ST12 Retro Space

SpaceTech 12
Central Case Project
Final Presentation
ESA/ESTEC 01/07/2010
Agenda

© SpaceTech 12. Do not reproduce and distribute without permission 1/71

The Problem: Space Debris

Definition:

"Space debris are all man-made objects including fragments
and elements thereof, in Earth orbit or re-entering the
atmosphere, that are not functional“
Source: Inter-Agency Debris Coordination Committee (IADC)
Introduction to RetroSpace


Agenda

Introduction into RetroSpace
The Scope
The Opportunity
The Solution
The Legal Framework

Market
System Solution
Business Case
Conclusion
Agenda


RetroSpace Scope

• $2.2 B return on a $90 M investment

• Revenues exceeding $400 M per year

• Protecting space assets valued over $500 B

• Providing public benefit


The Opportunity

• Space is valuable for everybody

• Value is threatened

• Threat is collision with orbital debris
Loss of assets

Creation of new fragments
Cascading collision
Restricted access to space


Historical Growth of Objects

Number of Objects in Earth Orbit by Object Type (SSN Catalog)

Growth rate 300 objects/year

Year
Source: NASA Orbital Debris Office
SSN: Space Surveillance Network
ASAT: Anti-Satellite Test

“Kessler Syndrome”

LEO: Low Earth Orbit
MEO: Medium Earth Orbit
GEO: Geostationary Earth Orbit

Future Growth of Collisions


PMD: Post-Mission Disposal

The Opportunity

• Need: Active removal of 10-15 large objects (6-7 total
tons) annually from most crowded LEO to stabilize
satellite population at existing level!

• No comprehensive solution

• Momentum to act is building


The Mission

Remove Hazardous Space Debris Using Robotics!
Remove Hazardous Space Debris Using Robotics!


What is RetroSpace?

Profitable End-to-End System for Active Debris Removal
Profitable End-to-End System for Active Debris Removal

Objectives
Objectives

Remove more than 15 large debris per year
Remove more than 15 large debris per year
In a safe manner
In a safe manner
With the consent of debris owner
With the consent of debris owner


The RetroSpace Solution

A fleet of spacecraft pushing debris
A fleet of spacecraft pushing debris
to a lower disposal orbit
to a lower disposal orbit

Using a vision system and
Using a vision system and
robotic arm for capture
robotic arm for capture

Spiralling up and down by
Spiralling up and down by
electrical propulsion
electrical propulsion


Debris and Orbits

Selected debris are large objects
Selected debris are large objects
• defunct spacecraft
• defunct spacecraft
• rocket bodies
• rocket bodies
ADEOS, 25 m, 3500 kg

Regions of interest are Low Earth Orbits
Regions of interest are Low Earth Orbits

H10 rocket body,10 m, 1200 kg

Disposal orbit altitude is 430 km
Disposal orbit altitude is 430 km


Performances

Each RetroSat de-orbits 2 to 3 debris/year
Each RetroSat de-orbits 2 to 3 debris/year We meet
Fleet of 7 will remove 18 debris/year
Fleet of 7 will remove 18 debris/year the need

Revenues exceeding $400 M per year
Revenues exceeding $400 M per year

Ready for operations in 2016
Ready for operations in 2016
Break-even in 2020
Break-even in 2020


The Legal Framework

Perceived Problems
Perceived Problems
•• Treaties not explicitly addressing debris
Treaties not explicitly addressing debris
•• Control and jurisdiction stay with owners
Control and jurisdiction stay with owners
•• Liability stays with launching States
Liability stays with launching States

States/owners are allowed to
States/owners are allowed to
clean up their own debris

clean up their own debris

Therefore, no prohibitions to
Therefore, no prohibitions to
start with active debris
start with active debris
removal
removal


Implications for RetroSpace

Within current framework
Within current framework
•• Seek cooperation with States and owners
Seek cooperation with States and owners
•• Perform safe operations
Perform safe operations
•• Ensure openness and visibility of activities
Ensure openness and visibility of activities

Potential future framework
Potential future framework
•• Modeled on Nairobi Convention on Wreck
Modeled on Nairobi Convention on Wreck

