Changes

[[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 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. 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 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.

=Overview=

=Overview=

=Goals and Requirements=

=Goals and Requirements=

The goal of the rocket design was to be capable of delivering an 8.8 pound payload to an altitude of 30,000 feet while employing as much student innovation as possible.

The goal of the rocket design is to be capable of delivering an 8.8 pound payload to an altitude of 30,000 feet while employing as much student innovation as possible.

=System Design=

=System Design=

Unlike the year before, the Olympus 2019 rocket used 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.

==Avionics==

==Avionics==

The avionics system consisted 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.

The main boards in the avionics system were:

The main boards in the avionics system are:

* [[SpaceSalmon]], a rocket flight computer developed by [[User:timv|Tim Vrakas]], both for Olympus and for [[Spaceshot]].

* [[SpaceSalmon]], a rocket flight computer developed by [[User:timv|Tim Vrakas]], both for Olympus and for [[Spaceshot]].