Commit eae18b3b authored by GATEAU Thibault's avatar GATEAU Thibault
Browse files

[dev] initial public release of CREME's Python code

parents
Output/*
Output/Figures/*
Data/ContactLocator1.txt
Data/EclipseLocator1.txt
!Output/Readme.md
!Output/Figures
!Output/Figures/Readme.md
!Output/Res_champ/
\ No newline at end of file
This diff is collapsed.
paths:
scilab_path: C:\Program Files\scilab-6.1.0\bin\Scilex.exe
GMAT_BIN : D:\j.puech\Documents\ISAE_Creme\creme-systeme\0_Simulation\GMAT_Application\bin\GMAT.exe
#GMAT_BIN : ../../0_Simulation/GMAT_Application\bin\GMAT.exe
#GMAT_BIN_linux : /home/tgateau/Utils/GMAT/GMAT/R2019aBeta1/bin/GMAT-R2019aBeta1
GMAT_BIN_linux : /home/tgateau/git/creme/creme-systeme/0_Simulation/GMAT_Application/GMAT/R2020a/bin/GmatConsole-R2020a
GMAT_BIN_linux_docker : gmat-console:dev
input_dir: ../GMAT/Cubesat_Creme_Lite/
output_dir: Output_Lite/
SIMULATION:
report_name: Creme_CircularOrbit_10h22h_ToulouseGS_SSO600km_5days_120s
total_time: 5[days] # Total simulation time [days]
dt: 120[sec] # simulation discretization time
ORBIT:
epoch : 2023,01,01,00,00,00 # Initial simulation epoch YYYY,MM,DD,hh,mm,ss
SMA : 6978.14[km] # Semi major axis [km]
ECC : 0 # Eccentricity
INC : 97.79[deg] # Inclination [deg]
RAAN : 250.09664[deg] # right ascension of the ascending node [deg]
AOP : 0.0[deg] # Argument of periapsis [deg]
TA : 0.0[deg] # True Anomaly [deg]
POWER_BUDGET:
TotBatPower: 80[Wh] # Max battery power [Wh]
SolarPower: 24[W] # Solar panels delivery power [W]
Pmesure: 9[W] # Power consumption in mode nominal (mesure) [W]
Pvidage: 18[W] # Power consumption in mode vidage station [W]
DATA_BUDGET:
TC_debit_nominal: 16[kbit/s] # nominal TeleCommand rate [kbit/s]
TM_debit_nominal: 85[kbits/s] # nominal TeleMetry rate [kbit/s]
CONSTANTS:
radius_earth : 6378.136[km] #km
c : 299792458[m/s] #m/s
k_dB : -228.6[dB] #dB Boltzman constant
SPACECRAFT_FLIGHT_DYNAMICS:
SC_altitude : 0[km] #altitude in km, put 0 if defined automatically later
GROUNDSTATION_LOCATION:
GS_altitude : 115[m] #altitude in m
GS_minElevation : 10[deg] #minimum elevation [deg]
GS_latitude : 43.6[deg]
GS_longitude: 1.5[deg]
DOWNLINK:
frequency: 2.2635e9[Hz]
#Hz downlink frequency - S-Band
data_rate : 85e3[bit/s]
#bit/s downlink data rate
required_BER_from_Modulation : 10.5
#12.5 pour un Eb/N0 de 10-9 #10.5 pour un Eb/N0 de 10-6
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "QPSK"
#cortL_bandwidth: 152.05
# Hz Cortex loop bandwidth
system_margin : 0[dB]
#dB System margin to take into account as a security
UPLINK:
frequency: 2.086e9[Hz]
#Hz downlink frequency - VHF
data_rate : 16e3[bit/s]
#bit/s downlink data rate
required_BER_from_Modulation: 9.6
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "PCM"
system_margin : 0[dB]
#dB System margin to take into account as a security
PROPAGATION_LOSSES:
# Data computed from https://amsat-uk.org/tag/link-budget/
loss_pol: 3[dB]
#dB Polarisation Loss (depends on both antennas)
loss_atm: 1.1[dB]
#dB Atmospheric gas attenuation (depends on the elevation angle)
loss_scin: 0.0[dB]
#db Scintillation loss
loss_rain: 0.0[dB]
#dB Rain attenuation
loss_cloud: 0.0[dB]
#dB Cloud attenuation
loss_si: 0.0[dB]
#dB Snow & Ice attenuation
loss_misc : 0.0[dB]
#dB
SPACECRAFT_TRANSMITTER:
SC_power_tx: 2[W]
#W Transmitter output power
SC_ant_gain_tx: 6.5[dB]
#dBi spacecraft transmitter antenna gain, combination of directivity and efficiency
SC_loss_cable_tx: 0.2[dB]
#dB spacecraft transmitter cable loss
SC_loss_connector_tx: 0.1[dB]
#dB spacecraft transmitter cable loss
SC_loss_feeder_tx: 4.5[dB]
#dB Coupler loss
SC_misc : 0[dB]
#Other in-line loisses, e.g. Antenna splitter #0.85 ?
