Preliminary Design Review (PDR) Version 1.2 …cansatcompetition.com › docs › teams › Cansat2018_5278_PDR.pdfengineering units (meters, meters/sec, Celsius, etc.) Competition

CanSat 2018 PDR: Team 5278 BUTTER 1

CanSat 2018 Preliminary Design Review (PDR)

Version 1.2

Team 5278B.U.T.T.E.R


Table of Contents

• Introduction: Alex Schneider….………....………………………………………..………..…..1

• Systems Overview: Alex Schneider....…………………………...……………..………...…...5

• Sensor Subsystem Design: Michael Campbell ...………………….………………….....…28

• Descent Control Design: Anthony McCourt……………..……..……….……...………...….37

• Mechanical Subsystem Design: Dwight Scott, Lyle Hailey...………….………………...…54

• Communication and Data Handling Subsystem Design: Sina Malek…….……....….…81

• Electrical Power Subsystem Design: Mecah Levy…….....………………………...……...89

• Flight Software Design: Vijay Ramakrishna…………………..…………...………...…..…..97

• Ground Control System Design: Vijay Ramakrishna………………………..….………...106

• CanSat Integration and Test: David Madden…....………………………………………....116

• Mission Operations and Analysis: Alex Schneider....……………...……….…...………..122

• Requirements Compliance: Mennatallah Hussein………………..….…….…...…………127

• Management: David Madden…...……………………………………...…………...………...134

• Conclusion: David Madden…...………………………………………..……………………..146

Presenter: Alex Schneider


Team Organization



Acronyms

• BUTTER - Ballistic Universal Timed Trajectory Egg Recovery• SDSL - Sun Devil Satellite Laboratory• SBC - Spherically Blunted Cone• ABS - Acrylonitrile butadiene styrene• RTC - Real-time Clock• I2C - Inter-Integrated Circuit• GS - Ground station• CAD - Computer Aided Design• GPS - Global Positioning System• RBF - Remove Before Flight• MET - Mission Elapsed Time• COM - Center of Mass• BATT - Battery• ASSY - Assembly• COMP - Compartment



Systems Overview

Alex Schneider


Mission Summary

• The probe shall be launched to an altitude of approximately 700m• Once the probe deploys from the rocket, it will expand an

aerobraking heat shield• With the heat shield deployed, the probe shall maintain a descent

rate between the objective 10 to 30 m/s• At an altitude of 300m, the heat shield will be decoupled and a

parachute shall be deployed.• The probe shall then continue descent at 5 m/s until landing, and

keep the egg and components intact• A camera will be mounted to the probe to record the heat shield

deployment and ground view during decent after a 300m altitude is reached– The camera bonus objective was selected because its addition does

not negatively affect the current design– The camera will also help in the post flight analysis


CanSat 2018 PDR: Team 5278 BUTTER

System Requirement Summary

7

ID Requirements Rationale Priority

SR-01 Total mass of the CanSat (probe) shall be 500 grams +/- 10 grams.

Competition Requirement High

SR-02 The aero-braking heat shield shall be used to protect the probe while in the rocket only and when deployed from the rocket. It shall envelope/shield the whole sides of the probe when in the stowed configuration in the rocket. The rear end of the probe can be open.


SR-03 The heat shield must not have any openings. Competition Requirement High

SR-04 The probe must maintain its heat shield orientation in the direction of descent.


SR-05 The probe shall not tumble during any portion of descent. Tumbling is rotating end-over-end.





8

SR-06 The probe with the aero-braking heat shield shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length. Tolerances are to be included to facilitate container deployment from the rocket fairing.


SR-07 The probe shall hold a large hen's egg and protect it from damage from launch until landing.


SR-08 The aero-braking heat shield shall be used to protect the probe while in the rocket only and when deployed from the rocket. It shall envelope/shield the whole sides of the probe when in the stowed configuration in the rocket. The rear end of the probe can be open.


SR-09 The probe shall accommodate a large hen’s egg with a mass ranging from 54 grams to 68 grams and a diameter of up to 50mm and length up to 70mm.





9

SR-10 The aero-braking heat shield shall be a fluorescent color; pink or orange.


SR-11 The rocket airframe shall not be used to restrain any deployable parts of the CanSat.


SR-12 The rocket airframe shall not be used as part of the CanSat operations.


SR-13 The CanSat, probe with heat shield attached shall deploy from the rocket payload section.


SR-14 The aero-braking heat shield shall be released from the probe at 300 meters.


SR-15 The probe shall deploy a parachute at 300 meters.


SR-16 All descent control device attachment components (aero-braking heat shield and parachute) shall survive 30 Gs of shock.





10

SR-17 All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock.


SR-18 All electronic components shall be enclosed and shielded from the environment with the exception of sensors.


SR-19 All structures shall be built to survive 15 Gs of launch acceleration.


SR-20 All structures shall be built to survive 30 Gs of shock.


SR-21 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.


SR-22 All mechanisms shall be capable of maintaining their configuration or states under all forces.





11

SR-23 Mechanisms shall not use pyrotechnics or chemicals.


SR-24 Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to the outside environment to reduce potential risk of setting vegetation on fire.


SR-25 During descent, the probe shall collect air pressure, outside air temperature, GPS position and battery voltage once per second and time tag the data with mission time.


SR-26 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts.


SR-27 Telemetry shall include mission time with one second or better resolution. Mission time shall be maintained in the event of a processor reset during the launch and mission.





12

SR-28 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.


SR-29 XBEE radios shall have their NETID/PANID set to their team number.


SR-30 XBEE radios shall not use broadcast mode. Competition Requirement High

SR-31 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.


SR-32 Each team shall develop their own ground station.


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


SR-34 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.)





13

SR-35 Teams shall plot each telemetry data field in real time during flight.


SR-36 The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a handheld antenna.


SR-37 The ground station must be portable so the team can be positioned at the 9 ground station operation site along the flight line. AC power will not be available at the ground station operation site.


SR-38 Both the heat shield and probe shall be labeled with team contact information including email address.





14

SR-39 The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.


SR-40 No lasers allowed. Competition Requirement High

SR-41 The probe must include an easily accessible power switch.


SR-42 The probe must include a power indicator such as an LED or sound generating device.


SR-43 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second.


SR-44 The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second.





15

SR-45 An audio beacon is required for the probe. It may be powered after landing or operate continuously.


SR-46 Battery source may be alkaline, Ni-Cad, Ni-MH or Lithium. Lithium polymer batteries are not allowed. Lithium cells must be manufactured with a metal package similar to 18650 cells.


