Adrestia. A mission for humanity, designed in Delft. Challenge the future

Transcription

1 Adrestia A mission for humanity, designed in Delft 1

2 Adrestia Vision Statement: To inspire humanity by taking the next step towards setting a footprint on Mars Mission Statement Our goal is to design an end-to-end fly-by mission to Mars for two people as safe, simple and cost effective as possible 2

3 Table of Contents Introduction Spacecraft/Mission Overview Flight Systems Costs Conclusion 3

4 Introduction Introduction Delft University of Technology International Group Aerospace Engineers Contribute to space exploration Generate the spark System engineering Functional analysis Requirements Preliminary design Trade-off Detailed design 4

5 Table of Contents Introduction Spacecraft/Mission Overview Trajectory Spacecraft Mission Launch Extra Vehicular Activities Flight Systems Budgets Costs Conclusion 5

6 Trajectory Spacecraft/Mission Overview Description Value Unit Departure Date Launch Energy (C3) km²/s² TMI (ΔV) km/s Mars fly-by date Mars fly-by altitude 100 km Earth arrival date Earth re-entry speed 14.2 km/s Mission duration 501 days 6

7 Spacecraft Overview Spacecraft/Mission Overview Dragon rider capsule Launch and re-entry Two Dragon trunks (extended) Pressurized Main cabin for journey Post-mission Four solar arrays Retractable Adjustable Main propulsion stage Falcon Heavy second stage Compatible 7

8 Mission Overview Spacecraft/Mission Overview 100 km 8

9 Launch Spacecraft/Mission Overview Required ΔV for TMI: km/s Required fuel for TMI: 71,490 kg Two Falcon Heavy launches required: Max payload mass to LEO 53,000 kg First launch fuel Second launch spacecraft with full tank Payload Weight [kg] Payload Weight [kg] RP-1 fuel 11,527 LOX oxidizer 29,508 Crycooler and isolation 4,559 RP-1 fuel 8,555 LOX oxidizer 21,900 Spacecraft 15,581 Total (LEO) 45,594 Total (LEO) 30,454 1 st Launch 2 nd Launch 9

10 Extra Vehicular Activities (Refueling) Spacecraft/Mission Overview 1. Docking LOX tank 2. Module decompression 3. Commence EVA 4. Connect RP-1 tank 5. Board main cabin 6. Disconnect fuel tank 7. Ignite thrusters 8. Orbit insertion Pa 10

11 Table of Contents Introduction Spacecraft/Mission Overview Flight Systems ECLSS Solar/Radiation Protection GNC Re-entry Scientific Payload Costs Conclusion 11

12 Flight Systems Overview Flight Systems Environmental Control and Life Support System (ECLSS) Spacecraft Structures Solar Flare & Radiation Protection Propulsion Guidance Navigation and Control (GNC) Telemetry, Tracking and Communications (TT&C) Command and Data Handling (C&DH) Scientific Payload Electrical Power Thermal Control Re-entry and Landing 12

13 ECLSS Specifications Flight Systems Sub-system Mass [kg] Volume [m 3 ] Power [kw] ESM [kg] Air ,283 Food 1, ,317 Thermal Waste Water EVA Human Accommodations Space-free Component Total 3, ,722 13

14 Solar Flare & Radiation Protection Flight Systems Two sources of radiation Galactic Cosmic Ray (GCR) Solar Particle Events (SPE) Radiation GCR 6% SPE 85% Required Reduction GCR SPE Protection Protection Method Radiation Reduction Polyethilene Kevlar MMOD 4% 49% water tank Circumferential 2.4% Water, Sub-systems food and 43% to waste storage 37% Total 6.4% Total 86% 14

15 Guidance, Navigation and Control Flight Systems High accuracy required Mars fly-by Ground based GNC not desirable Time delay AutoNav Deep Space 1 in 1998 Autonomous Miniature Integrated Camera And Spectrometer (MICAS) 15

16 Scientific Payload Flight Systems Post-mission Human Planetary experiments: Living Psychology Probe deployment module and continues cardiac functioning trajectory Measures Degradation Capture images Data: of bones and muscles Cognitive Deep-space and emotional radiation adaptation of crew Degradation of thermal control Sustainability of ECLSS 16

