DLR developments and application ideas for interplanetary cubesats

iCubeSat, Milano 2019

Jens Biele1, Michael Maibaum1, Caroline Lange2, Thimo Grundmann2, Stephan Ulamec1, Marcus Thomas Knopp3, Frank-Cyrus Roshani3

1DLR German Aerospace Center, RB-MUSC, Cologne, Germany 2DLR German Aerospace Center, Bremen, Germany 3DLR German Aerospace Center, GSOC, Munich, Germany www.DLR.de • Chart 3 > Lecture > Author • Document > Date

SKAD-Study [FRANK, MARCUS]

• Orbiter as relais station for Mars-Rover • ………. Designs flown or studied (DLR)

Hopper(10-25 kg) MASCOT (30, 70 kg)

Philae (100 kg)

Leonard MASCOT (10 kg)

Folie 4 > Vortrag > Autor Folie 5 > Vortrag > Autor

Study Flow of MASCOT („how to shrink a lander..“)

• December 2008 – September 2009: feasibility study, with CNES, in context of Marco Polo and Hayabusa-2, with common requirements: • 3 iterations of different mass (95kg, 35kg & 10kg) and P/L • Settled on 10 kg lander package including 3 kg of P/L • Ho, T.-M., et al. (2016). "MASCOT—The Mobile Asteroid Surface Scout Onboard the Hayabusa2 Mission." Space Science Reviews 208(1-4): 339– 374. • ➔ Design of MASCOT 10 kg: a nanosat (30x30*20 cm³) . Could be a 18 U cubesat!

Large ~ 95 kg, Philae hertitage

Middle ~ 35 kg, Xtra Small ~ 10 kg, No post-landing Up-righting + mobility mobility MASCOT Payload (25% of total mass!)

Instrument Science Goals Heritage Institute; PI/IM Mass [kg]

MAG magnetization of the NEA MAG of ROMAP on Rosetta TU Braunschweig Lander (Philae), ESA VEX, 0,15 → formation history Themis K.H. Glassmeier / U. Auster

mineralogical composition ESA ExoMars, Russia and characterize grains Phobos GRUNT, ESA size and structure of Rosetta, ESA ExoMars IAS Paris µOmega surface soil samples at μ- rover 2018, Rosetta / Philae J.P. Bibring / M. Berthé 1,9 scale / CIVA/MI Infrared hyperspectral microscope

map NEA‘s surface temperature to determine MUPUS-TM on Rosetta DLR PF (Berlin) the thermal inertia → Lander (Philae); MERTIS- MARA M. Grott / J. Knollenberg 0,12 Yarkovsky & Yorp effects RAD on BepiColombo

multispectral images of the ExoMars PanCam heads, DLR PF (Berlin) landing site and provide Rosetta-ROLIS head, ISS- CAM R. Jaumann / N. Schmitz 0,4 geological context RokViss head

Folie 6 > Vortrag > Autor Folie 7 > Vortrag > Autor

MASCOT+ ̶ Proposed Lander Packages for small body missions • On the basis of MASCOT (a ~10kg lander for the Hayabusa 2 mission), landers with various instrument complements have been studied

MAPOSSI - LIBS, MARA - APX -Thermal Mapper, - Mößbauer Spectrometer, LIBS for ExoMars - IR-spectrometer (MicrOmega), © DLR CAM - Camera,

- optional elements MicrOmega for MASCOT © IAS MAG μOmega FANTINA -Radar Tomographer MASCOT - Camera - optional elements Concept of Radar Tomogapher Image: IPAG Folie 8 > Vortrag > Autor Bus Design / Power System longevity – MASCOT-2 (AIM) • Unfoldable solar generator cover • Supports orientation and protects solar cells during touch-down • Active area 0,127 m²

• Energy output: ~23 Wh/Trot www.DLR.de • Chart 9 > Lecture > Author • Document > Date

Utilization of cubesats complementing conventional interplanetary probes to enhance the scientific outcome of the mission

• Focus • deployable payloads (e.g. Dobson space telescope), • fragmented systems (formation flying, e.g for SAR or high precision gravity field and • small body landers ➔ great potential to mitigate risks and advance accuracy of measurements. • Solar sail demonstrator Gossamer-1 (developed to QM) was an assemblage of 5 nano spacecraft (with CubeSat-avionics), due to their special mechanics bigger thatn usual Cubes. www.DLR.de • Chart 10 > Lecture > Author • Document > Date