SR-47 An easily accessible battery compartment must be included allowing batteries to be installed or removed in less than a minute and not require a total disassembly of the CanSat.


SR-48 Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects.





16

SR-49 A tilt sensor shall be used to verify the stability of the probe during descent with the heat shield deployed and be part of the telemetry.




System Level CanSat Configuration Trade & Selection

Heat Shield/Aero Brake Config 1 Heat Shield/Aero Brake Config 2

– This component was the deciding factor for overall system design– Directly affected the electrical components required– Structural component configuration relied heavily on this

component




• Configuration 1 – This configuration included a

deployable nylon heat shield– Spring tension would open the

heat shield to act as Aero Brake System

• CONOPS Variations – When stowed, fishing line will

be used to retain tensioned rods

– On payload deployment, a nichrome cutting circuit will release heat shield




• Configuration 1 Problems and Risks– Complex design at connection to payload– High risk of fishing line hanging up on expansion of heat shield– Did not comply with requirement S-2 as the heat shield did not fully

envelop the payload prior to deployment– This design over complicated the design of internal structural

components




• Configuration 2– This configuration will consists of a two piece heat shield and

aero-brake– The aero-brake will be affixed to a fiberglass sleeve surrounding the

payload– Spring tension will expand the aero-brake

• CONOPS Variations– fishing line will retain the aero-brake in stowed position– A nichrome cutting circuit will release heat aero-brake– The heat shield will separate into two parts on ejection




• Configuration 2 Benefits– Fully envelopes the payload prior to deployment to comply with

requirement S-2– Simple release mechanism reduces risk of failure during ejection of

heat shield and aero-brake– Allows the addition of a camera to complete the bonus objective



Physical Layout

• Overall Component Layout– Egg centered and well

protected by foam walled container

– Egg container Integrated into capsule

– Aero-Brake and Heat Shield form and assembly and fully enclose the probe

• Deployed Configuration shown

• RBF Pins accessible on exterior of payload

FOAM

EGG

PARACHUTE

FIBERGLASS AERO-BRAKE

HEAT SHIELD


265 mm

RBF Pins


Physical Layout

• Probe Component Layout– Batteries kept low for

to lower COM– Electronics kept

stowed under batteries and egg compartment

– Two part capsule for quick disassembly and access to batteries and egg compartment

– Press Tabs to detach top and bottom capsule sections

PRESS TABS

CAMERA


170 mm

PCB

BATTCOMP


Physical Layout

• Electronics Layout– 4 holes evenly spaced

for mounting screws– All components

thru-hole for ease of soldering

– Contains all sensors and control electronics

GPSRADIO

Altimeter

SD Card Reader GYRO

TEENSY 3.2

TEMP



System Concept of Operations

OP # CONOPS Flow Chart Stage

1 Establish Communication Between Probe and Ground Station

Pre-Flight

2 Pre-Flight System Check Pre-Flight

3 Mount Payload to Rocket Ascent

4 Launch (Apogee at 600m) Ascent

5 Expansion of Aero-Brake Descent

6 Descend at 10-30 m/s Until 300m Altitude Descent

7 Eject Heat Shield and Aero-Brake ASSY and Parachute Deployment

Descent



System Concept of Operations

OP # CONOPS Flow Chart Stage

8 Descend at 5m/s Descent

9 Landing Ground

10 Recovery Ground



Launch Vehicle Compatibility

• Launch Configuration– 3mm clearance on overall outer

diameter given for payload to allow for easy deployment

– 5mm clearance on overall height dimension to ensure the payload fits in the rocket, and so the to payload can easily clear the rocket section at apogee

– All edges are rounded to ensure no sharp surfaces will snag on deployment


295 mm

122 mm


Sensor Subsystem Design

Michael Campbell


Sensor Subsystem Overview

Presenter: Michael Campbell

Probe

Sensor Type Model Purpose

Air Pressure Sensor/Altimeter MS5607 Measure altitude and air pressure

Air Temperature Sensor TMP36 Measure external temperature

GPS MTK3339 w/ Breakout Determine position

Voltage Sensor Voltage Divider Measure power supply voltage

Camera Adafruit camera #3202 Record heat shield deployment

Gyroscope MPU-9250 Measure Tilt


CanSat 2017 PDR: Team ### (Team Number and Name)

30

Sensor Subsystem Requirements


Direct Requirements

Requirement Number Requirement Rationale Priority

SS-01 Total mass of the CanSat (probe) shall be 500 grams +/- 10 grams

Ensure deployment from the launching rocket within a reasonable margin. High

SS-02All electronic components shall be enclosed and shielded from the environment with the exception of sensors

This is meant to prevent the electronics from harming the environment. Medium

SS- 03All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.

To secure the electronics to the probe and prevent damage. Medium

SS-04

During descent, the probe shall collect air pressure, outside air temperature, GPS position and battery voltage once per second and time tag the data with mission time.

Provide information about the status and position of the probe and store it for recovery if possible.

High

SS-05Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.

Competition Requirement. Medium

SS-06A tilt sensor shall be used to verify the stability of the probe during the descent with the heat shield deployed and be part of the telemetry.

Probe orientation cannot easily be determined from the ground, so additional sensors are required.

High


Probe Air Pressure Sensor Trade & Selection


Model Power Usage Mass Dimensions Accuracy Interface

BMP180 3.3V, 32 µA, 105.6 µW per reading/sec

<1 g 3.6 mm X 3.55 mm ±0.25 meters I2C

MPL3115A2 3.3V, 40 µA, 132

µW per reading/sec

0.9 g 4.55 mm X 2.55 mm ±0.3 m / ±1 °C I2C

Selected Air Pressure Sensor – MPL3115A2-Temperature compensated altitude readings versus only pressure, little to no calibration needed-Acceptable accuracy-I2C interface-Secondary temperature sensor


Probe Air Temperature Sensor Trade & Selection


Selected Air Temperature Sensor – TMP36-Simple interface-Acceptable accuracy-Smaller footprint


TMP36 3.3V, 50 µA, 165 µW 0.2 g 2 mm X 2 mm ±1 °C Analog

TMP102 3.3V, 10 µA, 33 µW 0.8 g 14 mm X 14 mm ±0.5 °C I2C


GPS Sensor Trade & Selection



MTK 3339 3.3V, 20mA 8.5g 25.5mm x 35mm x 6.5mm

±3 Meters±0.1 m/s Tx/Rx

Venus638FLPx 3.3V, 67mA 6g 18mm x 29.5mm x 2mm ±2.5 Meters Tx/Rx

Selected GPS – MTK3339-Includes built in antenna-10Hz update rate-Reduced power draw and mass


