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FMI – IKI, NPOL Cooperation in space science (Planetary science) V. Linkin

FMI – IKI, NPOL Cooperation in space science (Planetary science) V. Linkin. Helsinki 2007, January. Mars 96. Overview. Small autonomous station FMI – participation in -       development system – CEU -       science (meteo, imaging) -       pre-flight test system. Met-Net.

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FMI – IKI, NPOL Cooperation in space science (Planetary science) V. Linkin

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  1. FMI – IKI, NPOL Cooperation in space science (Planetary science) V. Linkin Helsinki 2007, January

  2. Mars 96 Overview Small autonomous station FMI – participation in -       development system – CEU -       science (meteo, imaging) -       pre-flight test system Met-Net FMI – estimating of main goal Met-Net, science programme participation in development of Met-Net system   meteo hardware and   data analysis - meteo -       climate -       internal structure (seismic) -       imaging -       aerosols -

  3. Met-Net Principal science points -       light-weight Meteo-Station on Mars possibly to work during all seasons, latitudes and wide range elevation Principal technical points -       piggyback payload or independent flight with using law-coast rocket -       semi-hard landing -       Pu-heater, RTG -       Electrical propulsion -       Law mass bus and descent unit

  4. SPACE RESEARCH INSTITUTE RASFINNISH METEOROLOGICAL INSTITUTEBABAKIN SCIENCE & RESEARCH CENTER MARS PROJECT MET-NET

  5. Work Firm Prototype Readiness Launch POLET KOSMOS-3M (in addition to payload) Updating interface Interface with rocket POLET Old design Updating interface Spacecraft assembly structure IKI Design from project “Kalibry” Updating and manufacture Spacecraft avionics with structure IKI SSP design with updating Updating and manufacture Landing modules(mechanical system of atmospheric entry and landing) LA Already develop Only manufacture Meteostation with onboard service systems and scientific nstruments IKI Already developed Only manufacture EJPS with solar cell pads Energija Design from project “Modul-M” Updating and manufacture Development testing of spacecraft IKI\POLET Tests Ground Control Center IKI\POLET SSP design with updating Updating and manufacture Independent launch of two (or one) landing module by KOSMOS-3M rocket with electric jet propulsion system (EJPS)

  6. The general scheme of the expeditionMet-Net

  7. The general parameters mission Met-Net Total mass spacecraft ~100 kg PL mass (descend module with SMS) 18 kg Mass of Xe 43 kg Nominal power of Solar bat 1.4-1.8 kW Surface of solar bat 16.0-20.0 m2 (amorphous silicon PEC), or 5 м2 (As-Ga PEC), Thrust of 2 EJPS D-38 (D-55) 97 mN Resource EJPS 6000 hours Duration of mission 11-13 month Duration of injection into Mars-bound trajectory ~ 90 до 180 days Duration of brake ~1-2 month Height of initial orbit ~ 750 км The telemetry radio link Earth -SC 1-2 kbits\sec The command radio link SC-MSS 0,1 kbits\sec Dimensions of SC in folded state are 0.5x0.9x1.0 m After deployment of solar panels the dimensions are 0.5x18x1.0 m.

  8. BALLISTIC SUPPORT MET-NET The general scheme of the flight to the Mars consists of the following phases: -  Placing the Spacecraft and MSS onto low orbit; -  Speedup on the near-Earth orbit; -  Transfer from the Earth to the Mars; -  Jettison of SMS and injection of transfer module onto 2- or 3-day orbit around the Mars; -  Operations of the transfer module on the ASM orbit as a satellite-retransmitter;

  9. Total Power 2.8 кWPower Thruster 1.5 кWThrust 12.8 G Puls 2000 Sec

  10. Graphs with different puls

  11. MAX PULS Isp

  12. Total power about Mars 0.8 kWPower for thruster about Mars 0.45 kWThrust 3.6 gPuls Isp=2600 sec

  13. ElectroJet Propulsion System (EJPS) . EJPS consists of: · Engine D-55 (2,5 kg*2); · The engine gas distribution systems (2 kg); · Fuel tank (5,0 kg); · Working gas Хе (43 kg); · High-voltage power source (2 kg); · Structure (1.0 kg).

