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www.uni-stuttgart.de CUBESAT A TMOSPHERIC PROBE FOR EDUCATION (CAPE) Presenting author: Christoph Montag Institute of Space Systems, University of Stuttgart [email protected] 10 th 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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Page 1: UBESAT ATMOSPHERIC PROBE EDUCATION  … ·  CUBESAT ATMOSPHERIC PROBE FOR EDUCATION (CAPE) Presenting author: Christoph Montag Institute of Space Systems, University of Stuttgart

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CUBESAT ATMOSPHERIC PROBE FOR EDUCATION (CAPE)

Presenting author: Christoph Montag Institute of Space Systems, University of Stuttgart

[email protected]

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

Page 2: UBESAT ATMOSPHERIC PROBE EDUCATION  … ·  CUBESAT ATMOSPHERIC PROBE FOR EDUCATION (CAPE) Presenting author: Christoph Montag Institute of Space Systems, University of Stuttgart

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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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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 3

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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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 4

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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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 7

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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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 8

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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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 12

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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10th IAA Symposium on Small Satellites for Earth Observation 29/04/2015 13

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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29.04.2015 16

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)