The Path to Mars. December Matthew Duggan. Copyright 2010 Boeing. All rights reserved.

Transcription

1 The Path to Mars Matthew Duggan December

2 Overview ISS as a testbed for Exploration Systems Development Human Health and Performance Research LEO Cislunar Exploration Habitation capabilities for humans beyond LEO Power/propulsion for cislunar orbits Robotic and/or human lunar surface missions Long distance operations and resupply Human Health and Performance Proving Grounds Mars Exploration Habitation for long duration (1000+ days) missions Power/propulsion for interplanetary missions EDL Mars Author, 2

3 Deep Space Exploration Incremental Approach Phase 3+ Journey to Moons of Mars, and Mars Phase 0 Demonstrate exploration systems on Space Station Phase 1 Develop & Checkout critical enabling systems Orion Space Launch System Asteroid Redirect Mission Initial habitation Systems Precursor Robotic Exploration Missions Phase 2 Moon proximity; Increasing capability and duration Simulated Mars transit mission Lunar Landing - International Earth Reliant Missions: 6-12 months Return: Hours Distance: ~250 miles Proving Ground Missions: 1-12 months Return: Days Distance: ~240,000 miles Earth Independent Missions: 2-3 years Return: Months Distance: 36 to 250 million miles 3

4 ISS as a Testbed Mature life support systems for long duration dependability (ECLS) Assess network communications delays and effects of delayed communication on interplanetary crews. (Communications) Understand the extent of physical changes in astronauts who live in space for long periods of time, with an aim toward improving recovery time and developing injury prevention methods for future missions. (HH&P) 3-D Printing in Zero-G Technology Demonstration that gives crews the ability to manufacture new objects on demand while in space. (Additive Manufacturing) The ISS Veggie investigation studies how to best utilize a facility for growing fresh produce in microgravity. (Food) 4

5 Proving Grounds Emphasis on growth of capability built up over time Increasing complexity Useful at every stage for proving ground operations Goals Demonstrate long duration systems Demonstrate long duration deep space operations (earth independent) Demonstrate evolvability change over time & vehicle upgrades Demonstrate innovative technologies & mission designs Incremental growth allows steady progress at a controlled rate 5

6 Technologies Dependable ECLS Space Radiation Protection Long Duration Human Health and Performance High Rate Comm Long Distance/Reduced Supply Operations Deep Space Navigation & Staging Dust Mitigation Increasing Difficulty in Proving Grounds Demonstration Surface Power Generation and Storage Surface EVA & Mobility Mars EDL and Ascent and Earth-return EDL 6

7 Boeing Mars Architecture: The Easy Pieces Prop Orion Transit Habitat Mars Ascent Vehicle Space Launch System SEP/Hybrid Tug Mars EDL Earth/Cislunar Transit Mars 7

8 Technology Feedthrough Element Earth/Moon Mars Transit Phobos/Mars SLS Cargo/ Launch Orion Transportation Transport Sortie Vehicle/ Lunar Landing Mars Orbit Taxi MAV Propulsion Lunar Lander Taxi Propulsion MAV Propulsion Large Habitat Long Duration Transit Long Duration Transit Phobos Hab Mars Hab SEP Tug 50 kw Tug/ARV 400 kw SEP/ Hybrid Tug Mars EDL Mars EDLV 8

9 Boeing Mars Campaign - Missions 1. Phobos Outpost Emplacement Mission SEP MTV 1 + Phobos Hab/Lander + Phobos Taxi/ Module 2. Phobos Mission Hybrid MTV 1 + Transit Hab 3. Mars Surface Systems Emplacement 1 SEP MTV 2 + Mars Hab + Mars EDLV 4. Mars Surface Systems Emplacement 2 SEP MTV 3 + MAV + Mars EDLV + LMO Taxi/ Module 5. Mars Surface and Phobos Mission 1 Hybrid MTV 2 + Transit Hab + Phobos Taxi Propulsion _Boeing_2015_Mars.pp tx 9

10 Boeing 2015 Mars Campaign: 4 to Phobos (2033) 250 x 250 km 250 x 5500 km Phobos Deimos 5 Sol Trans Mars Trans Earth Cislunar LDRO LDHEO LGAs to C3 2 Transfer to LGA SEP MTV Cargo Mars Hab aerocaptures to Phobos Hybrid MTV Transfer to LGA Phobos Taxi aerocaptures to 250 x 5 sol LGAs to C3 = 2 Phobos Taxi to Phobos Hybrid MTV LGAs from C3 = 2 Phobos Taxi to 250 x 5 sol Phobos Taxi remains in 5 sol LGAs from C3 2 SEP MTV Cargo Transfer from LGA MEO Phobos Cargo x3 Phobos Cargo x3 C-O Earth Phobos Launch Phobos Return 10

11 Boeing 2015 Mars Campaign: to Mars & 2 to Phobos (2039) 250 x 250 km 250 x 5500 km Phobos Deimos 5 Sol Trans Mars Trans Earth Cislunar LDRO LDHEO LGAs to C3 2 Transfer to LGA Cargo EDLV 1 to Mars Mars Cargo EDLV 1 aerocaptures into 250 x 5500 km orbit SEP MTV Cargo x2 Mars EDLV 2 aerobrakes to 250 x 5500 LMO Taxi inserts EDLV 2 into 250 x 5 sol Hybrid MTV Transfer to LGA LMO Taxi takes 2 to 250 x 5500 km LMO & Phobos Taxis mate with MTV LGAs to C3 = 2 MAV EDLV 2 to Mars LMO Taxi to 250 x 250 Phobos Taxi takes 2 to Phobos Hybrid MTV LGAs from C3 = 2 MAV to LMO Taxi in 250 x 250 LMO Taxi to Phobos; stays Phobos Taxi takes 4 to MTV Phobos Taxi remains in 5 sol LGAs from C3 2 SEPMTV Cargo x2 Transfer from LGA MEO Mars Cargo x7- Mars Cargo x2+ C-O Earth Phobos Launch Phobos Return 11

12 Arrival 12

13 De-orbit 13

14 Ascent 14

15 Ascent 15

16 Ascent 16

17 Ascent 17

18 Arrival at Transit Vehicle 18

19 Key Architecture Points Cis-lunar tugs and SLS B1B are assumed 2 crew to Mars Mars mission elements are mostly evolved from Proving Grounds elements Early heavy robotics precursors can retire key EDL risks The cargo MTVs never enter Mars orbit; payloads are aerocaptured. MAV only ascends to 250 km to meet the taxi Key risk reduction by Phobos mission prior to Mars landing 19