Purpose

In this document, we outline a testing protocol to verify the capabilities of the TensorTech ADCS module in an integrated system for the FINCH remote sensing satellite operation.

Objectives

We aim to fulfill the following requirements specified in the Requirements Database

ADCS should be capable of stabilizing (detumbling) FINCH within 190 minutes after release into space from the launch vehicle
1. https://amostech.com/TechnicalPapers/2014/Poster/BINZ.pdf (pg 14) - 1deg/sec average tumble rate
2. TODO look into general tumbling rates for LEO spaceX launches
ADCS shall be capable of control FINCH from commands from the ground station
ADCCS shall record telemetry/telecommand parameters from sensor-actuator ICD's
Coarse pointing

How these requirements will be met?

Not sure if these are feasible

ADCS shall be capable of determining attitude to within +/-0.02 degrees (error tolerance range)
ADCS shall consistently know FINCH’s location relative to the SUN and Earth Position
1. check with position data, would require a light device for sun sensors
After release from the LV and acquisition of initial conditions (initial attitude + rates), ADCS shall progress through its predefined modes of operation to achieve final pointing accuracy in a safe and orderly manner
1. basic functional test
The ADCS shall achieve a relative pointing accuracy of 0.02° over 0.2s
The satellite will be oriented such that the sun and other luminous objects (moon, reflective spacecraft elements) is beyond 40 degrees (half cone) angle of the star tracker line of sight.
1. to be verified by attitude team on STK
The star tracker lens should be oriented in the TBD direction in order to maximize allowed slew rate without exceeding the 0.02 degree pointing accuracy requirement or having luminous objects within 40 degrees.