surface

• Originally designed for 3 months lifetime, the rovers have been operating for 3 years and funding has been provided to extend program until late 2007

• Considered to be most successful Mars mission to date

[3]

Mars Reconnaissance Orbiter

• NASA Multipurpose spacecraft designed to conduct reconnaissance and exploration of Mars from orbit

• Launched August 12, 2005 and attaining Martian orbit on March 10, 2006

• Scientific payload includes most advanced observational equipment sent to Mars to date

• Acting as primary communication between Rovers and other orbiting spacecraft and Earth

• Designed to act as guide to future missions to Mars including manned flights

[28]

Current Trends in Spaceflight

What will the next 50 years bring us?

• Since the decommissioning of the Apollo program, mankind has been languishing in Earth Orbit, no human getting farther than 400 miles from the surface of the earth.

• In the past 3 years, two separate events have revitalized the space industry– America’s renewed pledge to manned exploration– The founding of the private space flight industry

Overview

[29]

George W. Bush’s Mars Initiative

[5]

[4]

• In the wake of the Columbia tragedy, President Bush mandated a new direction for NASA, and outlined 4 directives– Develop a new spacecraft

to replace the shuttle, which is retiring in 2010

– Complete the ISS by 2010– Go back to the moon by

2020– Land a man on Mars by

2030• To accomplish this, G.W.B.

is increasing NASA’s budget, as well as reallocating NASA funding towards these directives

Privatized Space Flight

• While America takes the lead on manned exploration, private companies will set out to truly conquer space.

• Many private companies are beginning to realize the immense profits available in space, and are making plans on how to get there

[6]

Problem Definition

RFPRequirements &

ConstraintsElements & Subsystems

Request for Proposal (RFP)• Mission Statement: A new exploration transportation

system must be developed to support delivery of crew and cargo from the surface of the Earth to Mars and to return the crew safely to be ready by 2028

• Mission Objectives(1) to extend the search for life and understand the

history of the solar system (2) to expand the frontiers of human exploration(3) to advance U.S. scientific and technological

capabilities. • How will it be judged?

– Technical content 35 pts– Organization and presentation 20 pts– Originality 25 pts– Practical application and feasibility 25 pts

Requirements and Constraints

1. Transport crew and payload from LEO to Martian surface and return crew and payload to Earth

2. Transport a minimum of 4 crew members3. Transport a minimum of 500 kg payload (in addition

to crew) and return a minimum of 100kg to Earth4. MTV shall provide habitation and life support

systems for 18 months5. MTV will have the capability to conduct surface

Extra- Vehicular Activities (EVAs) for a minimum of 2 crew

6. MTV program shall support a minimum flight rate capability of 1 human exploration mission every 2 years

Elements and Subsystems

• Crew transfer vehicle• Habitation module• Mars ascent/descent

vehicle• Orbital,

interplanetary, and Martian landing/take-off propulsion systems

• Thermal protection• Life support

• Propellant and power subsystem

• Navigation and control• Communications• Radiation shielding

subsystem• Earth landing/recovery

subsystem• Crew safety subsystem• Vehicle health

monitoring subsystem

Value System Design

Objective HierarchyList of Priorities

Best Mars Transfer Vehicle

Performance Cost and Problems

Crew Capacity

Payload Capacity

To Minimize

To Maximize

Lifetime of Survivability

Habitat Sustainability

ConsumptionOperation Cost

Production Cost

Mass

Transfer Orbit Error (m)

Years

Measurement Unit

Number of Crew Over Time

Days

Number of Missions per 2 years

Kg

Kg

$$

$$

Propellant Cost

Launch Vehicle Cost

Lifetime

Safety Probability of safe operation

Fail SafetyTransfer Orbit and Landing Accuracy

EVA Activity

Flight Rate

Landing Error (m)

EVA Missions (number of)

Launch Cost

$$

$$

$$

Fail rate (λ )

OH Design and List of Priorities

• Objective Hierarchy is a diagram based upon the Needs, Alterables and Constraints (NAC) list

• Objectives are defined and their measures linked with the respective unit of measure

• Shows an overview of objectives and how to satisfy each objective by the defined measures

• Quantitative Matrix method may be derived from OH

• Lower Priorities– Other Costs– Complexity– Debris

• Main Priorities– Safety– Mission Success

Rate– Habitat

Sustainability– Flight Rate

• Medium Priorities– EVA Activity– Transfer Orbit and

Landing Accurately– Crew and Payload

Capacity– Operations Cost

Functional Subdivisions

A detailed look into the various

subdivisions of the Avant-Garde project

Structures

Thomas HornJan KaniewskiMike Wolfner

Structures

• Structures concerns itself with the overarching design of the spacecraft.

