Post on 12-Jan-2016
description
FMI – IKI, NPOLCooperation in space science
(Planetary science)V. Linkin
Helsinki 2007, January
- meteo- climate - internal structure (seismic)- imaging- aerosols
-
OverviewMars 96
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
- 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
Met-Net
Principal science points
MARS PROJECT MET-NET
SPACE RESEARCH INSTITUTE RASFINNISH METEOROLOGICAL INSTITUTEBABAKIN SCIENCE & RESEARCH CENTER
Independent launch of two (or one) landing module by KOSMOS-3M
rocket with electric jet propulsion system (EJPS)
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 andmanufacture
Landing modules(mechanical system of atmospheric entry and landing)
LA Already develop Onlymanufacture
Meteostation with onboard service systems and scientific nstruments
IKI Already developed Onlymanufacture
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
The general scheme of the expedition Met-Net
The general parameters mission Met-Net Total mass spacecraft ~100 kgPL mass (descend module with SMS) 18 kgMass of Xe 43 kgNominal power of Solar bat 1.4-1.8 kWSurface 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 mNResource EJPS 6000 hours
Duration of mission 11-13 month Duration of injection into Mars-bound trajectory ~ 90 до 180 daysDuration of brake ~1-2 monthHeight 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 mAfter deployment of solar panels the dimensions are 0.5x18x1.0 m.
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;
Total Power 2.8 кWPower Thruster 1.5 кWThrust 12.8 G
Puls 2000 Sec
1 2 3 4 5 6 7 8 9 10 11 12A cc e le ra tio n tim e , m o n th
5 5
6 0
6 5
7 0
7 5
Fin
al S
C m
ass,
kg
d ire c t f lig h t w ith free p e rig e e
d ire c t f lig h t w ith f ix e d p e rig e e
M o o n sw in g b y w ith fre e p e rig ee
Graphs with different puls
1 2 3 4 5 6 7 8 9 10 11 12A cc e le ra tio n tim e , m o n th
5 0
5 5
6 0
6 5
7 0
7 5
Fin
al S
C m
ass,
kg
T = 7 G , Isp = 1 6 0 0 s , P o w er = 1 k W
T = 8 G , Isp = 2 0 0 0 s , P o w er = 1 .4 k W
T = 1 2 .8 G , Isp = 2 0 0 0 s , P o w er = 2 .2 5 k W
T = 1 6 G , Isp = 2 0 0 0 s , P o w er = 2 .8 k W
MAX PULS Isp
Total power about Mars 0.8 kWPower for thruster about Mars 0.45 kW
Thrust 3.6 gPuls Isp=2600 sec
1 2 3 4 5 6 7 8 9 10 11 12A cce le ra tio n tim e , m o n th
0.87
0.88
0.89
0.9
0.91
0.92
m/m
0
h = 6 0 0 k m , T = 2 d
h = 6 0 0 k m , T = 3 d
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).
THE PARAMETERS THRUSTER
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
Configuration of MMS
MARS MET-NET SPACECRAFT
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
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
Ground stations
Bear Lakes station, Antenna П-1500, Transmitter-
10 kW
Tarusa station, Antenna 4*6m, Transmitter- 100 W
Radio system of bus
I. Radio relay ( Bus-MMS)Receiver 401,5 MHzTransmitter 437 MHzOutput power 5wOmnidirectional antenna, circular polarization, Gy 0,5
II. Bus-Earth Х -bandTransmitter 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
SPACECRAFT CONFIGURATION WITH 1 MMS ON KOSMOS-3M
SPACECRAFT CONFIGURATION WITH 2 SPACECRAFT ON KOSMOS-3M
SPACECRAFT WITH 1 MMS ON ORBIT
SPACECRAFT WITH 2 MMS ON ORBIT
Met-Net
Complete Units of Small Station (CUSS)
For
Mars Mission «Met-Net»
The Systems CUSS
• 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 )
Block - scheme of the Small Station
Ин
в.№
под
л.
По
дп.
и д
ата
Вза
м.
ин
в.№
Ин
в.
№ д
уб
л.
По
дп.
и д
ата
Central Unit
PANCAM
Antenn
temperatursensor 1
Temperatursensor 2
Temperatursensor 3
Humiditysensor 1
Wind sensor
Meteo boom
25
NDSP25P
ХП2 Х2
Х710
MN - 1.017.000.00 Э6
37
3
ХП4
ХТ19
437
37 ХП3
1
Pyro 1 Pyro 2 Pyro 3 Pyro 4 Pyro 5
1ЕТ 2ЕТ 3ЕТ 4ЕТ 5ЕТ4 4 4 4 4
Solerpanel
Р2
237
4 Х6
Landing Unit
10
МР
19
МР
Х8 Х9
Surface boom
DESCAM Temperaturesensor 4
Р1
temperatursensor 5
Humiditysensor 2
Pyro 8
ДатаИзм Лист № докум. Подп.
