Cansat2015_5251_PDR

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CanSat 2015 PDR: Team 5251, CosmoKnights 1

CanSat 2015

Preliminary Design Review (PDR)

Team #: 5251

Team: CosmoKnights

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Presentation Outline

Presenter: Hunter Williams

Introduction/ Outline Hunter Williams

System Overview Clayton Lambert

Sensor Subsystem Design Lietsel Richardson

Descent Control Design Vincent Coment

Mechanical Subsystem Design Jeremy Woodward

Communication and Data Handling (CDH) Subsystem Design Clayton Lambert

Electrical Power Subsystem (EPS) Design Philip Lane

Flight Software (FSW) Design Lietsel Richardson

Ground Control System (GCS) Design Philip Lane

CanSat Integration and Test Kyle Steunenberg

Mission Operations & Analysis Ethan Christian

Requirements Compliance Ethan Christian

Management Hunter Williams

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Team Organization


Faculty Advisor:

Jeffrey Kauffman

Team Lead:

Hunter Williams Junior

Structures Lead:

Jeremy Woodward Senior

Structures and Compliance Engineer:

John Christian Senior

Aerodynamic Engineer:

Vince ComentSenior

Structures Engineer:

Kyle Steunenberg Junior

Electronics Lead:

Clayton Lambert Junior

Electrical Engineer:

Phillip Lane

Junior

Technologist:

Lietsel Richardson

Junior

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Acronyms


ACRONYMS

A Microamperes CDR Critical Design Review g Gram

A Cross-sectional Area CFD Computational Fluid Dynamics G Gravity

ABS

Acrylonitrile butadiene

styrene cm Centimeters GCS Ground Control System

AIAA

American Institute of

Aeronautics and

Astronautics dbi Decibels GHz Gigahertz

C_d Coefficient of Drag EPS Electronic Power System GUI Graphic User Interface

CAD Computer Assisted Design FSW Flight Software Hz Hertz

CDH

Communication and Data

Handling FTDI

Future Technology Devices

International kB Kilobytes

ACRONYMS CONTINUED

kPa Kilopascals N/A Not Applicable SGA Student Government Association

Li-ion Lithium Ion NetID Network Identification UCF University of Central Florida

m/s Meters per Second PDR Preliminary Design Review USD United States Dollar

m_sv Mass of Science Vehicle rad/s Radians per Second v Velocity

m_t Total Mass Rev Revision V Voltage

Mm Millimeters Rho Density VDC Direct Current Voltage

mWh Miliwatt Hours RT Total Resistance Vout Voltage Out

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Systems Overview

Clayton Lambert

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(If You Want) Systems Overview

Systems overview explains the requirements of the mission

Discusses preliminary considerations and designs

Presents layout of vehicle

Demonstrates Concepts of CONOPS

6Presenter: Clayton Lambert Cansat 2015 PDR: Team 5251, Cosmoknights

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Mission Summary

Presenter: Clayton Lambert

External Objectives:

To follow the AIAA UCF mission of addressing the academic needs of the students through introducing new engineering practices and principles.

Selectable Objective:

To use an accelerometer to record external forces, resultant position and orientation.

Rationale: Will serve as an interface with the active stabilization system

The Mission Objective: To successfully design, build,

fly, and recover a science vehicle.

To collect and transmit atmospheric data to the ground

station.

To protect the payload during ascent and descent

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(If You Want) System Requirement Summary

CanSat 2015 PDR: Team 5251, CosmoKnights 8Presenter: Clayton Lambert

ID Requirement Priority Status

SR-01 Weigh 600 grams +/- 10

grams not including the egg.

High Planned design meets

requirements

SR-02 Science Vehicle shall be

completely contained in the

Container


requirements

SR-03 Container and Parachute

shall comply with payload

space specifications

Medium Planned design meets

requirements

SR-04 Container shall deploy from

the payload with ease


requirements

SR-05 Comply with all descent

requirements


requirements

SR-06 Comply with all

communication

requirements


requirements

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(If You Want) System Requirement Summary


ID Requirement Priority Status

SR-07 Comply with all recovery

requirements


requirements

SR-08 Meet all shock requirements High Planned design meets

requirements

SR-09 Meet all Environmental

Safety requirements


requirements

SR-10 Collect and transmit all

required data


requirements

SR-11 Restrict video rotation to

90 degrees


requirements

SR-12 Budget less than $1000 High Planned design meets

requirements

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System Level CanSat Configuration

Trade & Selection

Considerations

Lower lift to mass/weight ratio

More compact for limited space

Concerns

Higher risk of creating a moment and torque

Pitch, yaw, and roll stabilization

Generating proper lift for required controlled descent

rate limits


Final Design: Single Rotor Configuration

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Trade & Selection

Considerations

Stacking rotors allows more compact fitment

Gyroscopic properties controls torsion

Concerns

Generating proper lift for required controlled descent

rate limits

Higher mass requirement Requires taller container

More rotors and components


Preliminary Design: Counter-spinning Coaxial Rotor

Configuration

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Trade & Selection

Considerations

Larger rotors for greater lift

Stability control Yaw control

Concerns

Achieve equal lift from all blades

Stabilization

Pitch and roll control

Increase in mass budget More rotors, and rotor

assemblies

Deployment from container


Preliminary Concept: Quad-Rotor Configuration

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Trade & Selection

Single Rotor System was chosen as the best overall vehicle design for the mission requirements and

parameters


Design Mass

(1-5)

Internal space

(1-5)

Lift

(1-5)

Stability

(1-5)

Deployment

(1-5)

Quad-Rotor 1 2 5 3 1

Coaxial Rotor 3 3 3 2 2

Single Rotor 5 4 3 2 4

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Physical Layout- Science Vehicle


RotorsEgg

Payload

Electronics

Bay

Camera

Total Vehicle Height: 231.33mm

Wingspan: 525.05mm

Folded Width: 100mm

Height = 231.33mm

Folded Width = 100 mm

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Physical Layout- Container


Dimensions:

Total Container Height: 220mm

Inner Diameter: 118mm

Outer Diameter: 120mm

Composition:

Material: Carbon Fiber Composite

Color: Orange

Parachute attachment ring

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(If You Want) Relevant Configuration

16Presenter: Clayton Lambert CanSat 2015 PDR: Team 5251, CosmoKnights

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Launch Vehicle Compatibility


Pre-Launch Verification

Replica rocket payload will be constructed to specifications prior to launch date

CanSat Integration into Rocket Payload

Container will be positioned upside down in the rocket

payload

Container parachute will rest between container and

payload

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Launch Vehicle Compatibility and

Container Layout


Total Height = 310mm

Total Width = 125mm

Width Clearance: 5mm

Height Clearance: 100mm

Height clearance allows for fitment of the parachute.

