Tillbaka till svensk
rymdhistoria Sven Grahn
|
Fact/Factor |
Viking |
Freja |
Astrid-1 |
Astrid-2 |
Odin |
SMART-1 |
|
Mission |
Space Plasma Physics |
Space Plasma Physics |
Space Plasma Physics |
Space Plasma Physics |
Astronomy/Aeronomy |
EP test flight to the Moon + lunar surface studies from
orbit |
|
Proposed price Real cost/price |
Hard to compute due to depreciation etc: ~ 40 M$ (1995
ec) |
17 M$ (1995 ec) 19 M$ (1995 ec) |
7 MSEK (1995 ec) 9 MSEK (1995 ec) |
16 MSEK (1995 ec) 23 MSEK (1995 ec) |
35 M$ (1995 ec) 40? M$ (1995 ec) |
33 Meuro - |
|
Planned schedule Real schedule |
5 years (A+ B + C/D) 7 years (A + B + C/D) |
4 years (A + B+ C/D) 5 years (A+ B + C/D) |
1 year (A + B + C/D) 1 year (A + B + C/D) |
2 years (A + B + C/D) 4 years (A + B + C/D) |
3 years (C/D) 6 years (C/D) |
3 years (C/D) |
|
Contract type |
Cost plus incentive fee |
Cost-reimbursement |
Cost-reimbursement |
Cost plus incentive fee |
Cost-reimbursement |
Cost plus incentive fee |
|
Financing |
·
SNSB's budget ·
In-kind contributions from France, Canada, Germany,
Denmark |
·
SNSB's budget (~50%) ·
The Wallenberg Foundation
(~20%) ·
Cash from Germany (~20%) ·
SSC investment (10%) ·
In-kind from Germany ·
In-kind from Canada |
·
SSC investment (80%) ·
SNSB's budget (20%)
|
·
SNSB's budget |
·
SNSB's budget (~60%) ·
Cash and in-kind from France (~15%) ·
Cash and in-kind from Canada (~10%) ·
The Wallenberg Foundation
(~10%) ·
Cash and in-kind from Finland (~5%) |
·
ESA's Science budget ·
ESA's technology program ·
Swedish industrial “underreturn” |
|
System specification: ·
Driving factors ·
“Hardness of customer requirements” |
·
Apogee, EMC, data rate, S/C mass, L/V I/F ·
Apogee must not drop below 10000 km was a hard requirement. EMC
crucial. |
·
Apogee, EMC, data rate, S/C mass, L/V I/F ·
EMC crucial to mission science value. |
·
L/V I/F, Freja re-use, ENA instrument
field-of-view ·
ENA instrument field of view crucial |
·
L/V I/F, E-field boom system, axial magnetom. boom, experiment
mass, G/S size ·
Wire-boom length crucial |
·
Attitude control accuracy, Radiometer sensitivity, "must fit
Pegasus" ·
Scientific value of the project highly dependent on meeting
certain performance goals |
·
Electric propulsion, L/V I/F, FDIR, Science payload
mass. ·
Science P/L must stay above 15 kg |
|
Level of new developments |
·
Mission control centre |
·
On-board processor and its software was a new
development ·
EGSE and control centre large a new
development ·
Sun sensor |
·
Patch antennas ·
Sun sensor ·
Solar panel hinges ·
Spin rocket |
·
Axial boom system ·
Wire boom system ·
New main avionics unit |
·
ACS computer and software ·
Internal comms processor (OTS) ·
Cold box ·
Correlator ASIC ·
Most microwave units in P/L ·
Antenna reflectors and support |
·
Brand-new avionics ·
Onboard software ·
CAN data bus ·
Power system |
|
Heritage from previous projects |
·
Based on the Boeing S3-3 plasma physics satellite.
