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[[File:Launch1PrepOlympus2019.JPG|400px|thumb|right|frame|The team setting up the rocket on a pad at FAR for the first test launch of the year.]]
[[File:Launch1PrepOlympus2019.JPG|400px|thumb|right|frame|The team setting up the rocket on a pad at FAR for the first test launch of the year.]]
Olympus 2019 will be the third SSI team to compete in the [[Intercollegiate Rocketry Engineering Competition]], succeeding [[IREC 2018]]. The rocket features a compact avionics bay, a redesigned recovery system, a fiberglass airframe with a carbon fiber fin lay-up, and a protein crystallography payload. Currently, a liquid propulsion system is in development, and may be the motor for the final iteration of the rocket, though this is still undecided. This liquid motor was a continuation of the prior year's Helios project, and used many of the same design principles.
Olympus 2019 was the third SSI team to compete in the [[Intercollegiate Rocketry Engineering Competition]], succeeding [[IREC 2018]]. The rocket featured a compact avionics bay, a redesigned recovery system, a fiberglass airframe with a carbon fiber fin lay-up, and a protein crystallography payload. A liquid propulsion system was designed and tested as over the course of the year, although it was ultimately not flown in New Mexico. This liquid motor was a continuation of the prior year's Helios project, and used many of the same design principles, and Olympus 2020 is hoping to fly the liquid motor at IREC next year.
=Overview=
=Overview=
=System Design=
=System Design=
Unlike the year before, the Olympus 2019 rocket uses five-inch diameter body tubing instead of four-inch tubing. This choice was driven by the design of the tanks for the liquid propulsion system.
Unlike the year before, the Olympus 2019 rocket uses five-inch diameter body tubing instead of four-inch tubing. This choice was driven by the design of the tanks for the liquid propulsion system. The team also placed a much greater emphasis than past teams had put on designing all components to be as compact and light at possible.
==Avionics==
==Avionics==
The avionics system consists of multiple custom printed circuit board assemblies (PCBAs), which used direct board-to-board interconnects to eliminate the use of wires.
The avionics system consists of multiple custom printed circuit board assemblies (PCBAs), which used direct board-to-board interconnects to eliminate the use of wires. Olympus 2019 changed the layout of the avionics bay from using long vertical PCBs to be made up of a stack of circular PCBs to more minimize the size of the avionics bay.
The main boards in the avionics system are:
The main boards in the avionics system are:
==Recovery==
==Recovery==
The recovery system consists of the parachutes that are used to safely recovery the rocket, along with the hardware required to deploy those parachutes in flight. The recovery system uses a serial deployment system. The rocket is separated at apogee using a CO2 charge, and the drogue is deployed when the rocket separates. The main is held in a deployment bag for the majority of descent, and then is released and pulled out by the drogue at 1500ft.
In past [[IREC 2017]] and [[IREC 2018]] the recovery team struggled to deploy the main parachute. In 2019, the team attempted to fix this issue by loosening the deployment bag. This led to deploying the main at apogee in the first two test launches before deploying at the correct altitude on the third test launch.
==Structures==
==Structures==