Height = 210mm

Width= 120 mm

Total Container Height: 220mm

Inner Diameter: 118mm

Outer Diameter: 120mm

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Sensor Subsystem Design

Lietsel Richardson

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Sensor Subsystem Overview and

Requirements

Presenter: Lietsel Richardson

The sensor subsystem overview consists of the requirements

and trade studies for the following sensors:

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Sensor Subsystem Overview and

Requirements


Part Model

Number

Purpose Sub-

system

Requirement Implementation

Inertial

Measurement Unit

Razor component

ITG-3200 3 axis gyroscope

temperature

Vehicle Vehicle must stabilize

itself during fall as well as

record video facing earth

Serves to orientate the vehicle

during decent for nadir facing video,

records inside temperature

Inertial

Measurement Unit

Razor component

ADXL345 3 axis

accelerometer

Vehicle Vehicle must not rotate +/-

90 degrees, measure the

stability and angle of

descent of the Science

Vehicle during descent

Detects liftoff, contributes to

stabilization, senses landing impact

Inertial

Measurement Unit

Razor component

HMC5883L 3 axis

magnetometer

Vehicle Vehicle must not rotate +/-

90 degrees

Orientates vehicle to adjust rotational

procession

Altitude/Pressure

Sensor Breakout

MPL3115A2 Altitude,

pressure,

temperature

Vehicle /

Container

Data needs to be recorded

and transmuted as base

mission requirement

Detects pressure to predict altitude

necessary for stage progression,

Records outside temperature

Wire Connecting all

electronic

components

Vehicle/

Container

Physical connection for

peripheral devices to

microcontroller and power

Bridges i2c connection to relay data

as well as powers sensors

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Altitude Sensor Trade & Selection


Altitude/Pressure Unit Cost

(USD)

Weight (g) Amperage

(A)

Operating

Voltage

Range (V)

Accuracy

(kPa)

Dimensions

(mm)

Sample

Rate (Hz)

MPL3115A2 $14.95 1 40 1.96 3.60 .05 5.00 x 3.00 x

1.10

1.00

T5403 $14.95 6.50 790 1.70 3.60 0.015 2.78 x 2.23 x

.67

33.00

Sensor Chosen: MPL3115A2

Lowest weight

Reasonable cost

Less Amperage usage, aids in battery

lifetime

Operating voltage coincides with Arduinos

output

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IMU Trade & Selection


Altitude/Pressure Unit Cost (USD) Weight (g) Operating Voltage

Range (V)

Dimensions (mm) Sample

Rate (Hz)

SEN-10736 $74.95 22 g 3.5-16V 28 x 41mm 50 Hz

SEN-10121 $39.95 10 g 3.3V 15 x 17mm 20 Hz

Sensor Chosen: SEN-10736

Highly accurate

Greater operating voltage range

Other option suffers from drift

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Air Temperature Sensor

Trade & Selection

Sensor Chosen: TMP36

Lower cost

Wide operating range

Low weight

High sample rate

No external calibration required

Adequate Accuracy


Part Price (USD) Weight (g) Resolution

(Bits)

Connection

Type

Dimmension

s (mm)

Sample rate

(Hz)

TMP102 5.95 9g 12 I2C 1.6 x 1.6 4

TMP36 1.5 5.67 12 Serial 5.08 x 5.08 8.33

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Camera

Trade & Selection

Camera Chosen: 808 Car Key chain spy Camera

Lowest cost

Adequate video

Most compact dimensions

Weighed the least

Timestamp complies with requirement 28


Part Price(USD) Resolution(p) Dimensions(mm) Weight(g)

808 Car Key

Chain Spy

camera Recorder

7.50 720 32x51x13 19

HackHD 164.95 1080 25.4 x 76.2 28.3

Hidden Spy Ped

HD

35 1280 11.76 x 70mm 136

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3-Axis Accelerometer Sensor

Trade & Selection

Sensor Chosen: ITG-3200

Sample rate is far superior (overclocking feature)

ITG-3200 is integrated into Inertial measurement unit

Smaller footprint on board


Part Price (USD) Current

Draw (ma)

Resolution

(Bits)

Connection

Type

Dimensions

(mm)

Sample

rate (Hz)

ITG-3200 24.95 6.5 16 I2C 4x4x0.9 400kHz

Adxl335 14.95 0.35 16 I2C 4x4x1.45 50

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Descent Control Design

Vincent Coment

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Descent Control Overview

Presenter: Vincent Coment

The descent control overview:

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Decent Control System

Requirements


Sub-system Requirements Implementation

Spill hole parachute Avoid free fall Reduce oscillation in air

Bottom Geometry Survive 50 Gs of

shock

Impact the ground at a

controlled velocity

Auto gyro blades Descent speed less

than 10 m/s and

greater than 4 m/s

Maximum angular velocity

between 100 105 rad/s, at a 6.4 m/s descent rate.

Auto gyro blades No miscellaneous

materials between

the blades

ABS 3D printed blades will help

to trim out all the blades in twist

and taper

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Container Descent Control Strategy

Selection and Trade

Parachute chosen: Nylon PAR-30TM

Compact and Light weight

Durable

Shroud is less likely to tangle

Most Affordable


Parachute Parachute

Size (cm)

Shroud

Lines

Shape Descent

Rate Pre-

Deployment

(m/s)

Descent

Rate Post-

Deployment

(m/s)

Mass (g) Cost

(USD)

Nylon

PAR-

24TM

61 6 Circle 6.72 2.63 17 11.95

Nylon

PAR-

30TM

76 8 Circle 5.37 2.1 28 16.95

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Descent Rate Estimates


Container and science vehicle together: Approximately 6 m/s

Pre Separation Descent Rate

Container: 2.4 m/s Science Vehicle: 6.4 m/s

Post Separation Descent Rate

Pre separation Calculations

=2

Does not include spill hole

Post Separation Calculations

=2()

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Mechanical Subsystem Design

Jeremy Woodward

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Mechanical Subsystem Overview

Presenter: Jeremy Woodward

The Mechanical Subsystem section includes:

Overview of the structural design research and choices

Trade studies and rationale

Overview of requirements

Discussion and trade studies on subsystem components

Mass budget

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Mechanical Subsystem Overview

Aluminum Hexagonal plate

platform

Carbon Fiber Monocoque

Carbon Fiber Frame


Container to Payload interface

Payload suspended in container with Nichrome wire Nichrome wire to be wrapped to avoid conflagration

Electronics Black Box

Egg Container

Rotor Hub/Blades

Structural Designs Mechanical Components

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Structural Design Trade Study &

Selection Aluminum Hex Plate

Pros

cheap

easily accessible

good isotropic strength to density ratio

Cons

complex shapes of the hexagonal plates make soldering unreasonable

final weight for 50g shock loading too high

thickness of rods required gave less usable internal space


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Selection Monocoque

Pros

light

spacious

extremely high strength to weight ratio

Cons

higher cost of materials

cannot easily connect the rotating electronics frame to the outside air for atmospheric readings

too heavy when made to survive 50g


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Selection Carbon Fiber Frame

Pros

simple construction

easiest to build

lowest final weight of any design, as only electronics shielded

Cons

slightly more expensive


Chosen design, as it meets or

exceeds all design requirements.

