Mission Statement

ALL-STAR deliver a 3U CubeSat providing accesibility for on-board and on-orbit payload operations for one full year including tasks such as research, data collections, and test for future evolutions to the CubeSat structure in COSGC.

The Bus and Payload components split the 3U space evenly, to where ALL-STAR can provide for a 1.5U Payload size, such as the current payload THEIA, and in the future, PolarCube and PropSAT.

 

Objectives

  • Create a reproducible modular busCapable enough to be used for a variety of small research and technology based payloads
    • Conform to the standard CubeSat Structure
    • Create common payload interface
  • Built within six months of request after initial delivery in Spring 2012

 

ALLSTAR Storyboard

Launch

ALLSTAR will launch as a secondary payload attached to the upper stage of SpaceX's Falcon 9 rocket, version 1.1 from Cape Canaveral in November 2013.

P-POD Deployment

At a predetermined time and location decided by SpaceX, ALLSTAR will be ejected from the PPOD. Once clear of the vehicle, ALLSTAR will begin to power on Subsystems as well as checking for deployment. The satellite will not begin to beacon until 30 minutes after being ejected from the launch vehicle as required by the FCC.

 

 

 

 

Bus Exo-Skeleton Deployment

ALLSTAR’s first task will be to deploy the solar panel wings and extend to the satellite’s full length. This happens through a frangibolt burn, which releases the structure to its full length, which is tensioned by constant force springs.

This process is confirmed by a Star Camera lock, verification of deployment flag, ALLSTAR switching in to Bus Mode, and the satellite should begin beaconing.

First Contact

The GPS subsystem will trigger a switch to activate COM mode, and the ALLSTAR Mission Operations team will downlink Deployment logs, as well as Health and Status files. Then the ALLSTAR team will uplink a schedule for the spacecraft.

Begin Operations

Using the uploaded schedule, the satellite will switch into operational modes as directed by the scheduler file.

Normal Operations THEIA

Triggered by the schedule, the ALLSTAR ACS subsystem will point the THEIA payload towards the picture target and capture an image which is sent to CDH to be downlinked during the next pass.

Normal Operations COM Mode

Triggered by GPS proximity to the Ground Station location in Colorado, ALLSTAR aligns itself to where the antenna points nadir for transmit. At this time, files are downlinked, and new schedules are uplinked.

 

 

Normal Operations Bus Mode

Following the uplinked schedule, the ACS subsystem aims THEIA into the velocity vector which reduces drag on the satellite. ALLSTAR will also rotate along this vector in able to charge the batteries with maximum exposure of the solar panels to the Sun.

Error Mitigation Mode

Triggered by CDH, ALLSTAR will have the ability to attempt a resolution in issues onboard the spacecraft. If the Error Mitigation mode is successful, the spacecraft will switch itself back into Bus Mode. If the mitigation of the error is unsuccessful, ALLSTAR will go into Safe Mode to where it will await ground commands.

 

End of Life

After approximately 60 days, ALLSTAR will burn up during re-entry to the atmosphere due to orbital decay.

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