SC_loss_point_tx: 6[dB]
#dB spacecraft transmitter pointing loss 65° -> 6.9 # 30° -> 1.3 6 at 60°
SPACECRAFT_RECEIVER:
#AnyWaves
SC_ant_gain_rx: 6.5[dB]
#dBi spacecraft receiver antenna gain at 60°
#ANYWAVES-S-Band-Antenna
SC_eta_rx : 0.92
#efficiency
SC_loss_point_rx: 6[dB]
#dB spacecraft receiver pointing loss #65°-> 6.9dB | 30° -> 1.3 dB
SC_loss_cable_rx: 0.2[dB]
#dB spacecraft receiver cable loss
SC_loss_connector_rx: 4.6[dB]
#dB spacecraft receiver connector loss (+ feeder)
SC_LNA_gain : 0[dB]
SC_T_rx : 550[K]
#ground station Temperature in Kelvin : sky: 35K - default 200 ?? 400 in BE #K spacecraft effective noise temperature
GROUND_STATION_RECEIVER:
###############
#efficiency
eta_rx : 0.5
#efficiency
antennaDiameter : 3[m]
#diameter (m)
GS_LNA_gain: 25[dB]
#dB
GS_T_rx : 610[K]
#ground station Temperature in Kelvin : sky: 35K - default TP 200 ?? receiver noise temperature
GS_loss_point_rx: 3[dB]
#dB ground station receiver pointing loss -> 1 degree error : 1.2 / 2degree : 5.1 (source AMSAT)
GS_loss_cable_rx: 0[dB]
#dB ground station receiver cable loss
GS_loss_cable_D_rx: 16.9[dB]
#dB ground station receiver cable loss
GS_loss_connector_rx: 0.1[dB]
#dB ground station transmitter cable loss
GROUND_STATION_TRANSMITTER:
#https://www.rfhamdesign.com/products/parabolicdishkit/3-meter-6-petal-dish/index.php
GS_power_tx: 50[W]
#W
GS_line_loss_tx: 16.9[dB]
#dB ground station transmission line loss
GS_loss_connector_tx: 0.1[dB]
#dB spacecraft transmitter cable loss
GS_ant_gain_tx: 34.03[dB]
#dBi ground station transmitter antenna gain
GS_loss_point_rx: 3[dB]
#dB Ground station emitter pointing loss
\ No newline at end of file
paths:
scilab_path: C:\Program Files\scilab-6.1.0\bin\Scilex.exe
GMAT_BIN : D:\j.puech\Documents\ISAE_Creme\creme-systeme\0_Simulation\GMAT_Application\bin\GMAT.exe
#GMAT_BIN : ../../0_Simulation/GMAT_Application\bin\GMAT.exe
#GMAT_BIN_linux : /home/tgateau/Utils/GMAT/GMAT/R2019aBeta1/bin/GMAT-R2019aBeta1
GMAT_BIN_linux : /home/tgateau/git/creme/creme-systeme/0_Simulation/GMAT_Application/GMAT/R2020a/bin/GmatConsole-R2020a
GMAT_BIN_linux_docker : gmat-console:dev
input_dir: ../GMAT/Cubesat_Creme_Lite/
output_dir: Output_Lite/
SIMULATION:
report_name: Creme_CircularOrbit_10h22h_ToulouseGS_SSO2000km_1days_120s
total_time: 3[days] # Total simulation time [days]
dt: 120[sec] # simulation discretization time
ORBIT:
epoch : 2023,01,01,00,00,00 # Initial simulation epoch YYYY,MM,DD,hh,mm,ss
SMA : 8378.14[km] # Semi major axis [km]
ECC : 0 # Eccentricity
INC : 104.85[deg] # Inclination [deg]
RAAN : 250.09664[deg] # right ascension of the ascending node [deg]
AOP : 0.0[deg] # Argument of periapsis [deg]
TA : 0.0[deg] # True Anomaly [deg]
POWER_BUDGET:
TotBatPower: 80[Wh] # Max battery power [Wh]
SolarPower: 24[W] # Solar panels delivery power [W]
Pmesure: 14[W] # Power consumption in mode nominal (mesure) [W]
Pvidage: 18[W] # Power consumption in mode vidage station [W]
DATA_BUDGET:
TC_debit_nominal: 16[kbit/s] # nominal TeleCommand rate [kbit/s]
TM_debit_nominal: 85[kbits/s] # nominal TeleMetry rate [kbit/s]
CONSTANTS:
radius_earth : 6378.136[km] #km
c : 299792458[m/s] #m/s
k_dB : -228.6[dB] #dB Boltzman constant
SPACECRAFT_FLIGHT_DYNAMICS:
SC_altitude : 0[km] #altitude in km, put 0 if defined automatically later
GROUNDSTATION_LOCATION:
