Abstract: This paper introduces the conceptual design of a real-time Interferometry SAR mission, which is almost impossible in the conventional way for one satellite, with formation flying satellites. 6 SAR satellites forming in a circle at an altitude of 577km can achieve real-time INSAR earth observation in high resolution, diversified, or pervasive way. Ordinarily the satellites keep circular formation and make Digital Elevation Map (DEM). But once some kind of disasters happens anywhere on the earth, the satellites will change their orbit into the regression one and observe the disaster area in high frequency or high-resolution mode. The result of the conceptual design and the necessary theory confirms the feasibility of this mission in terms of technique and cost.
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Figure 1$B!!(BThe Image of 6 Satellite Circular Formation
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Table 1$B!!(BOrbit Information of 2 observation modes
| Mode |
Orbit |
M |
N |
T(min) |
h(km) |
i (deg) |
| Normal |
Semi-regression |
30 |
15 |
96.21 |
577.2 |
97.7 |
| Disaster |
Regression |
1 |
15 |
96 |
566.9 |
97.66 |
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Table 2$B!!(BSAR Conceptual Sizing (Extract)
|
L band |
C band |
X band |
| Swing Angle (deg) |
20 |
30 |
20 |
35 |
20 |
40 |
Antenna Length (m)
Beam Width (deg)
Real Azimuth Rez(m)
|
7.2
1.910
3.6
|
7.2
1.910
3.6
|
7.2
0.450
3.6
|
7.2
0.450
3.6
|
7.2
0.249
3.6
|
7.2
0.249
3.6
|
| Cross-track Rez (m) |
4.020 |
2.750 |
4.020 |
2.397 |
4.020 |
2.139 |
Antenna Width (m)
Peak Transmitting Power (W)
Average Transmitting Power (W)
S/N Ratio
|
1.5
6000
360
12.37
|
1.5
6000
252
2.84
|
1.5
6000
360
52.46
|
1.5
6000
360
7.84
|
1.5
6000
360
95.02
|
1.5
6000
360
10.04
|
Cross-track Observation Width (km)
Azimuth Observation Width (km)
|
107.1
20.7
|
129.9
20.7
|
25.3
4.9
|
35.1
5.7
|
13.9
2.7
|
22.9
3.4
|
| INSAR Correlation Factor |
0.904 |
0.731 |
0.885 |
0.855 |
0.813 |
0.869 |
Space Rez Diameter (m)
Data Rate (Mbps)
|
3.80
817
|
3.15
1195
|
3.80
193
|
2.94
323
|
3.80
106
|
2.78
200
|
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7.$B!!;29MJ88%(B
[1] Steven J. Isakowitz$B!X(BINTERNATIONAL REFERENCE GUIDE TO SPACE LAUNCH SYSTEMS .SE$B!Y(B(AIAA,1995)
[2] $B2,K\8,0l!XCO5e4D6-7WB,!Y(B($B%*!<%`
[3] $B>.NSC#<#!&G_86=SI'!&Fg0f>O;L!&:4C]!!@?!&>>2,7z;V!&1:DM@6Jv!X9R6u5!Ek:\(BSAR$B!J&P(B-SAR)$B$K$h$k%$%s%?!<%U%'%m%a%H%j=hM}(B $B!Y(B(CRL,1999)
[4] $B;q8;(I%$B4D6-4QB,2r@O%;%s%?!
[5] $B;q8;(I%$B4D6-4QB,2r@O%;%s%?!
[6] $B;q8;(I%$B4D6-4QB,2r@O%;%s%?!
[7] $B;q8;(I%$B4D6-4QB,2r@O%;%s%?!
[8] Wiley J.Larson, James R.Wertz$B!X(BSpace Mission Analysis and Design SE$B!Y(B(Microcosm,Inc,1992)
[9] $BEDJU1QFs!X%m%1%C%H(B $B%7%9%F%`!Y(B($BEDJU1QFs(B,1999)
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