DK Space Technology Innovation Activities

Slide1: 

ESA Space Technology Innovation Workshop Copenhagen, 6 – 7 September 2001 Space Technology Innovation Activities in Denmark Flemming Hansen Technology Manager, MScEE PhD Danish Small Satellite Programme Danish Space Research Institute e-mail: fh@dsri.dk web: http://www.dsri.dk Rømer 3D Model by Jan Erik Rasmussen, Danish Space Research Institute

Slide2: 

Why Develop Space Technology ??? What is actually the objective of space technology innovation on the long term ??? The Earth may become uninhabitable within 100 - 200 years from now due to accelerating climate changes, depletion of natural resources, ecological disasters, or the Earth may be hit by a NEO - an asteroid or comet - eradicating human life like the dinosaurs 65 million years ago Therefore . . . . . The objective of space technology innovation is to ensure the survival of humankind on other planets . . . . .

Slide3: 

Space Activities in a Small Country - 1 Why ? All technologies spun off from space to the mass market have started out as research fields driven by novel ideas or demands to fulfil specific requirements All applications of space such as satellite communication, navigation, Earth observation, have grown out of space research A large fraction of observations of the Earth, the solar system and the universe can only be done from space. Many research areas would stall if space observations were not possible. New observations and developments in space are crucial both for research and applications Satellite projects are excellent as incentives for education and technological innovations Increased skills and proficiencies in our society

Slide4: 

How ? International cooperation - in particular within ESA – has always been and will continue to be a cornerstore of Danish space activities. International co-operation is necessary for large projects International programmes are complemented by a national programme: The Danish Small Satellite Programme (DSSP) Space Activities in a Small Country - 2 Benefits of a National Programme DSSP is governed by Danish priorities and novel ideas DSSP allows Danish companies to gain prime contractorship and payload experience, otherwise not possible Small satellite missions are faster, cheaper (and better ?) - and they are the wave of the future A national programme increases public appeal and understanding (national pride) Provide precursor missions for larger, international misions.

Slide5: 

Vector Magnetometer and Star Imager Scalar Magnetometer ØRSTED – The First Danish Satellite Size: 62 kg, 34 x 45 x 72 cm Dedicated satellite for mapping the Earth magnetic field Launch: 23 February 1999 on Delta 2 from Vandenberg Near sun-sync, polar orbit: 650 - 860 km altitude First high-precision magnetic mapping in 19 years Participation: 50 research groups from 14 countries Provides sole basis for the international reference Earth magnetic field model: IGRF2000 Used in science and applications (cartography, mineral prospecting etc.) Flies in conjunction with Danish Ørsted-2 payload on Argentine SAC-C satellite, Danish Vector Magnetometer / Star Imager payload on German CHAMP satellite and the ESA Cluster II mission Ørsted 3D Model by Jan Erik Rasmussen, Danish Space Research Institute

Slide6: 

ØRSTED – The First Danish Satellite

Slide7: 

Rømer Mission Overview - Science PI: Prof. Jørgen Christensen-Dalsgaard ( jcd@obs.aau.dk) Institute of Physics and Astronomy/Theoretical Astrophysics Center, Aarhus University Primary Measuring Oscillations in Nearby Stars – MONS Measurement of intensity and colour oscillations in solar-like stars using a 32 cm telescope and a CCD-based precision photometric detector, to probe the stellar interior for determination of its composition, age, mixing and internal rotation. Secondary Secondary science is only implemented in the satellite design to the extent possible within the available on-board margins. Science may include discovery of extra-solar planets through the effects of transits across the stellar disk, detection of supernova explosions in distant galaxies and discovery of asteroids in our solar system. Stellar Oscillation Modes Trajectories of Sound Waves in a Star

Slide8: 

Rømer Mission Overview - Payload Primary science instruments MONS Telescope, strongly defocused Gregorian optics, 32 cm aperture, high-performance 1 k x 1 k photometric CCD detector for measuring tiny oscillations of stellar intensity and colour, using red and blue filters at telescope aperture (not shown). MONS Field Monitor for examining the field of view of the MONS Telescope for faint variable stars Secondary science instruments Forward- and aft-looking Star Trackers of the Attitude Control Subsystem, to be used for studying variable stars MONS Field Monitor (Basically a telephoto star tracker) MONS Telescope Field Monitor 3D Models by Jan Erik Rasmussen, Danish Space Research Institute

