Changes between Version 30 and Version 31 of TBR/UserApp/Space/Proba_2


Ignore:
Timestamp:
Nov 30, 2011, 8:49:50 AM (8 years ago)
Author:
JoelSherrill
Comment:

Formatting clean up

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  • TBR/UserApp/Space/Proba_2

    v30 v31  
    11= Proba 2 =
    22
    3 = ESA Proba-2 =
     3
     4
     5[[TOC(TBR/UserApp/Space/Proba_2, depth=2)]]
    46
    57'''Proba-2''', Proba stands for PRoject for OnBoard Autonomy. The Proba satellites are among the smallest spacecraft
    68ever to be flown by ESA, but they are making a big impact in the field of space technology. Proba-2 is the
    7 second of the series, building on nearly eight years of successful Proba-1 experience.
    8 
    9 [wiki:File:Proba-2-in-orbit-rear-view.jpg File:Proba-2-in-orbit-rear-view.jpg]
     9second of the series, building on nearly eight years of successful Proba-1 experience. [wiki:File:Proba-2-in-orbit-rear-view.jpg 400px]
     10
    1011= Mission Parameters =
    1112
    1213
    13 PROBA-2 Mission Parameters
    14 
    15 Sponsor:                  ESA
    16 
    17 Expected Life:            2 years
    18 
    19 Primary Applications:     Sun observations; technology demonstration
    20 
    21 Primary SLR Applications: Precision orbit determination
    22 
    23 COSPAR ID:                0905902
    24 
    25 SIC Code:                 8005
    26 
    27 NORAD SSC Code:           36037
    28 
    29 Launch Date:              02-Nov-2009
    30 
    31 NP Bin Size:              15 seconds
    32 
    33 RRA Diameter:             16 cm
    34 
    35 RRA Shape:                hemispherical
    36 
    37 Reflectors:               7 corner cubes
    38 
    39 Orbit:                    Sun-synchronous dusk-dawn
    40 
    41 Altitude (mean):          757 km
    42 
    43 Inclination:              98.445 degrees
    44 
    45 Eccentricity:             0.00116-0.0025
    46 
    47 Weight:                   130 kg
     14
     15
     16{| border="1"
     17|+ '''PROBA-2 Mission Parameters'''
     18|-
     19|Sponsor:
     20|ESA
     21|-
     22|Expected Life:
     23|2 years
     24|-
     25|Primary Applications:
     26|Sun observations; technology demonstration
     27|-
     28|Primary SLR Applications:
     29|Precision orbit determination
     30|-
     31|COSPAR ID:
     32|0905902
     33|-
     34|SIC Code:
     35|8005
     36|-
     37|NORAD SSC Code:
     38|36037
     39|-
     40|Launch Date:
     41|02-Nov-2009
     42|-
     43|NP Bin Size:
     44|15 seconds
     45|-
     46|RRA Diameter:
     47|16 cm
     48|-
     49|RRA Shape:
     50|hemispherical
     51|-
     52|Reflectors:
     53|7 corner cubes
     54|-
     55|Orbit:
     56|Sun-synchronous dusk-dawn
     57|-
     58|Altitude (mean):
     59|757 km
     60|-
     61|Inclination:
     62|98.445 degrees
     63|-
     64|Eccentricity:
     65|0.00116-0.0025
     66|-
     67|Weight:
     68|130 kg
     69|}
    4870= PROBA 2 MISSION SUMMARY =
    4971
     
    97119of ACNS units support Sun-pointing, inertial 3-axis attitude pointing as well as Earth pointing and a series
    98120of attitude maneuvers. Furthermore, it performs all required navigation and maneuvering computations
    99 onboard. The spacecraft platform provides full redundancy
    100 
    101 [wiki:File:PROBA2_Auto11.jpeg File:PROBA2 Auto11.jpeg]
    102 PROBA 2 block diagram
    103 
     121onboard. The spacecraft platform provides full redundancy.
     122
     123{| align="center"
     124|+'''PROBA 2 Block Diagram'''
     125|-
     126|PROBA2_Auto11.jpeg
     127|}
    104128= 2.1. PROBA 2 platform =
    105129= 2.1.1. Mechanical and thermal =
     
    137161sun-sensor in the control loop. Furthermore, the ACNS incorporates a technology demonstration of a series of
    138162new algorithms:
    139  *  low-cost determination of the attitude and orbit using temperature, light and/or magnetic-field
    140 sensors;
    141  * the use of a Square-Root Unscented Kalman Filter (SR-UKF) for attitude and orbit
    142 determination;
    143  *  autonomous, high-precision, recurrent largeangle manoeuvre capability during the Sun-
    144 Observation Mode to avoid star-sensor blinding by the Earth
     163 *  low-cost determination of the attitude and orbit using temperature, light and/or magnetic-field sensors;
     164 *the use of a Square-Root Unscented Kalman Filter (SR-UKF) for attitude and orbit determination;
     165 *  autonomous, high-precision, recurrent largeangle manoeuvre capability during the Sun-Observation Mode to avoid star-sensor blinding by the Earth
    145166
    146167Finally, the ACNS functions support automatic “image paving” for the Sun-Imaging instrument (SWAP)