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- ROT.TION 
- CURVATURE 
  
BARTH 4 - OBLATZNESS 
- MOREHOTOSY 
|- EXFOSURE ANGLE 
[- ALSITUDS VARIATION 
CABITAL Ln i 
TR To - VELOCI "7 VARTATION 
DYTAMTOS ver 
N — PAECASSION 
— TRACKING 
~ 
— A TU 
PLATPORM AT TITUDE 
~ DRIFT 
m 
— MISALTONMANT 
- VIBWING ANGLE 
- EON LINBARITIES 
SENSOR « - ZXPOSURE TINE (MLA) 
- SCAN TIEKE (S3CANHZR) 
- INTZRFRAME DEPORMATION 
[- CALIBRATION 
— ZENITH ANGLE 
- SHINING DIRECTION ANGLE 
SUN <= SUN-MORPHOLOGY INTERACTION 
— SUN-ATMOSPHERE INTERACTION 
|- SHADOW 
  
| 8 ABSORPTION 
ATMOSPHERE 
EMOSPHERG DIFFUSION 
tab. 1 Error sources taken into account ir the sirulation program 
lysis of two essential problens for 2 botter use of renotely sen- 
sed data. The first one is the simulation of à future space plat- 
for: when mission characteristics and data from other sensors are 
given (fige 2). The second allows the preprocessing of raw data 
taking into account geometric and radionetric errors (710.3, 40). 
The simulation rives the possibility of refining the 
processing procedure, such as classification and cartography, be- 
fore the starting of the space mission. Past experience has shown 
that the user needs an adequate time to focus his capacity of 
analysis. This time is of the same order of rognitude of the spa- 
ce missione 
The preprocessing produces an image in which each pixel 
has its height, slope, latitude and longitude, multitemporal and 
multispectral radiometric values, illumination and exposure anges. 
The remote sensing image is then integrated with a geographic 
25 
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