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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.
{{rocket-project
| header = Argus
| img link =
| launch details =
{{rocket-launch
|number=1
|launch class = Pending
|launch date = Pending
|launch site = Pending
|next={{rocket-launch
|number=2
|launch class = Pending
|launch date = Pending
|launch site = Pending
|next={{rocket-launch
|number=3
|launch class = Pending
|launch date = Pending
|launch site = Pending
}}
}}
}}
| program = Project Daedalus
| next = Charybdis
}}
= Team Summary =
* Person 1 - Team Lead?
* Person 2 - Structures Lead
* Person 3 - etc etc
= Launch Vehicle and Payload Summary =
* Expected Apogee: xx ft
* Payload: xx
= Vehicle Criteria =
== Mission Success Criteria ==
''EXAMPLE''
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.
== Constraints ==
''EXAMPLE''
# Tripoli height ceiling of 16,800 ft
# Rocket construction to be made using a “minimum of metallic parts” excepting those necessary for airframe integrity
# Motor impulse to not exceed 10,240 N-s
# Redundant avionics, wiring, and safe arm systems
# Automated program for descent path
# Manual back up control system for descent path
# Back up recovery system consisting of main parachute
# Vertical descent speed of 20 ft/s maximum upon landing
# Budget
= Manufacturing and Assembly =
''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? ''
= Systems Integration and Testing =
== Major Event Timetable==
{| class="wikitable"
|-
! Date
! Event
! Objectives
|-
| Soon
| PDR
| Full CAD, prototyped xyz
|-
| Someday
| Launch 1
| Expected apogee: some# ft; x # of things do these things
|}
= Risk Management =
== Safety Hazards ==
''EXAMPLE''
{| class="wikitable"
|-
! Risk
! Likelihood
! Consequence
! Mitigation
|-
| Ematches don't ignite
| Medium
| High - No separation event; descent at terminal velocity
| Redundant ematch events on heterogeneous altimeter systems
|-
| Parachute tangles
| High
| Medium - descent > recommended 20 ft/sec
| Extensive ground testing; procedural method for packing parachutes according to best practices
|}
== Budget Risks ==
''EXAMPLE''
{| class="wikitable"
|-
! Risk
! Likelihood
! Mitigation
|-
| Overspend on machining parts
| Medium
| Measure thrice, cut once; MATH
|-
| Unknown motor choices
| High
| Allocate x% margin for motor purchases for x test flights
|}
[[Category: Daedalus]]
[[Category: Rockets]]
[[Category: Documentation]]
{{rocket-project
| header = Argus
| img link =
| launch details =
{{rocket-launch
|number=1
|launch class = Pending
|launch date = Pending
|launch site = Pending
|next={{rocket-launch
|number=2
|launch class = Pending
|launch date = Pending
|launch site = Pending
|next={{rocket-launch
|number=3
|launch class = Pending
|launch date = Pending
|launch site = Pending
}}
}}
}}
| program = Project Daedalus
| next = Charybdis
}}
= Team Summary =
* Person 1 - Team Lead?
* Person 2 - Structures Lead
* Person 3 - etc etc
= Launch Vehicle and Payload Summary =
* Expected Apogee: xx ft
* Payload: xx
= Vehicle Criteria =
== Mission Success Criteria ==
''EXAMPLE''
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.
== Constraints ==
''EXAMPLE''
# Tripoli height ceiling of 16,800 ft
# Rocket construction to be made using a “minimum of metallic parts” excepting those necessary for airframe integrity
# Motor impulse to not exceed 10,240 N-s
# Redundant avionics, wiring, and safe arm systems
# Automated program for descent path
# Manual back up control system for descent path
# Back up recovery system consisting of main parachute
# Vertical descent speed of 20 ft/s maximum upon landing
# Budget
= Manufacturing and Assembly =
''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? ''
= Systems Integration and Testing =
== Major Event Timetable==
{| class="wikitable"
|-
! Date
! Event
! Objectives
|-
| Soon
| PDR
| Full CAD, prototyped xyz
|-
| Someday
| Launch 1
| Expected apogee: some# ft; x # of things do these things
|}
= Risk Management =
== Safety Hazards ==
''EXAMPLE''
{| class="wikitable"
|-
! Risk
! Likelihood
! Consequence
! Mitigation
|-
| Ematches don't ignite
| Medium
| High - No separation event; descent at terminal velocity
| Redundant ematch events on heterogeneous altimeter systems
|-
| Parachute tangles
| High
| Medium - descent > recommended 20 ft/sec
| Extensive ground testing; procedural method for packing parachutes according to best practices
|}
== Budget Risks ==
''EXAMPLE''
{| class="wikitable"
|-
! Risk
! Likelihood
! Mitigation
|-
| Overspend on machining parts
| Medium
| Measure thrice, cut once; MATH
|-
| Unknown motor choices
| High
| Allocate x% margin for motor purchases for x test flights
|}
[[Category: Daedalus]]
[[Category: Rockets]]
[[Category: Documentation]]