GS_altitude : 115[m] #altitude in m
GS_minElevation : 10[deg] #minimum elevation [deg]
GS_latitude : 43.6[deg]
GS_longitude: 1.5[deg]
DOWNLINK:
frequency: 2.2635e9[Hz]
#Hz downlink frequency - S-Band
data_rate : 85e3[bit/s]
#bit/s downlink data rate
required_BER_from_Modulation : 10.5
#12.5 pour un Eb/N0 de 10-9 #10.5 pour un Eb/N0 de 10-6
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "QPSK"
#cortL_bandwidth: 152.05
# Hz Cortex loop bandwidth
system_margin : 0[dB]
#dB System margin to take into account as a security
UPLINK:
frequency: 2.086e9[Hz]
#Hz downlink frequency - VHF
data_rate : 16e3[bit/s]
#bit/s downlink data rate
required_BER_from_Modulation: 9.6
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "PCM"
system_margin : 0[dB]
#dB System margin to take into account as a security
PROPAGATION_LOSSES:
# Data computed from https://amsat-uk.org/tag/link-budget/
loss_pol: 3[dB]
#dB Polarisation Loss (depends on both antennas)
loss_atm: 1.1[dB]
#dB Atmospheric gas attenuation (depends on the elevation angle)
loss_scin: 0.0[dB]
#db Scintillation loss
loss_rain: 0.0[dB]
#dB Rain attenuation
loss_cloud: 0.0[dB]
#dB Cloud attenuation
loss_si: 0.0[dB]
#dB Snow & Ice attenuation
loss_misc : 0.0[dB]
#dB
SPACECRAFT_TRANSMITTER:
SC_power_tx: 2[W]
#W Transmitter output power
SC_ant_gain_tx: 6.5[dB]
#dBi spacecraft transmitter antenna gain, combination of directivity and efficiency
SC_loss_cable_tx: 0.2[dB]
#dB spacecraft transmitter cable loss
SC_loss_connector_tx: 0.1[dB]
#dB spacecraft transmitter cable loss
SC_loss_feeder_tx: 4.5[dB]
#dB Coupler loss
SC_misc : 0[dB]
#Other in-line loisses, e.g. Antenna splitter #0.85 ?
SC_loss_point_tx: 6[dB]
#dB spacecraft transmitter pointing loss 65° -> 6.9 # 30° -> 1.3 6 at 60°
SPACECRAFT_RECEIVER:
#AnyWaves
SC_ant_gain_rx: 6.5[dB]
#dBi spacecraft receiver antenna gain at 60°
#ANYWAVES-S-Band-Antenna
SC_eta_rx : 0.92
#efficiency
SC_loss_point_rx: 6[dB]
#dB spacecraft receiver pointing loss #65°-> 6.9dB | 30° -> 1.3 dB
SC_loss_cable_rx: 0.2[dB]
#dB spacecraft receiver cable loss
SC_loss_connector_rx: 4.6[dB]
#dB spacecraft receiver connector loss (+ feeder)
SC_LNA_gain : 0[dB]
SC_T_rx : 550[K]
#ground station Temperature in Kelvin : sky: 35K - default 200 ?? 400 in BE #K spacecraft effective noise temperature
GROUND_STATION_RECEIVER:
###############
#efficiency
eta_rx : 0.5
#efficiency
antennaDiameter : 3[m]
#diameter (m)
GS_LNA_gain: 25[dB]
#dB
GS_T_rx : 610[K]
#ground station Temperature in Kelvin : sky: 35K - default TP 200 ?? receiver noise temperature
GS_loss_point_rx: 3[dB]
#dB ground station receiver pointing loss -> 1 degree error : 1.2 / 2degree : 5.1 (source AMSAT)
GS_loss_cable_rx: 0[dB]
#dB ground station receiver cable loss
GS_loss_cable_D_rx: 16.9[dB]
#dB ground station receiver cable loss
GS_loss_connector_rx: 0.1[dB]
#dB ground station transmitter cable loss
GROUND_STATION_TRANSMITTER:
#https://www.rfhamdesign.com/products/parabolicdishkit/3-meter-6-petal-dish/index.php
GS_power_tx: 50[W]
#W
GS_line_loss_tx: 16.9[dB]
#dB ground station transmission line loss
GS_loss_connector_tx: 0.1[dB]
#dB spacecraft transmitter cable loss
GS_ant_gain_tx: 34.03[dB]
#dBi ground station transmitter antenna gain
GS_loss_point_rx: 3[dB]
#dB Ground station emitter pointing loss
\ No newline at end of file