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Design Choice Rationale

RationaleDifferent format from trade studies

Multiplicity of related factors

Variability in strengths and weaknesses

Numerical model adopted to assist in selection

CriteriaCriteria used: cost, strength, weight, cost to build, safety, and internal space

Weighted evenly

Dramatic differences expressed through higher score

DefinitionsCost: cost of materials

Strength: buckling strength, elasticity, rigidity, fire resistance, etc.

Weight: weight of total design, not including electronics box

Cost to build: cost of either shop fees or equipment needed for building

Safety: as all designs safe for CanSat participants, this mostly detailed safety in manufacturing

Internal space: volume and shape allotted for electronics package


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Structural Design Choice Chart


As simple and lightweight as possible, while being able to shield the egg from the impact shock.

3D printed from ABS for both lower weight and the complexity of the fillets in the design.

Fillets important to reduce stress concentration.

Design Cost Strength Weight Ease to build Safety Internal

Space

Hex Plate

Platform

5 5 2 1 5 1

Carbon Fiber

Monocoque

3 4 3 3 4 5

Carbon Fiber

Frame

2 5 4 5 4 3

*Note: 5 is best, 1 is worst

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Mechanical Sub-System

Requirements


# Requirement Description Sub-system Rationale

1 All Every system is designed

with weight saving in mind.

2 The Science Vehicle will fit inside a container

that must fit into a 125mmX310mm envelope.

Rotor Hub Rotor blades fold along

body to fit in container.

3 All structures shall be built to survive 30 Gs of

shock and 15Gs of acceleration.

Carbon Fiber

Frame

Frame designed to absorb

impact shock

4 During descent, the video camera must not

rotate.

Electronic Black

Box

Servo/Ring Gear allows

camera to counter rotate

5 The vehicle must stabilize and collect data at an

altitude of 300m

Nichrome wire SV will release at 600m to

allow the blades to get to

top speed

6 Vehicle will descend between 4 and 10 m/s. Rotor Hub/Blades Sufficient lifting surface and

geometry to achieve this

terminal velocity

7 Egg will survive impact at maximum of 10 m/s. Egg

Container/Sabot

Memory foam sabot will

protect the egg from shock

Total weight must be under 600 grams.

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Rotor Hub / Rotor Blades


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Selection


Egg Container

As simple and lightweight as possible, while being able to

shield the egg from the impact

shock.

3D printed from ABS for strength to weight ratio and

complexity of the fillets in the

design.

Fillets important to reduce stress concentration.

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Egg Protection Trade & Selection


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Final Configuration Selection

Cylindrical container

Composed of ABS.

Memory foam chosen as cushioning due to a greater success rate during testing.

CanSat 2015 PDR: Team 5251, CosmoKnights 44Presenter: Jeremy Woodward

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Material Composition Cost Weight Pros Cons

Memory

Foam

Sponge like

absorbing

material.

$2.00 per

pound

11.8

grams

Great Protection

Weight Price

Availability

Packing

Peanuts

Styrofoam

Material

$9.00 for

1.5 Cubic

Feet

0.57

Grams

Light Cheap

Weaker than other

options

Polystyrene

Balls

Polystyrene $16.00 for

3 Cubic

Feet

2.95

grams

Light Cheap Packs

Well

Not as protective

as memory

foam.

CanSat 2015 PDR: Team 5251, CosmoKnights 45Presenter: Jeremy Woodward

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Electronics Black Box Subsystem

Plastic container meant to hold the electronics

Spins on an axle using a servo and ring gear

Small to allow atmospheric readings from outside and inside the box

Emergency off switch included

Actively complies with requirements 17, 21, 30, 42, 43


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Electronics Black Box Subsystem

Ring Gear/ Motor view

Bottom View

Top

view


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Mechanical Layout of Components

Trade & Selection

RotorsEgg

Payload

Electronics

Bay

Camera

Total Vehicle Height: 231.33mm

Wingspan: 525.05mm

Folded Width: 100mm

Height = 231.33mm

Folded Width = 100 mm


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(If You Want)Material Selections


ABS (Acrylonitrile Butadiene Styrene) Designer friendly Cheap Good strength to weight ratio

Egg Container Rotor Assembly

Black Box

Light weight Strong material Easy to form into shape of container

Carbon Fiber Plates

Container

Aluminum Light weight Sufficient strength Readily available for reasonable price

Fasteners

Steel Readily available Greater torque to weight ratio

Torsion Spring


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Container - Payload Interface

Mechanical Method


A servo motor will turn the connecting rod and threaded rod

The container rod will remain stationary, causing the nut to unscrew

A compressed spring will assist final separation

The Container bolt will remain attached to the container removing interference with descent control apparatus

Science Vehicle Separation

Little operational uncertainty Adds structural support Will utilize a switch or command to

insert and remove payload from container via threading

Benefits

Mass addition

Concerns

Container

bolt

Threaded

nut

Connecting

rod

Servo

motor

Container

bolt


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Nichrome wire wrapped around nylon twine

Science vehicle frame secured with nylon twine

Small current separates Nichrome and twine

Science Vehicle Separation

Small amount of nylon melted Electrical wire hole well sealed Nichrome never reaches

environment

3mm clearance between rotor blades and container

Safety

Container

(inside view)

Anchor for wire

Nylon cord

Nichrome wire for

separating nylon

cord

Electronics box


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(If You Want) Structure Survivability Trades

Option Cost Weight Effectiveness Ease to build

Monocoque 1 2 2 3

Black Box 3 4 4 5


Electronics Enclosure

Option Cost Weight Effectiveness Reusable

Aluminum Screws 2 2 3 5

Epoxy 3 4 3 1

Electronics Fastening Method

Epoxy strongpermanent

Fasteners convenient less fixative

Monocoque more material to absorb the impactmore susceptible to vibrations

Black Box isolates electronics from forceneeds testing to ensure survivability requirements


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Mass Budget


Components Material Weight Quantity Source

Egg Container ABS 14 grams 1 Measured

Egg sabot Memory Foam 11.8 grams 1 Calculated

Rotor Hub ABS 11.1 grams 1 Measured

Rotor Blades ABS 9.5 grams 6 Measured

Screw Aluminum .2 grams 15 Data Sheet

Nut Aluminum .1 grams 10 Data Sheet

Torsion Spring Music Wire .4 grams 6 Data Sheet

Screw and Post Aluminum 1.3 grams 2 Data Sheet

Black Box ABS 56.7 grams 1 Calculated

Electronics Plate Carbon Fiber 16.7 grams 2 Calculated

Container Carbon Fiber 149 grams 1 Calculated

Support Tubes Carbon Fiber 2.16 grams 4 Calculated

Parachute Nylon 30 grams 1 Data Sheet

Mass Total: 380.64 grams*

*washers will be used to achieve exact desired weight

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Communication and Data Handling

(CDH) Subsystem Design

Clayton Lambert

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CDH Overview


Demonstrates data handling and formatting

Outlines radio configuration

Provides trade study of processor, clock, and antenna

Explains requirements for Communications and Data Handling

The communication and data handling subsystem overview:

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CDH Overview

Sensor data sent over I2C to Arduino.

