Tests and results » History » Version 45
Version 44 (SERRA FONT, Anna, 03/23/2015 01:27 AM) → Version 45/49 (SERRA FONT, Anna, 03/23/2015 01:29 AM)
h1. Tests and results
The aim of this part is to demonstrate the proper functioning of the tool. That is, the explanation of how we have shown that the results of all the link budget operations are correct, as well as that the tool is understandable for a user who has never used before.
For that purpose, different test with other students have been carried out. Thus, it has been possible to identify the difficulties of understanding of some aspects. For instance, we have identified some hesitation to understand well what refers each input parameter, and so we could take steps to correct it, and add more explanation in the popup help, or add some diagrams blocks in some tabs in order to have an extra visual aid of the correct placement of each parameter in the process.
h2. Checking results
Below are shown the different verification carried out in each tab in order to verify the correct computation implementation.
h3. Services
{TODO}
tip. libro y proyecto 2
h3. System Geometry
In the Geometry tab are calculated basically three parameters: The distance between each earth station and the satellite (_Range_) and _elevation_ and _azimuth angles_.
The _Range_ is easily checked by placing both satellite and earth station in the latitudes and longitudes equal to 0, thus the range obtained will be equal to the altitude of the satellite orbit. As we are studying the case of a geostationary orbit this range corresponds to 35786 km.
To test the azimuth and elevation angles it has been used real cases with existing satellites and different places on Earth. For example, Eutelsat web (www.eutelsat.com) offers the possibility to make these calculations with the coordinates of one of its satellites. Thereby, figure 1 shows the elevation and azimuth angles obtained using the satellite _"Eutelsat 10 A"_ (Geostationary satellite at latitude 10º East) with respect to two earth stations placed in Rome (Italy) and Palmeira (Brazil). Figure 2 shows that placing the same input values in the _SatLinkTool_ we get the same results.
p=. !geometry_eutelsat_test.png!
Figure 1: Parameters obtained on the _Eutelsat_ web [1].
p=. !{width: 80%}Geometry_tool.png!
Figure 2: Parameters obtained using the _SatLinkTool_.
In Figure 3 it can be seen that the locations of the Earth stations obtained in the map shown on the _System Geometry_ tab are also correct.
p=. !{width: 70%}Geometry_map.png!
Figure 3: Position of the Earth Stations obtained in the _System Geometry_ tab of the _SatLinkTool_.
h3. Uplink
For checking the equations on the _Uplink_ tab we have made several test using either some book values or the calculations of _Project 2_ or other exercises realized throughout the year in the courses of STEL.
Specifically, for the calculation in terms of clear sky conditions we have used the examples of the book _”Space Communication Systems”_ : sections 5.4.2 (_Example 1: Uplink received power_) and 5.6.2 (_Clear sky uplink performance_), and checked that the results were exactly the same. For the case of rainy conditions we have test both calculations of _Project 2_ and the values of section 5.7.4 (_Link performance under rain conditions_).
h3. Payload
h4. Antenna depointing 1
In the payload we have two windows menu. The first is the Antenna and the second the transponder. The window antenna, in turn, has the Depointing 1 and Depointing 2 window. Only the first calculations of depointing were performed in the application, being the total depointing angle computation, an additional feature to be performed in further implementations of the _SatLinkTool_. In these first calculations, we have performed the _true view angles_ ($\theta$, $\varphi$), _the satellite antenna azimuth angle_ ($\alpha$) and _satellite antenna elevation angle_ ($\beta$), as well as two auxiliary angles $\alpha$*, $\beta$*.
In order to check if our results were correct, we have compared, using the same inputs values, the results showed in an example of the "Satellite Communications Systems" book (page 496). The figure below shows the verification of these results.
p=. !{width: 110%}antennaresult1.png!
<div style="margin-left: auto; margin-right: auto; width: 50em">Figure 4 - Comparison of results. In the left side the input values and results for _SatlinkTool_ and in the right the input and results of an example of calculating, found in the book.
</div>
h4. Transponder
In _SatlinkTool_ we have transparent payload, with two forms of carriers per transponder: single carrier or multicarrier (only 3 carriers/ transponder was applied). The formulas used for each case are exposed below.
* Single Carrier
The input is the $IBO$ value, which must be entered by the user, we can perform $OBO$ and $IM$ product equal to zero:
$${OBO}_{|_{dB}}={IBO}_{|_{dB}}+6-6\cdot exp \left(\frac{{IBO}_{|_{dB}}}{6}\right)$$
$$IM=0$$
$${\left(\frac{C}{N}\right)_{IM}}_{|_{dB}}=inf $$
$${\left(\frac{C}{N}\right)_{U,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{U}}_{|_{dB}} - {IBO}_{|_{dB}}$$
$${\left(\frac{C}{N}\right)_{D,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{D}}_{|_{dB}} - {OBO}_{|_{dB}}$$
We have the following table of values, performed with the SatLinkTool compared with results of reference [1] examples, and compared with matlab script.
p=. !{width: 30%}tablePayloadSingle.png!
