gonçalo lopes cto, d-orbit pt 1 4th unisec · 2016. 12. 2. · 3 cubesats are a growing trend...
TRANSCRIPT
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Gonçalo Lopes
CTO, D-Orbit PT
4th Unisec–Global Meeting
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CUBESATS ARE A GROWING TREND
SOURCE: SpaceWorks 2016 Nano/Microsatellite Market Forecast (adapted)
200
400
600
2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022
1-50 Kg satellites launch history and forecast
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CUBESATS ARE A GROWING TREND
SOURCE: SpaceWorks 2016 Nano/Microsatellite Market Forecast (adapted)
200
400
600
2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022
1-50 Kg satellites launch history and forecast
CAGR: 39 %
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CUBESATS ARE A GROWING TREND
SOURCE: SpaceWorks 2016 Nano/Microsatellite Market Forecast (adapted)
200
400
600
2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022
1-50 Kg satellites launch history and forecast
CAGR: 39 % CAGR: 13 %
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D-SAT IS A TECHNOLOGY DEMONSTRATOR
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D-SAT IS A TECHNOLOGY DEMONSTRATOR
FIRST SATELLITE TO BE REMOVED
IN A QUICK, SAFE AND
CONTROLLED MANNER
3U Cubesat4.3 Kg mass
LaunchQ2 2017
500 Kmorbital altitude
< 30 minutes maneuver
2 months mission duration
30 N 165 E Disposal area
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D-SAT IS A TECHNOLOGY DEMONSTRATOR
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MOST CUBESATS CANNOT SELECT THEIR
PREFERRED ORBIT
Flying as secondary payloads poses a
limitation on the orbital design
available for Cubesats without
propulsion.
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MOST CUBESATS CANNOT SELECT THEIR
PREFERRED ORBIT
Flying as secondary payloads poses a
limitation on the orbital design
available for Cubesats without
propulsion.
Lower Orbits
imply short
missions (less
than 1 year)
Higher orbits
allow longer
missions
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MOST CUBESATS CANNOT SELECT THEIR
PREFERRED ORBIT
Flying as secondary payloads poses a
limitation on the orbital design
available for Cubesats without
propulsion.
Lower Orbits
imply short
missions (less
than 1 year)
Higher orbits
allow longer
missions
Difficulty to
comply with
debris
mitigation
guidelines
Higher
constellation
maintenance
cost and launch
frequency
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D-ORBIT HAS A SOLUTION TO THIS COMMON
PROBLEM
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D-ORBIT HAS A SOLUTION TO THIS COMMON
PROBLEM
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FENIX PROVIDES MOBILITY TO CUBESATS
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FENIX PROVIDES MOBILITY TO CUBESATS
Two different integration configurations
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FENIX PROVIDES MOBILITY TO CUBESATS
Two different integration configurations
Circular centered payload
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FENIX PROVIDES MOBILITY TO CUBESATS
Two different integration configurations
Circular centered payload Standard component configuration - stack
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ORBITAL FLEXIBILITY IS NOW POSSIBLE
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ORBITAL FLEXIBILITY IS NOW POSSIBLE
360º full constellation deployment in
less than 20 days
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ORBITAL FLEXIBILITY IS NOW POSSIBLE
360º full constellation deployment in
less than 20 days
Mission lifetime increase up
to 67%
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ORBITAL FLEXIBILITY IS NOW POSSIBLE
360º full constellation deployment in
less than 20 days
Mission lifetime increase up
to 67%
3U Cubesat decommission
from 700 Km
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MISSION SIMULATION FOR 500 Km ORBIT
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DESIGNED FOR MODULARITY AND SCALABILITY
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DESIGNED FOR MODULARITY AND SCALABILITY
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DESIGNED FOR MODULARITY AND SCALABILITY
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DESIGNED FOR MODULARITY AND SCALABILITY
Solid
Propellant
Propellant
CaseNozzle
Electronic Explosive System
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TECHNICAL SPECIFICATIONS
0
20
40
60
80
100
120
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8
THR
UST
(N
EWTO
NS)
TIME (SECONDS)
BURN PROFILE
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ISP
Specifications
Total Impulse
Average Thrust
Thrust Time
System Mass
260 sec.
54 N-sec.
77 N
0.7 sec.
480 g
Propellant Mass 20 g
Δv (4Kg Cubesat) 13.4 m/s
TECHNICAL SPECIFICATIONS
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DEVELOPMENT ROADMAP INCLUDES IN-ORBIT
VALIDATION IN 2018
2016 2017 2018
QualificationExecution of
qualification tests.
DevelopmentConstruction of the first
prototype to validate the
concept.
In-Orbit ValidationFirst flight in space.
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