Slide9: 

Rømer Mission Overview – Detection of Stellar Oscillations Oscillation magnitudes in intensity and color are in the range of a few ppm A star will be observed for a period of 30 days Red and blue filters allow color oscillations to be measured as well as intensity oscillations The period of the fundamental mode stellar oscillation is typically a few minutes Rømer 3D Model by Jan Erik Rasmussen, Danish Space Research Institute

Slide10: 

Rømer Mission Overview - Satellite Dimensions: 60 x 60 x 71 cm Mass: 100 kg Separation System: Ariane 5 ASAP Power Consumption: 55 W orbit average Power Bus: 28 V unregulated Battery: Li-Ion, 4.5 Ah, 8 cells in series Radio Transmitter: 2 W, S-Band (2200 - 2290 MHz) TM/TC format: CCSDS Downlink Data Rate: 500 - 64000 bit/s FEC Encoding: Concatenated R-S (223,255) + R=½ Convolutional Downlink Transmission Capacity: min. 24 Mbyte/day Uplink Data Rate: 500 and 4000 bit/s Rømer 3D Model by Jan Erik Rasmussen, Danish Space Research Institute

Slide11: 

Rømer Mission Overview – Attitude Control Subsystem Actuators: 4 reaction wheels with rate sensors in tetrahedron configuration Momentum unloading: 3 magnetorquer coils Attitude sensors: Forward and aft looking star trackers Magnetic field sensor: Vector magnetometer Sun sensors: 12 slit-type sun sensors Control laws executed by on-board computer Pointing Accuracy at 95% confidence: Pitch/Yaw: 2 arcmin absolute 0.8 arcmin over 1 sec. 0.35 arcmin over 0.1 sec. Roll: 60 arcmin absolute 2 arcmin over 60 sec. Rømer 3D Model by Jan Erik Rasmussen, Danish Space Research Institute Electronics Rack Field Monitor Reaction Wheels Star Trackers Sun Sensors

Slide12: 

Rømer Mission Overview - Orbit Science observations need to be done outsde the radiation belts  Molniya orbit has been baselined for RØMER Apogee height: 40000 km Perigee height: 600 km Inclination: 63.4° Period: 11 hours 58 min. 02 sec. (= ½ siderial day, ideal) The Molniya orbit allows approx. 10 hours of observations outside the radiation belts. A satellite in Molniya orbit is subjected to a large dose of radiation from high-energy protons and electrons trapped in the Earth’s radiation belts: 200 krad behind 2.5 mm aluminium over 2 year mission

Slide13: 

Rømer Mission Overview - Launch RØMER is foreseen to be launched with a Russian SOYUZ/FREGAT rocket early 2005. The SOYUZ rocket has been launched more than 1650 times and its reliability exceeds 97% FREGAT is a new upper stage developed by Lavochkin Association. ESA’s CLUSTER-II satellites were launched successfully on 16 July and 09 August 2000 from Baikonur Cosmodrome using this new upper stage. RØMER

Slide14: 

Mission Objectives Do world class science in asteroseismology and strengthen Danmarks already leading position in this field Calibrate astrophysicists’ stellar models with data from many solar-like stars Multi-tiered cooperation between academia and industry Mission shall function as a development platform for new technologies Flight opportunity and hence flight heritage for new products “Satellite in a box” including “Attitude Control Subsystem in a box” concept High degree of software control High degree of on-board autonomy Clear platform/payload separation enable reuse of platform “Virtual control room” concept based on synergy of on-board autonomy, automated ground station and control center, state-of-the-art mobile communications and portable computer technology, secure Internet communications, space Internet (possibly)

Slide15: 

Rømer Budget & Co-Funding Overview

Slide16: 

Rømer Funding Sources in Denmark We had hoped to see a continuation of the Danish Small Satellite Programme in the Fiscal 2002 budget proposal at around 3.5 MEUR/year – but it is not there !!!!! The Rømer project can carry out a detailed design phase until end 2002 at 2/3 of originally anticipated activity level using remaining DSSP funds