  14. Тhrust, mN Puls, sec Power, W Voltage, V Current, А 97,3 1980 1796 450 3,99 91,4 1860 1608 400 4,02 85,9 1750 1420 350 4,06 70,4 1763 1323 450 2,94 67,8 1693 1208 400 3,02 63,5 1590 1068 350 3,05 59,1 1481 924 00 3,08 48,2 1567 923 450 2,05 45,5 1474 828 400 2,07 42,2 1385 732 350 2,09 39,8 1244 636 300 2,12 THE PARAMETERS THRUSTER

  15. Configuration of MMS

  16. Name Mass, Kg Power consumption, W AVIONICS: 5.8 63.5 CU of SSC-SSM 1.3 6 Star sensor 0.15*2 4 Solar sensor 0.15 3 Wheels 0.25*4 1,5 Angular speed sensor 0.09*4 4.0 GPS receiver with antenna 0.54 4.5 S-band receiver 0.5 0.5 X-band transmitter with antenna 0.7 30.0 Camera 0.1 3.0 UHF radiosystem with antenna 0.3 8.0 Cables 0.8 POWER SUPPLY SYSTEM: 11.0 ESB (Li-ion, 8 А*H) 1.0 Photoelectric batteries with radiator (amorphous silicon ), 1800 W 10.0 ELECTROJET PROPULSION SYSTEM: 58.0 1800 Dry mass of electric engine (including high-voltage power source) 15.0 Plasma-forming gas (Xe) 43.0 STRUCTURE: 6.0 2.0 Frame with thermoisolation 4.1 Adapter for SMS separation 0.9 Engines and pyrotechnics 1.0 2.0 MMS (or 2 MMS) 18 (or 36) Mass without propellant (Хе) 55.8 (73.8) Total 98.8 (116.8) 1800 MARS MET-NET SPACECRAFT

  17. Radio system Frequency band UHF: 401,5 MHz – TXT 437 MHz – RX TXT Power – 1 W Antenna-Ground Plane  800 и G 0 dB, linear polarization

  18. Ground stations Bear Lakes station, Antenna П-1500, Transmitter- 10 kW Tarusa station, Antenna 4*6m, Transmitter- 100 W

  19. Radio system of bus I. Radio relay ( Bus-MMS) Receiver 401,5 MHz Transmitter 437 MHz Output power 5w Omnidirectional antenna, circular polarization,Gy  0,5 II. Bus-Earth Х -band Transmitter 8,4GH Receiver 7,8 GH Output power10W Antennas:parabolic,diameter 0,4m, low-gain, circular polarization,antenna diagram +- 40deg,G=7dB, low-gain for back-side semi-sphere G=0 db

  20. SPACECRAFT CONFIGURATION WITH 1 MMS ON KOSMOS-3M

  21. SPACECRAFT CONFIGURATION WITH 2 SPACECRAFT ON KOSMOS-3M

  22. SPACECRAFT WITH 1 MMS ON ORBIT

  23. SPACECRAFT WITH 2 MMS ON ORBIT

  24. Met-Net Complete Units ofSmall Station (CUSS) For Mars Mission «Met-Net»

  25. CU Small Station have next system: 1 . Control system (CEU, DC/DC, Automatic control) 2. Power system ( Battery, RTG, Solar panels, DC/DC) 3.   Thermal system (Radiator, Evaporator) 4.   Radio system UHF (Transmitter, receiver, antenna) 5.   Control system Reduction gear (Motor, gear) 6.   Control system of pyro units(8 pcs) 7.    System of Fail/Safe Control (Switches, ADC) 8. Interface Units (Switches, ports, drivers) 9. Pay load ( Meteo, Nephelometer, PanCam, DesCam, Accelerometer-Seismometer ) The SystemsCUSS

  26. Block - scheme of the Small Station

  27. Small Station connectors

  28. Central unit of the Small Station • Central unit of the Small Station consists of : • 1.      processor • 2.      scheme control of processor • 3. Bus Interface Unit • 4. Chip-select Unit • 5. Clock & Power Management Unit • 6. Asynchronous Serial I/O • 7. Synchronous Serial I/O • 8.Timer/counters Unit • 9. I/O Ports • 10. Interrupts control unit • 12. memory • 13.     automatic • 14.     pyro schemes • 15.     telemetry schemes • 16.     command scheme • 17.     control units scheme • 18. motor control scheme • 19.  ADC • 20.  DC/DC

  29. Processor*:80С32 Processor clock : 24МГц Low clock processor[1][2]:1 МГц RAM [3]: 128K х 8 FLASH:128Mх 8 Serial portsRS232: 4 Telemetry data clock 64kBaud serial port clock :115 kBaud [1]Clock my be changed . [2] CPU clock may be selected by software. The range is 1 MHz to 24 MHz by step of 2. Special ports (for relay channels) 2 Interruptlevel:8 Bus Interface: 8 bits Logical channel : 32 Analog/Digital channel: 16 Power switch * 8 Pyro switch*8 Power consumption2W standby mode 0.1W Input Voltage 5to8V DC/DC output +5±0,25V * Reserved. Main parameters of CEU Small Station.