Arduino processes data and sends to XBEE 1 via serial

communication

XBEE 1 sends packaged data via a 2.4 GHz radio connection to XBEE 2

XBEE 2 communicates with computer via FDTI cable

Data parsed and graphed by MatLab


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CDH Requirements

Part Requirement Implementation

Arduino micro Vehicle must record data

onboard to be export to a

ground station

Vehicle must also

interpret and change

direction based on

sensor data in real time

Interprets and processes

data incoming from

sensors as well as export

data to be sent to a

peripheral wireless

linkage

XBEE Pro Series 2 Vehicle must transmit

data down to a ground

station to be recorded to

a second XBEE Pro

Series 2

Receives data from the

microcontroller and then

exports data via a

wireless link to another

XBEE on the ground

relaying data to a

computer


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CanSat 2015 PDR: Team 5251, CosmoKnights

58

Processor & Memory

Trade & Selection

Micro-

controll

er

Input

Voltage

(V)

Current

(mA)

Clock

Freq

# Digital

Pins

# Analog

Pins

Flash

Memory

(kB)

EEPR

OM

(kB)

Weight Dimensions Price

Arduino

Micro6-20 40 36 7 12 32 1 13 48 x 18 21.45

Arduino

Pro Mini9 40 8/16 14 6 16 0.512 1 17.8 x

33.02

18.95

Arduino

Uno9 40 16 14 6 32 1.024 32 85.58 x

53.34

29.95


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(If You Want) Real-Time Clock

Arduino

Has an onboard clock

Capable of time keeping from initial boot

Time.h library

Calls for the current time easily

Calculates elapsed time based on millis() function

Clock speed

16mHz

Accuracy calibratable to 1 nano second


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Antenna Trade & Selection

Antenna Selected: GigaAnt Integrated Antenna

Integrated into transceiver to reduce space

Small overall footprint

Capable of covering required range

Antenna Price(USD) Length(mm) Gain (dbi) Type

2.4GHz dipole Swivel

Antenna

6.95 100 2 2.4GHz

GigaAnt Integrated Antenna 1.35 30 -.5 2.4Ghz

2.4Ghz Circular Polarized

Antenna

14.40 65 2 2.4Ghz


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Radio Configuration

XBee radios

in constant communication

configured in AT mode

may only communicate in a point to point connection

NETID

synchronized over XCTU software

forces Xbees to recognize each other

tested to show correct passing of data

Point to point connection

eliminates static from other Xbees

ensures no malicious connections through optional encryption selection .

Transmission control

done by the Arduino

packages information at 1Hz rate

sends package from the vehicles Xbee to the ground station


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Telemetry Format

Data included

Temperature sensors: internal and external temperatures

Accelerometer: angle of descent

Altimeter: atmospheric pressure

Voltage divider: battery voltage

Internal Arduino clock: overall mission time

Arduino program: constitutes flight software state

Data format

teamID, missionTime, altSensor, outsideTemp, insideTemp, voltage, fswState, descentAngle

Example: 5251, 207.56, 350, 23, 20,5.4, 5, 40


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Electrical Power Subsystem (EPS)

Design

Philip Lane

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EPS Overview

The Electrical Power Subsystem overview covers the organization of the subsystem and the electrical

requirements:

The EPS section includes:

trade studies power usage

block diagram and voltage measurement diagram

The battery provides energy to:

Arduino sensors

Xbee

The electrical requirements include:

kill switch sensor requirements

environmental requirements

Presenter: Phillip Lane

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EPS Requirements


ID Requirement Rationale Priority VM

A I T D

EPS-01 All electronic devices shall

draw power from a single

unique battery.

There is only one external

power supply, a battery.

HIGH X

EPS-02 The battery shall be

capable of providing at

least 3.3 volts for the

duration of the flight.

The largest voltage output

required for any

component is 3.3 volts.

HIGH X X X

EPS-03 Voltage divider shall draw

1.00 micro-Amp

maximum.

Power preservation is

critical for mission

duration.

HIGH X X

EPS-04 Voltage divider output

shall not exceed 5 volts.

Maximum input voltage

to Arduino analog pin is 5

volts.

MEDIUM X X

EPS-05 Safety cutoff switch

directly connected to

battery power.

To cut off power to the

vehicle if needed (mission

requirement).

LOW X X

EPS-06 3.3 volts consistently

applied to power

accelerometer.

Mission bonus objective:

measuring stability angle

of descent.

LOW X X

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EPS Requirements


Component Current (mA) Voltage (V) Power

(mW)

Estimated

Time in use

(hours)

Total energy

consumed (mWh)

Arduino UNO 40 9 360 1 360

Arduino Micro 40 9 360 1 360

Temperature

sensor (external)

0.05 2.7 0.135 0.25 0.03375

Temperature

sensor (internal)

0.05 2.7 0.135 0.25 0.03375

XBEE radio 295 3.3 973.5 1 973.5

Sen-10736 (accel.,

gyro, mag.)

0.14 3.3 0.46 0.25 0.12

Buzzer (Beacon) 35 3.3 115.5 0.083 9.59

Altimeter 0.04 3.3 .132 0.25 0.033

TOTAL 1708.52

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Lander: Electrical Block Diagram


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Payload Power Source

Trade Study


Pros

safe

reliable

Cons

must be properly charged and discharged.

Li-ion 14500 selected

low weight

sufficient capacity

reliable built in charger

Li-ion battery


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Power Budget

Battery chosen: Li-ion 14500

Weighs less

Inexpensive

Meets capacity requirements

Already wired to protection circuit


Battery Type Voltage (V) Capacity

(mAh)

Size (mm) Weight (g) Price (USD)

Custom NiMH

Battery Pack

NiMH 3.6 800 32x48x12 63 12.95

18650 Li-ion

Rechargeable

(2pc)

Li-ion 3.7-4.2V 5000 67x18 47 6.99

Li-ion 14500

Battery

Li-ion 3.7V 750 54x18 20 9.95

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Power Bus Voltage Measurement

Trade and Selection

Battery measurements

uses voltage divider circuit

two resistors in series combination

configured to pull a max of 100 micro amps

based on the 3.7V nominal voltage of Li-ion 14500

minimizes electrical noise and power draw

total combined resistance ~ 37 kOhms.

outputs max voltage of 3.0 V

prevents damage to the controller.