Н. контр.
Разраб.
Провер.
Т. контр.
Масса
Утверд.
Лит. Масштаб
Лист 1 Листов 1
Small Station
Линкин В.
MN - 1.017.000.00 Э6
Версия 725.04.2003
Андреев о.
Липатов А.
Хлюстова Л.
CINCH9833/9828
Pyro 6
"+" "+" "-""-"
9
NDSP9P
ХР
CINCH9833/9828
CINCH9833/9828
CINCH9833/9828
Small Station connectors
ДатаИзм Лист № докум. Подп.
Н. контр.
Разраб.
Провер.
Т. контр.
Масса
Утверд.
Лит. Масштаб
Лист 1 Листов 1
Инв
.№ п
одл
.П
одп.
и д
ата
Вза
м.
инв.
№И
нв.
№ д
убл
.П
одп.
и д
ата
XP75Battery1
PSBprocessor
RTG
Battery2 5
XP8
NDSP5P
NDSP5P
PSBradiosystem
Motorboom
КLine
1
2
"+"U_DVG
0V
temperatur Fram
КLine
7
8
"+"TD6
0V
9
100V
"+"TD7
15 NDSP15P
NDSP9P
XP1
XP5
XP2
5
XP9NDSP5P
X2
P237
XP437 3
9
99
NDSP9P
NDSP9P
XD
XP
P1
CINCH9833 / 9828
37
temperatur RTG
7,8,9,10
Pyro Boom 2
Андреев О.
Липатов А.
Хлюстова Л.
Линкин В.
MN - 1.017.000.00. Э4
MN - 1.017.000.00. Э4
Марсианская малая станцияММС
Схема электрических соединений
Версия 325.04.2003.
5
XP6NDSP5P
1,2
37
XP3CINCH
9833 / 9828
12
X710Pyro1 Pyro2 Pyro3 Pyro4 Pyro5
1ET 2ET 3ET 4ET 5ET4 4 4 4 4
Solerbattery
4 X6
25NDSP25P
Sensortemperatur1
PSBcontroller for
Accelerometr &Wind &Pressure &
sensoraccelerometr
NDSP5P
NDSP5PXP10
NDSP5P
К Line
1
2
3
4
+5V
0 изм.
Uизм.
0V
SensorPressure
XP11
XP125
5
5
Sensorwind
Sensortemperatur2
Sensortemperatur3
SensorHumidity
ХNPSBconjtroller
lidar
PANCAM
CINCH9833 / 9828
CINCH9833 / 9828
4
Block of descent
10
МР
19
МР
X8 X9
Boom of surface
DESCAMSensor
temperaturof descent
Sensortemperaturof surface
Sensortemperaturofsurface Pyro Boom
XT19
PSBcontrollerpancam &Descam
LIDAR
XP139 NDSP9P
Anten
К line
1
2
3
OPT1
OPT2
OPT3
U темп5
К Line
1
2
3
4
"+"7V2
0V
"+"7V2
0V
5 Reserve
К line
1
2
3
4
"+"7V1
0V
"+"7V1
0V
5 Reserve
К Line
1
2
3
4
"+"RITEG
0V
"+"RITEG
0V
5 Reserv
КLine
1
2
3
4
"+"ЕТ7.2
"-"ЕТ7.2
5
"+"ЕТ7.1
"-"ЕТ7.1
Reserv
К Line
1
2
3
4
"+"U_AKS
0V
RXD_2
TXD_2
5 0V
К Line
1
2
3
4
"+"U_RPR
0V
5
6
7
8
9
"+"URPER
0V
RC2_1
RC1_0
RC3 SYNC
SSR_0
11..15 Reserv
SSR_1
10 0V
К Line
1
20
Заряд АБ2
TXD_4
Заряд АБ1
3
4
5
6
7
8
9 Контр обт ВР1
RXD_4
BL_BP1
0V
"+"TD5.2
"-"TD5.1
"+"U_DW
"+"ET8.1
"+"ET8.2
10 Контр обт ВР2
12+SwithON-T
13
14
32
2
22
Сброс21
"-"TD5.2
23
"+"TD5.1
24
25 Реверс двиг.