Probe Power Voltage Sensor Trade & Selection


Selected Voltage Measurement Method - Voltage divider-Integrated on the board-Can easily measure voltage before conversion-Acceptable power usage-Easily modified

Model Power Usage Mass Dimensions Accuracy Interface Model

NCP303 3.3V, .5μA <1 g 0.4 cm X 0.2 cm 2.0% Analog NCP303

Voltage divider 3.3V, 2mA 0.5 g 0.2 cm X 1 cm 2.0% Analog Voltage divider


Tilt Sensor Trade & Selection


Selected Tilt Sensor - Sparkfun MPU-9250- Small size- Lightweight- I2C interface- Correct operating Voltage


Adafruit LSM9DS1 1.9-3.6V, 4mA 3g 33.02 x 20.32 mm +/- 30 °/sec I2C

Sparkfun MPU-9250 2.4-3.6V, 3.2mA 1.5g 10.92 x 17.78 mm +/- 5 °/sec I2C


Bonus Camera Trade & Selection


Model Power Usage Mass Dimensions Resolution Interface

Adafruit camera #3202

5V80mA Standby110mA Active

2.8g 28.5mm x 17mm x 4.2mm

1280x720 Picture640x480 Video 3.3V Trigger

Adafruit camera #1386

3.3V75mA 3g 20mm x 28mm

640x480 Picture640x480

TTL VideoTeensy RX/TX

Selected Camera - Adafruit #3202-Able to record video-Built in SD memory card-Simple interface


Descent Control Design

Anthony McCourt

#slide=id.p5


Descent Control Requirements

Requirement Description Rationale

DC-01

The aero-braking heat shield shall be used to protect the probe while in the rocket only and when deployed from the rocket. It shall envelope/shield the whole sides of the probe when in the stowed configuration in the rocket. The rear end of the probe can be open.

Competition Requirement

DC-02 The probe shall not tumble during any portion of descent. Tumbling is rotating end-over-end.


DC-03

The probe with the aero-braking heat shield shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length. Tolerances are to be included to facilitate container deployment from the rocket fairing.


DC-04 The probe shall deploy a parachute at 300 meters. Competition Requirement

DC-05 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second.


DC-06 The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second.


Presenter: Anthony McCourt


Payload Descent Control Strategy Selection and Trade

Parachute Area(m2)

Mass(g) Shape

Shock Force

Survival

DCS Connections

Preflight Review

TestabilityColor

CFC-18” Chute(Fruity Chutes) 0.164 49.33

Elliptical and hole

(10% Area)

Good(Flexible) Nylon Lines Good

(Drop Test)Orange/

Black

TARC-18” Chute

(Fruity Chutes)0.164 22.68

Round and hole

(10% Area)

Good(Flexible)

Lightweight Spectra Lines

Good(Drop Test)

Orange/Black

● Both parachutes provided the desired 5 m/s descent rate● However, the TARC-18” parachute was decided on due to the 22.68 g mass

versus the CFC-18” Chute with more than double the mass of 49.33 g. This larger mass detracted from the mass budget for electronics as well as moving the center of mass further aft.



Descent Stability Control Strategy Selection and Trade

Heat Shield Design & Control System Overview


Spherically Blunted Cone (SBC)-Based Design

❖ Passive Control Mechanism➢ Mass is kept at the cone-shaped end to

keep center of mass below the center of pressure

➢ Aerodynamic properties of the body keep it stable with no need of active control system

➢ Minimizes need for unnecessary mechanical or electrical systems■ Frees mass budget for critical

components



First Iteration — SBC without capsule or skirt ❖ Based on the Apollo re-entry vehicles used by NASA (left)❖ Fluid analysis via Solidworks determined that preliminary

design would result in unwanted turbulence in the body’s wake (right)




First Iteration — SBC without capsule or skirt ❖ Pros:

➢ Passive stability control ➢ Mass can be kept at tip of cone to push center of

gravity near the nose➢ Simple geometry can be 3D printed at low cost and

mass➢ ABS plastic is rough enough to keep falling velocity

within limits ❖ Cons:

➢ Stubby design pushes center of pressure near center of gravity

➢ Wake turbulence may result in instability➢ Complicates heat shield and parachute deployment

42Presenter: Anthony McCourt



Second Iteration — SBC with capsule ❖ Added capsule with deployable heat shield (left)❖ Fluid analysis depicting smoother streamlines with smaller

wake vortices than first iteration (right)




Second Iteration — SBC with capsule❖ Pros:

➢ Center of pressure is pushed away from center of gravity due to elongated body, increasing stability

➢ Heat shield is easily detachable from the capsule❖ Cons:

➢ Slender profile causes body to fall too quickly due to smaller wetted area

➢ Parachute still somewhat difficult to deploy due to solid back-end




Third Iteration — SBC with capsule and skirt ❖ Added skirt produces skin friction drag which allows for a

slower decent (left)❖ Fluid analysis that turbulence develops on either side of the

skirt (right)




Third Iteration — SBC with capsule and skirt❖ Pros:

➢ Added surface area results in more drag, slowing descent

❖ Cons: ➢ ABS plastic is relatively heavy, resulting in large part of

mass budget being reserved for capsule➢ Turbulent flow between capsule and skirt may result in

instability




Fourth Iteration — Fiberglass SBC with capsule and spoked-skirt

❖ Fourth Iteration and current model of CanSat (left)❖ Flow simulation shows smooth streamlines leaving the

body (right)




Fourth Iteration — Fiberglass SBC with capsule and spoked-skirt

❖ Pros:➢ Parachute can be easily deployed through the hollow

tail➢ Fiberglass is lighter than ABS plastic resulting in less

mass needed for capsuled➢ Fiberglass has a higher structural integrity than ABS

plastic ➢ ABS plastic heat shield slows capsule down until

detachment ❖ Cons:

➢ Less surface roughness than ABS plastic



Descent Rate Estimates

Methodology


• A code was written inside of MatLab in order to estimate the Lift produced by the CanSat in both configurations by using the Slender-Body Theory and Cross-Flow Drag.