Battery output measured as the voltage drop across Resistor 2: Vout

Ratio multiplied by Vout used to calculate battery's remaining supply.

For analog to digital conversion, the remaining supply value is multiplied by 0.00488


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Power Bus Voltage Measurement

Diagram


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Flight Software (FSW) Design

Lietsel Richardson

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FSW Overview

Flight Software Design includes:

Mechanical and derived requirements

State diagram

Software development plan


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FSW Introduction

Basic Flight Software Architecture

In a runtime loop and at a rate of 1 Hz, the software will enable

communication between ground station and CanSat by

requesting data updates whilst monitoring time during the

mission.

Data measured by pressure sensors will be used to monitor

altitude which determines when commands will be sent, such

as separation.

Programming Language

-Arduino programming language (C)

Development Environment

-Arduino Integrated Development Environment


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FSW Requirements

Mechanical sub-system requirements

Maintain video recording in the nadir facing direction

Vehicle may not rotate +/- 90 degrees during descent

Vehicle must release from container

Derived requirements

Must have mechanism to rotate craft about z axis to provide stability

Vehicles mechanism must be able to withstand stabilization during freefall


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CanSat FSW State Diagram

Mission State: PreFlightTest

Sample Rate (Hz):

Altimeter 4

TemperatureIN 4

TemperatureOUT 4

Accelormeter 4

Voltage meter 4

Communications

1Hz telemetry

Logic

Record data to sdcard, send to GCS

Transition if data is correctly transmitted for 10 iterations and

flag received by GCS

Mission State: LaunchWait

Sample Rate (Hz):

Altimeter 4

TemperatureIN 4

TemperatureOUT 4

Accelormeter 4

Voltage meter 4

Communications

1Hz telemetry

Logic


Transition if altimeter reading is above launch threshold

Mission State: Ascent

Sample Rate (Hz):

Altimeter 20

TemperatureIN 4

TemperatureOUT 4

Accelormeter 4

Voltage meter 4

Communications

1Hz telemetry

Logic


Transition if altimeter's rate of ascent has

reached zero indicaing apogee and

trigger Camera to record


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Mission State: Rocket Deployment

Sample Rate (Hz):

Altimeter 20

TemperatureIN 4

TemperatureOUT 4

Accelormeter 20

Voltage meter 4

Communications

1Hz telemetry

Logic

Record data to sd card, send to GCS

Transition if data accelorameter's values exceed threshold shock

from ejection

Mission State: Seperation

Sample Rate (Hz):

Altimeter 4

TemperatureIN 4

TemperatureOUT 4

Accelormeter 4

Magnatometer 2000

Gyroscope 50

Voltage meter 4

Communications

1Hz telemetry

Logic


Signal servo to detach lander from canister

Transition if temp out registers a significant change showing

detachment of vehicle

Mission State: Stabilization

Sample Rate (Hz):

Altimeter 4

TemperatureIN 4

TemperatureOUT 4

Accelormeter 4

Magnatometer 2000

Gyroscope 50

Voltage meter 4

Communications

1Hz telemetry

Logic


Signal servo to spin rapidly to stabilize cansat, then gradually slow down to

single bearing guided by magnetometer

Transition if magnatometer stays in value range and gyroscope shows

realtivly vertical postion of vechicle for more then 2 seconds

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Mission State: Descent

Sample Rate (Hz):

Altimeter 20

TemperatureIN 4

TemperatureOUT 4

Accelormeter 20

Voltage meter 4

Communications

1Hz telemetry

Logic


Transition if data accelorameter's values exceed threshold shock from landing

Mission State: Landed

Sample Rate (Hz):

Altimeter 4

TemperatureIN 4

TemperatureOUT 4

Accelormeter 20

Voltage meter 4

Communications

1Hz telemetryAudio Alert

Logic


Turn off camera record, turn on audioSignal, send landed message in

telemetry


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Software Development Plan

Date Software Development Stage Description

August 24, 2014

December 31, 2014Overview and initial testing

Outlined foundation stages of flight

software Defined processes in each

stage

Tested each sensors data with

Arduino

Confirmed communication

with XBee

January 1, 2015

February 28, 2015Systems Design - Alpha

Prototyped electronics system

Integrated all peripherals

Tested each stages triggers and

actions Demonstrated full process

precession

March 1, 2015

June 12System Design - Beta

Design, create, and test electronics

board with integrated sensors

Test board in lab using fabricated

values Install board into vehicle

Test in real world environment

Program will be ready to test almost 5 months prior to competition deadline.


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Ground Control System (GCS) Design

Philip Lane

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GCS Overview


CanSat data stream

Xbee / breakout board

Arduino

Computer

GUI

An overview of the ground control system includes:

requirements trade selection for the antenna ground control software

The flow of information is unidirectional in the following pattern:

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GCS Requirements


GCS-01

GCS is to be portable. (Base Requirement)

GCS-02

GCS needs to be capable of receiving and plotting data from Science Vehicle in real time. (Base Requirement)

GCS-03

Team must have its own ground station. (Base Requirement)

GCS-04

Screen must be properly shielded.

GCS-05

There must be zero interference. (In order to prevent loss of signal/communication, antenna needs to be free of interference.)

GCS-06

GCS must include a laptop computer with no less than two hours of battery life, XBEE radio, and an antenna (either handheld or tabletop). (Base Requirement)

GCS-07

Flight software must telemeter a variable that will indicate the operating state at each given time. The software must analyze sensor data in order to initialize states. The states should include:

PreFlightTest(0), LaunchWait(1), Ascent(2), RocketDeployment(3), Stabilization(4), Separation(5),

Descent(6), and Landed(7). (Base Requirement)

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83

GCS Antenna Trade & Selection

Antenna chosen: 2.4GHz dipole Swivel Antenna

Wide coverage is necessary

Suitable gain


Antenna Price(USD) Length(mm) Gain (dbi) Type

2.4GHz dipole

Swivel

Antenna

6.95 100 2 2.4GHz

GigaAnt

Integrated

Antenna

1.35 30 -.5 2.4Ghz

2.4Ghz

Circular

Polarized

Antenna

14.40 65 2 2.4Ghz

CanSat 2015 PDR: Team 5251, CosmoKnights

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(If You Want) GCS Software

Raw telemetry display

Real-time plotting

Data archiving and retrieval

Command software and

interface

Data recording and media

presentation

.csv file creation

CanSat 2015 PDR: Team 5251, CosmoKnights 84Presenter: Phillip Lane

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CanSat Integration and Test

Kyle Steunenberg

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Overview

Presenter: Kyle Steunenberg

Integration Mechanical Systems

Aluminum fasteners Egg container, rotor

Ring gear Black box

Epoxy Nichrome wire (possibly)

