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CUBESAT ATMOSPHERIC PROBE FOR EDUCATION (CAPE)
Presenting author: Christoph Montag Institute of Space Systems, University of Stuttgart
10th IAA Symposium on Small Satellites for Earth Observation 20 – 24 April 2015, Berlin, Germany
Adam S. Pagan (1), Christoph Montag (1), Georg Herdrich (1, 2), René Laufer (2), the KSat Team (3)
(1) Institute of Space Systems, Stuttgart, Germany, (2) CASPER, Baylor University, Waco, Texas, USA, (3) The KSat student team: J.-P. Baumann, A. Behnke, M. Ehresmann, J. Franz, D. Galla, B. Gäßler, F. Grabi, F. Hessinger, R. Hießl, M. Koller, G. Kuhn, N. Müller, R. Müller, A. Papanikolaou, J. Rieser,
V. Schöneich, H. Seiler, M. Siedorf, V. Starlinger, A. Stier, A. Tabelander, R. Tietz, F. Vardar, S. Wizemann
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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 2
Overview
1. Motivation 2. The CAPE mission 3. Technologies and experiments 4. Student involvement 5. Potential applications 6. Summary
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Motivation
Education of space engineers and scientists at universities is often mainly theoretical and lacking in practical hands-on training. Reasons: High costs of space projects Extended timeframes Complex systems and architectures
CubeSat format promises plenty of flight opportunities and constitutes a very cost-effective platform for Educational purposes Qualification of new technological developments Small scientific experiments
Many technologies developed at/with IRS are ready for and would benefit from flight testing.
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Current Objectives of the CAPE Project
Educational Hands-on training for science and engineering students Students may participate in all phases of a multi-faceted space mission Training in specialised and systems engineering
Technological Demonstration of micro return capsule technology Flight qualification of novel ablative thermal protection system material Heavy duty electric micro-propulsion demonstrator (PPT)
Scientific Atmospheric characterisation of the lower thermosphere through on-board
experiments, e.g. atmospheric oxygen sensors or particle impact detectors
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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 5
CAPE Vehicle Configuration
MIRKA2 re-entry capsule (1 CubeSat unit): • Uses RICA (Resin-Impregnated Carbon
Ablator) or ZURAM-based ablative TPS • Scientific payloads: e.g. Thermocouples,
radiometer, pressure transducers, etc. • Potential standard for flight qualification of
heat shield materials
Service and Deorbit Module SDM (3 CubeSat units): • Performs deorbit manoeuvre using PPT • Demises upon re-entry • Scientific payload: e.g. FIPEX, dust sensors • Potential standard carrier for future
CubeSat science missions
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Deployment 1 2 De-orbit
3 Separation
4 Re-entry of MIRKA2
5 Transfer of re-entry data via satellite
6 Demise of SDM, impact of capsule
CAPE Mission Scenario
• De-orbit down to separation altitude • Atmospheric measurements • PPT demonstration
at 125 to 150 km altitude
Transmission of data through Iridium network
Measurement of the ambient conditions and the re-entry performance of the capsule
e.g. from ISS
Potential for monitoring of break-up and demise
6 29/04/2015 10th IAA Symposium on Small Satellites for Earth Observation
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Trajectory Analysis
Mission analysis performed with IRS in-house code REENT
Starting orbit: ISS • 400 km altitude • 51.56° inclination
Downward spiralling manoeuvre
Propulsion system: Pulsed Plasma Thruster (PPT):
• 93 µN at 5.8 W (continuous) • 48 µN at 3.0 W (continuous
operation with extra contingency for payloads)
De-orbit: • Min.: 56 days • Max.: 176 days
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Technology Demonstration: Pulsed Plasma Thruster
ADD-Simplex (ADvanceD Stuttgart Impulsing Magneto-Plasmadynamic Thruster for Lunar EXploration)
Technology Readiness Level 7
Criteria for propulsion system for CAPE: Solid fuels only Minimal complexity High efficiency / Isp
Pulsed plasma thruster (PPT): Teflon is ablated through pulsed
electrical discharges Propellant acceleration through
thermal expansion and Lorentz forces
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10th IAA Symposium on Small Satellites for Earth Observation
Technology Demonstration: Micro Return Capsule
29/04/2015 9
CubeSat-compatible size Small size allows for ground-based
testing of entire vehicle, e.g. in plasma wind tunnel
Basic measurements of: flight behaviour re-entry environment thermal protection system (TPS)
performance Transmission of data via Iridium
network after black-out phase Separation via LOTUS (Low Orbit
Technical Unit Separator) spring-powered ejection mechanism
High-performance ablator materials ZURAM and RICA considered as candidates for TPS → Flight qualification
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FIPEX In-situ measurement of atomic
oxygen concentrations in lower thermosphere
Successfully flown on ISS
Piezo Dust Detectors In-situ measurement of impact
velocity and incidence angle of µm- to mm-sized dust particles
Relies on piezoelectric effect
Scientific Application: Atmospheric Characterisation
Two optional on-board scientific experiments are under investigation. The gradual downward spiralling manoeuvre provides ideal conditions for a spatial characterisation of the lower thermosphere.