– The CanSat Profile was cut up by 1 mm slices and the change in radius, along with the oncoming velocity and Reynolds Number at each slice

– Integrating all the pieces produced a total Lift that could be run several times at varying angles of attack (AoA) and oncoming velocities

Assumptions:• The altitude of Stephenville, TX was used

for air density calculations • CanSat is perfectly cylindrical about center

Plot descriptions:• Top-Left - Lift produced by Cross-flow drag• Top-Right - Profile of CanSat• Bottom-Left - Slender Body Lift• Bottom-Right - Total Lift



Descent Rate Estimate of CanSat Pre-Deployment


• This configuration did not produce sufficient lift within the 10-30 m/s descent rate window. The Steady-State velocity for this configuration was calculated to be upwards from 32.5 m/s at a 29° Angle of attack. As the AoA decreased, the steady-state estimate rose.

• This configuration does not match the required descent rate window, however, this is acceptable due to this configuration only lasting, at most, a few seconds post-ejection from the rocket. The following “open” configuration does fall within the required descent window



Descent Rate Estimate of CanSat Post-Deployment


• This configuration is after the “skirt” of the CanSat is released shortly after ejection from the rocket.

• This configuration falls within the acceptable window of required descent rate.

• The plot on the bottom shows the steady-state velocity of the CanSat in this configuration at a varying AoA. Even at a small AoA, the CanSat will be producing enough lift to stay within the maximum 30 m/s descent rate.



Descent Rate Estimate of CanSat Post-Separation


● Current mass estimates place the CanSat mass, post-separation at 375 g○ Using the selected

TARC-18 parachute, and the drag estimates provided by FruityChutes, the current decent rate estimate is at 5.04 m/s

○ This mass is optimal for achieving a post-separation decent rate of ~5 m/s, for ±50 g of mass will move the descent rate by ±0.5 m/s

Shown above is a plot of the descent rate versus mass for the selected TARC-18 parachute



Summary of Descent Rate Estimates


● As stated before, both the CanSat post-deployment and post-heat shield separation fall within the required descent rate window.○ The only configuration that

falls outside of it is the pre-deployment configuration. This, however is only for a few seconds as the CanSat is being ejected from its stowed configuration

Shown above is the summary of the estimated descent rates of the CanSat for their respective Configurations

CanSat Configuration Calculated Descent Rate Range

Pre-Deployment 32.5+ m/s

Post-Deployment 10-30 m/s

Post-Heat Shield Separation 5.04 m/s


Mechanical Subsystem Design

Lyle Hailey and Dwight Scott

#slide=id.p5


Mechanical Subsystem Overview

Presenter: Lyle Hailey & Dwight Scott

FIBERGLASS SLEEVE3D PRINTED

CAPSULE TOP

NYLON RIPSTOP DROGUE

3D PRINTED CAPSULE BOTTOM

3D PRINTED HEAT SHIELD

E-STACK

FOAM PADDING

PRESS TABS X4

EGG CONTAINER LID


Mechanical Sub-System Requirements

Direct Requirements


M-1 Total mass of the CanSat (probe) shall be 500 grams +/- 10 grams Competition Requirement High

M-2The probe shall hold a large hen's egg and protect it from damage fromlaunch until landing.


M-3

The probe shall accommodate a large hen’s egg with a mass ranging from 54 grams to 68 grams and a diameter of up to 50mm and length up to 70mm.


M-4 The rocket airframe shall not be used to restrain any deployable parts of the CanSat. Competition Requirement High

M-5 The rocket airframe shall not be used as part of the CanSat operations. Competition Requirement High




Direct Requirements


M-6 The CanSat, probe with heat shield attached shall deploy from the rocket payload section. Competition Requirement High

M-7 The aero-braking heat shield shall be released from the probe at 300 meters. Competition Requirement. High

M-8 The probe shall deploy a parachute at 300 meters. Competition Requirement High

M-9All descent control device attachment components (aero-braking heat shield and parachute) shall survive 30 Gs of shock.


M-10All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock.

Competition Requirement. High




Direct Requirements


M-11 All structures shall be built to survive 15 Gs of launch acceleration Competition Requirement High

M-12 All structures shall be built to survive 30 Gs of shock. Competition Requirement. High

M-13 All mechanisms shall be capable of maintaining their configuration or states under all forces. Competition Requirement High

M-14 Mechanisms shall not use pyrotechnics or chemicals. Competition Requirement High

M-15

Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to the outside environment to reduce potential risk of setting vegetation on fire





Direct Requirements


M-16Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.


M-17Both the heat shield and probe shall be labeled with team contact information including email address.


M-18 No lasers allowed. Competition Requirement High

M-19 The probe must include an easily accessible power switch Competition Requirement High

M-20The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second.





Direct Requirements


M-21The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second.


M-22

Battery source may be alkaline, Ni-Cad, Ni-MH or Lithium. Lithium polymer batteries are not allowed. Lithium cells must be manufactured with a metal package similar to 18650 cells.


M-23

An easily accessible battery compartment must be included allowing batteries to be installed or removed in less than a minute and not require a total disassembly of the CanSat.


M-24Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects




Probe Mechanical Layout of Components Trade & Selection

• Probe Design 1: Glued Assembly Configuration– 3d Printed ABS Structure– Circular Heat Shield Attachment points – Electronics mount into bottom of Probe

HEAT SHIELD ATTACH POINTS

ELECTRONICS MOUNTING AREA

TAPERED THROUGHOUT

AERO FIN




• Probe Design 2: Press Tab Configuration (Chosen Configuration)– 3d Printed ABS Structure– E-Stack included for mounting PCB and Batteries

ELECTRONICS STACK

HEAT SHIELD ATTACH POINTS

STRAIGHT SECTION

TAPERED SECTION

PRESS TABS FOR DISASSEMBLY




• Overview– Both configurations were designed for 3d printing. This

was chosen as material because of the ease of adding mounting structures to the probe

– 4 heat shield attachment points were included in Design 2: Press Tab Config to hold securely

– Electronics mounting for both designs was nearly identical

– Design 2 included an egg container as part of the capsule body

– Design 1 included a fin for aerodynamic properties




• Selection Justification– Design 2: Press Tab Configuration was chosen– This design allow for easier disassembly than design one

because of the press tabs.– The straight section on Design 2 made manufacturing

and assembly simple– Design 2 allows for access to both batteries and egg

compartment in under 1 minute– The fin on Design 1 proved to be too flimsy to last under

defined loading and shock conditions– Heat shield detachment on Design 2 has less contacting

surface area for a smooth release, while still having better mechanical properties than Design 1



