PDR: CanSat-1.

Transcription

1 PDR: CanSat-1

2 Preliminary Design Review Presenters: Aaron Skiba - skiba@umich.edu Patrick Kellam - pjkellam@umich.edu Britton Bush - britbush@umich.edu Leslie Davies - Jeremy Jones jonjerm@umich.edu Matt Schottler - mshot@umich.edu

3 Initial Vehicle Dimensions Length in Diameter in Span Diameter in Mass oz CG in CP in Margin

4 Initial Vehicle Materials 3-3in Phenolic Tubes in Phenolic Couplers 3 - G10 Fiberglass Delta Fins 1-18in Drogue Parachute 1-36in Main Parachute Rip-Stop Nylon Chord in Phenolic Motor Mount (54mm opening) in Phenolic Motor Mount (75mm opening)

5 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

6 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

7 Static Stability Margin Static Margin for the CanSat-1 is This margin is considered stable for the proposed rocket This assumption was verified through a RockSim Simulation

8 Vehicle Safety Verification 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

9 Vehicle Safety Testing 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

10 Engine 54 mm Cesaroni J401BB engine Justification: Rocksim simulation estimates altitude of 5,563 ft. Well within 10% goal

11 Thrust to Weight Ratio Average Thrust - 400N Weight of Rocket lb Thrust to Weight Ratio N/lb

12 State Laws Pertaining to Motor Safety Michigan State Law Motors containing Ammonium Perchlorate = Explosive If not stored must use in 24 hours If stored contact Fire Personal Compliance procedure We understand the explosive natural of the rocket engines Rockets will be ordered at appropriate timing Fire Personal will be contacted if we choose to store engines

13 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

14 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

15 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

16 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

17 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

18 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

19 ARTS2 Flight Commputer Controls deployment of parachutes Barometric and accelerometer sensors Timer Supports 2 batteries which ignite charges Store in-flight data

20 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