Removal
Removal
•• Removal by external party
Removal by external party
•• Obligatory insurance to cover cost
Obligatory insurance to cover cost

Augmented with coordinating international body
Augmented with coordinating international body


Agenda


Market
Space Market
Primary Source Research
Target Market

System Solution
Business Case
Conclusion
Agenda


The Space Market

[Sources: State of the satellite Industry Report, SIA, 2009]
Public Sector Spending The Space Report 2010

– NASA 5.3%
– US DOD 2.2%
– ESA 18%
– Russia 200% $144 M

$261 Billion
End-User
Segment
Included

Private Sector Growth
Led by remote sensing with 12%
Market

NASA: National Aeronautics & Space Administration
US DOD: Unites States, Department of Defence
ESA: European Space Agency

Primary Source Research

60 questionnaires NASA/DARPA Debris Workshop:
– Debris is an issue
– Timeframe to act is now
– Large debris should be removed first
– Governments even willing to pay

Personal Interviews with Representatives of:
– National Governments
Most pressing need for – Space Agencies public sector
de-orbit services:
– Public & Private Operators
This manifests in: – Human Space Flight
• Increasing international Insurers
– coordination
• National implementation of IADC guidelines
– Manufacturers
• Public sector spending on debris removal studies
– Debris Specialists
– Legal Specialists
Market

NASA: National Aeronautics & Space Administration
DARPA: Defense Advanced Research Projects Agency
IADC: Inter-Agency Debris Coordination Committee

Primary Market: Risk Driven

Cost
- Shielding
- Development
- Launch
ISS
Community

Commercial
Impacts of Small Fragments Operators
Threat to Astronaut Lives

Negative Reputation
States - “Orbital” Polluter

Space
Value of Assets Agencies
Economic Prosperity
Market

ISS : International Space Station
MMOD : Micrometeorites & Orbital Debris
ADR: Active Debris Removal

Orbital Regimes in LEO at Risk

Inclination Altitude Active Inactive Rocket TOTAL
[km] Satellites Satellites Bodies Debris
Regime A (SSO) 99° ± 1° 800 ± 100 71 91 48 139
Regime B 82° ± 1° 1000 ± 100 3 160 157 317
Regime C 71° ± 1° 850 ± 100 1 40 23 63
Source: Heiner Klinkrad, Space Debris Office, ESA

Active Satellites in SSO

Debris in SSO

Market

SSO: Sun-Synchronous
CIS: Confederation of Independent States
USSR: Union of Soviet Socialist Republics
PPP: Public Private Partnerships

Market Projection Assumptions

• Conservative Launch Projection Scenario
• Stagnation at a Yearly Average of 22 Launches
• Rapidly Increasing Implementation of Debris Mitigation Guidelines
(up to 95% in the next 10 years), for:
• Satellites
• Rocket Bodies
• Satellite Lifetime: 7 Years on Average

Projected Launches into Sun-Synchronous Regimes
30
Satellite Launches / Year

25

20

15
Trend
10
Assessment of
Planned
5 Launches [DLR]
0
Market

27

29

33

35
99

01

03

05

07

09

11

13

15

17

19

21

23

25

31
20

20

20

20
19

20

20

20

20

20

20

20

20

20

20

20

20

20

20
DLR: German Aerospace Center

Market Projection

500
Total Number of Debris in Sun-Synchronous Regimes
450
Nummber of Objects

400 No Active Debris Removal
350
300
250
200 15 Objects / Year 10 / Year
150
100
50
0

10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35
20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20

• Conservative Scenarios
• Removal of 15 debris per year
• Many years of work for RetroSpace
• Huge Market
Market


Agenda

Market
System Solution
System Architecture
Mission Scenario
Platform
Launch System

Business Case
Conclusion
Agenda


System Architecture

DEBRIS

RetroSat
System Solution

POC: Payload Operations Center
MOC: Mission Operations Center
GSS: Ground Station System
TT&C: Telemetry, Tracking and Command

Ground Station System

• Single Ground Station
Typical contact times during
passes between 3 and 15
minutes.

