AIM/PALS AIM Industry ESTEC

Transcription

1 AIM/PALS AIM Industry ESTEC IRF, Uppsala & Kiruna ÅAC Microtec AB, Uppsala DLR, Bremen Emil Vinterhav emil.vinterhav@aacmicrotec.com ICE-IEEC, Barcelona KTH, Stockholm

2 Science IRF, Uppsala & Kiruna ICE-IEEC, Barcelona KTH, Stockholm Project Team System Analysis and Design ÅAC Microtec AB, Uppsala Mission Analysis DLR, Bremen

3 PALS Hugin & Munin PALS = Payload of Advanced Little Satellites Hugin and Munin are companions to Odin, the Norse god of wisdom Hugin ( thought, intuition ) Munin ( memory, common sense ) Hugin and Munin are ravens that fly over the world collecting information for Odin so that he can know all the secrets of the universe and create order from truth.

4 Payload Hugin: NAC: Narrow Angle Camera VCA: Volatile Composition Analyser Munin: VES: Video Emmision Spectrometer MAG: Fluxgate Magnetormeter (2m boom) Meeting and supporting AIM to meet primary and secondary science objectives

5 Possible Orbits inside the Binary System L4/L5 area are stable equilibrium points L1/L2 are instable equilibrium points and can be used for short transfers or flybys to the moon or as operations points where active control is necessary Close proximity operations to Didymoon (500 m) is not possible with standard keplerian orbits (like polar ones), to much perturbation from binary system and gravity field of the primary

6 Possible Orbits inside the Binary System

7 Mission Scenario

8 Detailed Mission Scenario Phase Activity Duration Platform Payload 1 Commissioning, 4 Commissioning, Detumbling, Delta V correction, In orbit test 2 Approach 1 Approach from >10 km, orbit insertion Science L4/L5 Operations 10 days station keeping Science 3 Transfer to L1/L2 1 day Manoeuvering L1/L2 Operations 10 days Station keeping Science 4 Impact 1 day Forced motion transfer to and station keeping 5 L1/L2 Operations 20 days station keeping Science 6 Transfer to L4/L5 1 day Manoeuvering L4/L5 Operations 10 days station keeping Science Total 58 days ~30 days margin for extended mission

9 Requirements & Constraints User requirements Mission Analysis requirements 1U Payload / PALS Cubesat Orbit navigation and Magnetically clean (<1 ma*m 2 ) maneuvering 3 axis stabilized (loose pointing Forced motion maneuvering requirements) Eclipse operations Station keeping and maneuvering Station acquisition in binary system External (customer) requirements CubeSat standard Customer furnished s-band ISL 1Gbit total data downlink Prefer COTS equipment Design constraints Autonomy COTS TRL 6

10 PALS spacecraft (1/3) Design philosophy COTS preferred (some modifications necessary) Aim for >TRL 6 Single string equipment, redundancy on logical level (TMR) TID tolerant to 20 krad Structure & Mechanisms 2x 3U Cubesats named Hugin and Munin (less than 4,5 kg each) identical equipment, differ in accomodation of equipment and thruster orientation 4 segments of deployable solar panels 2m boom for MAG on Munin

11 PALS spacecraft (2/3) 3-axis attitude stabilisation and 3 position nav and control startrackers and reaction wheels Optical sensors, laser altimeter, (s-band ranging) and Cold Gas thrusters Propulsion 16 cold gas thrusters in two modules 20 Hz Total ~12,5 m/s delta V Data handling 2x OBC, (OBDH and position navigation) FPGA, TMR, RTEMS, SpW 1x combined TM&TC and MM, 16 GB MM, EDAC, RTEMS, SpW, CCSDS, PUS stacks PUS for command distributuin, SpW for onboard data bus, CCSDS for ISL (TBC) Thumbnail data download selection for optimal use of link budget

12 PALS spacecraft (2/3) Communication ESA s-band ISL with ranging capability 2x patch antennae giving full sphere coverage Power 11W Average, 15 W maximum 4x deployable solar panels and power storage for eclipse Thermal Surface treatment for hot side, and MLI for cold side Heaters (TBD)

13 PALS:Hugin x z y

14 PALS:Munin x z y

15 PALS:Hugin

16 PALS:Munin

17 Schedule Team consolidation IRF, KTH, ICE-IEEC, DLR, ÅAC Mictorec Science definition Science objectives Instrument suite Mission Analysis Identification of constraints and possibilities System definition uin CEF Designing platform to support and payload requirements and science objectives System Consolidation Adress outstanding issues Preparation of system implementation plan Plan from here to delivery of system

18 Challenges & open issues AOCS with 2m boom Autonomy Position navigation and guidance Cubesat project in ESA inter-planetary mission context

19 Summary Strong project team Strong heritage from deep space and asteroid science and missions String heritage of deep space spacecraft operations Strong heritage of space system design Strong science case Supporting AIM to meet primary and secondary science objectives Advanced mission Highly autonomous High peformance AOCS Advancing the state of the art for Cubesats Strong technology State of the art payload with heritage from large scale missions Platform is COTS and TRL > 6

20 Thank you for your attention Emil Vinterhav