https://ssi-wiki.stanford.edu/w/index.php?action=history&feed=atom&title=ArgusArgus - Revision history2026-05-11T05:29:15ZRevision history for this page on the wikiMediaWiki 1.45.1https://ssi-wiki.stanford.edu/w/index.php?title=Argus&diff=3321&oldid=prevRwong: Page creation2017-10-22T21:42:53Z<p>Page creation</p>
<p><b>New page</b></p><div>The Argus team is one of the 2017-18 Daedalus Projects focused on designing a rocket dedicated to developing a wirelessly-activated camera network and live video telemetry.<br />
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{{rocket-project<br />
| header = Argus<br />
| img link =<br />
| launch details = <br />
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{{rocket-launch<br />
|number=1<br />
|launch class = Pending<br />
|launch date = Pending<br />
|launch site = Pending<br />
|next={{rocket-launch<br />
|number=2<br />
|launch class = Pending<br />
|launch date = Pending<br />
|launch site = Pending<br />
|next={{rocket-launch<br />
|number=3<br />
|launch class = Pending<br />
|launch date = Pending<br />
|launch site = Pending<br />
}}<br />
}}<br />
}}<br />
<br />
| program = Project Daedalus<br />
| next = Charybdis<br />
}}<br />
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= Team Summary =<br />
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* Person 1 - Team Lead?<br />
* Person 2 - Structures Lead<br />
* Person 3 - etc etc<br />
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= Launch Vehicle and Payload Summary =<br />
<br />
* Expected Apogee: xx ft<br />
* Payload: xx<br />
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= Vehicle Criteria =<br />
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== Mission Success Criteria ==<br />
''EXAMPLE''<br />
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The mission will be considered successful if the recovered rocket would be able to pass a L3 certification inspection. This means that if the rocket experiences excessive damage to the point that it could not be re-flown that day with a reloaded motor, then the recovery system will have failed. Another criteria is that the rocket will have landed within a 300ft radius of its original target landing space.<br />
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== Constraints ==<br />
''EXAMPLE''<br />
<br />
# Tripoli height ceiling of 16,800 ft<br />
# Rocket construction to be made using a “minimum of metallic parts” excepting those necessary for airframe integrity<br />
# Motor impulse to not exceed 10,240 N-s<br />
# Redundant avionics, wiring, and safe arm systems<br />
# Automated program for descent path<br />
# Manual back up control system for descent path<br />
# Back up recovery system consisting of main parachute<br />
# Vertical descent speed of 20 ft/s maximum upon landing<br />
# Budget<br />
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= Manufacturing and Assembly =<br />
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''What are you making the rocket out of? What manufacturing processes? Who has oversight over assembly? What considerations are affecting your choices for materials, processes, workflow? ''<br />
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= Systems Integration and Testing =<br />
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== Major Event Timetable==<br />
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{| class="wikitable"<br />
|-<br />
! Date<br />
! Event<br />
! Objectives<br />
|-<br />
| Soon<br />
| PDR<br />
| Full CAD, prototyped xyz<br />
|- <br />
| Someday<br />
| Launch 1 <br />
| Expected apogee: some# ft; x # of things do these things<br />
|}<br />
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= Risk Management =<br />
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== Safety Hazards ==<br />
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''EXAMPLE''<br />
<br />
<br />
{| class="wikitable"<br />
|-<br />
! Risk<br />
! Likelihood<br />
! Consequence<br />
! Mitigation<br />
|-<br />
| Ematches don't ignite<br />
| Medium<br />
| High - No separation event; descent at terminal velocity<br />
| Redundant ematch events on heterogeneous altimeter systems<br />
|-<br />
| Parachute tangles<br />
| High<br />
| Medium - descent > recommended 20 ft/sec<br />
| Extensive ground testing; procedural method for packing parachutes according to best practices<br />
|}<br />
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== Budget Risks ==<br />
<br />
''EXAMPLE''<br />
<br />
<br />
{| class="wikitable"<br />
|-<br />
! Risk<br />
! Likelihood<br />
! Mitigation<br />
|-<br />
| Overspend on machining parts<br />
| Medium<br />
| Measure thrice, cut once; MATH<br />
|-<br />
| Unknown motor choices<br />
| High<br />
| Allocate x% margin for motor purchases for x test flights<br />
|}<br />
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[[Category: Daedalus]]<br />
[[Category: Rockets]]<br />
[[Category: Documentation]]</div>Rwong