Electronics Systems

Printed board Sensors

Epoxy(Electronics restraint) Printed board, wire, camera

Descent System

Auto gyro Fastener system

Parachute Chords

Testing Mechanical Systems

Egg container Drop tests

Main structure FEM/CFD, drop tests

Nichrome wire Safety tests, separation tests

Electronics System

Sensor package Accuracy test, transmission tests

Servo Speed test, spin response test

Camera Drop test

Descent System

Auto gyro Low drop test

Balloon drop test

Parachute Low drop test

Balloon drop test

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Overview - Mechanical System

Egg Container

Drop eggs on material from heights of 1m, 3m, then 15m

Main Structure

FEM Analysis

High altitude test

Use weather balloon

Achieve height necessary for terminal v

Test container and frame separately

Conduct final test using separation mechanism and dummy black box

Nichrome Wire Separation

Ground test for fire safety, convenience, and effectiveness

Weather balloon test for effectiveness


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Overview Electronics System

Accelerometer

Single Sensor -> Arduino-> computer display in lab:

Shake test to show working conditions and correct output values

Integrated into prototype test:

Drop from 20m drop, and vertical launch test to be recorded and displayed

Altitude Sensor


Show correct pressure output, show correct altitude output


Record reading continuously while walking up 4 flights of outside stairs and drop test

Temperature Sensor


Show correct temperature readout in Celsius and Fahrenheit


Record internal and external readings from test drop

Magnetometer


Demonstrate sensor accuracy and bearing hold mapped to servo output


Find maximum speed of servo reaction to spinning in outdoor test


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Overview Electronics System Ctd.

Camera


Demonstrate control of camera with Arduino by recording and stopping video


Shock test outside to show non corrupted video via a 20m drop

Servo

Single Output -> Arduino-> computer display in lab:

Demonstrate control of sensor with magnetometer values in lab

Integrated into prototype test

Outdoor test to find max rotational speed of servo being controlled by magnetometer

Xbee Radios

Arduino -> Radio1 -> Radio 2-> computer display in lab:

Demonstrate transmission of data from sensors at 1hz rate

Integrated into prototype test

During drop test, show live telemetry from ground station during test


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Overview - Descent Systems

Auto Gyro

Analyzed using CFD

Tested in wind tunnel to determine actual lift generated versus calculated.

Integrated into vehicle for weather balloon drop test

Parachute

Drop tested at low altitude

Drop tested at high altitude with weather balloon


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Overview

91CanSat 2015 PDR: Team 5251, CosmoKnights

Selection of devices and electronics.

Programming of devices completed.

Successful test of battery strength and

devices.

Size and specifications of electronics bay

determined.

Egg drop testing.

Size and specifications of egg

container determined.

Design and development of

vehicle.

Design and development of auto

gyro.

Integration of electronics bay, egg container, and auto

gyro onto the vehicle.

Design and integration of

parachute and container.

Test of auto gyro without electronics

Test of all parts integrated

Sequence of Integration


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Mission Operations & Analysis

Ethan Christian

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Mission Operations and Analysis

Overview

Presenter: Ethan Christian

The missions operations and analysis section includes:

CanSat location and discovery strategy

Mission ops development plan

Concept of operations

Sequence of events

Team roles and responsibilities

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System Concept of Operations


Launch wait: vehicle will constantly stream environment data to be

shown in real time, in engineering units, on ground station and wait for

altimeter to detect liftoff

Ascent: Vehicle will transmit data and calculate rate of ascent as well as use accelerometer data to detect separation from rocket and trigger

camera to record

Rocket Deployment: Canister will automatically deploy parachute upon separation from rocket and

wait for either stabilized gyroscopes, altitude, or set time to eject lander

Stabilization: lander will continue to transmit telemetry and begin

spinning internal camera housing to always face a single direction. Will determine best conditions for

separation.

Descent: Lander will continue to transmit data, self correct spin, and wait for accelerometers to detect

landed

Landed: Lander will transmit a "landed" signal via telemetry, turn

off stabilization routine, turn off camera record and signal an

audio tone for the lander to be physically found

Post landed: Lander's camera data will be retrieved and displayed on computer

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Overview of Mission Sequence of

Events


Team Launch Roles and Responsibilities:

Mission Control Officer:Hunter Williams

Ground Station Crew:Clayton Lambert

Phillip Lane

CanSat Crew: Jeremy Woodward

John Christian

Kyle Steunenberg

Recovery Crew:Vincent Coment

Lietsel Richardson

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Events


Arrival at Launch

Site

Set up ground control station

Connect and

position antenna

Final vehicle

and container assemblie

s

Pre-Flight Inspection

Go through pre-flight checklist

Power on CanSat

Check CanSat &

station communic

ation

Rocket Integration

Fold Parachute

Ensure CanSat

power on

Integrate into rocket

payload

Pre Flight Sequence

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Events


Rocket Launch

Maintain rocket visual

Monitor ground station

communications

Monitor vehicle state

Deployment

Observe for Container parachute

deployment

Monitor communicat

ions

Monitor separation conditions

Separation

Observe Science Vehicle

Separation

Monitor and graph

incoming telemetry

data

Visually track both

descents for recovery

Landing

Follow audible beacon which

activated on impact

Launch Sequence

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Events


RecoveryRecover Science

Vehicle and Container

Check payload condition

Data AnalysisRetrieve video

data from Science Vehicle

Consolidate transmitted

telemetry data

Review Present data

Post-Flight Sequence

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Mission Operations Manual

Development Plan

Operations Manual Development

Once final designs and components are chosen, the final sequence of procedures for initialization can be

composed.

Will contain a checklist for: Ground station configuration and initialization

CanSat preparation and initialization

CanSat Integration into the rocket

Will also contain: Launch sequence

Recovery sequence


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CanSat Location and Recovery

Container

Will be painted an orange color and have a orange colored parachute to remain easily visible as it descends

to the surface.

This will also provide a contrasting color for location on most terrains for surface location.

Will contain a label with contact information for return.

Payload

Will use an audible alert to broadcast location.

Will contain a label with contact information for return.


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Requirements Compliance

Ethan Christian

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(If You Want) Requirements Compliance Overview


Container

Complies will all competition requirements

Protection of the science vehicle until deployment

Stabilize vehicle and slow descent before deployment

Return to surface passively

Science Vehicle

Complies with all competition requirements

Eject from container at optimal conditions

Return to surface at controlled descent

Transmit flight data and record flight video

Protect Egg

Compliance Challenges

Total mass of vehicle and Container


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(multiple slides, as needed)


Rqmt

NumRequirement

Comply / No

Comply /

Partial

X-Ref Slide(s)

Demonstrating

Compliance

Team Comments

or Notes

1

Total mass of CanSat, container, and all descent control

devices shall be 600 grams. Mass shall not vary more than +/-

10 grams.

Partial Comply 53Planned mass < 600 grams, no vehicle to weigh built

2

The Science Vehicle shall be completely contained in the

Container. No part of the Science Vehicle may extend beyond

the Container

Comply 14-15

3

The Container shall fit in the envelope of 125 mm x 310 mm

including the Container passive descent control system.

