Beredos2
commented
8 months ago Frame of reference
To be able to calculate the effective area for each of the CubeSat faces, we need to calculate several unknown relative vectors (Sun-Spacecraft, Albedo-Spacecraft, Earth-Spacecraft). For this to be possible, we need all known vectors to be expressed in the same frame of reference. Because the ground station is set on Earth, I suggest Earth-Centered Inertial.
- Sun-Spacecraft Vector: Earth-spacecraft vector - Earth-sun vector.
- Albedo-Spacecraft vector: More complexly defined. Under study by Loreign and Dila
Additional requirement (from ADCS team): A rotation matrix that can set any of the surface normal from the spacecraft fixed frame of reference, to the ECI frame of reference.
chgio
Add internal structure to the Thermal block for use in the high level mathematical model of a 3U Spacecraft in low earth orbit. The block must take: orbital elements or position_ECI, spacecraft attitude, and internally dissipated heat as inputs, and must provide the overall spacecraft temperature as an output.
*Note: Additionally, the model takes visible light absorptance and infrared emittance as design parameter inputs. These are independent of other systems.