CUBESAT ATMOSPHERIC PROBE FOR EDUCATION (CAPE)

Transcription

1 Presenting author: Christoph Montag Institute of Space Systems, University of Stuttgart CUBESAT ATMOSPHERIC PROBE FOR EDUCATION (CAPE) 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 April 2015, Berlin, Germany

2 Overview 1. Motivation 2. The CAPE mission 3. Technologies and experiments 4. Student involvement 5. Potential applications 6. Summary 29/04/2015 2

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. 29/04/2015 3

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 29/04/2015 4

5 CAPE Vehicle Configuration 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 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 29/04/2015 5

6 CAPE Mission Scenario 1 Deployment e.g. from ISS 3 Separation at 125 to 150 km altitude 2 De-orbit De-orbit down to separation altitude Atmospheric measurements PPT demonstration 5 Transfer of re-entry data via satellite Transmission of data through Iridium network 4 Re-entry of MIRKA2 Measurement of the ambient conditions and the re-entry performance of the capsule 6 Demise of SDM, impact of capsule Potential for monitoring of break-up and demise 29/04/2015 6

7 Trajectory Analysis Mission analysis performed with IRS in-house code REENT Starting orbit: ISS 400 km altitude 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 29/04/2015 7

8 Technology Demonstration: Pulsed Plasma Thruster Criteria for propulsion system for CAPE: Solid fuels only Minimal complexity High efficiency / I sp Pulsed plasma thruster (PPT): Teflon is ablated through pulsed electrical discharges Propellant acceleration through thermal expansion and Lorentz forces ADD-Simplex (ADvanceD Stuttgart Impulsing Magneto- Plasmadynamic Thruster for Lunar EXploration) Technology Readiness Level 7 29/04/2015 8

9 Technology Demonstration: Micro Return Capsule 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) springpowered ejection mechanism High-performance ablator materials ZURAM and RICA considered as candidates for TPS Flight qualification 29/04/2015 9

10 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. 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 (DLR) 29/04/

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!) 29/04/

12 MIRKA2-RX Mission Overview (PDR passed) T=26s: burn-out REXUS sounding rocket T=140s: apogee at km Ejection MIRKA2-RX Mirror System MIRKA2-RX Capsule Deutschland T=0s: launch (ESA 2007) T=~800s 29/04/

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 29/04/

14 Summary CAPE is a primarily educational project, yielding extensive participation opportunities for student CAPE combines multiple active fields of research into one highly costeffective 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 29/04/

15 Appendix: Participants (1/2) IRS (G. Herdrich) Management and lead, System Design Thermochemistry, Instrum. DLR Stuttgart (H. Hald) Integration of capsule NASA Goddard (J. Esper) Potential flight opportunity 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 ÖWF (N. Frischauf) International outreach CE (R. Gabrielli) National outreach and regulations (CE) KSat IRS Student team ASA (M. Auweter-Kurtz) System and mission analysis support

16 Appendix: Participants (2/2) Gradel (D. Petkow) Modelling + simulation of capsule's dynamic motion during initial reentry phase Thales Alenia Space Deutschland Facilities and logistical support of student activities OHB Sweden (A. Demairé) PPU for deorbit electric propulsion