DTU Satellite Systems and Design Course Space Environment · DTU Satellite Systems and Design...

FH 2001-08-21 Space_Environment.pptSlide # 1

Danish Space Research Institute

Danish Small Satellite Programme

Flemming HansenMScEE, PhDTechnology ManagerDanish Small Satellite ProgrammeDanish Space Research Institute

Phone: 3532 5721E-mail: [email protected]

DTU Satellite Systems and Design CourseSpace Environment

Downloads available from:http://www.dsri.dk/roemer/pub/Cubesat




Overview of the Space Environment

External FactorsResidual atmosphere (up to ≈≈≈≈800 km) - Drag causes orbit decay and reentry

Trapped protons - Degrades materials and electronic components, causes single-event effects in semiconductor components.

Trapped electrons - Degrades materials and electronic components

Solar protons from flares - Degrades materials and electronic components, causes single-event effects in semiconductor components.

Cosmic rays - causes single-event effects in semiconductor components.

Solar radiation: IR, Visible, UV, X-Ray - Degrades materials

Plasma from magnetic substorms - Causes spacecraft charging

Atomic oxygen - Erodes exposed surfaces

Local FactorsOutgassing - Deposits on cold surfaces, e.g. optical apertures.




Earth’s Radiation Belts

Trapped Protons Trapped Electrons




Effects of High-Energy Charged Particles in the Space Environment

• Biological effects (Prolonged exposure of astronauts in MIR and International Space Station)

Shielding, return to ground in case of majorsolar flares

• Degradation of materials and semiconductors by ionization and lattice displacements

Materials selection, radiation hardening, shielding

• Single-Event Upsets in computer memory cellsError Detection and Correction (EDAC), radiation hardening

• Radiation background (Increased noise level in CCD, X-ray and gamma-ray detectors)

Radiation hardening, shielding, select orbit outside or inside radiation belts, disable payload while passing through radiation belts




Calculation of Effects of Ionizing Radiation in the Space Environment

ESA has created a web-facility - SPENVIS that gives the user acess to a number of useful modeling and calculation resources –see SPENVIS opening vindow at right

You have to be a registered user to gain access to the facility.

http://www.spenvis.oma.be/spenvis/




Radiation in Syn-Synchronous Polar Low Earth Orbit

Cubesat in 600 km Sun-Synchronous Dawn-Dusk Orbit Solar Maximum Conditions

4*Pi Total Dose at Center of Aluminium Spheres

1.00E+00

1.00E+01

1.00E+02

1.00E+03

1.00E+04

1.00E+05

1.00E+06

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Absorber Thickness [mm]

To

tal D

ose

[ra

d(S

i)]

Total

Electrons

Bremsstrahlung

Trapped Protons

Solar Flare Protons




Radiation in Molniya Orbit (RØMER)

MON S & B allerina in Molniya Orbit. 2 Years Mission. Solar Max. C onditions. R AAN = 125 deg

4*Pi Total D ose at C enter of Aluminium Spheres

1 .0 0 E+0 2

1 .0 0 E+0 3

1 .0 0 E+0 4

1 .0 0 E+0 5

1 .0 0 E+0 6

1 .0 0 E+0 7

1 .0 0 E+0 8

0 1 2 3 4 5 6 7 8 9 1 0 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 2 0

Absorbe r Thickne ss [mm]

To

tal D

ose

[ra

d(S

i)]

T o ta l

E le c tro n s

Bre msstra h lu n g

T ra p p e d Pro to n s

So la r F la re Pro to n s

Perigee height 600 km

Apogee height 39767 km

Semi-major axis (ideal) 26561.764 km

Eccentricity 0.737286

Inclination 63.4°

Orbit period 11 hours 58 min

Argument of perigee 270°

Right Ascension of Ascending Node 293°




Radiation Environment in Molniya Orbit - Trapped Proton Fluxes Along Orbit

T rapped Proton Fluxes in M olniya O rbit

1.0000E + 00

1.0000E + 01

1.0000E + 02

1.0000E + 03

1.0000E + 04

1.0000E + 05

1.0000E + 06

1.0000E + 07

1.0000E + 08

1.0000E + 09

00 :00 :00

00 :06 :00

00 :12 :00

00 :22 :00

00 :34 :00

00 :46 :00

01 :46 :00

02 :46 :00

03 :46 :00

04 :46 :00

05 :46 :00

06 :46 :00

07 :46 :00

08 :46 :00

09 :46 :00

10 :46 :00

11 :30 :00

11 :42 :00

11 :54 :00

Tim e [h:m :s]

