Mission to Mars Piecescanada.marssociety.org/winnipeg/files/Raftery_5-14-14.pdf · 2016-05-25 ·...

Mission to Mars in Six (not so easy) Pieces May 14, 2014

Mars Mission Studies

National Aeronaut ics and

Space Admi nistration

Report of the 90-Day Study

on Human Exploration

of the Moon and Mars

November 1989

1960s 1970s 1980s 1990s 2000s

Mars Mission IMLEO (NASA Studies)

1 2 3 4 5 6 7 8 9 10 11 12

1 1988 Mars Expedition (Chem A/B)

2 1989 Mars Evolution (Chem A/B)

3 1990 90-Day Study (NTR)

4 1991 Synthesis Group (NTR)

5 1995 DRM 1 Long Stay (NTR)

6 1997 DRM 3 Refinement (NTR)

7 1998 DRM 4 Refinement (NTR or SEP)

8 1999 Dual Landers (SEP)

9 2000 DPT/NEXT (NTR or SEP)

10 2009 DRA 5 (NTR Option)

11 2009 DRA 5 (Chemical Option)

12 2013 DRA 5 Addendum (SEP Hybrid)

ISS IMLEO = 2800t

1998 1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012

88 96 101 98 105 112

102 108 113

100 110

104 111

114 121 117 122 126 128 131 134

115 118 123 119 129 132 135

116 120 124 127 130 133

FGB 1R

5P 7P 9P

11P 14P 16P

10P 12P

6S 7S 8S 9S 10S 11S 12S 13S

13P 15P 17P 19P 21P

18P 20P 22P

23P 25P 27P

14S 15S 16S 17S

26P 28P 30P

29P 31P 33P 35P 37P

32P 34P 36P 38P 40P 42P

39P 41P 43P

44P 46P

45P 47P

22S 24S 26S

21S 23S 25S 27S

28S 30S

29S 31S ATV1

HTV1 HTV2 HTV3

ATV2 ATV3

SpXD SpX1

Building & Operating ISS

Injected Mass to Low Earth Orbit (IMLEO)

Assembly

Complete

Six (not so easy) Pieces for Mars

Space Launch System

Transit Habitat

Mars Lander

Mars Ascent Vehicle

SEP Tug

Element Phasing

Space Launch System

Transit Habitat

Mars Lander

Mars Ascent Vehicle

SEP Tug

Phase 1 – Earth’s

Gravity Well

Phase 2 – In-Space

Elements

Phase 3 – Mars

Gravity Well

Humans 2 Mars Drake Webinar

A trip to Mars with a return back to Earth is a double rendezvous problem

— Mars round-trip missions are flown in heliocentric space

— Relative planetary alignment is a key driver in the mission duration and propulsion required

Mars Trajectory Classes

EARTH DEPARTURE

MARS ARRIVAL

MARS DEPARTURE

VENUS SWING-BY

EARTH RETURN

EARTH DEPARTURE

MARS ARRIVAL

MARS DEPARTURE

EARTH RETURN

Example “Short-Stay” Opposition Class Mission

Example “Long-Stay” Conjunction Class Mission

Timing for a Mission to Mars

CREDIT: Lockheed Martin Corp.

Solar System Velocity Map

Reference: http://en.wikibooks.org/wiki/Space_Transport_and_Engineering_Methods/Orbital_Mechanics

DV & Propellant Requirements for Mars

Launch

Capture

Launch

Capture

Red text denotes Aero-assisted Entry

6900* 210 * Three Block 2 SLS

Launches

Mars Ascent is

One of the Key

Architecture

Drivers

Stepping Stone Approach to Mars

• Understanding the Destination – Robotic Precursors

• Operations “Beyond the Belts” – Testing the waters

• Building the Spacecraft – Assembly and departure options

• Early Scouting – Free return trajectory options

• Proving the Pieces – Deimos and/or Phobos precursor missions

• First Landing – Flags, Footprints, & Follow-through

• Recurring Operations – Incremental Improvements

We need an incremental plan for developing and maturing

the six (not so easy) pieces

Mission Objectives and Trades

1. Deliver the crew safely to the surface of Mars and return them

safely to the Earth

2. Provide a good balance of mission risks to ensure a reasonable

(>90%) probability of accomplishing objective #1

Top Level Objectives:

• Crew size (3,4,5,6)

• Cost of the mission

• Cost to repeat the mission

• International participation

• Timing of the mission

• Mode of transportation

• Propulsion technology

• Aerobraking technology

Tradable parameters:

• Duration of surface stay

• Surface landing site

• Surface mobility

• Quantity and quality of science

• Quantity of sample returns

• In-situ propellant production

• Radiation protection

Mission Description Approach

Working Backwards:

• With Mars as the objective, first describe a full-up human landing

mission to Mars and then determine the precursor activities that can

best lead to and support this landing

• Provide a cadence of launches (no more than 2 per year) that could

reasonably be supported by an extrapolation of existing budgets

• Be mindful that significant elements on the critical path will need to

be provided by International Partners; Seek element roles that fit

well with these Partners

First Landing Campaign

Six Main Elements for Mars

Space Launch System

Transit Habitat

Mars Lander

Mars Ascent Vehicle

SEP Tug

Transit to Mars

Initial Mars Landing Campaign

Cargo Lander

on Mars

(July 2034)

2030 2031 2032 2033 2034 2035 2036 2037 2038 2039

Assembly at EML2

Spiral to EML2

Humans Land

on Mars

(May 2036)

