Science Week 2018 The ORIGINS Laboratory for Rapid Space … · 2019. 1. 8. · classification...

M.J. Losekamm | Technical University of Munich

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The ORIGINS Laboratory for Rapid Space Missions

Science Week 2018

Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

ISS Internal Payload

• Payload mass: < 10 kg

• Cost: “free”, ~ 50 k€ per kg

• Time to orbit: < 1 year

ISS External Payload


• Cost: “free”, ~ 100 – 200 k€ per kg

• Time to orbit: 1 – 2 years

Small Satellites


• Cost: 60 – 80 k€ per kg


Commercial Spacecraft/Landers


• Cost: ?


Why Rapid Space Missions? Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Technology Readiness Level Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Actual system flight proven through

successful mission operations

System prototype demonstration

in space environment

System/subsystem model or prototype

demonstration in a relevant

environment (ground or space)

Analytical or experimental critical function

and/or characteristic proof of concept

Critical Steps

• Instrument R&D

• Scientific methods

• Data analysis

The ORIGINS Laboratory for Rapid Space Missions Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

ORIGINS LRSM

Science Community Tech Community

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• “Space” experience

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• Payload instruments

• “Science” experience

• Spacecraft R&D

• Space mission design

• Mission operations

Mission Coordinator

PhD students for common R&D

Small Satellites Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

CubeSats Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Solar and Space Physics

• Targeted science missions using novel

measurements techniques

• Augmentation of larger facilities

• Constellation and swarm missions

Earth Science

• Technology demonstration

• Augmentation of larger facilities

• Constellation and swarm missions

• Mitigate data gaps

From: Achieving Science with CubeSats: Thinking Inside the Box; National

Academies Press

Planetary Science

• Unique vantage point / multipoint measurements

• High-risk missions

• Low-gravity laboratories

Astronomy and Astrophysics

• Interferometry: multi-aperture observations

• Technology demonstration

Biological and Physical Sciences

• Microgravity laboratories

• Access to space environment (microgravity,

radiation)

Science on CubeSats Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

First-MOVE

• 1U CubeSat, 0.912 kg

• Experimental triple-junction solar cells

• 1.3 MP camera

• Launch: 21 Nov 2013

MOVE-II

• 1U CubeSat

• Experimental quadruple-junction solar cells

• Tech demo: S-band transceiver, magnetic ADCS

• Launch: TODAY (18:32:54 UTC)

CubeSats at TUM Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

MOVE-II CubeSat Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Communications

TRL 8 (MOVE-II)

• UHF/VHF transceiver (< 2.5 W, 25 kbit/s)

• S-band transceiver (< 5 W, < 40 Mbit/s)

TRL 2/3

• X-band transmitter (< 15 W, > 100 Mbit/s)

• V-band inter-satellite link

Attitude Determination and Control

TRL 8 (MOVE-II)

• Embedded magnetorquers

• De-tumbling / sun-pointing

• 10 deg pointing, 1 deg determination accuracy

TRL 2

• Reaction wheels / gyros

Subsystem Expertise Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Electrical Power System

TRL 7/8 (M2)

• Extendable Modular Power Supply (EMPS)

• Solar cell, battery, and electronic in one board

• Redundancy through distributed system

Command and Data Handling

• Commercial system on MOVE-II

TRL 2

• Modular, scalable system under development for

several projects

• Fault- and radiation-tolerant computing

Subsystem Expertise Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Electronics

Batteries

Test Electronics

MOVE-II

• 1U CubeSat

• Technology demonstration (ADCS, COM)

Launch: TODAY (18:32:54 UTC)

MOVE-III

• 3U CubeSat

• Technology demonstration (all subsystems)

Launch: 2022

Upcoming TUM CubeSat Missions Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

2018 2019 2020 2021 2022

MOVE-IIb

• 1U CubeSat

• Technology demonstration (ADCS, COM)

Launch: March 2019

M2/EMPS

• 2 CubeSats

• Technology demonstration (EPS)

Launch: Spring 2019

SG-Sat

• 2 8U to 12U CubeSats (tethered)

• Technology demonstration, payloads

Launch: 2022

Other Expertise Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

• Instrument R&D


• Data analysis

The ORIGINS Laboratory for Rapid Space Missions Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

ORIGINS LRSM


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• Spacecraft R&D



Mission Coordinator


• 12U CubeSat, 600-km sun-synchronous orbit

• 20 x 10 cm2 3-mirro anastigmat telescope

• > 0.25 x 0.25 deg2 field of view

• Actively cooled, 2048 x 2048 pxs IR sensor

− 4-band simultaneous imaging

• 4 reaction wheels, 3 deg/s slew rate

− 1000x faster than Hubble

− pointing stability ~ 0.001 deg

➢ Poster about dichroic prism for 4-band imaging

by Jochen Greiner

Trailblazer #1: SkyHopper Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Search for Earth-like Exoplanets