• Strip of Multiple Ground
Stations
Fairbanks, Svalbard, Kiruna and
Fucino can provide every day at
least 4 continuous contacts
longer than 20 minutes.
System Solution


Concept of Operations

Operational phases

• Command from mission
planning
• Rendezvous with selected
debris and inspection (15 days)
• Command of robotic arm and
capture debris (14 minutes)
• Analyze and stabilize the
newly formed composite and
move to the disposal orbit (80
days)
• Release the debris, wait for
next debris opportunity and
System Solution

return to the region of interest
(65 days)
• Debris orbit decays over time Total: 160 days
and burns up on re-entry


Mission Planning

• A service to provide characterization of
the selected debris:
• Regularly updated orbital elements
and attitude
• Size, shape and end-of-life mass
• Available info from manufacturer

• Possible service providers:
• US Space Surveillance Network
• ESA – Space Situational Awareness
System Solution

• Commercial providers (e.g. Center
for Space Standards & Innovation) Third stage of Ariane 4 (H10): a common debris in
the Sun-Synchronous orbit region.

US: United States Source: Arianespace
ESA: European Space Agency

Debris Orbital Parameters Analysis

• Inclination [98o – 100o]
• Altitude [700 km - 900 km]
• Right Ascension of Ascending Node (RAAN) [0o - 360o]
RAAN distribution in the selected region
14
12
Number of objects

10
8
6
4
2
0
0 30 60 90 120 150 180 210 240 270 300 330 360

RAAN [deg]
System Solution

• Propellant to go from one debris to the following depends
mainly on RAAN change required
• Removal sequence must be designed accordingly
RAAN: Right Ascension of Ascending Node

From Launch to Orbit Injection

• The orbit plane of the first debris in the sequence is reached by direct
injection by the launcher

• Launch takes place when
the launch site crosses the
first debris orbital plane:
twice per day

• An acceptable deviation of
±1.12 deg in RAAN results
in a daily 9 minute launch
window
System Solution

Launch and orbit injection sequence [Source: Jet Propulsion Laboratory]


Phasing Strategy

• Injection of RetroSat into an orbit 20 km below the debris orbit
• Reduction of the phase angle between RetroSat and the debris (1 deg/hour)
• All maneuvers controlled from the ground
• Phasing ends with the acquisition of the Hold Point 0 (HP0)
System Solution


Debris Spin Status

• Still or very low tumble rates
• Theory: Magnetic drag stops residual tumble within a year
• Visual observations from PPAS databse agree
• Possible orbital resonance with Lorentz force (low relative tumble rate <0.1deg/s)
System Solution

COSPAR: Committee on Space Research
PPAS: Database of Photometric Periods of Artificial Satellites
Note: Numbers represent the time in seconds between flashes or peaks in magnitude.

Rendezvous

Hold Point 1 (HP1) Hold Point 0 (HP0)
Debris location
•Transition to medium range sensors •Transition to relative navigation
error ≈ 1km
•Verify location and state •Verify heading and range

HP2 2 HP1 4 HP0 6
V-bar (km)

0.5
Location error
Hold Point 2 (HP2)
reducing
1 •Transition to close range sensors
•Inspect debris
•Verify ID & State
System Solution

•Determine final approach plan

R-bar (km)


Capture

L
• Manual Capture:
– Cameras systems
• Visual
• Infrared
– LIDAR
– GPS
• Rocket Body Capture
– Rocket nozzle
– Inter-stage
System Solution

mounting ring
– Launch adapter

LIDAR: Light Detection And Ranging
GPS: Global Positioning System

Robotic Arm

DLR DEOS Robotic Arm Capabilities
Length 3m
Mass 45kg
Degrees of Freedom 7 joints system
Max. Joint Rate 180°/sec
Max. Bearing Torque 120Nm
Grasping Torque / Joint 10Nm
Simulated Spin Rate 6° / sec
Simulated Grasp Mass 7 tons
System Solution