  30. FLASH FPGA 1.1 RAM RAM 80C32 FLASH + 5V1 RAM Generator ROM RAM С К +5В FPGA 1.2 FLASH RAM ADSP 2191 + 5V2 RAM Generator ROM ADC + SWITH Block –scheme of CEU

  31. CEU SOFTWARE • Software includes : • Code initialization; • Cyclogram ; • Unit tasks; • Driver tasks.

  32. Tasks : Control test Cyclogram 2a. Absolute cyclogram 2b. Local cyclogram 3Task for transmitter: -        datarelayfrom the memory -       direct device data relays -    combination of the both 4. Task reload software Memory control task 6. ADC control task Telemetry task Motor task Energy distribution switches (ON/OFF) task Control task of the charge/discharge battery Control of normal mode unit operation Control task serviceabilityService tasks Driver tasks: Initialization driver Serial port driver Transmitter driver Receiver driver Pyro driver Power switch driver Motor driver Small Station Software

  33. Includes : Current generator –2pcs Block of diodes Solar panel

  34. Parameters Value Output power 3W Voltage generator 9V Temperature range -80 - +50 degrees Mass 70 g Active area of the solar panel 0,0225 m2 Basic parameters of the Solar Panel

  35. RTG • 1-box • 2-thermal isolation • 3-thermal box • 4-separator • 5-fastener • 6-fastener • 7-thermoelectric battery • 8-connector • 9-nuts

  36. Battery • Includes: • Li-ionelements –4 pcs • Scheme of charge/discharge control

  37. Parameter Value Capacity 2 х 0,875 А*H. Output voltage 5,3to 8,3V Temperature range -20 - +50 degrees Mass 120g Basic parameters of the Battery

  38. Pressure sensor (PS) • Includes : • Sensor • Capacity value to digital converter • Microprocessor • DC/DC converter

  39. Parameter Value Range of value 0- 10mBar Sensitivity 0,01 mBar Sample rate < 1 .0 Hz The interface RS232 Baud rate of RS232 115 kBaud Power consumption 0,2 W Temperature range -55 до +50 degrees Mass 65g Dimensions Ø60х35 mm Input voltage 5-8 В Basic parameters of the Pressure Sensor.

  40. Wind sensor (WS) • Includes: • Sensor • Current-to-digital converter • Microprocessor • DC/DC converter

  41. Parameter Value Range +\- 50m\s Sensitivity 0,1 m\s Sample rate < 10 Hz Interface RS232 Baud rate of RS232 115 kBaud Power consumption 0,1W Temperature range -70 до +50 degrees Mass 82g Dimensions Ø55х50mm Input voltage 5-8 V Basic parameters of the Wind Sensor

  42. PANCAM • Includes: • Optical block • ADC • Motor • Microprocessor • DC/DC converter

  43. Parameter Value Angle resolution 4minute of arc 50µs-500 ms Dynamic range of image sensor 1000 Dynamic range of exposition sharp focus range 0,5 toinfinity Sample rate 0.1Hz Field of view 50х360degrees Color number (RGB) 3 Dimensions of the sensor 1280х1024 pix Interface RS232 Baud rate of the RS232 2kBaud Power consumption 2W Temperature range -55 to +50 degrees Mass 150 g Input power voltage 4.5-9V Basic parameters of the PanCam

  44. DesCam • Includes : • Optical block • ADC • Microprocessor • DC/DC converter

  45. Parameter Value Angle resolution 4minute of arc 50µs-500 ms Dynamics range of the image sensor 1000 Dynamic range of the exposition Sharp focus range from0.5m toinfinity Sample rate 2Hz Field of view 75х63degrees Color number (RGB) 3 Dimension of the sensor 1280х1024 pix Interface RS232 Baud rate of the RS232 2 kBaud Power consumption 1.5W Temperature range -55 to +50 degrees Mass 40 g Input power voltage 4.5-9V Basic parameters of the DesCam

  46. Accelerometer • Includes: • Sensor • Capacity value to digital converter • Microprocessor • DC/DC converter

  47. Parameter Value Range +\- 200 m\s2 Sensitivity 0.00001 m\s2 Sample rate < 10 Hz Interface RS232 Baud rate of the RS232 115 kBaud Power consumption 0,25W Temperature range -50 до +50 degrees Mass 250g Dimensions 90х60x40mm Input power voltage 5-8 V Basic parameters of the Accelerometer

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