“A mission for humanity, designed in Delft”...•Advanced Mission Cost Model •TRANSCOST •5.767 B$ Challenge the future 21 Table of Contents •Introduction •Spacecraft/Mission

1 Challenge the future

Adrestia

“A mission for humanity, designed in Delft”


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”


Table of Contents

• Introduction

• Spacecraft/Mission Overview

• Flight Systems

• Costs

• Conclusion


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

Introduction


Table of Contents

• Introduction


• Trajectory

• Spacecraft

• Mission

• Launch

• Extra Vehicular Activities

• Flight Systems

• Budgets

• Costs

• Conclusion


Trajectory Spacecraft/Mission Overview

Description Value Unit

Departure Date 4-1-2018 -

Launch Energy (C3) 38.605 km²/s²

TMI (ΔV) 4.857 km/s

Mars fly-by date 20-8-2018 -

Mars fly-by altitude 100 km

Earth arrival date 20-5-2019 -

Earth re-entry speed 14.2 km/s

Mission duration 501 days


Spacecraft 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

Spacecraft/Mission Overview


Mission Overview

100 km



Launch

• Required ΔV for TMI:

• 4.857 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


1st Launch 2nd Launch

Payload Weight [kg]

RP-1 fuel 11,527

LOX oxidizer 29,508

Crycooler and isolation 4,559

Total (LEO) 45,594

Payload Weight [kg]

RP-1 fuel 8,555

LOX oxidizer 21,900

Spacecraft 15,581

Total (LEO) 30,454



Extra Vehicular Activities (Refueling)

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


Table of Contents

• Introduction


• Flight Systems

• ECLSS

• Solar/Radiation Protection

• GNC

• Re-entry

• Scientific Payload

• Costs

• Conclusion


Flight Systems Overview

• 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

Flight Systems


ECLSS Specifications

Sub-system Mass [𝒌𝒈] Volume [𝒎𝟑] Power [𝒌𝑾]

ESM [𝒌𝒈]

Air 696 1.50 2.21 1,283

Food 1,146 5.11 0.47 1,317

Thermal 172 0.52 0.46 301

Waste 130 3.16 0.01 161

Water 315 1.49 1.56 694

EVA 435 3.00 - 435

Human Accommodations 440 0.69 0.32 531

Space-free Component - 10.20 - -

Total 3,334 25.66 5.03 4,722

Flight Systems


Protection Method

Radiation Reduction

Polyethilene water tank

49%

Water, food and waste storage

43% to 37%

Total 86%

Solar Flare & Radiation Protection

Protection Method

Radiation Reduction

Kevlar MMOD 4%

Circumferential Sub-systems

2.4%

Total 6.4%

GCR Protection SPE Protection

Flight Systems • Two sources of radiation

• Galactic Cosmic Ray (GCR)

• Solar Particle Events (SPE)

Radiation Required Reduction

GCR 6%

SPE 85%


Guidance, Navigation and Control

• 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)

Flight Systems


• Post-mission experiments:

• Living module continues trajectory

• Measures Data:

• Deep-space radiation

• Degradation of thermal control

• Sustainability of ECLSS

Scientific Payload

• Human experiments:

• Psychology and cardiac functioning

• Degradation of bones and muscles

• Cognitive and emotional adaptation of crew

• Planetary experiments:

• Probe deployment

• Capture images

Flight Systems


• G-loads:

• 7.8g maximum

• 5.1g average

Re-entry Flight Systems

• Heat:

• 3100 kW/m² flux at stagnation point

• 310 K splashdown cabin temperature

Trade-off

G-load Heat


Mass, Volume and Power Budget

Budgets

Description Volume (m³)

Sub-system (SS) 63.21

SS + Margin (20%) 75.85

Available 87.53

Remaining 11.68

Total free space:

21.88 m³


Table of Contents

• Introduction


• Flight Systems

• Budgets

• Costs

• Conclusion


Cost

Year Costs (M$)

2013 287.37

2014 804.06

2015 1143.68

2016 1248.19

2017 1108.84

2018 778.27

2019 371.55

2020 63.86

Total 5767.74

0

200

400

600

800

1000

1200

1400

2013 2014 2015 2016 2017 2018 2019 2020

Co

st

[M$

]

Year [-]

Cost of Mission

Schedule and Cost

• Cost Methods:

• Advanced Mission Cost Model

• TRANSCOST

• 5.767 B$


Table of Contents

• Introduction


• Flight Systems

• Budgets

• Costs

• 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

Conclusion


Solar Flare & Radiation Protection

• Two sources of radiation

• Solar Particle Events (SPE)

• Galactic Cosmic Ray (GCR)

Radiation Unit Deep Space Maximum Allowed

Required Reduction

Daily Dose Sv/day 0.0017 (GCR) 0.0016 (GCR) 6%

Acute Dose Sv 3.38 (SPE) 0.5 (SPE) 85%

Flight Systems


• Advanced Technology

• Lower mass

• Lower volume

• More power intensive

• Hanford, 2005

• Mars Transit Vehicle

• Modification

Environmental Control and Life Support System

Flight Systems


Re-entry

• 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

Flight Systems


Mass, Volume and Power Budget

Budgets

Description Volume (m³)

Sub-system (SS) 63.21

SS + Margin (20%) 75.85

Available 87.53

Remaining 11.68

Total free space:

21.88 m³



Extra Vehicular Activities (Pre-re-entry)

1. EVA transfer to re-entry vehicle

2. Re-entry vehicle pressurization

3. Disconnect from main-cabin

4. Re-enter Earth/ main-cabin continuation

Pa


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


Schedule

Phase 0 Mission Analysis

•Mission definition review

Phase A Feasibility •Feasibility review

Phase B Preliminary Definition

•Preliminary design review

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

Phase F Post-Mission

•Vehicle disposal

•Data retrieval

Phase 0: 11th November 2013 to 12th December 2013

Phase A: 12th November 2013 to 3rd February 2014

Phase B: 3rd February 2014 to 1st November 2014

Phase C: 1st November 2014 to 1st September 2015

Phase D: 1st September 2015 to 30th December 2017

Phase E: 31st December 2017 to 20th May 2019

Phase F: 20th May 2019 to 20th October 2021

Number Description

A Crew

B Payload

C Launcher

D Spacebus

E Re-entry

F Operations

H Cost

I Schedule

J Trajectory


Spacecraft Dimensions Budget and Dimensions


Mission Timeline

Table 5.1: Mission Timeline



Internal Layout

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

Flight Systems


References

[1] Team Adrestia – Competition Report

[2] Haalbeeld Fotografie

[3] Team Adrestia – Final Report

Documents

“A mission for humanity, designed in Delft”...•Advanced Mission Cost Model •TRANSCOST •5.767 B$ Challenge the future 21 Table of Contents •Introduction •Spacecraft/Mission