• The Structures group must build a spacecraft to get to Mars and back, while incorporating the subsystems associated with the other subdivisions

[7]

Responsibilities of Structures

• Habitat Module• Ascent/Descent

Module• Launch Vehicle• Transit Vehicle

[8]

[10] [11]

[9]

Propulsion and Power

Brian CarterBrian Williams

Propulsion• The propulsion system

has two primary functions: 1. Achieve orbit2. Produce a certain ΔV

• A propulsion system consists of a power source, mechanism to generate thrust, and the controls needed to stabilize the craft under the generative force

[12]

Power• The electrical system needed to supply sufficient

energy to all components of the spacecraft• Four methods of supplying power to the spacecraft

– Photovoltaic– Static– Dynamic– Fuel Cells

[32] [33]

Dynamics and Control

Mike WolfnerZarrin Chua

Orbits and Trajectory• The study and

determination of a vehicle’s path through space based on physical limitations and mission constraints

• Responsibilities include:– Establishing a relationship between mission performance

and orbit selection to best accomplish the mission goals– Develop concepts for orbit determination and

maintenance– Design the ΔV budget– Complete an orbit design trade study

[17]

Attitude Determination and Control System

• Determining a spacecraft’s attitude in space and orienting it in a specific direction through the use of a control system

• Responsibilities include:– Examine mission requirements

to determine required accuracies

– Quantify the disturbance torques

– Study, select, and develop systems for ADCS

– Develop control algorithms

[37]

[38]

Entry, Descent, Landing

• EDL is the phase of flight beginning at the atmospheric entry point and ending at surface touchdown

• Possible EDL approaches– Parachute deploy

(MERs)– Autonomous landing

system (NASA or ESA)– Apollo-era landing– Aerobraking

[18]

[30]

Communications, Command and Data

Handling

Brian WilliamsAnthony

Consumano

Communications• Select low gain antennas for short

range communications– Wire antennas– Horn antennas

• Select high gain antennas for deep space communications– Reflector antennas– Phased array antennas

• Select receivers and transmitters• Determine needed transmitter

power, data rate and broadcast frequency

[19]

Command and Data Handling

• Select on-board computer with needed processing power and power consumption– Crucial for spacecraft

control and communication– Interface with all

spacecraft subsystems– Monitor hardware health– Must be able to interpret

and execute commands• Select or develop needed

operational software– Software depends on

complexity of spacecraft and mission

• Develop telemetry modulation and transmission system– Provide spacecraft health

and status information to ground

[40]

Thermal and Environment

Anthony Consumano

Jan KaniewskiThomas Horn

Thermal

• Heat dissipation• Cooling systems

– Spray cool technology– Radiators– Conveyor belt idea moves

heat away from components

• Protect vital components from temperature variations

• Heating systems– Localized heaters– Insulations– Coatings

• Major issues protecting during launch and ascent phases

[34]

[35]

Environment

• Spacecraft protection from outside sources and harsh environment– Radiation affects on

spacecraft and humans– Orbital debris– Plasma (ionized gas)

causes arching– Magnetic fields

• Climate control for vital instruments

• Protective coatings on outside of spacecraft

• Spacecraft in LEO will experience gravity torques from Earth– Gravity gradient is a

passive method to restore spacecraft stabilization

• Solar flares and effects on communications

[36]

Human Factors

Jan Kaniewski

Human…• Human Factors is an umbrella term

covering Human-Environment interface

• Dual Term: Ergonomics• It covers several areas of research

including human performance, technology, design, and human-computer interaction

• Key concerns lie in– Safety– Sustainability– Efficiency

• For long term Mars presence several environment factors become important for success of missions and future objectives [24]

…Factors• Concerns in detail with:

– workload, fatigue and stress, situational awareness, user interface, usability, human performance and reliability, control, display designs, safety, working in extreme environments, human error and decision making

• In long duration space environments, Biosphere research becomes increasingly involved

[21]

[22]

Autonomy

Zarrin Chua

Autonomy

• Autonomy needed to relieve operator workload

• Apollo missions used autonomy extensively during landing sequence – Programs 66 & 67 for

manual landing

• Current autonomy limited by state of sensors and actuators

[31]

System Hierarchy

Subsystem Relationships

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy

Thermal/Radiation protection

Landing Sequence

Type of Propellant

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy

Type of trajectory

Propellant Mass Propellant

Type

Propulsion & Power

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

EnvironmentalCost Analysis

Structures

Autonomy

Orientation

Level of Autonomy

Electronics Housing

System Solution

(Mission to Mars)

Command, Communication

s & Data Handling

Human Factors Dynamics & Control

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy Flight speed

ΔV, trajectory

ΔV, trajectory

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy

HabitatG forces, radiation

Radiation, Climate Control

Autonomy Required

Autonomy Required

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy

Type of landing

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy G forces, sensors/actuators

G forces

Environmental

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

Cost Analysis

Structures

Autonomy

Politics, Economic

trends

Technological Development

Technological Development

Technological Development

System Solution

(Mission to Mars)

Human Factors

Dynamics & Control

Command, Communication

s & Data Handling

Propulsion & Power

EnvironmentalCost Analysis

Structures

Autonomy

Level of Autonomy

Manned spaceflight design

Destination

Potential Solutions

How are we going to get there?

