Miniaturised Asteroid Remote Geophysical Observer (M-ARGO): A stand-alone deep space CubeSat system for lowcost science and exploration missions

Transcription

1 Miniaturised Asterid Remte Gephysical Observer (M-ARGO): A stand-alne deep space CubeSat system fr lwcst science and explratin missins Prepared by R. Walker (1), D. Kschny, C. Bramanti & ESA CDF study team Presenter Philipp Hager, Ph.D (2) (1) System Engineer (IOD CubeSat lead) (2) Thermal Engineer, Thermal Cntrl Sectin Directrate f Technlgy, Engineering & Quality, ESA/ESTEC Interplanetary Prbe Wrkshp, Bulder, CO, USA, 14 th f June 2018 ESA UNCLASSIFIED - Fr Official Use

2 Miniaturised Asterid Remte Gephysical Observer (M-ARGO) Missin Cncept Missin bjectives: Missin phases: Grund segment: rendezvus with an asterid characterise the physical prperties f asterid (shape, surface, mass) assess ptential fr resurce explitatin (cmpsitin, hydratin) piggyback launch n Sun-Earth L2 transfer (astrnmy missin) parking in Sun-Earth L2 hal rbit interplanetary transfer using lw-thrust slar electric prpulsin clse prximity peratins fr 6 mnths f remte sensing 15/35 m ESA ESTRACK statins + Sardinia Radi Telescpe (64 m) Missin Operatins Centre with flight dynamics, Science Ops Centre Prgrammatics: Budget (1 st missin incl. NRE): <25 MEur ROM Schedule: launch 2021 ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 2

3 M-ARGO System Overview Attribute Specificatin S/C vlume 12U frm factr (226x226x340 mm) Paylad vlume 1U available Prpulsin µrit Gridded In Engine, gimbal, PPU, neutraliser 2 Xenn prpellant tanks & feed system (Max. 2.8 kg) Cmmunicatins X -band DS transpnder with ranging/dppler (2 Rx, 3 Tx channels) 4x patch antennas fr mni-directinal TT&C Deplyable HGA reflect-array fr P/L data Pwer Single bdy munted panel (6U face) + Li-in battery 2 -wing deplyable slar array with slar array drive mechanism (SADM) Pwer t 1 AU 93 W (6 panels) 120 W (8 panels) 1 AU 1.7 mn 2.4 mn 1 AU 3050 s 3180 s S/C wet mass (w/ margins) 21.6 kg 22.3 kg AOCS Sensrs: visnav camera, star tracker, 6 sun sensrs, IMU Actuatrs: 3 reactin wheels, 8 Xe cld gas RCS thrusters Data handling Mdular avinics with paylad data prcessing Thermal cntrl Passive with radiatrs & heaters ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 3

4 M-ARGO Spacecraft Cnfiguratin ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 4

5 Science ratinale - All asterids visited s far are >300 m in size - Fr asterids with a size <100 m, mdels predict a cmpact mnlithic bdy which has n reglith and is fast spinning -> New science! ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 5

6 Multi-Spectral Imager ASPECT Multi-spectral (VTT, Finland) imager VIS channel nm NIR channel nm SWIR channel nm Field f View [deg] 6 x x circular Spectral res. [nm] < 20 nm < 50 nm < 25 nm 1 U Spectral bands (tunable in flight) ~ 14 ~ 24 ~ 30 Image size [pixels] 614 x x pixel 1 U 1 U Pixel size (um) Fcal length (mm) F/# GSD at 500 m 9 cm 18 cm 44 m SNR at phase angle <20 >40 (tint = 50 ms) at nm >40 (tint = 15 ms) at nm >100 (tint = 10 ms) at nm Mass: 950g Pwer: 7 W TRL 6, Aalt-1 heritage (space qualified) ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 6

7 NEO Target Screening MPCORB database (23/1/2017) 725,896 bjects Pre-filtering (3-impulse chemical) 63 bjects (<2.6 km/s, n>80, V<28.1) Lw-thrust trajectry ptimisatin tl 30 bjects (mp <2.5 kg) Assumptins Starting frm Earth-Sun L2 with n initial C3 Spacecraft initial mass 20 kg Maximum thrust f 1.7 mn, specific impulse f 3000 s Launch windw: between 2020 and 2023 (included) Maximum time f flight: 3 years Maximum prpellant mass: 2.5 kg ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 7

8 Sun Beam t In Beam Optimisatin Final pwer int EP [W ] panels 8 panels Thrust [mn] panels 8 panels Cnstant Isp [s] panels 8 panels Cnstant Sun distance [AU] Sun distance [AU] Sun distance [AU] ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 8

