MSc in Economics of Science & Innovation Innovation & Challenges: Nanotechnology & Space (3a)

1. MSc in Economics of Science & Innovation Innovation & Challenges:Nanotechnology & Space(3a) Space Mission Jordi Isern Institut de Ciències de l’Espai (CSIC-IEEC)

2. Bibliography: * “Spacecraft mission analysis and design”,J.R. Wertz & W.J. Larson (eds.), Kluwer Academic Publishers * “Spacecraft systems engineering”, P. Fortescue & J. Stark (eds.), J. Wiley & Sons

3. Space mission analysis # Space missions range widely from communications to planetary exploration, to proposals for space manufacturing or even space burial => NO SINGLE PROCESS CAN COVER ALL THE CONTINGENCIES # Space is expensive. Cost is a fundamental limitation # Analysis & design are iterative. Succesive iterations will usually lead to a more detailed better defined mission concept # The results of this iterations have to be documented in order to guarantee the reproductibility of the process Old ESA joke: 1 tm of documents for each payload kg 1Gb

4. The Space Mission concept: • Mission objectives * The subject(s) • Mission design • Production and deployment • Operations and support • Mission end The concept of payload: Combination of hardware and software on the spacecraft that interacts with the subject to accomplish the mission objectives

5. Defining a mission concept What space characteristic makes a space mission desirable or necessary? • Global perspective  Earth observation • Above the atmosphere  Space observatory • Gravity-free environment  Materials processing, etc • Exploration of space itself  Solar System exploration Is there a rendez-vous or a strong date demand?(ex. a Halley’s comet mission).

6. Setting top level mission requirements Functional requirements: • Performance  primary objective definition, payload size, orbit, pointing. • Coverage  orbit, number of satellites, scheduling. • Responsiveness  communications, processing, operations. Operational requirements: • Duration  altitude, level of redundancy, consumables. • Availability  level or redundancy, orbit. • Survivability  electronics, orbit. • Data distribution  communications. • Data content and format  payload, processing, user support. Constraints: • Environment  orbit, lifetime. • Cost, schedule, ...

7. Broad Steps in Mission Analysis Step 0 - Mission statement Step 1 - Define objectives • Define broad objectives and constraints • Estimate quantitative mission needs and requirements Step 2 – Characterize the mission • Define alternative mission concepts • Define alternative mission architectures • Identify system drivers for each alternative • Define in detail what the system is and does Step 3 – Evaluate the mission concepts • Identify critical requirements for each mission concept • Evaluate mission utility • Select one or more baseline system designs Step 4 – Define requirements • Define system requirements • Allocate requirements to each system component

8. Mission arquitecture

9. The ECSS (European Cooperation for Space Standardization) standard project phasing • Phase 0: Mission Analysis/Needs Identification • Phase A: Feasibility • Phase B: Preliminary Definition (Project and Product) • Phase C: Detailed Definition (Product) • Phase D: Production/Ground Qualification Testing • Phase E: Utilization • Phase F: Disposal

10. Types of space missions • Manned vs. unmanned level of autonomy? • By objectives: * Communications * Navigation * Earth observation * Science – Remote sensing » Solar System science » Astronomy » Fundamental physics – In situ science » Solar System exploration » Applied physics » Life sciences » Others (materials science, …) * Others

12. FUEGO Mission statement • FUEGO is a system based on space technology that will allow the early detection and monitoring of forest fires through the acquisition of satellite images with high spatial resolution and high frequency of revisit of the fire scene. • The main objective of FUEGO is to contribute decisively to the fight against fires in the Mediterranean forests. • FUEGO end users will be the national fire fighting and civil protection services. Data flow and formats must meet the needs of both groups without specialized training and must allow them to respond promptly to changing conditions.

14. SIXE Mission statement: • The ultimate goal of the MINISAT program was the development and construction of a series of medium size and versatile platforms which could be able to be used in different missions without the need of substantial changes in their structure. • After the construction of the first spacecraft of this series, the MINISAT-01 one, the Spanish National Plan for Space Research (PNIE) made a call for proposals to choose a new payload for the next mission. • SIXE (Spanish Italian X-Ray Experiment) is the final result of a cooperative effort between a spanish institution, the Institut d’Estudis Espacials de Catalunya (IEEC), and an italian one, the Istituto di Astrofisica Spaziale (IAS).