Tolerances are to be included to facilitate Container

deployment from the rocket fairing

Comply

14-15

4

The Container shall use a passive control system. It cannot free

fall. A parachute is allowed and highly recommended. Include a

spill hole to reduce swaying.

Comply29-30

5The Container shall not have any sharp edges to cause it to get

stuck in the payload section.Comply 15

6 The container must be a florescent color, pink or orange. Comply 15,98

7The rocket air frame shall not be used to restrain any

deployable parts of the CanSat. Comply 16

8The rocket air frame shall not be used as part of the CanSat

operations. Comply 16

9The CanSat (Container and Science Vehicle) Shall deploy from

the rocket payload section. Comply 16


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Rqmt

NumRequirement

Comply / No

Comply /

Partial

X-Ref Slide(s)

Demonstrating

Compliance

Team Comments

or Notes

10

The Container or Science Vehicle shall include electronics and

mechanisms to determine the best conditions to release the

Science Vehicle based on stability and pointing. It is up to the

team to determine appropriate conditions for releasing the

Science Vehicle.

Comply 95

11The Science Vehicle shall use a helicopter recovery system. No

fabric or other material are allowed between the blades.Comply 29,31

12All descent control device attachment components shall survive

50 Gs of shock.Partial comply

52

Complies through calculations. Have not

tested vehicle.

13 All descent control devices shall survive 50 Gs of shock. Partial Comply52


tested vehicle.

14All electronic components shall be enclosed and shielded from

the environment with the exception of sensors. Comply 46-47

15 All structures shall be built to survive 15 Gs of acceleration.Partial Comply 52


tested vehicle.

16 All structures shall be built to survive 30 Gs of shock.Partial Comply 52


tested vehicle.

17All electronics shall be hard mounted using proper mounts such

as standoffs, screws, or high performance adhesives. Comply 52

18All mechanisms shall be capable of maintaining their

configuration or states under all forces.Partial Comply 52


tested vehicle.


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Rqmt

NumRequirement

Comply / No

Comply /

Partial

X-Ref Slide(s)

Demonstrating

Compliance

Team Comments

or Notes

19 Mechanisms shall not use pyrotechnics or chemicals Comply 50-51

20

Mechanisms that heat (e.g. nichrome wire) shall not be

exposed to the outside environment to reduce potential risk of

setting vegetation on fire.

Comply51

21

During descent, the Science Vehicle shall collect and telemeter

air pressure (for altitude determination), outside and inside air

temperature, flight software state, battery voltage, and bonus

objective data (accelerometer data and/or rotor rate)

Comply

62

22 The Science Vehicle shall transmit telemetry at a 1 Hz rate.Comply

74

23

Telemetry shall include mission time with one second or better

resolutions, which begins when the science vehicle is powered

on.

Comply62

24

XBEE radios shall be used for telemetry. 2.4 GHz series 1 and

2 radios are allowed. 900 MHz XBEE Pro radios are also

allowed.

Comply56,60,63

25XBEE radios shall have their NETID/PANID set to their team

number (decimal).

Comply61

26 XBEE shall not use broadcast modeComply

61

27

The science vehicle shall have a video camera installed and

recording the complete descent from deployment to landing.

The video recording can start at any time and must support up

to one hour of recording.

Comply25,75


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Rqmt

NumRequirement

Comply / No

Comply /

Partial

X-Ref Slide(s)

Demonstrating

Compliance

Team Comments

or Notes

28

The video camera shall include a time stamp on the video. The

time stamp must for from the time of deployment to the time of

landing.

Comply25

29The descent rate of the Science Vehicle shall be less that 10

meters/second and greater than 4 meters/second.

Partial Comply30-31


tested vehicle.

30

During descent, the video camera must not rotate. The image

of the ground shall maintain one orientation with no more than

+/- 90 degree rotation.

Partial Comply

46-47


tested vehicle.

31Cost of the CanSat shall be under $1000. Ground support and

analysis tolls are not included in the cost.

Comply

111-114

32 Each team shall develop their own ground station.Comply

83-84

33 All telemetry shall be displayed in real time during descent.Comply

95

34All telemetry shall be displayed in engineering units ( meters,

meters/second, Celsius, ect.).Comply

95

35Teams shall plot data in real time during flight on the ground

station computer.Comply

61,74,76-78

36

The ground station shall include one laptop with a minimum of

two hours of batter operations, XBEE radio and a hand held or

table top antenna.Comply

81,82


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Rqmt

NumRequirement

Comply / No

Comply /

Partial

X-Ref Slide(s)

Demonstrating

Compliance

Team Comments

or Notes

37

The ground station shall be portable so the team can be

positioned at the ground station operation site along the flight

line. AC power will not be available at the ground station

operation site.

Comply 81, 82

38The Science Vehicle shall hold one large raw hens egg which shall survive launch, deployment, and landing.

Comply14,42-45

39Both the Container and Science Vehicle Shall be labeled with

team contact information included email address.

Comply

100

40

The CanSat flight software shall maintain and telemeter a

variable indicating its operating state. In case of processor

reset, the flight software shall re-initialize to the correct state

either by analyzing sensor data and/or reading stored state

data from non-volatile memory. The states are to be defined by

each team. Example states include: PreFlightTest(0),

LaunchWait(1), Ascend(2), RocketDeployment(3),

Stabilazation(4), Separation(5), Descend(6), Landed(7).

Comply

76-78

41 No lasers are allowed.Comply

No lasers in design

42

The Science Vehicle shall include an easily accessible power

switch which does not require removal from the Container for

access. An access hole or panel in the container is allowed.Comply

46,64


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Rqmt

NumRequirement

Comply / No

Comply /

Partial

X-Ref Slide(s)

Demonstrating

Compliance

Team Comments

or Notes

43

The Science Vehicle Shall must include a battery that is well

secured. (Note: a common cause of failure is disconnections of

batteries and/or wiring during launch).

Comply68-70

44Lithium polymer cells are not allowed due to being a fire

hazard.

Comply68-70

45

Alkaline, Ni-MH, lithium ion built with a metal cause, and Ni-

Cad cells are allowed. Other types must be approved before

use.

Comply

68-70

46

The Science Vehicle and Container must be subjected to the

drop test as described in the Environmental Testing

Requirements document.

Partial ComplyComponents not built for testing required. Testing planned for future dates.

47


vibration test as described in the Environmental Testing

Requirements document. Partial Comply

Components not built for testing required. Testing planned for future dates.

