Boundless 2018


The SARP team will dedicate itself to developing a student-designed and manufactured reusable rocket and scientific payload. The SARP team will compete in the AGL 30,000 feet apogee category with a hybrid rocket.

Leading up to these events, the team leaders and advisors will commit themselves to facilitate team member growth in areas of engineering and leadership. The team members will gain valuable skills in engineering design, systems engineering, manufacturing, testing, and documentation.

Explore our rocket

Click on the rocket to learn about its components!


Mission: Characterize climate of areas surrounding landing site

● 3U CubeSat enclosure 
● 8.8 lbs
● Arduino controller
● Ultrasonic sensors for object detection and avoidance
● Expandable wheels for increased clearance after deployment
● Stabilizing tail
● LoRa Radio Transceiver for data transmission back to rocket and then back to Ground Control



Objective: Safely return the rocket to the ground after reaching apogee. Requires repeated tests until there are no uncertainties in the system's performance.

● SRAD toroidal parachutes
● Parachute stage separator utilizing three ring design
● Raven altimeter used onboard
● Redundant CO2 injection mechanism

● Successful ground testing of CO2 injection and drogue deployment
● Successful main parachute separation testing
● Kevlar strength testing on Instron machine


Objective: Design, build, and test a robust and efficient structure for the rocket while developing the structural analysis and manufacturing skills of its members. All parts will be designed with integration of neighboring parts in mind so that final assembly is reliable and simple. To ensure robustness and efficiency, the structure will optimize aerodynamic drag and structural weight while providing sufficient strength to all parts of the rocket. Determination of strength will be justified by thorough and well documented quantitative analysis of loads and stresses. In addition, the structure will remain dynamically stable in all flight regimes until recovery is initiated.

● Carbon fiber body tube
● Glass fiber nose cone and actuated valve bay doors for data transmission
● Carbon fiber and high-density foam swept fins


Objective: Safely produce an improved hybrid-rocket motor over previous years, and integrate it into the launch vehicle prior to full-scale flight test. Maintain accurate documentation of the design, analysis, and testing that occurs. Advance the understanding of hybrid rocket motor performance.

● Paraffin wax and liquid nitrous oxide hybrid motor
● Aluminum oxidizer tank with welded bulkheads
● Graphite nozzle
● Oxidizer release into combustion chamber initiated via a pneumatic vane actuator
● Acrylic fuel grain liner
● Impinging doublet injector
● Linen phenolic thermal protection in combustion chamber
● Rocket candy igniter
● Remote fill and igniter commanded from Ground Control via onboard RPi and Arduino over wifi bridges

● Subscale static motor testing for fuel grain composition development
● Injector characterization and mass flow verification
● Cold flows to validate fill and actuation systems
● Successful pressure vessel testing to 1.5 times operating pressure for double the expected load duration
● Successful full-scale static motor testing for full propulsion system validation and performance data collection