Slide17: 

Danish Space Companies Terma A/S: Main contractor for Rømer Systems engineering, on-board software, attitude control software, power subsystems, star trackers, DC/DC-converters, metal and composite structural elements Alcatel Space Denmark A/S: Responsible for part of power system on Rømer DC/DC converters, Electronic Power Conditioners, Power Distribution Units, Batteries Rovsing A/S: Presently no responsibility on Rømer On-board software, check-out systems, ground station software, microgravity facilities TICRA A/S: Presently no responsibility on Rømer Antenna analysis and design software, consulting Innovision A/S: Presently no responsibility on Rømer Medical space equipment: Respiratory monitoring systems and bicycle ergometers DAMEC Research A/S: Presently no responsibility on Rømer Support space medical and human physiological research and instrumentation ACE Contractors A/S: Presently no responsibility on Rømer Carbon fiber composite structural elements Unigate Innovation A/S: Presently no responsibility on Rømer Ground support equipment

Slide18: 

Danish Space Institutions - 1 Danish Space Research Institute: Small Satellite Programme Office Mission analysis, systems engineering, payload engineering, space instrument design and manufacturing, astrophysics research, solar system physics research, climate research Institute of Physics and Astronomy, University of Aarhus: Proposer and responsible for the Rømer science mission World leading center in asteroseismology research Danish Meteorological Institute: Presently no responsibility on Rømer Meteorology, atmospheric and climate research; solar-terrestrial physics research; space instrument design and manufacturing Danish Planetary Center (Jointly operated by DSRI and Universities of Copenhagen and Aarhus, Technical University of Denmark, Risø National Laboratory, National Museum) Solar system physics, planetary physics

Slide19: 

University of Copenhagen, Niels Bohr Institute, Astronomical Observatory Astrophysics, cosmology, astronomical instrumentation and telescopes, Hipparcos & Tycho catalogues, ESA GAIA mission University of Copenhagen, Niels Bohr Institute, Department of Geophysics Geophysics including research based on spaceborne instruments Technical University of Denmark Ørsted•DTU, Electromagnetic Systems (EMI): Rømer antennas Antennas, SAR and radiomater systems & signal processing, Earth Science Research Ørsted•DTU, Measurements and Instrumentation Systems: Rømer attitude control Star trackers, vector magnetometers, control systems incl. attitude control, autonomous systems, failure tolerant systems Aalborg University, Department of Control Engineering: Rømer attitude control Control systems incl. attitude control, autonomous systems, failure tolerant systems Danish Space Institutions - 2

Slide20: 

Vector Magnetometers: DSRI, Oersted•DTU Evolution trends: Smaller sensors, digital signal processing, enhanced magnetics Applications: Attitude determination, precision planetary magnetic field mapping Missions: Ørsted-1/2, CHAMP, Astrid-2 Future: Mars Netlander, Beppi-Colombo (Proposed), Bering (Proposed) Qualification level: Flight proven   Star Trackers: Oersted • DTU (University/Agency Small Missions) Evolution trends: Active pixel sensors, enhanced DPU, miniaturization Applications: Attitude determination, finding celestial pole, detection of wind systems Missions: ØRSTED-1/2, TEAMSAT, CHAMP, ASTRID-2, PROBA-1 Future: MARS SPIDER, GRACE, CONTOUR, SMART-1, MAXI (ISS), SMILES (ISS), ADEOS-2 , PROBA-2, DEMETER, FBM, PARASOL, Bering (Proposed) Qualification level: Flight proven X-Ray Detectors and Multilayer X-Ray Mirrors: Danish Space Research Institute Evolution Trends: Higher spatial and energy resolution for detectors, higher reflectivity and larger energy range for mirrors Applications:  X-ray imaging instruments for space science, medical equipment Qualification level: Under development Danish Space Technology Strongholds - 1

Slide21: 

Danish Space Technology Strongholds - 2 Star Trackers: Terma A/S (commercial missions) Evolution trends: 12 bit/pixel resolution, back illuminated CCD, active pixel sensors, enhanced DPU Applications: Attitude determination, precision stellar photometry and other astronomical observations Missions: USAF NEMO, ESA CRYOSAT, RØMER Qualification level: Qualified DC/DC Converters: Alcatel Space Denmark A/S Evolution trends: Conversion efficiency, lower parts count, producability Applications: Low to medium power converters for space electronics including receivers, solid state (microwave) power amplifiers etc. Missions: Too numerous to list Qualification level: Flight proven