Payload Pre DeploymentConfiguration Trade & Selection

• Design 1: Inverted Umbrella• Uses a torsion spring tensioned

rod to hold in stowed configuration.– Fishing line used to connect

tensioned rod to nichrome cutting circuit

– Nichrome circuit used to cut fishing line and release aero-brake

– Outward facing to allow for easy expansion

NICHROME CIRCUIT

TORSIONSPRINGS

FISHING LINE




• Design 2: Aero-Brake Drogue (Chosen Configuration)

• Uses a torsion spring tensioned rod to hold in stowed configuration.– Fishing line used to connect

tensioned rod to nichrome cutting circuit

– Nichrome circuit used to cut fishing line and release aero-brake

– Fishing line tied to ends of rods for more torque

TORSIONSPRINGS

FISHING LINE

NICHROME CIRCUIT




• Selection Justification– Design 2: Aero-Brake Drogue was chosen– This design used the same mechanism as Design 1, but

the moving parts were more concealed– The Brake facing inward pre-deployment eliminated risk

of sharp edges snagging on inside of rocket section.– The inward angle also meant that the fishing lines would

have less stress on them to hold the payload in the stowed configuration

– Design 1 did not fully cover the probe pre deployment



Heat shield Deployment Configuration Trade & Selection

• Deployment Options–Passive (using force from surrounding air–Active (using spring tension)

• PassivePros:

–The idea of this method was to allow the air to push open the heat shield into deployed configuration–Requires no electronic control circuitry or power–The weight would be considerably less

Cons:–Unreliable–Unstable Aerodynamic properties




• Active (chosen option)Pros:

–Reliable –Much less risk of payload becoming unstable on descent–Solid construction–Can ensure expansion of Aero-Brake on deployment from rocketCons:

–More complicated design–Requires more more electronics–More costly on mass budget




• Selection Justification–Maintaining stability and the proper descent rate was vital to the mission operations–The reliability of the payload deployment far outweighed the effect this had on the mass budget–The Payload was light enough to allow for flexibility in choosing this option –Nichrome circuits have been proven to work, and are an effective way to release a deployable structure



Heat shield Mechanical Layout of Components Trade & Selection

• Position of Heat Shield Aero-Braking Assembly was a major factor in design.

• 3 Design configurations were considered• Major Selection Criteria:

– Weight: location and material will factor into the overall mass of the payload

– Material: considered both weight and strength of material– Requirement compliance: needed to comply with all

mission requirements– Ease of Assembly: Need quick access to Egg and

Batteries– Strength: Considered structure and material properties– Deployment Reliability: Ability to release from rocket




• Heat Shield Mechanical Layout Design 1 (Upside Down Umbrella)

Criteria Score (1-10)

Weight 6

Material 10

Requirement Compliance

4

Ease of Assembly 6

Structural integrity 6

Deployment Reliability 6

TORSIONSPRINGS

PROBE

HEAT SHIELD

DEPLOYED CONFIG

LAUNCH CONFIG




• Heat Shield Mechanical Layout Design 2 (Fiberglass Sleeve Aero-Brake Assembly)


Weight 9

Material 10


10

Ease of Assembly 9



PROBE

TORSIONSPRINGS

HEAT SHIELD

DEPLOYED CONFIG

LAUNCH CONFIG

AERO-BRAKE




• Heat Shield Mechanical Layout Design 3 (Side Wall Heat Shield)


Weight 8

Material 10


8

Ease of Assembly 5



TORSIONSPRINGS

PROBE

HEAT SHIELDDEPLOYED CONFIG

LAUNCH CONFIG




• Overview and Selection:• Layout Design 2 was chosen

– Bringing the deployment structure away from the internal components allowed for lowest overall weight

– Fulfilled all mission requirements regarding heat shield– Best deployment reliability due to inward facing stowed

configuration, which meant less obstructions and no sharp surfaces on outside of payload

– Similar structural integrity to Design 3, but far better than Design 1 due to mounting structures and springs being covered by the heat shield

– All designs combined 3d printed structures, with a spring tensioned Nylon Ripstop Aero-Brake



Heat shield Release Mechanism

• The heat shield is connected to the probe with 3d printed tabs that insert into the probe– Tabs have holes to tie fishing line– Fishing line attaches toboth the heat shield &Fiberglass sleeve forsimultaneous deployment– Fishing line is cut withnichrome cutting circuit

RELEASE POINTS



Probe Parachute Release Mechanism

•Probe Parachute will be stowed on top of probe, under pre deployed Aero-Brake in the launch configuration

– A wrap will be wound up on parachute and fixed to the fiberglass sleeve portion of the Aero-Brake

– This will unwind and deploy the parachute when the heat shield and Aero-Brake are released.

77

RELEASE STRING



Egg Protection Structure

•Foam was chosen as the primary egg protection•Design of probe includes a container for the egg with foam lining to provide protection

– The egg container lid features a twist-locking mechanism that is easily accessible, but also securely holds the egg in place during flight

TWIST LOCK LID

FOAM LINED CONTAINER



Electronics Structural Integrity

• Electronics will be connected using screws and threaded inserts– Inserts will be fixed in bottom surface of satellite – No separate enclosure will be used for the pcb board, but

all structures above the pcb will be secured to the body of payload fully enclosed by the capsule

– M3 screws will be used to affix the pcd to the fixed inserts• Descent control attachments will be deployed using

nichrome wire – The nichrome wire will activate the deployable aerobrake– A separate nichrome circuit will detach both the heat

shield and aerobrake from the satellite at the 300m altitude

– 79Presenter: Lyle Hailey & Dwight Scott


Mass Budget

ComponentEstimated

Weight (grams)

Sources

Structural Elements 110 From

Estimates

Egg 68From

Competition Guidelines

Parachute 60 From Estimates

Electronic Components 112 Data Sheets

Probe Final Weight 350

ComponentEstimated

Weight (grams)

Sources

Probe Weight 350 From Table

to Left

Heat Shield 100 From Estimates

Margin 50Remaining

Mass Budget

CanSat Final

Weight500



Communication and Data Handling (CDH) Subsystem Design

Presenter: Sina Malek

#slide=id.p5


CDH Overview


● Teensy 3.2○ Data telemetry control○ Sensor data acquisition

● XBEE-Pro 900-HP○ Main radio communication with ground station

● 900 Mhz Duck Antenna○ Antenna for XBEE radio

● Real-time clock integrated in Ultimate GPS Module○ Mission time tracking


CDH Requirements


ID Requirement Rationale Priority

CDH-01

During descent, the probe shall collect air pressure, outside air temperature, GPS position, and battery voltage once per second and time tag the data with mission time.