·
TM/TC system modification of standard Saab
unit. |
·
EMC specifications, wire boom system, magnetic torquers from
Viking directly. ·
Stiff boom design from AMPTE ·
Avionics based on sounding rocket
telemetry |
·
Freja avionics, onboard software and ground
station. ·
Separation system derived from sounding
rocket |
·
Separation system, patch antennas, and spin rocket from
Astrid-1 |
·
Freja avionics, onboard software and ground
station. |
·
Odin control laws |
|
Model philosophy |
·
Protoflight on system level |
·
Protoflight + BTM on system level ·
Full set of models for new developments ·
Flight spares for key "off-the-shelf"
units |
·
Protoflight on system level ·
EM for new SU |
·
Protoflight on system level ·
Breadboard for new SU |
·
Protoflight + BTM on system level ·
Full set of models for new developments ·
Flight spares for key "off-the-shelf"
units |
·
BTM, STM, FM on system level ·
TEM, EM, QM, FM for new avionics |
|
Test philosophy |
·
Static load test ·
Acceptance, Qual vibration, sine/random ·
Acoustic noise test on
satellite level ·
Solar vacuum sim. ·
Magnetic survey ·
System level EMC ·
G/S compat. test |
·
Static load test ·
Acceptance, Qual vibration, sine/random ·
Acoustic noise test on satellite level ·
Solar vacuum sim. ·
Magnetic survey ·
System level EMC ·
G/S compat. test |
·
Acceptance, Qual vibration, sine/random ·
Solar vacuum sim. |
·
Acceptance, Qual vibration, sine/random ·
Solar vacuum sim. ·
Magnetic survey ·
System level EMC ·
G/S compat. test |
·
Static load test ·
Acceptance, Qual vibration, sine/random ·
Solar vacuum sim. ·
Magnetic survey ·
System level EMC ·
G/S compat. test |
·
Static load test on STM ·
Acceptance, Qual vibration, sine/random ·
Solar vacuum sim. ·
Magnetic survey ·
System level EMC ·
G/S compat. Test (suitcase) |
|
Designation, Cat.nr |
1986-19B, 16614 |
1992-64A, 22161 |
1995-02B,
23464 |
1998-72B,
25568 |
|
|
|
Launch date |
22 February 1986 |
6 October 1992 |
24 January 1995 |
10 December 1998 |
|
|
|
Technical data | ||||||
|
Orbit |
H = 822-13500 km, i=98.7 |
H = 600-1756 km, i = 63 |
H = 1000 km, i = 83 |
H = 1000 km, i = 83 |
H = 605 km, i = 97.73 |
GTO initially-> lunar orbit |
|
Launch vehicle |
Ariane-1 piggyback with SPOT-1 |
CZ-2C piggyback with FSW-1 |
Kosmos-3M piggyback w Nadezhda |
Kosmos-3M piggyback with Nadezhda |
Start-1 |
Ariane-5 piggyback w telecom sat |
|
Dry mass |
286 kg |
214 kg |
27 kg |
30 kg |
242 kg |
262 kg |
|
Payload mass |
90 kg |
73.1 kg |
4.36 kg |
9 kg |
83 kg |
15 kg (science)
44.2 kg (total) |
|
Payload Mass fraction |
31 % |
34 % |
16 % |
30 % |
34 % |
17 % |
|
Size |
Æ1.8 m |
Æ2.2 m, 0.5 m high |
0.45 ´ 0.45 ´ 0.29 m stowed |
0.45 ´ 0.45 ´ 0.30 m main part
of stowed S/C |
0.78 ´ 0.78 ´ 2.0 m stowed |
1 m cube, 14 m
across solar array |
|
Structure design |
·
Al central tube, ·
Sheet metal P/L deck |
·
Mg central tube, ·
4 honeycomb webs, ·
2 honeycomb decks ·
Fixed solar array |
·
2 honeycomb decks ·
Al corner supports ·
Deployed solar panels |
·
2 honeycomb decks ·
Al corner supports ·
Deployed solar panels |
·
2 honeycomb decks ·
2 honeycomb webs ·
CFRP antenna & support ·
Deployed, fixed solar array |
·
Al sheet-metal central tube ·
Al honeycomb decks ·