paths:
scilab_path: C:\Program Files\scilab-6.1.0\bin\Scilex.exe
GMAT_BIN : D:\j.puech\Documents\ISAE_Creme\creme-systeme\0_Simulation\GMAT_Application\bin\GMAT.exe
#GMAT_BIN : ../../0_Simulation/GMAT_Application\bin\GMAT.exe
#GMAT_BIN_linux : /home/tgateau/Utils/GMAT/GMAT/R2019aBeta1/bin/GMAT-R2019aBeta1
GMAT_BIN_linux : /home/tgateau/git/creme/creme-systeme/0_Simulation/GMAT_Application/GMAT/R2020a/bin/GmatConsole-R2020a
GMAT_BIN_linux_docker : gmat-console:dev
input_dir: ../GMAT/Cubesat_Creme_Lite/
output_dir: Output_Lite/
SIMULATION:
report_name: Creme_CircularOrbit_10h22h_ToulouseGS_SSO600km_1days_120s
total_time: 1[days] # Total simulation time [days]
dt: 120[sec] # simulation discretization time
ORBIT:
epoch : 2023,01,01,00,00,00 # Initial simulation epoch YYYY,MM,DD,hh,mm,ss
SMA : 6978.14[km] # Semi major axis [km]
ECC : 0 # Eccentricity
INC : 97.79[deg] # Inclination [deg]
RAAN : 250.09664[deg] # right ascension of the ascending node [deg]
AOP : 0.0[deg] # Argument of periapsis [deg]
TA : 0.0[deg] # True Anomaly [deg]
POWER_BUDGET:
TotBatPower: 80[Wh] # Max battery power [Wh]
SolarPower: 24[W] # Solar panels delivery power [W]
Pmesure: 9[W] # Power consumption in mode nominal (mesure) [W]
Pvidage: 18[W] # Power consumption in mode vidage station [W]
DATA_BUDGET:
TC_debit_nominal: 16[kbit/s] # nominal TeleCommand rate [kbit/s]
TM_debit_nominal: 85[kbits/s] # nominal TeleMetry rate [kbit/s]
CONSTANTS:
radius_earth : 6378.136[km] #km
c : 299792458[m/s] #m/s
k_dB : -228.6[dB] #dB Boltzman constant
SPACECRAFT_FLIGHT_DYNAMICS:
SC_altitude : 0[km] #altitude in km, put 0 if defined automatically later
GROUNDSTATION_LOCATION:
GS_altitude : 115[m] #altitude in m
GS_minElevation : 10[deg] #minimum elevation [deg]
GS_latitude : 43.6[deg]
GS_longitude: 1.5[deg]
DOWNLINK:
frequency: 2.2635e9[Hz]
#Hz downlink frequency - S-Band
data_rate : 85e3[bit/s]
#bit/s downlink data rate
required_BER_from_Modulation : 10.5
#12.5 pour un Eb/N0 de 10-9 #10.5 pour un Eb/N0 de 10-6
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "QPSK"
#cortL_bandwidth: 152.05
# Hz Cortex loop bandwidth
system_margin : 0[dB]
#dB System margin to take into account as a security
UPLINK:
frequency: 2.086e9[Hz]
#Hz downlink frequency - VHF
data_rate : 16e3[bit/s]
#bit/s downlink data rate
required_BER_from_Modulation: 9.6
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "PCM"
system_margin : 0[dB]
#dB System margin to take into account as a security
PROPAGATION_LOSSES:
# Data computed from https://amsat-uk.org/tag/link-budget/
loss_pol: 3[dB]
#dB Polarisation Loss (depends on both antennas)
loss_atm: 1.1[dB]
#dB Atmospheric gas attenuation (depends on the elevation angle)
loss_scin: 0.0[dB]
#db Scintillation loss
loss_rain: 0.0[dB]
#dB Rain attenuation
loss_cloud: 0.0[dB]
#dB Cloud attenuation
loss_si: 0.0[dB]
#dB Snow & Ice attenuation
loss_misc : 0.0[dB]
#dB
SPACECRAFT_TRANSMITTER:
SC_power_tx: 2[W]
#W Transmitter output power
SC_ant_gain_tx: 6.5[dB]
#dBi spacecraft transmitter antenna gain, combination of directivity and efficiency
SC_loss_cable_tx: 0.2[dB]
#dB spacecraft transmitter cable loss
SC_loss_connector_tx: 0.1[dB]
#dB spacecraft transmitter cable loss
SC_loss_feeder_tx: 4.5[dB]
#dB Coupler loss
SC_misc : 0[dB]
#Other in-line loisses, e.g. Antenna splitter #0.85 ?