9 Missin Analysis f Ptential Targets Designatin! [AU] " # [AU] " $ [AU] % & [ ] ' ) [km/s] * + [kg] 2012 UV EK XB YORP BS FU MD YORP: rbital elements seem prmising but frm 2020 n, YORP is getting away frm the Earth EK24: all rbital elements are in the gd ranges but inclinatin is t high 1996 XB27: at rendezvus the range t Earth is t large fr cmmunicatin ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 9

10 Missin Analysis Variable thrust & Isp vs. sun distance 8 panels ptin Delta-v: 3.17 km/s Xe mass: 2.2 kg Thrust-n: 395 d Sun distance <1.2 AU Earth range: <0.8 AU SAA during thrust-n phases deg 2012 UV136 ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 10

11 Clse Prximity Operatins Target 2012 UV136, 7 day repeat cycle ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 11

12 Alternative L5 Space Weather Missin Radiatin mnitr Magnetmeter + 1 m bm Departure date (frm SEL2) 2024/2/6 Earth encunter N/A Asterid arrival date 2025/9/22 Delta-V 2.62 km/s Prpellant mass (withut margin) 1.70 kg Thrust-n time 342 days Range f distance frm Sun AU Range f distance frm Earth AU Range f SAA value during thrust-n deg 20-mnth transfer ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 12

13 Stand-Alne Deep Space Cubesats High ptential t cut the entry-level cst f space explratin by an rder f magnitude Piggyback launch ptins t near Earth escape: Lunar transfer/rbit, Sun-Earth L1/L2 transfer, uter planet 12U CubeSat with enabling miniaturised technlgies: Ptential missins: high specific impulse electric prpulsin system & cld gas RCS deep space transpnder & HGA high pwer deplyable steerable slar array highly integrated rad-hardened avinics NEO rendezvus fr physical characterisatin (science, resurces) Sun-Earth L5 fr space weather (strm advance warning) Technlgy Reference Study perfrmed in ESA Cncurrent Design Facility t assess feasibility, tech develpments, cst/schedule ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 13

14 Cnclusins Stand-alne Deep Space CubeSats are technically feasible in the near-term Delta-V capability (3.75 km/s) encmpasses at least 4 NEO targets fr rendezvus (up t 30 as f time f study), and transfer t Sun-Earth L5 fr space weather missin Technlgies are either high TRL fr CubeSat COTS prducts r TRL 3/4 t be develped t TRL 6 within the frame f the ESA Technlgy Prgramme (SADM, EPROP subsystem, X-band transpnder & HGA) Radiatin hardness assurance f COTS electrnics cmpnents wrt destructive latchups needed in the prject, and sme delta-qualificatin f equipment Schedule t flight readiness in early 2021, launch July 2021 assuming technlgy develpments start sn ROM cst is cnsidered t be marginally feasible within 25 M budget Majr cst driver is the Flight Dynamics supprt cst (50% f the verall ROM cst estimate) -> lwer cst appraches t be investigated Next steps: kick-ff tech dev activities & identify piggyback launch, then start Phase A/B ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 14

15 Acknwledgements t ESA CDF Study Team CUSTOMER TEAM LEADER AOCS I. Carnelli (General Studies Prgramme) R. Walker M. Casasc PROGRAMMATICS/ J. Gil Fernandez T. Muresan AIV D. Hagelschuer Y. Le Deuff COMMUNICATIONS P. Cncari ELECTRIC PROPULSION D. Feili N. Wallace F. Marguet CONFIGURATION S. Mangunsng RISK D. Wegner COST G. Cifani L. Viscnti MISSION ANALYSIS M. Khan M. Scbeau DATA HANDLING T. Szewczyk SPACE ENVIRONMENT M. Millinger M. Grulich GS&OPS D. Taubert STRUCTURES U. Blck MECHANISMS M. Yrck SYSTEMS D. Binns D. Bjilff M. Scherrmann V. Pesquita PAYLOAD/ DETECTORS P. Crradi O. Sqalli THERMAL P. Hager V. Laneve T. Flecht POWER P. Fernandez TARGET SCREENING D. Izz A. Merata ESA UNCLASSIFIED - Fr Official Use ESA IPPW 14-JUN-2018 Slide 15

16 THANK YOU Philipp Hager, Ph.D. (n behalf f Rger Walker Ph.D.) ESA/ESTEC Keplerlaan AZ Nrdwijk The Netherlands Acknwledgments: - Based n slides and input by Rger Walker and the M- ARGO CDF study team philipp.hager@esa.int ESA UNCLASSIFIED - Fr Official Use