Assy at EML2

Surface Ops

Transit

Crew Home

Feb 2038

Spiral to EML2

Transit

454 days

936 days

204 days 256 days 515 days

Cargo Launch to LEO

Spiral out to EML2

Arrival at EML2 Gateway

TransHab / Kickstage Launch

Arrival at EML2 Gateway

Cargo Departure for Mars

2013 Mars Design Reference Architecture – Departure with no kick-stage

– Krypton Propellant

– 4600s Isp (high efficiency)

– Cargo Outbound Total Prop: 24.8t

– Duration to Mars: 510 days

2033 Cargo Outbound Trajectory

Depart EML2:

1/7/2033

Thrust Segment 1:

48.7 days @ 4.2t prop

Coast Segment:

49.5 days

Thrust Segment 2:

326.9 days @ 17.3t

Mars Capture 17K km:

89 days @ 3.3t prop

6/6/2034

Arriving at Mars

Cargo Lander Preparing for Entry

Cargo Lander during Aero Descent

Altitude Zone

Opportunity

(2003)

Viking 2

(1975)

Spirit

(2003)

Phoenix

(2008)

Mars 3

(1971)

Viking 1

(1975)

Pathfinder

(1996)

Historical Landing Sites

Curiosity

(2013)

+45 deg

-45 deg

Cargo Lander during Terminal Phase

Cargo Lander on the Surface

SEP Tug Climbs to 17,000 Km Orbit

Launch of the Crew Lander

Crew Cabin Configuration

Spiral out to EML2

Crew Lander at EML2 Gateway

Second Transhab Launch

Human Mission Elements at Gateway

Crew Launch

Crew Capture of Fuel Module

Orion Lunar Fly-by

Expedition Crew Arrives at Gateway

SEP Refuel

Expedition Crew Departing for Mars

2013 Mars Design Reference Architecture – Departure with Earth Swing-By

– 3000s Isp (increased thrust)

– Crew Outbound Total Prop: 29.2t

– Duration to Mars 17K km: 256 days Does not include Earth Swing-By time

Duration trade on-going

2035 Crew Outbound Trajectory

Depart EML2:

8/3/2035

Thrust Segment 1:

211 days @ 25.4t prop

Mars Capture 17K km:

45 days @ 3.8t prop

4/15/2036

2013 Mars Design Reference Architecture – Currently refining crew outbound trajectory in STK/Astrogator

– 2014 goal of integrating Earth swing-by departure with heliocentric trajectory

2035 Crew Outbound Trajectory

Arriving at Mars

Crew during Entry

Crew Landing

Crew on the Surface of Mars

Crew Departing Mars

During Ascent

Mars MAV Analysis

Refinement of OTIS trajectory in STK – Use OTIS ephemeris through first stage jettison, then modeled rest of ascent with STK/Astrogator

Rendezvous in High Mars Orbit

Departing Mars for the Journey Home

2013 Mars Design Reference Architecture – Departure with kick-stage

3500Kg Inert

21,000Kg LOX/Methane

Isp 360

– 4600s Isp (high efficiency)

– Crew Return Total Prop: 11.0t

– Duration to EML2: 210.3 days

2037 Crew Return Trajectory

Arrive EML2:

2/2/2038 Thrust Segment 1: 80

days @ 3.8t prop

Coast Segment:

40.4 days

Thrust Segment 2:

Mars Departure 17K

km: 7/13/2037

2013 Mars Design Reference Architecture – Departure with no kick-stage

– 4600s Isp

– Cargo Return Total Prop: 4.4t

– Duration to EML2: 206.6 days

2037 Cargo Return Trajectory

Arrive EML2:

1/29/2038

Thrust Segment 1:

Coast Segment:

124.3 days

Thrust Segment 2:

Mars Departure 17K km:

7 days @ 0.3t prop

7/14/2037

Back at EML2

From EML2 to Earth

Crew Returns Home

Deimos Precursor

Example Mission

Deimos Mission Elements

Space Launch System

Transit Habitat Mars Ascent Vehicle

SEP Tug

Subscale Robotic

Lander (10t)

Mars Lander

Stage Sortie

Deimos Mission Campaign

Mars Surface

Transit to Mars

Crew at

Deimos

Return

Robotic Lander Sample Return

EML2 Ops

Deimos Crew

Arrives Home

Departure for

EML2 Ops

Spiral out to EML2

Tug arrival at

620 days

EM-11 EM-10

EM-12 EM-14

Translunar

Deep Space Deimos

2030 2031 2032 2033 2029

Deimos Mission Spacecraft

Arrival in High Mars Orbit

Crew at Deimos

Robotic Lander & Rovers

Loading Sample Return Cannisters

Asteroid Redirect Precursor

Asteroid Mission Elements

Space Launch System

SEP Tug Mars Lander

Asteroid Redirect

Vehicle (ARV) (50KW)

Block 1B

Exploration Augmentation

Module (EAM)

Exploration Augmentation Module

Crew operations at a redirected asteroid could be significantly enhanced by providing additional systems and EVA capabilities beyond those available from Orion only missions.

Placing an Exploration Augmentation Module (EAM) at the redirected asteroid would :

– Extend mission duration – Reduce EVA and consumables mass requirements on Orion

– Increase capability – Supply additional EVA functions and crew volume

– Reduce risk - Provide an abort location for Orion

80 Three Concepts

Russian SPM-derived EAM Example

• International Participation

• Robust Capabilities

*SPM – Science Power Module

ISS Test Campaign

ISS Test Elements

Space Launch System

SEP Tug Mars Lander

Solar Array Wing Test

Exploration Augmentation

Module (EAM)

High Energy Atmospheric

Entry Test (HEART)

Mission to Mars Piecescanada.marssociety.org/winnipeg/files/Raftery_5-14-14.pdf · 2016-05-25 ·...

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