Direct- Reusable

• Travels to Mars in a single reusable spacecraft– Spacecraft contains supplies for entire trip– In-situ resource utilization possible for return trip fuel

• Travels directly to Mars with no orbital rendezvous• Surface habitat travels with spacecraft

– Habitat may remain on Mars surface after mission• Spacecraft is refit and reused every 2 years

– Spacecraft may need extensive overhaul upon return– If necessary, multiple spacecraft can be built to create

MTV fleet

Habitat Module

ISRU supplies, etc

18 months later…

Spacecraft reused next mission

Click to Start

Animation

Mars Transfer Vehicle

Direct- Modular• Uses modular spacecraft

– Spacecraft modules discarded during mission when no longer needed

– May require on-orbit assembly– May have some reusable parts– May need rendezvous in Earth or Mars Orbit

• Earth return vehicle may be separate from Mars departure vehicle– Return vehicle may use In-Situ resources for propellant

• Mars habitat may travel to Mars separate from crew– Most likely incorporated with Earth return vehicle

• New spacecraft needed for each mission– New spacecraft may reuse some parts from previous mission

Habitat Module

Earth Return Vehicle

ISRU supplies, etc

Mars Transfer Vehicle

With Crew

18 months later…

New modules used for next trip

Click to Start

Animation

Unmanned & in one vehicle

Large Scale Exploration• Travels to and returns from Mars on a large mother ship

– Mother ship exists for Earth-Mars transit only– Docks with space station orbiting Mars– Requires on orbit fueling and maintenance

• Ascent/Descent module used to travel to Earth or Mars surfaces– Transfer vehicle fueled with In-Situ resources

• Mars-orbiting space station acts as staging point for Mars landings and Earth returns– Provides simultaneous docking capability for mother ship and

transfer vehicles• Uses one or more permanent surface habitats for crew

accommodations– Opens up possibility of Mars base construction

Mars Space Station

Mars Transfer Vehicle

(mothership)Ascent-Descent

Module

Habitat Module

ISRU supplies, etc

Existing or future permanent Mars

base

18 months later…

Same vehicle brings new crew + supplies

Click to Start

Animation

The Australia Approach

• Send large craft with prisoner populace to maintain operations on the planet

• Follows Britain’s approach to Australia

18 months later…

G’day, mate!

Crikey, she’s a big

‘un!

Click to Start

AnimationNOT UNDER SERIOUS CONSIDERATION

Project Planning

Timeline ofKey Events

TimelineIntroduction of RFP

Subdivision organization and initial planning

Systems engineering period

Fall semester progress presentation

Letter of intent: March 07

Proposal delivered to AIAA Headquarters

Project Completion

Technical design period

Dec 06

May 07

• General Introduction– Past and present status of Mars missions

• Problem Definition– Introduction to the AIAA– AIAA RFP– Project Requirements & Constraints

• Value System Design– Objective Hierarchy– Objective Priority

• Descriptions of the functional subdivisions

• System Hierarchy & Subsystem Interaction

• Possible approaches to accomplish mission

• Project Timeline/Future Planning

Summary

Contacts• Team Leader & Project Point of Contact:

Brian Carter, bscarter@vt.edu• Structures lead:

Thomas Horn, horn@vt.edu• Propulsion & Power lead:

Brian Carter, bscarter@vt.edu• Dynamics & Control lead:

Mike Wolfner, wolfner@vt.edu• Communications, Command, & Data handling lead:

Brian Williams, bwilliam@vt.edu• Autonomy lead:

Zarrin Chua, zarrinc@vt.edu• Thermal/Environmental lead:

Anthony Consumano, aconsuma@vt.edu• Human Factors lead:

Jan Kaniewski, getnamo@vt.edu

Extended Information

In-Situ Resource Utilization

• Utilization of resources on Mars• Can be used to produce fuel, water, food and other

items• Critical component of most Mars mission architectures

Fuel production plant built for Mars mission study

[39]

[15]

[13][14]

[16]

General References1. Goodson, A., J. Slough, T. Ziemba, Winglee, R. M. “Mini

magnetospheric plasma propulsion: Tapping the energy of the solar wind for spacecraft propulsion.” Technical report, J.Geophys. Res., 105, 21,067, 2000.