29/04/2015 10 10th IAA Symposium on Small Satellites for Earth Observation
(DLR)
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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 11
Student Involvement
CAPE is a primarily educational project. Past activities have encompassed: Annual iteration of the Planetary Probe Design Workshop at IRS Numerous student theses and project works Student small satellite interest group KSat e.V. at IRS:
• Currently 25 highly motivated active members and growing • Current focus on CAPE and tie-in precursor REXUS sounding rocket
experiment MIRKA2-RX (PDR passed!)
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MIRKA2-RX Mission Overview (PDR passed)
T=0s: launch
T=26s: burn-out
T=140s: apogee at 80-100 km Ejection
MIRKA2-RX Mirror System
T=~800s
MIRKA2-RX Capsule
(ESA 2007)
REXUS sounding rocket
Deutschland
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Potential Applications of CAPE
Technological / Economical Cost-effective potential standard for
Flight qualification of thermal protection system materials Nanosatellite servicing
Conceivably controlled capture and deorbit of space debris and meteoroids using SDM
Scientific Standardised platform for spatially and temporally resolved atmospheric
measurements in general. Quantitative data of contamination of atmospheric gas sensor
measurements through electric thruster exhaust. Micro return capsule data provides valuable reference scenario with direct
application to ground testing facilities. Potential for tracking of atmospheric break-up and demise of SDM
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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 14
Summary
CAPE is a primarily educational project, yielding extensive participation opportunities for student
CAPE combines multiple active fields of research into one highly cost-effective package: Atmospheric science „Heavy duty“ electric micro-propulsion CubeSat technology Controlled re-entry using ablative heat shield technology
Ideal low-cost technology demonstrator
Potential baseline for future similar missions
Micro return capsule MIRKA2, Service and Deorbit Module (SDM) and educational aspects detailed in further presentations and posters at this symposium
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Appendix: Participants (1/2)
NASA Goddard (J. Esper) Potential flight opportunity
DLR Stuttgart (H. Hald) Integration of capsule
29.04.2015 15
IRS (G. Herdrich) Management and lead,
System Design
Thermochemistry, Instrum.
Space Science Lab (R. Laufer, CASPER, Baylor University) Systems Engineering Support
Small Satellite Design
University of Adelaide (M. Kim)
Blackout assessment
ISA (Ph. Reynier) Assessment of laminar/
turbulent transition
Trajectory simulation
KSat IRS Student team
ASA (M. Auweter-Kurtz) System and mission analysis
support
ÖWF (N. Frischauf) International outreach
CE (R. Gabrielli) National outreach and
regulations (CE)
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Gradel (D. Petkow) Modelling + simulation of
capsule's dynamic motion during initial reentry phase
OHB Sweden (A. Demairé) PPU for deorbit electric
propulsion
Thales Alenia Space Deutschland Facilities and logistical
support of student activities
Appendix: Participants (2/2)
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