ADCS.satellite_factory.satellites.create_cubesats module

ADCS.satellite_factory.satellites.create_cubesats.create_3_3_beavercube2_cubesat(estimated=False, include_biases=True)

Parameters:

• estimated (bool)

• include_biases (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_beavercube1_cubesat(estimated=False)

Parameters:

estimated (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_beavercube2_cubesat(estimated=False, include_biases=True)

Parameters:

• estimated (bool)

• include_biases (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_brite_austria(estimated=False)

Create a BRITE-Austria/TUGSAT-1 spacecraft model.

BRITE-Austria used the Generic Nanosatellite Bus with three reaction wheels, three magnetorquers, three rate sensors, one three-axis magnetometer, six dedicated Sun sensors, and one AeroAstro Miniature Star Tracker. The representative BRITE/GNB inertia tensor is used here. No defensible numerical TUGSAT-1 COM vector was found, so COM = 0. Disturbances use a 20 cm cube geometry from the public BRITE/GNB bus description with generic optical and aerodynamic coefficients.

Parameters:

estimated (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_estcube1_cubesat(estimated=False)

Create an ESTCube-1 magnetic-control CubeSat model.

The preset captures the best-documented ESTCube-1 flight-fitted inertia and published ADCS component configuration: two Honeywell HMC5883L three-axis magnetometers, four InvenSense ITG-3200 three-axis gyros, twelve Hamamatsu S3931 one-dimensional Sun sensor channels arranged as six two-channel Sun sensor assemblies, and three nominal electromagnetic coils with no reaction wheels.

Sources:

• ESTCube-1 attitude determination flight results

• ESTCube-1 magnetic actuator flight results

Parameters:

estimated (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_lightsail2(estimated=False)

Create a LightSail 2 deployed-sail spacecraft model.

LightSail 2 used one +Y Sinclair Interplanetary momentum wheel, three Stras Space magnetic torque rods, two three-axis Honeywell magnetometers, three primary PIB gyros, three secondary mainboard gyros, and five coarse Elmos Sun sensors. The inertia tensor is the published deployed-sail tensor and the COM is taken from the LightSail-B deployed corner-cube drawing. Disturbances use a 3U bus plus a two-sided 32 m^2 deployed-sail geometry with generic aerodynamic and approximate aluminized-Mylar optical coefficients.

Parameters:

estimated (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_moveii_cubesat(estimated=False)

Create a MOVE-II CubeSat model.

MOVE-II is a 1U CubeSat with a distributed magnetorquer-based ADCS: six ADCS PCBs carry Bosch Sensortec BMX055 gyros and magnetometers, the five outer panels carry Solar MEMS NANO-ISS60 Sun sensors, and the ADCS panels include custom PCB magnetorquer coils.

The inertia tensor follows the diagonal values printed in the MOVE-II magnetic-control simulation paper, diag(0.00297, 0.00330, 0.00320) kg m^2. No public center-of-mass vector was found in the attached source summary, so the factory uses COM = 0.

Source:

Hardware-In-The-Loop and Software-In-The-Loop Testing of the MOVE-II CubeSat

Parameters:

estimated (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_rax1_cubesat(estimated=False)

Create a RAX-1 spacecraft model.

RAX-1 was a 3U CubeSat using passive magnetic attitude stabilization: four permanent magnets aligned with the long body-Z axis and two HyMu80 hysteresis strips along transverse axes. This package does not yet have passive magnetic stabilization actuator classes, so those devices are documented here but are not returned as commandable actuators.

The inertia tensor follows the published RAX dynamics model, diag(2.91058, 2.91058, 0.59261) * 1e-2 kg m^2, reflecting the body-Z principal symmetry axis.

Source: RAX attitude determination system design

Parameters:

estimated (bool)

ADCS.satellite_factory.satellites.create_cubesats.create_rax2_cubesat(estimated=False)

Create a RAX-2 spacecraft model.

RAX-2 used the same core RAX attitude-determination hardware as RAX-1, with the revised 17-photodiode OSRAM SFH2430 Sun-sensor layout. Passive magnetic stabilization hardware is documented but not represented as commandable actuators because this package does not yet include permanent-magnet or hysteresis-strip actuator models.

The inertia tensor follows the published RAX dynamics model, diag(2.91058, 2.91058, 0.59261) * 1e-2 kg m^2, reflecting the body-Z principal symmetry axis.

Source: RAX-1/RAX-2 flight attitude-determination results

Parameters:

estimated (bool)