Source: DLR Dimensions in mm
DEOS: Deutsche Orbitale Servicing Mission

Capture & Stabilization
System Solution

Clip courtesy of DLR Institute of Robotics and Mechatronics


Composite Operations

• Re-orient for
retro burn
• Calibrate
• Orientate for
composite
pitch over
response to
• Spin rate • Pitch over for
test burn
• Center of mass retro burn
• Lock arm
• Thrust line • Verify
• Velocity vector orientation
• Dynamic De-Orbiting
responses
Test

Orientate

Control
Capture
System Solution

18 h

18 h
18 h

12 h

24 h

24 h
12 h

24 h

12 h
6h

6h
6h

DAY 1 DAY 2 DAY 3


Disposal Orbit Trade-Off

Constraints

1. The decay time shall be
less than 25 years

2. No risk to human space Area-Mass ratio

flights

3. The debris shall leave the
region within 1 year Computation obtained using NASA Debris Assessment Software (DAS)

ISS altitude

Disposal Orbit Altitude Lifetime Area to Mass ratio
System Solution

(km) (years) (m2/kg)

430 <10 0.001 (Worst case)

NASA: National Aeronautics and Space Administration
ISS: International Space Station


Composite De-Orbiting

• Using electric propulsion RetroSat spirals down the composite to the
circular 430 km disposal orbit
• Typical time to de-orbit a debris object of 500 kg is approximately 80
days, consuming nearly 32 kg of Xenon propellant

• The electric propulsion is switched off
during the eclipse periods for power
budget reasons
• Eclipse duration is never higher than 39%
of orbital period
System Solution


Release Strategy

• The release is operated from the ground
• RetroSat controls the composite attitude so that the debris is in
nadir direction
• After the end-effectors opening, dynamics naturally separates
RetroSat from the object
System Solution


…To the Next Debris

• The next debris RAAN is reached taking advantage of the differential
nodal regression due to the two different altitudes

• Typical waiting time before starting a new transfer is 25 days …

Ronf
• The low thrust propulsion … RAAN … Ronf
is started again when the … RAAN
RAAN difference can be
covered during the transfer
System Solution

Ronf: Onomatopoetic word that imitates the sound of a snoring lion

RetroSat

RetroSat Technical Details
Lifetime 7 years
Payload Robotic arm, cameras and LIDAR
Configuration 3-axis stabilized satellite
2 m x 1.8 m x 2 m
Dry Mass 680 kg
Wet Mass 1,296 kg
Propulsion Electric Propulsion
5 thrusters mounted on gimbals
Electrical 50V regulated bus
Power Gallium Arsenide (GaAs) solar array 9m2
Lithium-Ion battery
2.3 kW (Beginning of Life)
Attitude control Pitch, roll and yaw maneuvers
System Solution

Precise orbit determination
Thermal control Passive with heaters

Telemetry & S-band up and down links
Command Telecommand Data Rate: 256 kbps
Telemetry Data Rate: 3.6 Mbps

Satellite Configuration

Robotic Arm GPS antenna

EP Thrusters

‐Z

LIDAR +X
‐Y

Cameras
System Solution

S-band Antennas

EP: Electrical Propulsion
Solar Array
LIDAR: Light Detection And Ranging

RetroSat Functional Diagram

Internal Redundancy
Non Redundant

Cold/Hot Redundant
Power lines
Can Bus
System Solution

AOCS: Attitude and Orbit Control System

Launcher Selection

Drivers Flexible Launch Strategy
• Up to 2 tons Single Dual Triple

• Direct launch into SSO
• Low cost
• Available in 2016
System Solution

LM-4B Soyuz Falcon 9

Cluster launch of 2-3 RetroSats and/or dedicated single launch
Cluster launch of 2-3 RetroSats and/or dedicated single launch

SSO: Sun Synchronous Orbit
LM-4B: Long March 4B

Design and Development Plan (1/2)

PDR: Preliminary Design Review
RetroSat Design & Development Plan CDR: Critical Design Review
QR: Qualification Review
AR: Acceptance Review
ORR: Operational Readiness Review
PDR FRR: Flight Readiness Review
CRR: Commissioning Result Review
CDR

