Attitude determination and control system (ADCS), sun sensor, and star tracker
An ADCS module may be configured to use coordinate data from 2 D photodiodes in one or more sun sensors to determine a sun vector. The ADCS module may then use the sun vector in reference to its own body faced (BF) coordinate system to calculate a change in the orientation of the space vehicle. The change in orientation mechanism may be accomplished by reaction wheels, ion thrusters, or other orientation altering mechanisms. A miniature, intelligent star tracker may be included that improves satellite attitude determination and pointing accuracy. An improved reaction wheel assembly may be included that is more robust and suitable for inclusion in small space vehicles.
1. An attitude determination and control system (ADCS), comprising:
an ADCS module comprising a reaction wheel and motor assembly configured to be operated by the ADCS module, wherein
the reaction wheel and motor assembly comprises a wheel assembly and a motor assembly that are separate from one another and connected to one another via silicone rubber rivets, the wheel assembly comprising a reaction wheel and the motor assembly comprising a drive wheel, the reaction wheel directly connected to the drive wheel via the silicone rubber rivets, and
the ADCS is a component of a space vehicle.
2. The ADCS of claim 1 , wherein the wheel assembly comprises:
a wheel shaft housing;
a wheel shaft mounted to the wheel shaft housing;
a plurality of flanged precision bearings mounted to the wheel shaft; and
a reaction wheel mounted to the plurality of flanged precision bearings.
3. The ADCS of claim 1 , wherein the motor assembly comprises:
a motor housing;
a motor comprising a drive shaft, the motor mounted to the motor housing; and
a drive wheel mounted directly to the drive shaft of the motor.
4. The ADCS of claim 1 , wherein the motor assembly comprises a motor housing, the motor housing comprising an interface board that interfaces with the ADCS.
5. The ADCS of claim 1 , further comprising:
a sun sensor comprising a pinhole aperture and a two-dimensional (2D) photodiode, the sun sensor configured to provide coordinates of a position of the sun to the ADCS module.
6. The ADCS of claim 5 , wherein the ADCS module is configured to orient a space vehicle to a new orientation based on the coordinates from the sun sensor and a body frame coordinate system of the ADCS module.
7. The ADCS of claim 6 , wherein
the ADCS system comprises a plurality of sun sensors on different sides of a space vehicle.
8. The ADCS of claim 1 , further comprising:
a star tracker comprising a processor board configured to determine an attitude of a space vehicle at a star tracker sensor.
9. The ADCS system of claim 8 , wherein the star tracker further comprises:
an optical assembly comprising a camera lens, a lens assembly, a baffle, and a detector, wherein
the optical assembly is attached to a mount.