17 Re-entry Flight Systems Trade-off G-load Heat G-loads: 7.8g maximum 5.1g average Heat: 3100 kw/m² flux at stagnation point 310 K splashdown cabin temperature 17

18 Mass, Volume and Power Budget Budgets Description Volume (m³) Sub-system (SS) SS + Margin (20%) Available Remaining Total free space: m³ 18

19 Table of Contents Introduction Spacecraft/Mission Overview Flight Systems Budgets Costs Conclusion 19

20 Cost [M$] Cost Schedule and Cost Cost Methods: Advanced Mission Cost Model TRANSCOST B$ Year Costs (M$) Cost of Mission Total Year [-] 20

21 Table of Contents Introduction Spacecraft/Mission Overview Flight Systems Budgets Costs Conclusion 21

22 Conclusion Conclusion Vision System engineering Multi-disciplinary Interconnected Trade-off Multiple designs The best was chosen Detailed system design Mass, volume and power Schedule and Cost Adrestia 22

23 23

24 24

25 Solar Flare & Radiation Protection Flight Systems Two sources of radiation Solar Particle Events (SPE) Galactic Cosmic Ray (GCR) Radiation Unit Deep Space Maximum Allowed Daily Dose Sv/day (GCR) (GCR) 6% Acute Dose Sv 3.38 (SPE) 0.5 (SPE) 85% Required Reduction 25

26 Environmental Control and Life Support System Flight Systems Advanced Technology Lower mass Lower volume More power intensive Hanford, 2005 Mars Transit Vehicle Modification 26

27 Re-entry Flight Systems Re-entry velocity 14.2 km/s Corridor width 0.04 deg G-load Peak 8g Average 6g Temperature Peak heat flux 20 MW/m² Cabin 313 K Bank angle modification 27

28 Mass, Volume and Power Budget Budgets Description Volume (m³) Sub-system (SS) SS + Margin (20%) Available Remaining Total free space: m³ 28

29 Extra Vehicular Activities (Pre-re-entry) Spacecraft/Mission Overview Pa 1. EVA transfer to re-entry vehicle 2. Re-entry vehicle pressurization 3. Disconnect from main-cabin 4. Re-enter Earth/ main-cabin continuation 29

30 Strengths Conclusion Design process: Requirement analysis Verification and validation Risk analysis Detailed schedule/budget analysis ESA margins Final design: Two launches Minimum fuel required Existing technology Compatible EVA available on mission Post mission usability High free-space volume 30

31 Schedule Phase 0 Mission Analysis Mission definition review Phase 0: 11 th November 2013 to 12 th December 2013 Phase A: 12 th November 2013 to 3 rd February 2014 Phase B: 3 rd February 2014 to 1 st November 2014 Phase C: 1 st November 2014 to 1 st September 2015 Phase A Feasibility Feasibility review Phase D: 1 st September 2015 to 30th December 2017 Phase E: 31st December 2017 to 20th May 2019 Phase B Preliminary Definition Preliminary design review Phase F: 20th May 2019 to 20th October 2021 Number A B C D E F H Description Crew Payload Launcher Spacebus Re-entry Operations Cost Phase C Detailed Definition Detailed design MAIT Plan Phase D Qualification and Production Production and qualification of components Integration and testing Platform preparation Phase E Utilization Launch Fly-by mission Re-entry Retrieval I J Schedule Trajectory Phase F Post-Mission Vehicle disposal Data retrieval 31

32 Spacecraft Dimensions Budget and Dimensions 32

33 Mission Timeline Spacecraft/Mission Overview Table 5.1: Mission Timeline 33

34 Internal Layout Flight Systems 1. MMOD 2. Storage 3. EVA 4. Window 5. C&DH 6. GNC 7. ECLSS 8. TC&C 9. Thermal Control 10.Food & Waste 11.Thrusters 12.Hydrogen tank 13.Oxygen tank 14.Power 15.Water tank 34

35 References [1] Team Adrestia Competition Report [2] Haalbeeld Fotografie [3] Team Adrestia Final Report 35