27
"-"ET8.126
"-"ET8.2
28 0V
29 0V
+Swith ON11
-Swith OFF30
BL_BP231
Контр "+"6,5V
0V
15..19
33..37
Reserv
Reserv
К Line
1
2
3
4
"+"U_VK
0V
5
6
7
8
9
"+"U_NEF
0V
RXD_3
TXD_3
RXD_1
TXD_1
0V
К Line
1
2
3
4
+7V
-7V
5
6
0V
RXD_4
TXD_4
+3V
RXD_1
TXD_1
К Line
1
2
3
4
+7V
-7V
5
6
0V
+3V
RXD_1
TXD_1
К Line
1
2
3
4
5
0V
"+"U_NEF
0V
К line
1
2
3
4
5
6
7
8
11,12
13
14
15
16
17
18
19
20
23..25 Reserv
reserv
"+"TD1.1
"+"TD1.2
"-"TD1.1
"-"TD1.2
"+"TD2.1
"+"TD2.2
"-"TD2.1
"-"TD2.2
"+"TD3.1
"+"TD3.2
"-"TD3.1
"-"TD3.2
"+"H1.1
"+"H1.2
"-"H1.1
"-"H1.2
9
21
10
22
"+"V1.2
"-"V1.2
"+"V1.1
"-"V1.1
К Line
1
20
3
4
5
6
7
8
9
"+"ET3.1
"+"ET2.2
10
12
+swith ON
13
14
32
2
22
21
23
24
25
27
"-"ET3.1
26
"-"ET2.2
28
29
0V
11
30
"+"BF1
31 0V
reserv
reserv
reserv
"+"ET1.1
"-"ET1.1
"+"ET1.2
"-"ET1.2
"+"ET2.1
"-"ET2.1
"+"ET3.2
"-"ET3.2
15
33
"+"ET4.1
"-"ET4.1
16
34
17
35
18
36
19
37
"+"ET4.2
"-"ET4.2
"+"ET6.1
"-"ET6.1
"+"ET6.2
"-"ET6.2
"+"ET5.1
"-"ET5.1
"+"ET5.2
"-"ET5.2
+Swith ON
-Swith OFF
-Swith OFF
"-"TМ
"+"TМ
"+"BF2
SensorHumidity
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
Main parameters of CEU Small Station.
• Processor*: 80С32
• Processor clock : 24МГц
• Low clock processor[1] [2]: 1 МГц
• RAM [3] : 128K х 8
• FLASH: 128Mх 8
• Serial ports RS232: 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
• Interrupt level: 8
• Bus Interface : 8 bits
• Logical channel : 32
• Analog/Digital channel: 16
• Power switch * 8
• Pyro switch* 8
• Power consumption 2 W
• standby mode 0.1W
• Input Voltage 5 to 8 V
• DC/DC output +5±0,25 V
• •
• * Reserved.
Block –scheme of CEU
+5В
+ 5V2
+ 5V1
ADC +SWITH
ADSP2191
80C32
FLASH
RAM
RAM
FPGA 1.1
Generator
ROM
FPGA 1.2
Generator
ROM
FLASH
RAM
RAM
FLASH
RAM
RAM
С
К
CEU SOFTWARE
• Software includes :
1. Code initialization;
2. Cyclogram ;
3. Unit tasks;
4. Driver tasks.
Small Station Software
• Tasks :
1. Control test
2. Cyclogram
2a. Absolute cyclogram
2b. Local cyclogram
3 Task for transmitter:
• - data relay from the memory
• - direct device data relays
• - combination of the both
4. Task reload software
5. Memory control task
6. ADC control task
10 Telemetry task
11 Motor task
12 Energy distribution switches (ON/OFF) task
13 Control task of the charge/discharge battery
14 Control of normal mode unit operation
15 Control task serviceabilityService tasks
• Driver tasks:
• Initialization driver
• Serial port driver
• Transmitter driver
• Receiver driver
• Pyro driver
• Power switch driver
• Motor driver
Solar panel
• Includes :1. Current generator –2pcs
2. Block of diodes
Basic parameters of the Solar Panel
Parameters
Value
Output power3 W
Voltage generator 9 V
Temperature range -80 - +50 degrees
Mass 70 g
Active area of the solar panel 0,0225 m2
RTG
• 1-box
• 2-thermal isolation
• 3-thermal box
• 4-separator
• 5-fastener
• 6-fastener
• 7-thermoelectric battery
• 8-connector
• 9-nuts
Battery
• Includes:
• Li-ion elements –4 pcs
• Scheme of charge/discharge control
Basic parameters of the Battery
Parameter
Value
Capacity2 х 0,875
А*H.
Output voltage 5,3 to 8,3 V
Temperature range -20 - +50 degrees
Mass 120 g
Pressure sensor (PS)
• Includes :
1. Sensor
2. Capacity value to digital converter
3. Microprocessor
4. DC/DC converter
Basic parameters of the Pressure Sensor.