Deployed and rotating solar array |
|
Stabilisation |
Spin at 3 rpm |
Spin at 10 rpm |
|
Spin at 9 rpm |
Three-axes |
Three-axes |
|
Attitude control accuracy |
5o? |
5o? |
5o? |
5o? |
·
15 arcsec (Astro) ·
2 arcmin (Aero) |
·
8 arcmin |
|
Attitude determination accuracy |
<0.5o? processing |
<0.5o? processing |
5o? no processing |
<0.5o? processing |
·
15 arcsec (Astro) ·
2 arcmin (Aero) |
·
4 arcmin |
|
Attitude actuators |
Magnetic torque coils Nutation damper |
Magnetic torque coils Nutation damper |
Magnetic torque coils Nutation damper |
Magnetic torque coils Nutation damper |
Reaction wheels Magnetic torque coils |
Reaction wheels Hydrazine thrusters Electric thruster |
|
Attitude sensors |
Sun sensor Magnetometer Horizon-crossing indicator |
Sun sensors Magnetometer Horizon-crossing indicator |
Sun sensor Magnetometer |
Sun sensor Magnetometer Star tracker |
Sun sensors Magnetometer Star tracker |
Sun sensors Star tracker |
|
Solar panel area/power |
2.21 m2, 85 W |
1.63 m2,
149 W |
0.52 m2 42 W |
0.67 m2 90 W |
3.43
m2, 408 W |
1975 W (BOL) |
|
Battery type, Ah, mfg |
Ni-Cd, 12 Ah, Eagle-Picher |
Ni-Cd, 2 ´ 6.3 Ah, SISP |
Ni-Cd 2.3 Ah,
Gates |
NiCd ,1.6 Ah, SAFT |
Ni-Cd, 2 ´ 6.3 Ah, SISP |
Li-ion, 5 ´ 40 Ah, SAFT |
|
Bus voltage, regulation |
28 ± 4 V |
26-29 V |
|
|
|
50 V |
|
Transponder Y/N |
Yes |
No |
No |
No |
No |
Yes |
|
Orbit determination |
Ranging |
Angle tracking |
TLE |
TLE |
SGPS |
Ranging |
|
Downlink fx, MHz |
2208.1629 MHz |
2208.1629 MHz 400.55 MHz |
2208.1629 MHz 400.55 MHz |
2208.1629 MHz |
2208.1629 MHz |
2235.1 MHz 8453 MHz |
|
Downlink RF power |
2 Watts |
2 Watts on S-band 2 watts on UHF |
2 Watts on S-band 2 watts on UHF |
5 Watts |
2 Watts |
5 Watts |
|
Downlink RF modulation |
PM |
PM on S-band FM on UHF |
PM on S-band FM on UHF |
BPSK |
PM |
PM |
|
Downlink data rate |
55 kbps, Viterbi |
500 kbps |
131 kbps, S-band 8 kbps, UHF |
128 kbps , Viterbi |
720 kbps, Viterbi |
60 kbps, Reed-Solomon, Viterbi |
|
Uplink fx, MHz |
2033.35 MHz |
449.95 MHz |
449.95 MHz |
2033.35 MHz |
2033.35 MHz |
2058.1546 MHz |
|
Uplink Rx sensitivity dBm |
|
|
|
-100 dBm |
|
-125 dBm |
|
Uplink data rate |
1 kbps |
1.2 kbps |
1.2 kbps |
4.8 kbps |
10.4 kbps |
2 kbps |
|
Uplink modulation |
PCM(NRZ)/PSK/PM |
FSK, Bi-Æ |
FSK, Bi-Æ |
FSK, Bi-Æ |
PM, 1 MHz subcarrier |
PSK on 16 kHz PM subc. |
|
Thermal control design |
MLI, paint, louvers and heaters at
battery |
MLI, paint, and heaters at battery |
MLI, paint, and heaters at battery |
MLI, paint, and heaters at battery |
MLI, paint, and heaters at battery. Stirling cooler for mixer
diode. |
MLI, paint, and heaters |
|
Propulsion: ·
Type: ·
Delta-V: |
Solid STAR 26 B 1.6 km/s ARC 36B1 spin rockets |
Solid STAR 6B + STAR 13A 84 + 344 m/s Chinese spin rockets |
Solid spin rocket 10-20 Ns |
Solid spin rocket 10-20 Ns |
None |
Solar Electric SP-100 3500 m/s Hydrazine ACS |
|
On-board processor |
None |
MHS 80C31, 12 MHz |
MHS 80C31, 12 MHz |
Motorola, 68302, 16 MHz |
MHS 80C31, 12 MHz Motorola, 68302, 16 MHz Saab Ericsson Space THOR |
TEMIC ERC-32 |
|
Real-time OS |
None |
"Round-Robin" |
"Round-Robin" |
"Round-Robin" |
"Round-Robin" |
VxWorks |
|
Language |
None |
PL/M |
PL/M |
C |
PL/M, C, Ada |
C++ |