2. Martin J.L. Turner. Rocket and Spacecraft Propulsion: Principles, Practice, and New Developments. Praxis Publishing, 2005.

3. Martin Tajmar. Advanced Space Propulsion Systems. Wien New York, Austria, 2003.

4. Jones, Eric M. “Apollo Lunar Surface Journal.” NASA Online. August 2006. Accessed Nov. 14 2006.

<http://www.hq.nasa.gov/alsj/>5. Wiley, J.L. and Wertz, J.R. Space Mission Analysis and Design.

Microcosm Press and Kluwer Academic Publishers, third edition, 1999.

Figure References[1] <http://nssdc.gsfc.nasa.gov/image/spacecraft/mariner04.gif>[2] <http://nssdc.gsfc.nasa.gov/image/spacecraft/mars3_iki.jpg>[3] NASA/JPL-Caltech/Cornell[4] <http://www.thespacereview.com/article/119/2>[5] <http://www.lockheedmartin.com/data/assets/13280.gif>[6] <http://www.intelligence-creative.com/z0163_space_ship_one.jpg>[7] <mysite.verizon.net/res0nnid/index.html>[8] <mysite.verizon.net/res0nnid/index.html>[9] http://www.nasa.gov/mission_pages/constellation/main/index.html[10] www.marssociety.org/interactive/art/robinson.asp[11] <mysite.verizon.net/res0nnid/index.html>[12] <http://nix.larc.nasa.gov/info;jsessionid=woonvix0dy2r?id=S81-

30492&orgid=8>[13]< http://exploration.nasa.gov/common/images/prom_1.jpg>[14] <http://www.users.cloud9.net/~bradmcc/GO/SpaceShipOne29S04-

100km.jpg>[15] <http://www.nasa.gov/search/multimedia/>[16] Robert M. Winglee. Mini-magnetospheric plasma propulsion

(M2P2). University of Washington: Earth and Space Sciences, 2006.<http://www.ess.washington.edu/Space/M2P2/>.

[17] <http://marsprogram.jpl.nasa.gov/mro/gallery/artwork/>[18] <http://marsprogram.jpl.nasa.gov/mro/gallery/artwork/>[19] SAAB Space. <http://www.space.se>[20] Space Shuttle Cockpit

<htttp://www.msgc.org/images/shuttlecockpit.gif>[21] Biosphere 2 <http://www.biospheretechnologies.com/>[22] Human Factors Testing April 24, 2001 UMD

<http://spacecraft.ssl.umd.edu>[23] Laboratory Biosphere for Mars on Earth Project

<http://www.biospheretechnologies.com/>[24] Apollo Suit, NASA

<http://search.nasa.gov/centers/ames/images/content/76466main_apollo_suit.jpg>

[25] Carl Sagan with a model of the Viking lander, NASA <http://solarsystem.nasa.gov/multimedia/display.cfm?IM_ID=244>

[26] Mars Global Surveyor, NASA <http://nssdc.gsfc.nasa.gov/planetary/image/mars_global_surveyor.jpg>

[27] Sojourner Rover, NASA <http://mars.jpl.nasa.gov/spotlight/pathfinder-image01.html>

[28] Conceptual drawing of Mars Reconnaissance Orbiter <http://marsprogram.jpl.nasa.gov/mro/gallery/artwork/>

[29] SpaceShipOne, Scaled Composites <http://www.scaled.com> [30] Z. Chua, “Autonomous Planetary Landing”. Presentation to AOE

4065 Fall 2006 class. Virginia Tech, Blacksburg VA[31] Robonaut, NASA JSC,

<http://robonaut.jsc.nasa.gov/imagez/Tether%20Hook%20Wide.JPG>

[32] Fuel cell. <http://www.cnn.com/US/9710/27/fuel.cells/fuel.cell.large.jpg>

[33] Stardust solar panels. <http://www.cnn.com/TECH/space/9902/06/nasa.stardust/stardust.story.photo.lg.jpg>

[34] Solar radiator. <http://www.jhuapl.edu/newscenter/pressreleases/2006/images/MEMS-Radiator_lg.jpg>

[35] Spacecraft Insulation. <http://www.clavius.org/img/as11-ftpad.jpg>

[36] Solar flare comparison to Earth <http://antwrp.gsfc.nasa.gov/apod/image/0608/sunprom_soho_big.jpg>

[37] VSCMGs <http://www.ecpsystems.com/subPageImages/cmgbig.gif>[38] Star Camera

<http://iris.iau.dtu.dk/research/ASC/billeder/kameralinselink.jpg> CAMERA

[39] Zubrin, Robert and Wagner, Richard. The Case for Mars. New York: Simon and Schuster, 1996.

[40] New World Consulting. <http://www.new-world-consulting.com/PC104%20Stabilization.htm >