<div style="margin-left: auto; margin-right: auto; width: 25em">Table 1 - Comparison of results. For a $IBO$=-16.4 dB, matlab script ( "download":https://sourceforge.isae.fr/attachments/download/860/ibosinglecarrer.m ) was used for to perform similar computing.
</div>
* Multi Carrier - Three carriers drive for transponder.
The input is the $IBO$ value, which must be entered by the user, once we have $IBO$ we can perform the following values:
=>$OBO$, => $IM$, => ${\left(\frac{C}{N}\right)_{IM}}$, => ${\left(\frac{C}{N}\right)_{U,sat}}$, => ${\left(\frac{C}{N}\right)_{D,sat}}$
$${OBO}_{|_{dB}}={IBO}_{|_{dB}}+6-6.4\cdot exp \left(\frac{{IBO}_{|_{dB}}+6}{6.4}\right)$$
$$IM =3 {IBO}_{|_{dB}} +17-6.25 exp \left(\frac{{IBO}_{|_{dB}}+11.75}{6.25}\right)$$
$${\left(\frac{C}{N}\right)_{IM}}_{|_{dB}}={OBO}_{|_{dB}}-IM$$
$${\left(\frac{C}{N}\right)_{U,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{U}}_{|_{dB}} - {IBO}_{|_{dB}}$$
$${\left(\frac{C}{N}\right)_{D,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{D}}_{|_{dB}} - {OBO}_{|_{dB}}$$
We have the following table of values, performed with the SatLinkTool compared with matlab script.
p=. !{width: 30%}tablePayloadMulti.png!
<div style="margin-left: auto; margin-right: auto; width: 25em">Table2 - Comparison of results. For a $IBO$=-16.4 dB, matlab script ("download":https://sourceforge.isae.fr/attachments/download/859/ibomulticarrier.m ) was used for to perform similar computing.
</div>
h3. Downlink
The checking process of the equations on the _Downlink_ tab are similar as the ones done in the _Uplink_ tab. In this case, for the calculation in terms of clear sky conditions we also have used some examples of the book _”Space Communication Systems”_ : sections 5.4.3 (_Example 2: Downlink received power_) and 5.6.3 (_Clear sky downlink performance_), and we also checked that the results were the same. For the case of rainy conditions we also have test both calculations of _Project 2_ and the values of section 5.7.4 (_Link performance under rain conditions_).
h3. Overall link
{TODO}
h1. References
[1] www.eutelsat.com/deploy_SorbamLight/pages/azimuthElevation.do?action=calculate
The aim of this part is to demonstrate the proper functioning of the tool. That is, the explanation of how we have shown that the results of all the link budget operations are correct, as well as that the tool is understandable for a user who has never used before.
For that purpose, different test with other students have been carried out. Thus, it has been possible to identify the difficulties of understanding of some aspects. For instance, we have identified some hesitation to understand well what refers each input parameter, and so we could take steps to correct it, and add more explanation in the popup help, or add some diagrams blocks in some tabs in order to have an extra visual aid of the correct placement of each parameter in the process.
h2. Checking results
Below are shown the different verification carried out in each tab in order to verify the correct computation implementation.
h3. Services
{TODO}
tip. libro y proyecto 2
h3. System Geometry
In the Geometry tab are calculated basically three parameters: The distance between each earth station and the satellite (_Range_) and _elevation_ and _azimuth angles_.
The _Range_ is easily checked by placing both satellite and earth station in the latitudes and longitudes equal to 0, thus the range obtained will be equal to the altitude of the satellite orbit. As we are studying the case of a geostationary orbit this range corresponds to 35786 km.
To test the azimuth and elevation angles it has been used real cases with existing satellites and different places on Earth. For example, Eutelsat web (www.eutelsat.com) offers the possibility to make these calculations with the coordinates of one of its satellites. Thereby, figure 1 shows the elevation and azimuth angles obtained using the satellite _"Eutelsat 10 A"_ (Geostationary satellite at latitude 10º East) with respect to two earth stations placed in Rome (Italy) and Palmeira (Brazil). Figure 2 shows that placing the same input values in the _SatLinkTool_ we get the same results.
p=. !geometry_eutelsat_test.png!
Figure 1: Parameters obtained on the _Eutelsat_ web [1].
p=. !{width: 80%}Geometry_tool.png!
Figure 2: Parameters obtained using the _SatLinkTool_.
In Figure 3 it can be seen that the locations of the Earth stations obtained in the map shown on the _System Geometry_ tab are also correct.
p=. !{width: 70%}Geometry_map.png!
Figure 3: Position of the Earth Stations obtained in the _System Geometry_ tab of the _SatLinkTool_.
h3. Uplink
For checking the equations on the _Uplink_ tab we have made several test using either some book values or the calculations of _Project 2_ or other exercises realized throughout the year in the courses of STEL.