• Complementary to NASA’s TESS

• Measure masses through transit-timing variations

Near-IR Observation of Gamma-Ray Bursts

• Redshift z > 5

• Expected discovery rate: 5 ± 2 yr-1

Measure Cosmic Microwave Background

• Broadband imaging

• Constrain history of star formation

Observe Planetary System Formation

• Multi-day observations of NEOs

• Characterize spin, binarity, and spectral

classification

Trailblazer #1: Science Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Galactic Cosmic Rays (GCR)

• 98% nuclear component

− 87% protons, 12% helium, 1% heavier elements

• 2% electrons, protons

• energies up to 1020 eV

• galactic sources: supernovae

• extragalactic sources for highest energies?

• hardly shieldable

Solar Energetic Particles (SEP)

• protons, electrons, some nuclei

• produced in local bursts of radio waves, X rays, and

coronal matter

• energies up to several GeV

• travel along interplanetary magnetic field lines

• potentially harmful events quite rare

• easily shieldable, except during EVA

Van Allen Radiation Belts

• Earth’s magnetic field

− deflects low-energy particles

− traps particles

• inner belt: protons & electrons from albedo neutron decay

• outer belt: solar electrons

• energies up to

− 7 MeV (electrons)

− 2 GeV (protons)

• large portion of dose received on ISS from radiation belts

and secondary neutron production

Trailblazer #2: (Ionizing) Radiation in SpacePage 33 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

From Interstellar Space to Earth

Heliopause Magnetopause Exosphere Boundary

Interstellar Space Heliosphere

Magnetosphere

Atmosphere

- Solar Wind

- Magnetic Field

- Magnetic Field

- Radiation Belts

- Atmospheric Particles

and Molecules

- Interstellar Medium

Production Detection

Transport

Interactions with…

Interplanetary Space

Interplanetary Space

From Interstellar Space to Earth

Heliopause Magnetopause Exosphere Boundary

Interstellar Space Heliosphere

Magnetosphere

Atmosphere

- Solar Wind

- Magnetic Field

- Magnetic Field

- Radiation Belts

- Atmospheric Particles

and Molecules

- Interstellar Medium

Production Detection

Interactions with…

Transport Codes Monte-Carlo Simulations

Transport

The geomagnetic field is approximated by a

tilted dipole field.

➢ Rigidity- and position-dependent

shielding

➢ Cut-off rigidity varies due to solar

magnetic disturbances

Back-tracing of charged particles through

magnetosphere using

• PLANETOCOSMICS and

• IGRF & Tsyganenko models

Magnetosphere

Effective vertical cut-off rigidity (h = 20 km)

The geomagnetic field is approximated by a

tilted dipole field.

➢ Rigidity- and position-dependent

shielding

➢ Cut-off rigidity varies due to solar

magnetic disturbances

Back-tracing of charged particles through

magnetosphere using


• IGRF & Tsyganenko field models

➢ AMS-02 exposed to low-rigidity

antiprotons only about 10% of its

measurement time!

Magnetosphere

pbar

Rigidity (GV)

Energy (GeV)0.4330.005 9.105# o

f days p

bar

reach d

ete

cto

r

Matter traversed by CR

in IM: ~ 6 to 10 g/cm2

in atmosphere: ~ 6 g/cm2

1. Attenuation

• Energy loss ~10% at ground level

for 0.1 GeV/n < E < 10 GeV/n

2. Background production

• Upscattering into space (albedo)

• Low-energy particles at locations with high

geomagnetic cut off

Corrections using


• semi-analytical models

➢ More in-depth studies needed!

Atmosphere

50 km

100 km

700 km

~190,000 km

~10-17 to 10-8 g/cm3

~10-8 to 10-6 g/cm3

~10-6 to 10-3 g/cm3

Total mass: ~1 kg/cm2

• Measurements at energies below ~ 10 GeV per nucleon require strict event selection and complicated

corrections

• Measurements below ~ 500 MeV almost impossible in LEO

Cosmic Ray Measurements in LEO

Science Case #1: Space Radiation MonitoringPage 40 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Age at Exposure (y) Exposure Limit (Sv)

Female Male

25 0.4 0.7

35 0.6 1.0

45 0.9 1.5

55 1.7 3.0

1000-day Mars

mission> 1.0

Exposure (µSv/day)

Earth (world average) 8.2

ISS 600

Mars surface 640

Mars cruise 1800

Typical Exposures in Space

Ten-Year NCRP Limits for Astronauts

Earth: 𝛽 particles, 𝛾 rays, and low-energy 𝛼 particles

Space: protons, neutrons, and high-charge, high-energy (HZE) particles

Science Case #1: Space Radiation MonitoringPage 41 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