48


thermal test as described in the Environmental Testing

Requirements document. Partial Comply


49Environmental test results must be documented and submitted

to the judges at the flight readiness review. Partial Comply



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Management

Hunter Williams

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CanSat Management Overview


The Management section contains:

Gantt chart

Timeline

Final total budget

Detailed budgets on electronics, structural components, and other costs

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CanSat Budget Electronics


Electronics BudgetItem Description Cost # Total Cost Actual Estimated Budgeted

Arduino Micro Microcontroller $21.45 1 $21.45 Actual

WRL-10419 Xbee Transmitter $44.95 2 $89.90 Actual

WRL-11373 Xbee Boad $9.95 2 $19.90 Actual

MPL3115A2 Pressure Sensor $14.95 1 $14.95 Actual

TMP36 Temp Sensor 1.5 2 $3.00 Budgeted

SEN-10736 IMU $74.95 1 $74.95 Budgeted

808 Car Key Chain Camera 7.5 1 $7.50 Budgeted

PRT-12002 Breadboard $4.95 1 $4.95 Budgeted

RTL-11242 Jumper Wires $5.95 1 $5.95 Budgeted

ROB-10333 Servo $10.95 1 $10.95 Budgeted

GigaAnt Antenna Antenna $1.35 2 $2.70 Budgeted

PCB Board $100 1 $100.00 Estimated

Total $356.20

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CanSat Budget Structural

Structures Budget

Item Description Cost # Total Cost

Actual, estimated,

Budgeted

Carbon Fiber Sheet 9.5ozX50X3 $ 25.50 1 $ 25.50 Estimated

Carbon Fiber Epoxy3 to 1 Epoxy/Hardener $ 39.75 1 $ 39.75 Estimated

Measuring Pump $ 6.95 2 $ 13.90 Estimated

Molding Wax 24 oz $ 10.50 1 $ 10.50 Estimated

Torsion Spring 180 Deg $ 6.89 1 $ 6.89 EstimatedAluminum Screw and Post $ 0.80 4 $ 3.20 Estimated

Aluminum screw 6-32 X $ 7.06 1 $ 7.06 Estimated

Aluminum nut 6-32 $ 3.94 1 $ 3.94 Estimated

Nylon Eye bolt 10-24 $ 6.15 1 $ 6.15 Estimated

Respirator $ 29.87 2 $ 59.74 Estimated

2 Gallon Bucket $ 3.42 1 $ 3.42 Estimated

Brushes $ 14.99 1 $ 14.99 Estimated


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CanSat Budget Structural Contd. Structural Cont.

Other Costs and Total

Item Description Cost # Total Cost Actual, estimated, Budgeted

Putty Knives $ 3.11 1 $ 3.11 Estimated

Wood Planks 2X6X8 $ 5.42 1 $ 5.42 Estimated

Nitrile Gloves 12 Pack $ 4.98 1 $ 4.98 Estimated

Loctite Blue threadlocker $ 6.48 1 $ 6.48 Estimated

Carbon Fiber

Tubes

750mm Long

5mm OD $ 2.01 2 $ 4.02 Estimated

Carbon Fiber

Plates 300X100X2mm $ 20.30 3 $ 60.90 Estimated

Wood Glue $ 3.98 1 $ 3.98 Estimated

Total $283.93


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CanSat Budget Other Costs

Other Costs and Total

Type Item Description Cost

Prototype N/A

Prototyping budget was included in the original budgets N/A

Test Equipment Eggs

Eggs used for egg drop materials selection $4

Test Equipment Weather Balloon $15 $15

Test Equipment Helium $3.03 per cubic meter $3.03

Ground Station Computer Laptop $650

Travel Gas

Calculated at $2.5 per gallon from Orlando to Burkett and back $320+

Travel Hotel At $75 per night, 3 rooms, 4 nights $900

Travel Food $25 per day, 4 days, 8 people $800

Total Electronics and Structural

(Not Including Other Costs) $640.13

Grand Total $3332.16


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CanSat Budget Funding Sources

Funding Sources

Source Type Name Description Amount

Government Grant Florida Space Grant

Covered cost of CanSat application fee and project materials $250

University Grant SGA Project Funding

$1000 for project materials, electronic and structural $1000

University Grant SGA Competition Travel Funding

$200 per person, 8 people, covers hotels and transportation $1600

Previous Projects AIAA UCF Project Materials

Previous projects used Arduino and breakout boards. These were used for introductions to programming,

but not used for prototyping. $800+

Since the SGA grant and Florida Space Grant cover the cost of the CanSat and its

testing materials, there is no danger of running out of funds before project

completion.

Since team members will be driving instead of flying, covering their own food costs,

and sleeping 3 to a room in inexpensive hotels, the SGA Travel Funding will

adequately cover the costs of going to the competition.


Team Logo

Here

(If You Want)


CanSat Timeline Description

Phase 1:

Design: CAD design in Solidworks High level design

Build: Find materials for egg drop

testing

Buy breakout board sensors for use with Arduino to get initial idea on code

Test: Conduct egg drop test Do CFD analysis and FEM

buckling analysis

Learn all sensors and integrate into GUI

Phase 2:

Design: Finish budget Purchase materials for initial

prototype

Build: Construct first prototype Finish organizing code

architecture

Test: Integrate code into single

autonomous code

Drop test prototype

Phase 3:

Design: Analyze results from drop

test

Make minor changes to design as appropriate

Finish GUI for ground control Build:

Implement structural changes

Integrate sensor package into structure

Test: Do final drop test using

weather balloon and full sensor package


Team Logo

Here

(If You Want) Timeline


3/9/2015 Spring Break Begins

3/13/2015 Begin Design Phase 3

3/15/2015 Spring Break Ends

4/10/2015 Begin Build Phase 3

29/04/2015 CDR/ End of Spring Semester

5/8/2015 Begin Test Phase 3

6/12/2015 Competition

11/27/2014 Thanksgiving

12/12/2014 Winter Break Starts


1/2/2015 Spring Semester Starts


2/1/2015 PDR


8/25/2014 Post Fliers

9/1/2014 Labor Day

9/5/2014 First Meeting

9/12/2014 Assign Teams




PROJECT TIMELINE


Team Logo

Here

(If You Want) Gantt Chart Pt. 1 and 2

118Presenter: Hunter Williams CanSat 2015 PDR: Team 5251, CosmoKnights

Team Logo

Here

(If You Want)


Conclusions

Major Accomplishments

Completed CAD and CFD of initial structural design, revised to optimize strength, weight, and speed

Successfully transmitted sensor data between CanSat and Ground Station, wired all sensors with Arduino

Conducted trade studies and budgeted accordingly

Major Unfinished Work

Finish manufacturing primary prototype

Finish integrating code into single, automated package

Print circuit, integrate servo and ring gear

Readiness

As all computational analysis is finished and budgeting shows financial viability, primary prototype construction is ready


Team Logo

Here

(If You Want)

CanSat 2015 PDR: Team 5251, CosmoKnights 120Presenter: Hunter Williams

Cansat2015_5251_PDR

Documents

team organizationpresenter

cosmoknightsteam logohereif

compliance engineer

clayton lambert cansat

hunter williamsfaculty

aiaa ucf mission

wantteam logoherecansat

mission summarypresenter