Probe data must be collected for transmission to monitor its status.

HIGH

CDH-02During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts.

Live feed of collected probe data. HIGH

CDH-03During XBEE radios shall be used for telemetry. 2.4 Ghz Series 1 and 2 or 900 MHz XBEE Pro radios shall be used.

Standardization of telemetry broadcast frequencies.

HIGH

CDH-04 XBEE radios shall have their NETID/PANID set to the team’s number.

Uniquely identify radio transmissions. HIGH

CDH-05 XBEE radios shall not use broadcast mode.

Minimize risk of radio interference between teams.

HIGH


Probe Processor & Memory Trade & Selection


Board Processor Memory I/O Power Dimensions

Teensy 3.2 32-bit ARM Cortex M4 @ 72Mhz

256K Flash64K RAM2K EEPROM

Serial (3)SPI (1)I2C (2)

3.3V (5V Tolerant) 3.5cm x 1.8cm

Arduino Nano

ATmega328P @ 16Mhz

32K Flash2K RAM1K EEPROM

Serial (1)SPI (1)I2C (1)

5V (7-12V Unregulated)

4.5cm x 1.8cm

Selected: Teensy 3.2● Significantly higher clock speed● Larger program and runtime memory

allows more flexibility in development● Additional hardware serial I/O● More compact


Probe Real-Time Clock

85Presenter: Sina Malek

Type Model Dimensions Power Loss Mitigation

Software Teensy/Arduino millis() function (integrated)

Integrated File I/O

Hardware Ultimate GPS Breakout (integrated)

Integrated Battery backup (CR1220)

Selected: Ultimate GPS (integrated RTC)● Backup battery maintains time through

processor resets● Simple serial query● Integrated into GPS hardware


Probe Antenna Trade & Selection


Model Gain VSWR Dimensions Interface

900 MHz Rubber Duck Antenna

2 dBi 2.0:1 Height: 160mm RP-SMA

LCOM patch HG902PU

2 dBi 2.0:1 40x8mm x 53.6mm U.FL

Selected: 900Mhz Duck antenna● Appropriate interface for selected XBee

900 MHz modules● Smaller size● suitable radiation pattern


Probe Radio Configuration


Radio Selection: XBEE-PRO 900-HP

Frequency: 900 MhzConfigured in Transparent (AT) ModeNETID: Team 5278

Transmission ControlContinuous transmission at a rate of 1Hz with the ground station will be managed by the flight software during the descent state of its operation.


Probe Telemetry Format

• The probe telemetry consists of ASCII comma separated fields followed by a carriage return.

• Data will be transmitted once per second at 9600 baud in continuous mode.• Sensor data as well as mission time, packet count, and the current software

state will be transmitted.

The data format is as follows:<TEAM ID>,<MISSION TIME>,<PACKET COUNT>,<ALTITUDE>, <PRESSURE>,<TEMP>,<VOLTAGE>,<GPS TIME>,<GPS LATITUDE>,<GPS LONGITUDE>,<GPS ALTITUDE>,<GPS SATS>,<TILT X>,<TILT Y>,<TILT Z>,<SOFTWARE STATE>

Example data:[5278,60,40,1000,1013,20,3.3,123.5,33.5,-111.9,1410,3,0.01,0.0,0.3,3]



Electrical Power Subsystem (EPS) Design

Mecah Levy

#slide=id.p5


EPS Overview

Presenter: Mecah Levy

Payload

Component Type Model Description

Battery Pack A AAAA Battery x4 Main power source

Battery Pack B AAAA Battery x4 Powers nichrome cutting circuit and camera

3.3V Voltage Regulator LD33V regulator Regulates voltage to components

5V Regulator L7805CV Regulator Regulates voltage for camera

Power Control RBF pin Controls power on/off

Tertiary battery CR2032 Power for RTC


EPS Overview Diagram

91

RBF Switch

3.3V Regulator

Nichrome Cutting Circuit

Sensors

Microcontroller4x

AAAAPack A

Micro-USB Power

4x AAAAPack B

RBF Switch

91Presenter: Mecah Levy

5V Regulator Camera


EPS Requirements


ID Requirements Rationale Priority

EPS-01The probe must include an easily accessible power switch.

To easily restrict power to the probe High

EPS-02 The probe must include a power indicator such as an LED or sound generating device. To easily indicate if the probe is

on/off High

EPS-03

Battery source may be alkaline, Ni-Cad, Ni-MH or Lithium. Lithium polymer batteries are not allowed. Lithium cells must be manufactured with a metal package similar to 18650 cells.

To comply with competition rules on power supplies High

EPS-04 An easily accessible battery compartment must be included allowing batteries to be installed or removed in less than a minute and not require a total disassembly of the CanSat.

Easily access power supply High

EPS-05 Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects.

For no loss of power High


Probe Electrical Block Diagram


Audio Beacon

3.3V Regulator

3.3V

Microcontroller

Temperature GPS Micro SD AltimeterXBEE Pro

CR2032 RTC

RBF Switch

6V~2.7 - 6V4x AAAA

Alkaline Batteries

RBF Switch

6V4x AAAA Alkaline Batteries

Micro-USB Power

*Umbilical Power

Nichrome Cutting Circuit

~2.7 - 6V

5V Regulator 5V Camera

Gyroscope

● Power will be controlled by an external switch.