Slide22: 

Future Danish Space Technology Areas Nanotechnology and Micro Electro-Mechanical Systems (MEMS) Microelectronics Center (MIC) at the Technical University of Denmark has a solid foundation in nanotechnology and MEMS and is interested in space applications Status: Initial discussions MIC – DSRI Missions: DTU or AAU CubeSat mission November 2002. Lithium-Polymer Batteries and Supercapacitors Danionics A/S is a leading supplier of state-of-the-art planar Li-Polymer batteries to the computer and mobile phone industry Status: Discussions to be initiated Missions: DTU or AAU CubeSat mission November 2002. There is no formal Danish space technology innovation programme, but we are working towards instituting such a programme under DSSP within a 1 – 2 year time frame. Two recently started student CubeSat projects at Technical University of Denmark and Aalborg University will provide flight opportunities for technology demonstrations compliant with a November 2002 launch

Slide23: 

Danish University Pico-Satellite Projects - 1 This summer two university pico-satellite projects has been kicked off, one at the Technical University of Denmark (DTU), the other at Aalborg University (AAU) The satellites will be based on the CubeSat conecpt developed by Stanford University and California Polytechnic State University. A CubeSat is characterized by three figures: Size: 10 x 10 x 10 cm cube Mass: 1 kg Orbit average power: Approx. 1 W, The Cubesat concept includes a standardized mechanical external interface Summer courses in satellite technology and design are held at both universities with lecturers from both universities, industry and Danish Space Research Institute Payload Still under consederation: CCD camera, tether, propulsion, technlogy demonstration …..

Slide24: 

Danish University Pico-Satellite Projects - 2 Project Costs Less than EUR 180000 total per satellite Launch Launch service is provided by One Stop Satellite Services Inc. in Ogden, Utah, USA, using a russian Dnepr launcher (based on decommissioned SS-18 missiles) at a cost of USD 75000 (EUR 85000) per satellite Three Cubesats are mounted in a standard dispenser (P-POD) and ejected simultaneously. The P-PODs are mounted on a Multi-Payload Adapter (MPA) holding up to 30 CubeSats and other small satellites. The MPA is released from the launcher before CubeSats are ejected. Launch of the Danish CubeSats are foreseen in November 2002 Orbit Orbit will be 600 km polar LEO. Dnepr launcher

Slide25: 

The Mars Spider - 1 The Mars Spider is proposed by Ass. Prof. John L. Jørgensen, Ørsted•DTU, Measurement & Instrumentation The easy part: Piggyback ride to Mars proximity on larger mission The challenge: Enter Mars atmosphere using Inflatable structure for initial braking Unroll 20 km carbon fiber tether for aerobraking through the descent phase. Cut the tether a few tens of meters above ground. At touch-down, a spear will penetrate the Martian crust to a depth of about 30cm providing a stable anchor to the planet

Slide26: 

The probe will measure the rotation of Mars with high precision, and detect the shear of changing wind system patterns  Tested succesfully at Mauna Kea, Hawaii. The probe will perform studies of electrical and magnetic properties of the Martian dust A magnetometer will study the variations of the magnetic field at the surface of the planet A geophone will detect possible Mars seismic activity The Mars Spider - 2 Size: 500 x 150 x 150 mm, stowed Mass: 3.5 kg (lander) Power: Max. 8 W, avg. 1.2 W

Slide27: 

The Mars Spider - 3 The communication challenge: Lander will support a 25 cm parabolic dish. Link budget dictates Ka-band communication and 34 meter ground station for acceptable bit rate. Find direction to Earth using star tracker at antenna (using CMOS active pixel sensor based mini star tracker)  Tested succesfully at Mauna Kea. Tracks planets within 6 arcmin following 100 sec. acquisition period - or - Optical communication payload using semiconductor laser and small reflector telescope - even more difficult to establish communication link due to narrowing of the beam  Not tested

Slide28: 

The Good Circles in Space