Phase A/BPreliminary Definition
QR AR ORR

RetroSat
Phase C Detailed Definition Disposal
FRR CRR
Qualification/Production
Phase D / Verification

Phase E Operational Phase

Phase F Launch Demonstrator
System Solution

2013

2015

2016
2011

2021

2023
2022

2024
2014
2010

2018

2020
2012

2017

2019

Design and Development Plan (2/2)

• Design based on flight proven technology
• Robotic arm – TRL level 8, in flight demonstration in 2015
(DEOS current launch date)

DLR EPOS Facility – DEOS configuration

Spacecraft Model Philosophy
• Avionics Test bench
• PFM (Proto Flight Model)
• FM (Flight Model)

Critical Rendezvous & Capturing
Operations Test and Verification
System Solution

• DLR EPOS (*) Facility

TRL: Technology Readiness Level
DLR: Deutsches Zentrum für Luft- und Raumfahrt
EPOS: European Proximity Operations Simulator
DEOS: Deutsche Orbitale Servicing Mission

Agenda

Market
System Solution
Business Case
Business Environment
Revenue
Financing

Conclusion
Agenda


Business Environment

Financiers Suppliers
• Private investors / founders • Satellite providers
• Strategic partner • Operation service providers
(satellite manufacturer) • Facility & service leasing
• Guaranteed public bond

Customers Operational Interfaces
Business Case

• Intergovernmental body • Support services
• Commercial • Debris owner


Phased Business Approach – (1/4)

Completion of:
• Strategic partnering
• Lobbying for bond and fund implementation
• Acquisition of flagship customer
• Preparation of service level agreements (with service providers)

Funding:
• Private investors / founders
• Strategic partner (satellite manufacturer)
• Guaranteed public bond

Development
& Production
Business Case

2013

2015

2021

2023

2029

2031
2011

2017

2019

2025

2027

2033

2035
2014

2022

2030

2032
2016

2018

2020

2024

2026

2028

2034
2012



• Establishment of dedicated fund
• First space debris removals
• Initial operations
Proof-of-
Concept

Development
& Production
Business Case

2013

2015

2021

2023

2029

2031
2011

2017

2019

2025

2027

2033

2035
2014

2022

2030

2032
2016

2018

2020

2024

2026

2028

2034
2012



• Full deployment of RetroSat satellite fleet
• Gradual increase of capabilities up to 18 debris / year
• Routine debris removal operations
• Extension of customer basis towards commercial
• Preparation for new business lines

Proof-of-
Concept Operational Phase

Development
& Production
Business Case

2013

2015

2021

2023

2029

2031
2011

2017

2019

2025

2027

2033

2035
2014

2022

2030

2032
2016

2018

2020

2024

2026

2028

2034
2012



• Sales of RetroSat satellites
• Damage inspection missions
• Space-tug service
• Provision of secondary payload hosting capabilities

Service Extension Phase

Proof-of-
Concept Operational Phase

Development
& Production
Business Case

2013

2015

2021

2023

2029

2031
2011

2017

2019

2025

2027

2033

2035
2014

2022

2030

2032
2016

2018

2020

2024

2026

2028

2034
2012


Deployment Scenario

Dual launch Single launch Primary satellite Replacement satellite

Extended Services

Orbital Region B
85

s
altitude=1000 km

lite
i=82° debris
removed

tel
Sa
Orbital Region A
altitude=800km 218

t
i=99° debris

en
removed

cem
pla
Re
RetroSat Demonstrator
Business Case

2020

2022

2024

2026

2028

2030

2034
2012

2014

2016

2032
2018

YEAR

24 satellites in 20 years


Space Debris Removal Fund (SDRF)

• International Governance
Launch
• RetroSpace proposes and will lobby for the Provider
creation of a Space Debris Removal Fund (SDRF)
Launch
• Source of funding for space debris removal Levy

Launcher State
• RetroSpace is uniquely positioned to become
the preferred de-orbit service provider
– First to market Contributions
International
– End-to-end solution SDRF
Organization Fund
– High TRL supervision
Debris
removal
fee
Business Case