● Will verify battery voltage using voltage divider reading from microcontroller


Probe Power Trade & Selection

94

Model Capacity Nominal Voltage Mass Dimensions

Energizer E96 AAAA Alkaline

Battery550 mAh 1.5V 6.5g 40.7mm x 8mm

Powerizer 123A Li-ion battery 650 mAh 3.7V 18g 36mm x 17mm

Energizer E92 AAA Alkaline Battery 500 mAh 1.5V 11.5g 44.5mm x 10.5mm

Selected Battery - 4x in Series Energizer AAAA

- Small Profile - High capacity- Past success



Probe Power Budget


Component Model Duty Cycle Current (A) Voltage (V) Power (W) Source

Microcontroller Teensy 3.2 100% 0.039 3.3 0.1287 Estimated

Radio XBEE Pro 900 Hp 100% 0.244 3.3 0.8052 Data sheet

GPS FGPMMOPA6H 100% 0.025 3.3 0.0825 Data sheet

Memory micro SD card 30% 0.01 3.3 0.033 Estimated

Altimeter MS5607 100% 0.00174 3.3 0.005742 Data sheet

Temperature TMP36 100% 0.000023 3.3 0.0000759 Data sheet

Gyroscope MPU-9250 30% 0.0032 3.3 0.01056 Data sheet

3.3V Regulator L4931 100% 0.3 3.7 1.11 Data sheet

Audio Beacon Piezo Buzzer 12% 0.035 3.3 0.1155 Data sheet

Total A 0.657963 2.2912779Power supply B

Camera (Standby) Adafruit #320297.63%-98% use 98% 0.08 5 0.4 Data sheet

Camera (Operating) Adafruit #3202 2.4%-3% used 3% 0.11 5 0.55 Data sheet

5V Regulator L7805CV 100% 0.0008 5 0.004 Data sheet

Cutting Circuit Nichrome wire 1% 3 6 18 Calculated

Total B 3.08 18.4


Probe Power Margin


Battery Pack A Power Available: 3300 mWh

Sensor Power Consumption: 1501.2203 mWh

Battery A Power Margin: 55%

Battery Pack B Power Available: 3300 mWh

Sensor Power Consumption: 293.7633 mWh

Battery B Power Margin: 91%


Flight Software (FSW) Design

Vijay Ramakrishna

#slide=id.p5


FSW Overview

• Overview – During startup, CanSat evaluates startup state based on telemetry and

non-volatile EEPROM• Programming language:

– Arduino/C++• Development environment:

– Atom/Arduino IDE/Teensy bootloader• FSW tasks:

– Collect and save telemetry at 1Hz– Transmit telemetry packets to Ground Station– Trigger parachute deployment and heat shield release

Presenter: Vijay Ramakrishna


FSW Requirements


ID Requirement Rationale

FSW-01 The aero-braking heat shield shall be released from the probe at 300 meters.

The probe will have already entered the atmosphere, and so drag will be less of an issue. A parachute will provide better slowing of the descent at this phase.

FSW-02 The probe shall not tumble during any part of the descent. Tumbling is rotating end-over-end.

Tumbling can potentially throw off or damage sensors, other electronic components, and the payload contained in the probe.

FSW-03 During descent, the probe shall collect air pressure, outside air temperature, GPS position, and battery voltage once per second and time tag the data with mission time

Telemetry from the probe must be collected and time-stamped in order to determine the current status of the probee.


FSW Requirements



FSW-04 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts.

The probe must be able to communicate with the ground station in order to relay information about the probe’s status

FSW-05 Telemetry shall include mission time with one second or better resolution. Mission time shall be maintained in the event of a processor reset during the launch and mission

Data collected by the probe must be accurate.

FSW-06 All telemetry shall be displayed in real-time during the descent

The probe must provide recent data samples to the ground station.


FSW Requirements



FSW-07 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.)

Required in order to ensure the accuracy and understandability of the data.

FSW-08 The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.

Ensures that accurate telemetry is transmitted even if the processor is reset mid-flight.

FSW-09 No lasers allowed. Lasers pose a threat to the flora and fauna of the launch site!


FSW Requirements



FSW-10 (MISSION-45) An audio beacon is required for the probe. It may be powered after landing or operate continuously.

The probe must be able to be easily located after flight.

FSW-11 (MISSION-49) A tilt sensor shall be used to verify the stability of the probe during descent with the heat shield deployed and be part of the telemetry.

The probe must remain stable in order to ensure the safety of the payload. Stability must be verifiable for this purpose.


FSW Requirements



FSW-12 (Telemetry Requirements)

Upon powering up, the CanSat probe shall collect the required telemetry at a 1 Hz sample rate.The telemetry data shall be transmitted with ASCII comma separated fields followed by a carriage return in the following format:

<TEAMID>,<MISSION TIME>,<PACKET COUNT>,<ALTITUDE>,<PRESSURE>,<TEMP>,<VOLTAGE>,<GPS TIME>,<GPS LATITUDE>,<GPS LONGITUDE>,<GPS ALTITUDE>,<GPS SATS>,<TILT X>,<TILT Y>,<TILT Z>,<SOFTWARE STATE>

The telemetry data from the probe must be structured in order to be easily understandable.


Probe FSW State Diagram


Recovery- Non-volatile

EEPROM is used on reset to determine state, packet count, and initialize MET

Power- Power management

is handled via Teensy 3.2


Software Development Plan

• Top priority: Early development– Agile development scheme – Rapid response to changes in design– Prioritize organization and clarity

• Regression tests– Hardware integration will require system checks– Verifies software and hardware configuration

• Subsystem modularity– Remove external dependencies in each package



Ground Control System (GCS) Design

Vijay Ramakrishna

#slide=id.p5


GCS Overview



GCS Requirements



GCS-01 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.

XBEE shall be used to communicate with the probe

GCS-02 XBEE radios shall have their NETID/PANID set to their team number.

The telemetry must be identifiable to a specific team.

GCS-03 XBEE radios shall not use broadcast mode.

The XBEE radios must not be allowed to broadcast data over to other teams during competition.


GCS Requirements



GCS-04 Each team shall develop their own ground station.

The ground station must be

custom, and cannot be shared between teams.

GCS-05 Teams shall plot each telemetry data field in real time during flight.

The ground station must be aware of the current state of the probe at any time, to within a 1Hz resolution.

GCS-06 The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a handheld antenna.

The ground station must be able to fit in the allotted space during competition.


GCS Requirements



GCS-07 The ground station must 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.

The ground station must be able to continue to collect data for the duration of the mission.


GCS Design

111

Laptop (>=two hour battery life)

XBee Pro 900HP

900 MHzTrue Gain Antenna

DATA

GCS Desktop GUI Sparkfun XBee Explorer Dongle



GCS Design

• GCS Specifications– Operation Time

•GCS can operate for two hours on battery (or however long the battery on the laptop used lasts)

– Overheating mitigation •Umbrella to block direct exposure to sunlight

– Auto update mitigation•Disable Auto-Updates for the duration of the competition (48 hours beforehand to be safe). Ensure that any mandatory updates will have already taken place at least 48 hours before competition time

–On Windows: Disable Automatic Updates in Control Panel–On Mac: Disable Automatic Updates in Preferences

– Critical Error Mitigation•Program in a reset command. Make it require multiple inputs from the user (In case something goes wrong with translating data packets)•Have another laptop fully charged and ready to go in the event of one laptop outright failing