Specifically, for the calculation in terms of clear sky conditions we have used the examples of the book _”Space Communication Systems”_ : sections 5.4.2 (_Example 1: Uplink received power_) and 5.6.2 (_Clear sky uplink performance_), and checked that the results were exactly the same. For the case of rainy conditions we have test both calculations of _Project 2_ and the values of section 5.7.4 (_Link performance under rain conditions_).
h3. Payload
h4. Antenna depointing 1
In the payload we have two windows menu. The first is the Antenna and the second the transponder. The window antenna, in turn, has the Depointing 1 and Depointing 2 window. Only the first calculations of depointing were performed in the application, being the total depointing angle computation, an additional feature to be performed in further implementations of the _SatLinkTool_. In these first calculations, we have performed the _true view angles_ ($\theta$, $\varphi$), _the satellite antenna azimuth angle_ ($\alpha$) and _satellite antenna elevation angle_ ($\beta$), as well as two auxiliary angles $\alpha$*, $\beta$*.
In order to check if our results were correct, we have compared, using the same inputs values, the results showed in an example of the "Satellite Communications Systems" book (page 496). The figure below shows the verification of these results.
p=. !{width: 110%}antennaresult1.png!
<div style="margin-left: auto; margin-right: auto; width: 50em">Figure 4 - Comparison of results. In the left side the input values and results for _SatlinkTool_ and in the right the input and results of an example of calculating, found in the book.
</div>
h4. Transponder
In _SatlinkTool_ we have transparent payload, with two forms of carriers per transponder: single carrier or multicarrier (only 3 carriers/ transponder was applied). The formulas used for each case are exposed below.
* Single Carrier
The input is the $IBO$ value, which must be entered by the user, we can perform $OBO$ and $IM$ product equal to zero:
$${OBO}_{|_{dB}}={IBO}_{|_{dB}}+6-6\cdot exp \left(\frac{{IBO}_{|_{dB}}}{6}\right)$$
$$IM=0$$
$${\left(\frac{C}{N}\right)_{IM}}_{|_{dB}}=inf $$
$${\left(\frac{C}{N}\right)_{U,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{U}}_{|_{dB}} - {IBO}_{|_{dB}}$$
$${\left(\frac{C}{N}\right)_{D,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{D}}_{|_{dB}} - {OBO}_{|_{dB}}$$
We have the following table of values, performed with the SatLinkTool compared with results of reference [1] examples, and compared with matlab script.
p=. !{width: 30%}tablePayloadSingle.png!
<div style="margin-left: auto; margin-right: auto; width: 25em">Table 1 - Comparison of results. For a $IBO$=-16.4 dB, matlab script ( "download":https://sourceforge.isae.fr/attachments/download/860/ibosinglecarrer.m ) was used for to perform similar computing.
</div>
* Multi Carrier - Three carriers drive for transponder.
The input is the $IBO$ value, which must be entered by the user, once we have $IBO$ we can perform the following values:
=>$OBO$, => $IM$, => ${\left(\frac{C}{N}\right)_{IM}}$, => ${\left(\frac{C}{N}\right)_{U,sat}}$, => ${\left(\frac{C}{N}\right)_{D,sat}}$
$${OBO}_{|_{dB}}={IBO}_{|_{dB}}+6-6.4\cdot exp \left(\frac{{IBO}_{|_{dB}}+6}{6.4}\right)$$
$$IM =3 {IBO}_{|_{dB}} +17-6.25 exp \left(\frac{{IBO}_{|_{dB}}+11.75}{6.25}\right)$$
$${\left(\frac{C}{N}\right)_{IM}}_{|_{dB}}={OBO}_{|_{dB}}-IM$$
$${\left(\frac{C}{N}\right)_{U,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{U}}_{|_{dB}} - {IBO}_{|_{dB}}$$
$${\left(\frac{C}{N}\right)_{D,sat}}_{|_{dB}} = {\left(\frac{C}{N}\right)_{D}}_{|_{dB}} - {OBO}_{|_{dB}}$$
We have the following table of values, performed with the SatLinkTool compared with matlab script.
p=. !{width: 30%}tablePayloadMulti.png!
<div style="margin-left: auto; margin-right: auto; width: 25em">Table2 - Comparison of results. For a $IBO$=-16.4 dB, matlab script ("download":https://sourceforge.isae.fr/attachments/download/859/ibomulticarrier.m ) was used for to perform similar computing.
</div>
h3. Downlink
The checking process of the equations on the _Downlink_ tab are similar as the ones done in the _Uplink_ tab. In this case, for the calculation in terms of clear sky conditions we also have used some examples of the book _”Space Communication Systems”_ : sections 5.4.3 (_Example 2: Downlink received power_) and 5.6.3 (_Clear sky downlink performance_), and we also checked that the results were the same. For the case of rainy conditions we also have test both calculations of _Project 2_ and the values of section 5.7.4 (_Link performance under rain conditions_).
h3. Overall link
{TODO}
h1. References
[1] www.eutelsat.com/deploy_SorbamLight/pages/azimuthElevation.do?action=calculate