SDRF: Space Debris Removal Fund
TRL: Technical Readiness Level

Sources of Funding for the SDRF

• Governments will pay Government Owners of Debris
– $100 M to $200 M per year Satellite Box Score
Rocket
– Contributions proportional Bodies &
to ownership of debris Country Payloads Debris Total
China 78 2695 2773
• Levy on launch fees
CIS 1379 3036 4415
– $500 / kg ESA 38 36 74
• Less than 0.5% of the annual France 49 331 380
India 36 111 147
global public space budgets
Japan 105 69 174
US 1098 3161 4259
Other 425 96 521
Source: The Orbital Debris Quarterly News, Vol. 13,
Issue 1 January 2009
Business Case

SDRF: Space Debris Removal Fund

Pricing - Space Debris Removal

• Price per piece of debris removed
– Fee charged for successful debris removal
– $15 M / piece of debris

• Primary source of revenue for RetroSpace will be the
debris removal service
Business Case


Additional Sources of Revenue

• Sale of RetroSat Satellites
– Sell units to selected customers to conduct de-orbit of their own
satellites
• “Space Tug” Service
– Use robotic arm to capture and relocate other satellites
• Damage Inspection Service
– Use visualization system to inspect other satellites
• Extend Services to GEO
• Secondary Payload
Business Case

GEO: Geostationary Earth Orbit

Revenue Projection

500
Further Growth
450 Potential
Other
400 RetroSat Sales
Debris Removal
350
Revenue [M$]

300

250
200

150
100

50
0
Business Case

2011
2012
2013
2014
2015
2016
2017
2018
2019
2020
2021
2022
2023
2024
2025
2026
2027
2028
2029
2030
2031
2032
2033
2034
2035
Year


Financing Strategy

350 Public Bond

Total financing need:
Total financing need: 300
Equity (Investors)

2011 2020: $390 M
2011 --2020: $390 M
Equity (Strategic Partner)
250

Investment [M$]
Investment Need

•• CAPEX //OPEX: $250 M
CAPEX OPEX: $250 M 200
•• Liquidity:
Liquidity: $140 M
$140 M 150 300

100

Satellite Unit Cost 50
70
[M$] 0
20

Satellite 2011 2012 2013 2014 2015 2016 2017
135.5
Development Year

1st Unit Cost 66.5 2011:
2011: $20 M --Founders //Financial Investor
$20 M Founders Financial Investor
2012:
2012: $70 M --Strategic Investor
$70 M Strategic Investor
Additional Units 52.7 2013:
2013: $300 M --“Clean Skies Bond”:
$300 M “Clean Skies Bond”:
•• 10-year public bond (5% p.a.)
10-year public bond (5% p.a.)
Business Case

Launch Cost 18.0
•• Issued by financial institution
Issued by financial institution
•• Guaranteed by international
Guaranteed by international
Insurance Cost 13.7 governments
governments
CAPEX: Capital Expenditures
OPEX: Operating Expenditures

Cash Flow

500
Total Revenues
CAPEX
400
COGS
OPEX
300 Revenue Debris Removal
Free Cash Flow
Bond Issue
200
[M$]

100

0
2011 2016 2021 2026 2031
-100

-200

Year Bond Repayment

Total CAPEX: $2190 M Total Revenues: $5.7 B
Business Case

Total CAPEX: $2190 M Total Revenues: $5.7 B
Total OPEX:
Total OPEX: $641 M
$641 M Debris Removal:
Debris Removal: $4.7 B
$4.7 B
Total COGS:
Total COGS: $158 M
$158 M Extended Services:
Extended Services: $1.0 B
$1.0 B
CAPEX: Capital Expenditures
OPEX: Operating Expenditures
COGS: Cost of Goods Sold

Financial Performance

500
Revenues
400 Net Income
Cash Flow (operating)
300
Million US$

200

100

Payback Period: 10 years
0
Time to Profit: 6 years
-100
Business Case

2014
2015
2016
2017
2018

2025
2026
2027

2034
2035
2019

2028
2029
2030
2011
2012
2013

2020
2021
2022
2023
2024

2031
2032
2033
Year


25 Year Financial Summary

Founders
Founders
•• Minority stake in RetroSpace
Minority stake in RetroSpace
•• Multiple exit options
Multiple exit options

Financial Investor (2017)
Financial Investor (2017)
•• Capital gain: $80 M
Capital gain: $80 M
•• Multiple: 5
Multiple: 5
•• IRR: 31% p.a.
IRR: 31% p.a.

