fmi – iki, npol cooperation in space science (planetary science) v. linkin

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



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


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




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


Power consumption 4 W


Mass 150 g


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


Mass 120 g


Basic parameters of the UHF

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



LANDER CONFIGURATION

Pre-landing configuration Landing configuration

Additional IBD

Body

Main IBD (Entry) Assembly

Body



DESCENT PROFILE

Main IBD deployment.Entry

Additional IBD deployment

Braking by Additional IBD

Science mission.On-surface operations

Landing event



TESTSAerodynamic

Soil penetration

Thermal

Hardware

fmi – iki, npol cooperation in space science (planetary science) v. linkin

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