(1) Direct Production

𝑝 + 𝐴 → 𝑝 + 𝑝 + ҧ𝑝 + 𝑋

𝐴: ቊ60% Hydrogen40% Helium

kinematic threshold (lab frame): 𝐸𝑝 = 6𝑚𝑝 ≈ 5.63 GeV

(1a) prompt hadronization

(1b) weak decay of hyperons (𝑡~10−10 s)

ഥΛ → ҧ𝑝 + 𝜋+ (Br: 63.9 ± 0.5%)

തΣ+ → ҧ𝑝 + 𝜋0 (Br: 51.6 ± 0.3%)

𝑓hyp

𝑓prompt= 0.2 − 0.3

(2) Decay of Antineutrons (CRANbarD)

ത𝑛 → ҧ𝑝 + 𝑒+ + 𝜈𝑒

Science Case #2: Radiation-Belt AntiprotonsPage 42 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Dark Matter Annihilation

𝜒 + ഥ𝜒 ⇌ 𝑓 + ҧ𝑓,𝑊+ +𝑊−, 𝑍0 + 𝑍0, … ⇌ ҧ𝑝, ഥ𝐷,𝐻𝑒, 𝑒+, 𝛾, …

Science Case #3: Indirect Dark Matter DetectionPage 43 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

neutralino mass: a) 36.5 GeV, b) 61.2 GeV,

c) 90.4 GeV, d) 120 GeV

Science Case #3: AMS-02 Antideuteron Sensitivity

??

??

• 1024-channel active-target detector

• Scintillating-fibers and silicon photomultipliers

• ~800 cm2sr acceptance

• < 2 deg angular resolution

• 2% / 10% energy resolution (< 100 / < 600 MeV/n)

Trailblazer #2: RadMap TelescopePage 45 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Trailblazer #2: EvolutionPage 46 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

?

Technology ISS CubeSat

ISS

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LOP-GPage 47 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Plans for assembly of new LOP-G in moon

orbit in 2020’ies.

The LOP-G will spend about two thirds of

its time outside of Earth’s magnetosphere

• No shielding of low-energy cosmic rays

• Passage through bow shock,

magnetosheath, and magnetotail

➢ Why not install a new detector there?

Lunar Orbital Platform-Gateway (LOP-G)

Moon orbit, ~60 RE

(not to scale)

Bow shock, ~15 RE

Antimatter Observatory on the Gateway

• Sensitivity at lower energies significantly decreases system complexity, size, and cost

• Advances in processing electronics and algorithms ensure increased performance at

lower data volumes through better pre-processing of science data on instrument

50DEEP SPACE GATEWAY CONCEPT SCIENCE WORKSHOP | FEBRUARY 27 – MARCH 1, 2018

PARAMETER INSTRUMENT ON LOP-G AMS-02 ON ISS

MASS (KG) 100 to 200 8,500

VOLUME (M) < 1 m3 64 m3

POWER (W) 200 to 400 (steady state) 2,500

DAILY DATA VOLUME ~ 10 GB (gigabytes) or ~ 0.9 Mb/s > 100 GB (gigabytes) or > 9 Mb/s

WAG COST & BASIS$10 – $15 million for hardware & instrument

tests~ $1.5 billion total cost

DURATION OF

EXPERIMENT

Open-ended, but min. 2 years Operating since 2011

OTHER PARAMETERS - 1,200-kg Neodymium magnet

Antimatter Observatory on the Gateway

The proposed instrument concept is similar to the one of AMS-02 on the ISS.

Major difference: Sensitivity at lower particle energies.

However, recent advances in

• embedded processing electronics (ASICs, FPGAs, real-time MCUs),

• on-line data analysis and reduction algorithms (e.g. neural networks),

• photosensors (silicon-based photodetection vs. photomultiplier tubes), and

• silicon-based tracking detectors

allow to build an instrument that is more compact, lighter, and more efficient than previous ones.

51DEEP SPACE GATEWAY CONCEPT SCIENCE WORKSHOP | FEBRUARY 27 – MARCH 1, 2018

• Instrument R&D


• Data analysis

The ORIGINS Laboratory for Rapid Space MissionsPage 53 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

ORIGINS LRSM


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• Spacecraft R&D



Mission Coordinator


• Identify potentially interesting Missions of Opportunity

• Identify other parties (beyond ORIGINS) who might be interested in LRSM technology

Science

• Identify potential payloads / experiments beyond trailblazers

• Assess TRL of potential payloads

• Payload R&D

Technology

• Identify potential for common hardware

• Assess scalability

• Perform TRL-raising activities / missions (e.g. MOVE-III)

• Develop 12U to 16U CubeSat bus

LRSM: Next StepsPage 54 Technical University of Munich | M.J. Losekamm | ORIGINS LRSM Overview

Thank you!

Science Week 2018 The ORIGINS Laboratory for Rapid Space … · 2019. 1. 8. · classification...

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