Difference between revisions of "Olympus 2019"
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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 | + | 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= | ||
| Line 7: | Line 7: | ||
=Goals and Requirements= | =Goals and Requirements= | ||
| − | The goal of the rocket design | + | 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 | + | 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 | + | 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 | + | 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]]. | ||
Revision as of 04:53, 7 March 2019
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
Goals and Requirements
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
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
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 are:
- SpaceSalmon, a rocket flight computer developed by Tim Vrakas, both for Olympus and for Spaceshot.
- COTS Carrier, a board designed by Shreya Ravi to interface a Stratologger commercial altimeter to the rest of the avionics system.
- RF Carrier, a board designed by Albert Landa which was the interface between the avionics bay, the GPS module, and the S6C long-distance radio.
- Bulkhead Board, the interface between the avionics bay and the e-match connectors, designed by Jainil Sutaria.
Recovery
Structures
Payload
Propulsion
Staging
Test Launches
Launch 1, March 2nd at FAR
Launch 1 tested all systems at some level of functionality, except for propulsion. The rocket flew to an altitude of approximately 8,000 feet. The main parachute deployed at apogee, which, along with 20 mph winds, caused the rocket to drift 3.6 miles downrange before landing.