SC_loss_point_tx: 6[dB]
#dB spacecraft transmitter pointing loss 65° -> 6.9 # 30° -> 1.3 6 at 60°
SPACECRAFT_RECEIVER:
#AnyWaves
SC_ant_gain_rx: 6.5[dB]
#dBi spacecraft receiver antenna gain at 60°
#ANYWAVES-S-Band-Antenna
SC_eta_rx : 0.92
#efficiency
SC_loss_point_rx: 6[dB]
#dB spacecraft receiver pointing loss #65°-> 6.9dB | 30° -> 1.3 dB
SC_loss_cable_rx: 0.2[dB]
#dB spacecraft receiver cable loss
SC_loss_connector_rx: 4.6[dB]
#dB spacecraft receiver connector loss (+ feeder)
SC_LNA_gain : 0[dB]
SC_T_rx : 550[K]
#ground station Temperature in Kelvin : sky: 35K - default 200 ?? 400 in BE #K spacecraft effective noise temperature
GROUND_STATION_RECEIVER:
###############
#efficiency
eta_rx : 0.5
#efficiency
antennaDiameter : 3[m]
#diameter (m)
GS_LNA_gain: 25[dB]
#dB
GS_T_rx : 610[K]
#ground station Temperature in Kelvin : sky: 35K - default TP 200 ?? receiver noise temperature
GS_loss_point_rx: 3[dB]
#dB ground station receiver pointing loss -> 1 degree error : 1.2 / 2degree : 5.1 (source AMSAT)
GS_loss_cable_rx: 0[dB]
#dB ground station receiver cable loss
GS_loss_cable_D_rx: 16.9[dB]
#dB ground station receiver cable loss
GS_loss_connector_rx: 0.1[dB]
#dB ground station transmitter cable loss
GROUND_STATION_TRANSMITTER:
#https://www.rfhamdesign.com/products/parabolicdishkit/3-meter-6-petal-dish/index.php
GS_power_tx: 50[W]
#W
GS_line_loss_tx: 16.9[dB]
#dB ground station transmission line loss
GS_loss_connector_tx: 0.1[dB]
#dB spacecraft transmitter cable loss
GS_ant_gain_tx: 34.03[dB]
#dBi ground station transmitter antenna gain
GS_loss_point_rx: 3[dB]
#dB Ground station emitter pointing loss
\ No newline at end of file
paths:
scilab_path: C:\Program Files\scilab-6.1.0\bin\Scilex.exe
GMAT_BIN : D:\j.puech\Documents\ISAE_Creme\creme-systeme\0_Simulation\GMAT_Application\bin\GMAT.exe
#GMAT_BIN : ../../0_Simulation/GMAT_Application\bin\GMAT.exe
#GMAT_BIN : /home/tgateau/Utils/GMAT/GMAT/R2019aBeta1/bin/GMAT-R2019aBeta1
SIMULATION:
report_name: Creme_Elliptic_12h_00h_30Wh
total_time: 1[days] # Total simulation time [days]
ORBIT:
epoch : 2023,03,20,00,00,00 # Initial simulation epoch YYYY,MM,DD,hh,mm,ss
SMA : 7078.14[km] # Semi major axis [km]
ECC : 0.0353 # Eccentricity
INC : 98.167025[deg] # Inclination [deg]
RAAN : 0[deg] # right ascension of the ascending node [deg]
AOP : 0.0[deg] # Argument of periapsis [deg]
TA : 0.0[deg] # True Anomaly [deg]
POWER_BUDGET:
TotBatPower: 50[Wh] # Max battery power [Wh]
SolarPower: 24[W] # Solar panels delivery power [W]
Pmesure: 9[W] # Power consumption in mode nominal (mesure) [W]
Pvidage: 18[W] # Power consumption in mode vidage station [W]
DATA_BUDGET:
TC_debit_nominal: 16[kbit/s] # nominal TeleCommand rate [kbit/s]
TM_debit_nominal: 225[kbits/s] # nominal TeleMetry rate [kbit/s]
CONSTANTS:
radius_earth : 6378.136 #km
