PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in •...
Transcript of PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in •...
![Page 2: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/2.jpg)
Preliminary Design Review
Presenters: Aaron Skiba - [email protected]
Patrick Kellam - [email protected]
Britton Bush - [email protected]
Leslie Davies -
Jeremy Jones – [email protected]
Matt Schottler - [email protected]
![Page 3: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/3.jpg)
Initial Vehicle Dimensions
• Length - 75.075 in
• Diameter - 3.13 in
• Span Diameter - 9.63 in
• Mass - 152.49 oz
• CG - 52.57 in
• CP - 56.73 in
• Margin - 1.34
![Page 4: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/4.jpg)
Initial Vehicle Materials
• 3 - 3in Phenolic Tubes
• 2 - 2.942in Phenolic Couplers
• 3 - G10 Fiberglass Delta Fins
• 1 - 18in Drogue Parachute
• 1 - 36in Main Parachute
• Rip-Stop Nylon Chord
• 1 - 17.5in Phenolic Motor Mount (54mm opening)
• 1 - 17.5in Phenolic Motor Mount (75mm opening)
![Page 5: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/5.jpg)
Material Justification
• Phenolic Tubing - High strength to weight ratio, ease of
handling (e.g. painting, bonding and finishing), low-cost.
• G10 Fiberglass - High strength and low cost
• Drogue Parachute - decreases sway and drift
• Rip-Stop Nylon - resistance to tearing, light weight, durability
![Page 6: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/6.jpg)
Motor Design
• Aluminium sleeve, with nozzle, to secure position
• The inner motor mount will be secured to the airframe
via 3 quarter inch thick plywood centering rings and the
G10 fiberglass fins.
• Two motor option
![Page 7: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/7.jpg)
Static Stability Margin
• Static Margin for the CanSat-1 is 1.34.
• This margin is considered stable for the proposed rocket
• This assumption was verified through a RockSim Simulation
![Page 8: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/8.jpg)
•Inspect fins and motor mount to ensure secure attachment
•Fold parachute and shock cord to avoid tangling
•Arm ejection charges only when rocket is on launch pad
•Install igniters only when rocket is on launch pad
Vehicle Safety Verification
![Page 9: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/9.jpg)
•Ejection charges tested using static fire test and flight
computer
•NAR regulations obeyed
•Open area at launch site and in flight path
•“Heads up” shout given at launch
•Vehicle transported in separate compartment
Vehicle Safety Testing
![Page 10: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/10.jpg)
Engine
• 54 mm Cesaroni J401BB engine
• Justification:
Rocksim simulation estimates
altitude of 5,563 ft. – Well within
10% goal
![Page 11: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/11.jpg)
Thrust to Weight Ratio
• Average Thrust - 400N
• Weight of Rocket - 9.53lb
• Thrust to Weight Ratio - 41.97 N/lb
![Page 12: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/12.jpg)
State Laws Pertaining to
Motor Safety
Michigan State Law Compliance procedure
Motors containing
Ammonium Perchlorate =
Explosive
We understand the explosive
natural of the rocket engines
If not stored must use in 24
hours
Rockets will be ordered at
appropriate timing
If stored contact Fire
Personal
Fire Personal will be
contacted if we choose to
store engines
![Page 13: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/13.jpg)
Motor Safety Verification
Dual Deploy Recovery
System
• Verification of motor through full scale testing
• Full scale test at Jackson Model Rocketry Club meeting
• Motor system based of off previously verified systems
– System similar to MASA’s past rockets
• Verified through rocksim simulation
![Page 14: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/14.jpg)
Baseline Payload Design
• Compact cylindrical structure that fits snuggly inside
payload bay of rocket to reduce vibrational effects of
flight until deployment
• Shape and size matching with rocket for ease of
deployment
• External switch to reduce energy waste during
packaging and integration.
• Indicator light to verify operation after initial integration
and before final launch perparation
![Page 15: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/15.jpg)
Payload Design (Cont’d)
• Descent Control device deploys upon ejection from payload bay
• Forms an umbrealla-type structure to create drag
• Brightly colored
webbing for
visual
identification
• No risk of
tangled
parachute strings
![Page 16: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/16.jpg)
Structure Safety Verification
• Multiple drop tests from low altitudes
– First in low wind, controlled pressure and temperature environments (i.e. from
upper floor of indoor structure)
– Secondly in variable atmospheric conditions (i.e. from a land spanning bridge
with ease of access to lower level.
• Webbing material adjustment early in project
![Page 17: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/17.jpg)
Data Collection
Safety Verification
• Using tested data collection components
• Running multiple ground tests before deployment
• Collecting test data during low altitude tests
• Using low altitude data to estimate errors since distances and times can
easily be measured on the ground and compared to the collected data
![Page 18: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/18.jpg)
Recovery System Design
• Dual Deploy system
– 18” drogue parachute deployed at apogee
• Spill holes of 4 and 8 inches
– 36” main parachute deployed at desired altitude
• ARTS2 Flight Computer controls delayed blasts
– Ideal for Dual Deploy system
![Page 19: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/19.jpg)
•Controls deployment of parachutes
•Barometric and accelerometer sensors
•Timer
•Supports 2 batteries which ignite charges
•Store in-flight data
ARTS2 Flight Commputer
![Page 20: PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in • Diameter - 3.13 in • Span Diameter - 9.63 in • Mass - 152.49 oz • CG - 52.57](https://reader034.fdocumento.com/reader034/viewer/2022043002/5f7dbd2ff54342671d7cf3a6/html5/thumbnails/20.jpg)
Recovery System
Verification
• Verification test at full scale launch
• Recovery Sub-systems verification prior to launch
– Flight Computer undergo computational simulations
– Nylon cords apply predicated applied stresses to cords
– Parachutes parachutes will be dropped from designated
heights to calculate rate of descent and verify function ability
• Integration of Systems will be verified in full scale launch