PDR: CanSat-1jgrohosk/usli/pdrPresentation.pdfInitial Vehicle Dimensions • Length - 75.075 in •...

PDR: CanSat-1

masacontact@umich.edu

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

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

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)

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

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

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

•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

•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

Engine

• 54 mm Cesaroni J401BB engine

• Justification:

Rocksim simulation estimates

altitude of 5,563 ft. – Well within

10% goal

Thrust to Weight Ratio

• Average Thrust - 400N

• Weight of Rocket - 9.53lb

• Thrust to Weight Ratio - 41.97 N/lb

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

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

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

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

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

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

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

•Controls deployment of parachutes

•Barometric and accelerometer sensors

•Timer

•Supports 2 batteries which ignite charges

•Store in-flight data

ARTS2 Flight Commputer

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