Satellite Manufacturer
•• Profit from satellite sales: $130 M
Profit from satellite sales: $130 M
•• Majority stake in RetroSpace
Majority stake in RetroSpace
•• Dividends from 2020 onwards
Dividends from 2020 onwards
Business Case

General public (2023)
General public (2023)
•• Interest income: $150 M
Interest income: $150 M

IRR: Internal Rate of Return

NextGen PPP Rationale

• Creation of public good with commercial efficiency
• Creation of public good with commercial efficiency
• Lifecycle-based phased approach
• Lifecycle-based phased approach
• Exploitation of partner’s capabilities & strengths
• Exploitation of partner’s capabilities & strengths
• Apportionment of risk and finance geared to
• Apportionment of risk and finance geared to
• Investors
• Investors
• Private Industry
• Private Industry
• Public sector
• Public sector
• General public
• General public
• Balanced risk-reward ratio for all partners
• Balanced risk-reward ratio for all partners

Private
Investors
Industry
Business Case

International General
Governments
Organization Public

NextGen PPP: Next Generation Public-Private Partnership

Global Economic Summary

Private Investments Economic Benefit

Government Tax Income
$701 M

Economic Benefit: $3.5 B
Insurance Companies
$320 M

Revenues: $2.8 B
Launch Service Provider
$432 M

Operator Company
$663 M

$70 M Satellite Manufacturer
Business Case

$1436 M
Financial Investor
$20 M


Agenda

Market
System Solution
Business Case
Conclusion
Summary
Closing Thoughts
Acknowledgements
Agenda


RetroSpace Summary (1/2)

• Core Business:
• Providing a public service

• Primary Customer:
• Space Agencies / Governments

• Public-Private Partnership:
• Strategic manufacturing partner
• “Clean Skies Bond“

• Revenues exceeding $400 M per year
Conclusion


RetroSpace Summary (2/2)

• End-to-end system

• Fleet of 7
• Robotic capture
• Electrical propulsion

• Operational in 2016
Business Rendezvous, Grab, and De-orbit Launch

Removal of 15+ large debris per year
Removal of 15+ large debris per year
Reducing risk to space assets
Reducing risk to space assets
Securing future access
Securing future access
Conclusion


Risk Assessment

• International Cooperation
• Agencies must agree to fund this solution collaboratively

• Clarity of Ownership
• Consent required from debris owners

• Maturity of Technology
• Readiness levels are high (some details to iron out)

Low Risk
Low Risk
Conclusion


RetroSpace is the Solution!

• Responsive
• Bringing today’s technologies together

• Effective
• Preserving Earth orbit into the future

• Affordable
• Achievable funding requirements

• Profitable
• Attractive returns for all parties
Conclusion


RetroSpace Focus

• Lobbying for international coordination

• Securing key partnerships

• Investing in key technology

Be part of the solution!
Conclusion


RetroSpace

Restoring Space…
2010

2030

2040

2050

…to the way it was
Conclusion


RetroSpace is… (1/2)

Wolfgang Jung

Frank de Bruin

Susanne Wagenbach

Marco Castronuovo

Simon Hyde

Francesco Longo
Conclusion


RetroSpace is… (2/2)

Monica Martinez
Fernandez
Fabio Covello

Kristina Springborn

Martin Lösch

Shawn Mason

James Geary
Conclusion


Acknowledgments

• Central Case Project sponsor:
• Deutsches Zentrum für Luft- und Raumfahrt e.V.

• Delft University of Technology

• ESA ESTEC

• Our Coaches

• Jon & Jon
Conclusion


Thank You!

Any questions?
Conclusion


ST12 Retro Space

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ST12 Retro Space