part

icle

s/cm

2 /sec

0.1 M eV

0.5 M eV

1 M eV

2 M eV

3 M eV

4 M eV

5 M eV

6 M eV

8 M eV

10 M eV

12 M eV

15 M eV

17 M eV

20 M eV

25 M eV

30 M eV

35 M eV

40 M eV

45 M eV

50 M eV

60 M eV

70 M eV

80 M eV

90 M V




Trapped Electron Fluxes in Molniya Orbitt

1.00E+00

1.00E+01

1.00E+02

1.00E+03

1.00E+04

1.00E+05

1.00E+06

1.00E+07

1.00E+08

1.00E+09

0:00

0:06

0:12

0:22

0:34

0:46

1:46

2:46

3:46

4:46

5:46

6:46

7:46

8:46

9:46

10:46

11:30

11:42

11:54

Time [h:m:s]

par

ticl

es/c

m2 /s

ec

0.04 MeV

0.1 MeV

0.2 MeV

0.3 MeV

0.4 MeV

0.5 MeV

0.6 MeV

0.7 MeV

0.8 MeV

1 MeV

1.25 MeV

1.5 MeV

1.75 MeV

2 MeV

2.25 MeV

2.5 MeV

2.75 MeV

3 MeV

3.25 MeV

3.5 MeV

3.75 MeV

4 MeV

4.25 MeV

Radiation Environment in Molniya Orbit - Trapped Electron Fluxes Along Orbit




Radiation Environment in Geostationary Transfer Orbit, 28.5° Inclination

RØMER in GTO Orbit. 28.5º Inclination. 2 Years Mission. Solar Max. Conditions. RAAN = 120 deg

4*Pi Total Dose at Center of Aluminium Spheres

1.00E+02

1.00E+03

1.00E+04

1.00E+05

1.00E+06

1.00E+07

1.00E+08

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Absorber Thickness [mm]

To

tal D

ose

[ra

d(S

i)]

Total

Electrons

Bremsstrahlung

Trapped Protons

Solar Flare Protons




Trapped Proton Fluxes in GTO Orbit. 28.5º Inclination

1.00E+00

1.00E+01

1.00E+02

1.00E+03

1.00E+04

1.00E+05

1.00E+06

1.00E+07

1.00E+08

1.00E+09

0:00

0:06

0:12

0:22

0:34

0:46

1:46

2:46

3:46

4:46

5:46

6:46

7:46

8:46

9:46

10:46

11:14

11:26

11:36

Time [h:m:s]

par

ticl

es/c

m2 /s

ec0.1 MeV

0.5 MeV

1 MeV

2 MeV

3 MeV

4 MeV

5 MeV

6 MeV

8 MeV

10 MeV

12 MeV

15 MeV

17 MeV

20 MeV

25 MeV

30 MeV

35 MeV

40 MeV

45 MeV

50 MeV

60 MeV

70 MeV

80 MeV

90 M V

Radiation Environment in Molniya Orbit - Trapped Proton Fluxes Along Orbit




ØRSTED Magnetic Field Model

Today’s Field

Changes Since 1980

South-Atlantic Anomaly (SAA)




Effects of South-Atlantic Anomaly

UoSAT-3 Single-Event Upsets




Radiation Dose Tolerance of Materials




Solar FlaresProtons above 10 MeV

Probability of exceeding a given fluence level for various mission durations

Major Solar Flare




Cosmic Rays

Cosmic ray species vs particle energy Effect of high-energy charged particle in integrated circuit




Single-Event Latch-Up

Two-transistor model for latch-up in CMOS device showing parasitic elements

Latch-up protection circuit for ADSP-2100 digital signal processor




Typical Radiation Tolerences of Rad Hard and COTS Parts

COTS: Commercial Off-the-Shelf (parts)




Linear Energy Transfer (LET) Spectra in Orbit




Single-Event Upset - Linear Energy Transfer Threshold

Radiation Hard

Radiation Soft




Single-Event Upset Protection Methods

DTU Satellite Systems and Design Course Space Environment · DTU Satellite Systems and Design...

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