SKAD-Study

• November 2016 – March 2017 Feasibility study initiated by DLR Space Administration to investigate future Mars exploration by means of autonomous and heterogeneous swarms of robots and drones. • At first terrestrial anologue mission in desert environment to validate concepts • Small satellite acting as data relay satellite www.DLR.de • Chart 11 > Lecture > Author • Document > Date

HERA

• Hera is an ESA technology demonstration mission for asteroid impact mitigation (HERA+DART[NASA]=AIDA). • Supported by Germany • Target is the Didymos binary asteroid system • Need approval at ESA ministerial, end-2019. • Will fly 2 cubesats, one of which will land on Didymoon in the end: APEX, Juventas www.DLR.de • Chart 12 > Lecture > Author • Document > Date

small means focused, not less: from many parallel boxes to all in one box MARA DACC bouncing (hidden) MasCAM heritage landers: MasMAG • cover all fields (hidden) • medium-integrated design concept • separate instrument interfaces ‘as usual‘

• requirements-driven bouncing design, drives mission bouncing Communication LFR Main Antenna MASCOTs: Antenna bouncing • focus on key topics GNC PEC GNC PEC GNC OPS target body properties addressed… thermal IR • organically integrated radiometer GNC OPS • surface structure (MARA) design LED illumination • composition Camera (CAM) • mechanical properties • across unit border MicrOmega (hidden) • thermal properties optimized interfaces

• interior structure magnetometer • constraints-driven (MAG) • spacecraft orientation design GNC PEC GNC OTS note: no Scout would go outdoors without a compass! → www.DLR.de • Chart 13 > Lecture > Author • Document > Date

cooperating cubes: GOSSAMER -1 solar sail demo

(a) Launch Configuration (b) BSDU is released and deployment started; the belt (green) is coiled by BWM (a) Launch Configuration (b) BSDU is released and (a) Launch Configuration (b) BSDU is released and deployment started; the belt deployment started; the belt • 1 GOSSAMER sailcraft = 5 independent spacecraft (green) is coiled by BWM (green) is coiled by BWM • @ launch connected to act as one (c) Sails fully deployed; (d) BSFR separated and • electrical – thermal – mechanical(a) Launch(a) interfacesLaunch Configuration Configuration (b)(b) BSDU BSDU is is BSFRreleased released is locked andand by tape remaining boom is deployed (a) Launch Configuration (b) BSDU is releasedspring on boomand • cubesat electronics in GOSSAMER -1 design deploymentdeployment starte startedd;; thethe belt deployment(green)(green) is is coiled coiledstarte by dby; the BWMBWM belt • EQM done, PFM design ready to go @ termination (green) is coiled by BWM

• launch contract was with QB50 (tech-dem on PSLV) (c) Sails fully(e) Belt deployed; connected by Velcro (f)(d) BSDU BSFR is jettisoned separated and and (c) Sails fully deployed; (d) BSFR separated and BSFR is lockedis separated by tapefrom boom remainingdrifts away boom is deployed BSFR is locked by tape remaining boom is deployed spring on boom spring on boom

(c) Sails fully deployed; (d) BSFR separated and (c) SailsBSFR fully is locked deployed; by tape remaining(d) BSFR boomseparated is deployed and (c)BSFR Sails is spring fullylocked deployed; on by boom tape remaining(d) BSFR boom separated is deployed and BSFRspring is locked on boom by tape remaining boom is deployed spring on boom

(e) Belt connected by Velcro (f) BSDU is jettisoned and (e) Belt connected by Velcro (f) BSDU is jettisoned and is separated from boom drifts away is separated from boom drifts away

(e) Belt connected by Velcro (f) BSDU is jettisoned and is separated from boom drifts away figures(e): Belt connected by Velcro (f) BSDU is jettisoned and Seefeldt et al.,(e) 2016is Belt separated connected from by boom Velcro (f) BSDUdrifts is jettisoned away and is separated from boom drifts away

www.DLR.de • Chart 14 > Lecture > Author • Document > Date say HY2 your scouting little friends

• 1 mission • 7 active nano-spacecraft • 5 passive nano-spacecraft

figures : ISAS / JAXA www.DLR.de • Chart 15 > Lecture > Author • Document > Date

Thank you for your attention!