Changes between Version 40 and Version 41 of TBR/UserApp/Space/Proba_2

Timestamp:

11/13/18 21:08:00 (5 years ago)

Author:

Marçal Comajoan Cara

Comment:

change image links to attachments

TBR/UserApp/Space/Proba_2

@@ -5 +5 @@
 PROBA stands for PRoject for !OnBoard Autonomy. The PROBA satellites are among the smallest spacecraft ever to be flown by ESA, but they are making a big impact in the field of space technology. PROBA-2 is the second of the series, building on nearly eight years of successful PROBA-1 experience. 
 
-[[Image(https://devel.rtems.org/old_images/Proba-2-in-orbit-rear-view.jpg, 400px)]]
+[[Image(Proba-2-in-orbit-rear-view.jpg, 400px)]]
 
 Figure 1: Rear view of PROBA-2 in orbit
@@ -81 +81 @@
 onboard. The spacecraft platform provides full redundancy.
 
-[[Image(https://devel.rtems.org/old_images/PROBA2_Auto11.jpeg)]]
+[[Image(PROBA2_Auto11.jpeg)]]
 
 Figure 2: PROBA-2 Block Diagram
@@ -108 +108 @@
 possible.
 
-[[Image(https://devel.rtems.org/old_images/PROBA2_Auto14.jpeg)]]
+[[Image(PROBA2_Auto14.jpeg)]]
 
 Figure 3: PROBA-2 internal structure and accommodation
@@ -145 +145 @@
 set of Phoenix GPS receivers provided by DLR.
 
-[[Image(https://devel.rtems.org/old_images/PROBA2_Auto2.jpeg)]]
+[[Image(PROBA2_Auto2.jpeg)]]
 
 Figure 4: Phoenix GPS architecture for PROBA-2
@@ -339 +339 @@
 allowing autonomous flare tracking up to 3 times the sun radius.
 
-[[Image(https://devel.rtems.org/old_images/PROBA2_Auto1F.jpeg)]]
+[[Image(PROBA2_Auto1F.jpeg)]]
 
 Figure 5: Open view of the main components of SWAP and SWAP Flight Model (image courtesy AMOS S.A.)
@@ -506 +506 @@
 
  *  Provision of daily global coverage of the land masses in the latitudes 35º and 75º North and in the latitudes between 35° and 56° South, with a 90% daily coverage of equatorial zones - and 100% two-daily imaging, during day time, of the land masses in the latitudes between 35º North and 35º South.. 
-[[Image(https://devel.rtems.org/old_images/ProbaV_Auto12.jpeg)]]
+[[Image(ProbaV_Auto12.jpeg)]]
 
 Figure 6: Artist's view of the PROBA-V spacecraft (image credit: ESA) 12) 13)
@@ -524 +524 @@
  *  HMA (Heterogeneous Mission Access) and QA4EO (Quality Assurance for Earth Observation) implementation for user data. Planned interoperability with GSCDA V2 (GMES Space Component Data Access Version 2). 
 
-[[Image(https://devel.rtems.org/old_images/ProbaV_Auto11.jpeg)]]
+[[Image(ProbaV_Auto11.jpeg)]]
 
 Figure 7: PROBA-V project organization (image credit: ESA, Ref. 9)
@@ -538 +538 @@
 The power distribution and conditioning part of ADPMS supplies an unregulated bus, with each equipment having its internal DC/DC converter. The power conditioning system is designed around a Li-ion battery. 
 
-[[Image(https://devel.rtems.org/old_images/ProbaV_Auto10.jpeg)]]
+[[Image(ProbaV_Auto10.jpeg)]]
 Figure 8: PROBA-V spacecraft accommodation (image credit: QinetiQ Space)
 
@@ -595 +595 @@
 The development of the new X-band transmitter is based almost exclusively on COTS components to achieve at the same time high performances and low recurrent cost. The transmitter also features an innovative functionality with an on-board programmable RF output power from 1-10 W which allows to match finely with the chosen bit rate, and to reduce as much as possible the margins of the link budget and therefore the consumption power. PROBA-V is the first mission to use this newly developed transmitter. The transmitter has a mass of 1 kg, a size of 160 mm x 115 mm x 46 mm, an in-orbit life time of 5 years, and a radiation hardness of 10 krad. Data rates from 10-100 Mbit/s are available. The X-band transmitter was manufactured by TES Electonic Solutions of Bruz, France. 18) 
 
-[[Image(https://devel.rtems.org/old_images/ProbaV_AutoF.jpeg)]]
+[[Image(ProbaV_AutoF.jpeg)]]
 
 Figure 9: Overview of the transmitter architecture (CNES, TES)
 
-[[Image(https://devel.rtems.org/old_images/ProbaV_AutoE.jpeg)]]
+[[Image(ProbaV_AutoE.jpeg)]]
 
 Figure 10: Photo of the X-band transmitter (image credit: CNES, ESA)