Parameter Value
Range of value 0- 10 mBar
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
Wind sensor (WS)
• Includes :
1. Sensor
2. Current-to-digital converter
3. Microprocessor
4. DC/DC converter
Basic parameters of the Wind Sensor
Parameter Value
Range +\- 50m\s
Sensitivity 0,1 m\s
Sample rate < 10 Hz
Interface RS232
Baud rate of RS232 115 kBaud
Power consumption 0,1 W
Temperature range -70 до +50 degrees
Mass 82 g
Dimensions Ø55х50 mm
Input voltage 5-8 V
PANCAM
• Includes:1. Optical block
2. ADC
3. Motor
4. Microprocessor
5. DC/DC converter
Basic parameters of the PanCam
Parameter ValueAngle resolution 4 minute of arc
Dynamic range of exposition 50µs-500 ms
Dynamic range of image sensor 1000
sharp focus range 0,5 to infinity
Sample rate 0.1 Hz
Field of view 50х360 degrees
Color number (RGB) 3
Dimensions of the sensor 1280х1024 pix
Interface RS232
Baud rate of the RS232 2kBaud
Power consumption 2 W
Temperature range -55 to +50 degrees
Mass 150 g
Input power voltage 4.5-9 V
DesCam
• Includes :1. Optical block
2. ADC
3. Microprocessor
4. DC/DC converter
Basic parameters of the DesCam
Parameter ValueAngle resolution 4 minute of arc
Dynamic range of the exposition 50µs-500 ms
Dynamics range of the image sensor 1000
Sharp focus range from 0.5m to infinity
Sample rate 2 Hz
Field of view 75х63 degrees
Color number (RGB) 3
Dimension of the sensor 1280х1024 pix
Interface RS232
Baud rate of the RS232 2 kBaud
Power consumption 1.5 W
Temperature range -55 to +50 degrees
Mass 40 g
Input power voltage 4.5-9 V
Accelerometer
• Includes:
1. Sensor
2. Capacity value to digital converter
3. Microprocessor
4. DC/DC converter
Basic parameters of the Accelerometer
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 0,25 W
Temperature range -50 до +50 degrees
Mass 250 g
Dimensions 90х60x40 mm
Input power voltage 5-8 V
Nephelometer
• Includes :1. Optical block
2. Acquisition scheme
3. TEC controllers
4. Microprocessor
5. DC/DC converter
Parameter Value
Ranges range1 (day) range 2 (night) range 3 (humidity)
from 5m to 1000mfrom 5 m to 10000mfrom 5m to 300 m
Sensitivity range 1 range 2 range 3
> 2*106 m-3 > 106 m-3 > 1014 m-3
Sample rate range 1 range 2 range 3
> 1 .0 Hz > 0.1 Hz > 0.01 Hz
Interface RS232
Baud rate of the RS232 115 kBaud
Power consumption 4 W
Temperature range -55 to +50 degrees
Mass 150 g
Input power voltage 5-8 V
Basic parameters of the Nephelometer
UHF Radio system
• Includes :
1. Antenna
2. Receiver
3. Transmitter
4. DC/DC converter
Parameter ValueFrequency :TransmitterReceiver
401,5 MHz437,1 MHz
Modulation: Transmitter Receiver
Phase-modulatedFrequency Modulated(deviation +\-4,3 kHz)
Power consumption: Transmitter (At Output power) Receiver
4 W (1W) 0,3 W
Thermal noise of the receiver 300К
Data relay transmitter rateCommand relay receiver rate
256 kbits\sec 40 bits\sec
Sensitivity of the receiver -144 dB
Temperature range -55 to +50 degrees
Mass 120 g
Input power voltage 5-8 V
Basic parameters of the UHF
EDL
Packed for Launch
Station with Main Decelerator Inflated prior to Entry
Station with Auxiliary Decelerator Inflated
Main Decelerator Released
Station Prior to Landing
ROBOTIC MARS MISSIONSROBOTIC MARS MISSIONS
MET-NET (MICRO-LANDER) MARS MISSIONMET-NET (MICRO-LANDER) MARS MISSION
LANDER CONFIGURATION
Adapter
Met-Net Lander
Launch configuration Entry configuration
Main IBD
Additional IBD
Body
ROBOTIC MARS MISSIONSROBOTIC MARS MISSIONS
MET-NET (MICRO-LANDER) MARS MISSIONMET-NET (MICRO-LANDER) MARS MISSION
LANDER CONFIGURATION
Pre-landing configuration Landing configuration
Additional IBD
Body
Main IBD (Entry) Assembly
Body
ROBOTIC MARS MISSIONSROBOTIC MARS MISSIONS
MET-NET (MICRO-LANDER) MARS MISSIONMET-NET (MICRO-LANDER) MARS MISSION
DESCENT PROFILE
Main IBD deployment.Entry
Additional IBD deployment
Braking by Additional IBD
Science mission.On-surface operations
Landing event
ROBOTIC MARS MISSIONSROBOTIC MARS MISSIONS
MET-NET (MICRO-LANDER) MARS MISSIONMET-NET (MICRO-LANDER) MARS MISSION
TESTSAerodynamic
Soil penetration
Thermal
Hardware