15. SIXE has beendesigned to meetthefollowing set of criteria: a) The goal of the experiment is to provide a reliableX-ray observatoryable to studyfrontier topics throughhigh-precisionX-raytiming. b) The technicalrequirements of the experiment arefully compatible withthe MINISAT-01 platform and only a fewchangesarerequiredwithrespect to theinitialdesign of thespacecraft. c) According to thespirit of a missionbased on a smallspacecraftthe experiment has beendesigned to fulfillthescientificgoals in a short time and with a smalleconomicbudget.

17. Systemdrivers: Principal missionparameters or characteristicswhichinfluenceperformance (and cost) and whichthedesignercan control. Choose a fewalternativedesigns based on differentoptions for a fewsystemdrivers.

18. Examples of system drivers

19. Allocatingrequirements: Identify all sources of error thataffect to the final product (not just fromthespacecraft!) Elements frequentlybudgeted in spacemissiondesign:

20. Payload design: • Types of payloads: • • In situ (ex. collection and analysis of solar wind particles) • • Remote sensing (uses only e.m. spectrum, so far) • * Imaging (imagers, cameras, …) • * Intensity measurement (radiometers, polarimeters, scatterometers, …) • * Spectral distribution (spectrometers, …) • * Topographic mapping (altimeters, …) • Issues: optics, electronics, thermal, structures, mechanisms • Active or passive sensors?

21. The “ideal” detector: • High spatial resolution AND large useful area. • Good temporal resolution AND ability to handle large count rates. • Good energy resolution AND unit quantum efficiency over large bandwidth. • Light in weight AND minimal power consumption. • Output stable on timescales of years. • Negligibly low internal background. • Immune to damage by radiation environment. • Require no consumables. • No moving parts. • Low output data rates. • ... and simple and cheap to construct (and pretty!!)

22. Bus design and payloads requirements: • Spacecraft bus provides support to the payload • through subsystems: • • Attitude maintenance • • Orbit control • • Power • • Command • • Telemetry and data handling • • Structure and rigidity • • Thermal control • Design the spacecraft to meet payload, orbit, and • communications requirements. • • Orbit affects propulsion, attitude control, thermal design, and power. • • Environment (radiation, ...) affects usable materials, • spacecraft lifetime, and electronics. • • Instruments, sensors, solar arrays, and thermal radiators have pointing and FOV requirements.

23. Mainrequirements and constraints for spacecraftdesign

24. Spacecraft configuration drivers

27. Spacecraft subsystems: • • Propulsion subsystem • • Attitude Determination and Control Subsystem (ADCS) • * Goal: Pointing of instruments, solar panels, antennas, etc. (common or independent pointings). • * Sensors to determine the attitude (solar sensor, star tracker, horizon sensor) • * Passive (spinning, interaction with Earth’s magnetic or gravity fields) or active (controllers, actuators, torquers, thrusters) control. • * Capabilities depend on the number of appendages to be controlled, control accuracy, speed of response and disturbance environment. • • Communications subsystem • * Goal: Uplink commands and ranging tones, and downlink status telemetry, ranging tones, and payload data. • * Design depends on data rate, allowable error rate, communications path length, and RF frequency. • • On-Board Data Handling (OBDH) subsystem • * Integrated on the communications subsystem or with an independent structure (computer, etc.)

28. • Power subsystem • * Components: Solar cells, batteries, power conversion, and distribution equipment. • * Design depends on average power needed, power needs during eclipses, peak power consumption. • * Performance degrades  establish requirements for BOL and EOL. • • Thermal control subsystem • * Goal: Keep instruments, batteries, … inside the operative or the survival temperature range. • * Passive (thermal insulation and coatings to balance power dissipation, absorption from Earth & Sun, and radiation to space) or active (electrical heaters, heat pipes). • • Structural subsystem BOL: beginning of life EOL: End of life