c : 299792458 #m/s
k_dB : -228.6 #dB Boltzman constant
SPACECRAFT_FLIGHT_DYNAMICS:
SC_altitude : 0 #altitude in km, put 0 if defined automatically later
GROUNDSTATION_LOCATION:
GS_altitude : 115 #altitude in m
GS_minElevation : 10 #minimum elevation [deg]
GS_latitude : 43[deg]
GS_longitude: 1.5[deg]
DOWNLINK:
frequency: 2.2635e9
#Hz downlink frequency - S-Band
data_rate : 225e3
#bit/s downlink data rate
required_BER_from_Modulation : 5
#12.5 pour un Eb/N0 de 10-9 #10.5 pour un Eb/N0 de 10-7
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "QPSK"
#cortL_bandwidth: 152.05
# Hz Cortex loop bandwidth
system_margin : 5
#dB System margin to take into account as a security
UPLINK:
frequency: 2.086e9
#Hz downlink frequency - VHF
data_rate : 16e3
#bit/s downlink data rate
required_BER_from_Modulation: 10.5
#dB Required Eb/N0 to get the Bit Error Rate you want, function of the modulation
modulation: "PCM"
system_margin : 5
#dB System margin to take into account as a security
PROPAGATION_LOSSES:
# Data computed from https://amsat-uk.org/tag/link-budget/
loss_pol: 3
#dB Polarisation Loss (depends on both antennas)
loss_atm: 1.1
#dB Atmospheric gas attenuation (depends on the elevation angle)
loss_scin: 0.0
#db Scintillation loss
loss_rain: 0.0
#dB Rain attenuation
loss_cloud: 0.0
#dB Cloud attenuation
loss_si: 0.0
#dB Snow & Ice attenuation
loss_misc : 1.5
#dB
SPACECRAFT_TRANSMITTER:
SC_power_tx: 2
#W Transmitter output power
SC_ant_gain_tx: 6.5
#dBi spacecraft transmitter antenna gain, combination of directivity and efficiency
SC_loss_cable_tx: 0.5
#dB spacecraft transmitter cable loss
SC_loss_connector_tx: 0.5
#dB spacecraft transmitter cable loss
SC_loss_feeder_tx: 1.5
#dB Coupler loss
SC_misc : 0
#Other in-line loisses, e.g. Antenna splitter #0.85 ?
SC_loss_point_tx: 6
#dB spacecraft transmitter pointing loss 65° -> 6.9 # 30° -> 1.3 6 at 60°
SPACECRAFT_RECEIVER:
#AnyWaves
SC_ant_gain_rx: 6.5
#dBi spacecraft receiver antenna gain at 60°
#ANYWAVES-S-Band-Antenna
SC_eta_rx : 0.92
#efficiency
SC_loss_point_rx: 6
#dB spacecraft receiver pointing loss #65°-> 6.9dB | 30° -> 1.3 dB
SC_loss_cable_rx: 0.5
#dB spacecraft receiver cable loss
SC_loss_connector_rx: 0.5
#dB spacecraft receiver connector loss
SC_LNA_gain : 0
SC_T_rx : 500
#ground station Temperature in Kelvin : sky: 35K - default 200 ?? 400 in BE #K spacecraft effective noise temperature
GROUND_STATION_RECEIVER:
###############
#efficiency
eta_rx : 0.5
#efficiency
antennaDiameter : 3
#diameter (m)
GS_LNA_gain: 0
#20
#dB
GS_T_rx : 300
#ground station Temperature in Kelvin : sky: 35K - default TP 200 ?? receiver noise temperature
GS_loss_point_rx: 3
#dB ground station receiver pointing loss -> 1 degree error : 1.2 / 2degree : 5.1 (source AMSAT)
GS_loss_cable_rx: 0.5
#dB ground station receiver cable loss