VelcroSat History

VelcroSat 

Justin Hunter History

Learning Outcomes

Quantitatively evaluate the need to remove excess orbital matter that can inhibit, or endanger the life expectancy of a current satellite mission.

Quantitatively evaluate the relationship between the orbital debris belt, and the life expectancy of scientific missions in the modern space environment.

Evaluate the need of anti-impact contingency options for on-going low earth orbit satellite missions

Mission Objectives

·         To promote engineering and science education

·         To establish communications with a networked satellite

·         To receive telemetry  from the satellite in orbit

·         To send commands and verify reception of commands

·         To achieve stability and control using 3 axis stabilization methods

·         To ensure functionality of primary mission mechanism

·         To determine correct orbit to ensure rendezvous with debris

·         To maneuver space debris to a safe deorbit position

·         To ensure functionality of the propulsion system

·         To ensure thrust to weight ratio is sufficient to move the VelcroSat and space debris

·         To ensure fuel reserves are sufficient to rendezvous with and maneuver space debris

We have been trying our best to follow our initial plan, but as time goes by we realize that more things need to be added. One aspect of space debris capture the group has been gravitating towards is effectively tracking and mapping the debris.  We have been doing a lot of talking, and now we are moving we are putting our money and hands where our mouth is. We are finally testing out our concepts and moving along our plan.

Departmental Concentration

Ground System Configuration

Spacecraft Design

Electrical and Power Subsystem (EPS)

Attitude Control and Determination (FDS)

Communication Network (COMM)

Network Security