112Presenter: Vijay Ramakrishna


GCS Antenna Trade & Selection

Model Gain Mass Type Interface Mount

L-Com HG909Y-RSP 9dBi 0.7kg Directional Yagi RP-SMA Hand

True Gain TG-Y915-15 13dBi 0.74kg Directional Yagi RP-SMA Hand

L-Com HG908U-PRO 8dBi 1.7 kg Omnidirectional N-Type Table

Selected: True Gain Yagi-Lightweight-Operational up to 100mph-Suitable gain-Prior success



GCS Software

114

• Example Telemetry Data:

–<5278>,<48.325>,<48>,<235>,<1013>,<14.86>,<22.8>,<3.5>,<128.4>,<DESCENT>

• COTS software packages:

–Arduino IDE - board programming

–C# - real-time plotting, sending of serial commands via Winforms, GBee libraries

–XCTU - Configuring XBee radios

• Real-time plotting

–Using C# libraries to process and display telemetry

• Data archiving

–saved on GS and onboard payload

–.csv file created by GC software from received data

• Commands over C#:

–Mission start, override parachute deployment/heat shield release, override audio beacon



GCS Bonus Wind Sensor

• Our team is not pursuing this bonus objective at this time

115Presenter: Vijay Ramakrishna


CanSat Integration and Test

David Madden


Subsystem Level Testing Plan

• Aeronautics Subsystem– Windtunnel test.– Testing of heat shield

deployment at ground level– Testing of heat shield

deployment while in free fall.– Completed Parachute Test of

10 meters– Completed Parachute and

Egg Test of 10 meters Successfully

117Presenter: David Madden



• Mechanical Subsystem– Drop test of payload with

parachute from 10 meters completed successfully

– Drop test of payload with 30g’s of impulse from string completed successfully

– Drop test of final design without egg

– Drop test of final design with egg

– Drop test of all parts integrated




• Electrical Subsystem– Nichrome Wire cutting circuit testing from ground level,

cutting a taut fishing line.– GPS testing individually by physical displacement.– GPS testing while integrated into the CanSat by

physical displacement– XBees testing through configuration and set up with

other proven electronics– Range test for radio communication– Sensor data collection prototypes have been tested.– Gyroscope to be tested through random motion– Remainder tests scheduled for completion at ground

level and during test launch in March



Integrated Level Functional Test Plan

• Drop container with payload from quadcopter at a height above 300m to test full parachute deployment, nichrome wire cutting circuit, heat shield release, and the survival of an

• Drop container with payload from quadcopter at a height above 300m to test full sensors, communications, the camera, and electronics integration and range.

• Full drop test of payload in container from rocket launch. To be deployed at competition height (670m-725m) for full testing of every subsystem.



Environmental Test Plan

Drop Tests• Various Drop Tests with varying heights to ensure survivability of CanSat and Egg contained within.Thermal tests• Perform thermal test on entire system by placing system in an insulating container and using a heat gun to maintain a hightemperature for 1 hour to ensure survivability duringtransport.Vibration tests• Vibration tests on payload to test structure stability to survive launch. This will also be used to ensure survivability of the Egg inside the CanSat.



Mission Operations & Analysis

Mecah Levy


Overview of Mission Sequence of Events


Team Member Roles and Responsibilities• Mission control officer (M)

– Alex Schneider• Ground Station crew (G)

– Mecah Levy– Vijay Ramakrishna– Sina Malek

• Recovery crew (R)– Lyle Hailey– Anthony McCourt– Mennatallah Hussein

• Cansat Crew (C)– Frank Pinon– David “Jack” Madden– Michael Campbell


Overview of Mission Sequence of Events


Key:(G) Ground Station Crew (R) Recovery Crew(C) Container Crew (M) Mission Control Officer


Mission Operations Manual Development Plan


Mission Operation Manual includes instructions and checklists for the following:

• Ground Station Configuration– Operation– Testing

• Payload Preparation – Assembly – Individual subsystems testing

• Rocket Integration Checklist• Launch

– Rocket preparation• Removal

– Recovery– Data handling

Mission Operation Manual also includes:• Team members, launch operations, crew assignments, and descriptions• Sequence of events• Safety instructions


CanSat Location and Recovery


In order to facilitate payload recovery, the following measures will be implemented:

• Payload will be visually tracked by recovery team

Probe• Utilizes fluorescent orange ripstop nylon parachute• Audio beacon will start automatically after landing• Recovery crew will utilize last GPS coordinates transmitted to narrow search

area.• Labeled with team contact information

Heat-Shield• Exterior surface is painted fluorescent orange. • Team name and number, and team leader contact information is written on

exterior surface


Requirements Compliance

Mennahtallah Hussein


Requirements Compliance Overview

State of CanSat System• The CanSat currently meets the general requirements that are laid out in

the following slides

• The main thing that need to be improved/tested more is deployment and

separation. Integration needs to be tested

• Further environmental testing will be done in the coming month like

shock, thermal, and vibration tests

• Overall, the CanSat shows great results, but will continue to be

developed and perfected through future tests

Presenter: Mennatallah Hussein



129Presenter: Mennatallah Hussein

RqmtNum Requirement

Comply / No Comply /

Partial

X-Ref Slide(s) Demonstrating

Compliance

Team Commentsor Notes

1 Total mass of the CanSat (probe) shall be 500 grams +/- 10 grams. Comply 52 The CanSat mass is 375g

2

The aero-braking heat shield shall be used to protect the probe while in the rocket only and when deployed from the rocket. It shall envelope/shield the whole sides of the probe when in the stowed configuration in the rocket. The rear end of the probe can be open.

Comply 22

3 The heat shield must not have any openings. Comply 22Heat shield is rigid with no openings

4 The probe must maintain its heat shield orientation in the direction of descent. Comply 117

5 The probe shall not tumble during any portion of descent. Tumbling is rotating end-over-end. Partial 117

current simulations show compliance/physical tests

need to be done

6

The probe with the aero-braking heat shield shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length. Tolerances are to be included to facilitate container deployment from the rocket fairing.

Comply 27 Our probe fits in a cylinder with a 295mm length and a 122mm diameter

7 The probe shall hold a large hen's egg and protect it from damage from launch until landing. Comply 23

The egg is secured in the probe with the electronics underneath

8The probe shall accommodate a large hen’s egg with a mass ranging from 54 grams to 68 grams and a diameter of up to 50mm and length up to 70mm.

Comply 27Probe is designed to accommodate the max egg’s dimensions and mass

9The aero-braking heat shield shall not have any sharp edges to cause it to get stuck in the rocket payload section which is made of cardboard.

Comply 27 No sharp edges are in the heat shield




RqmtNum Requirement


Partial


Compliance


10 The aero-braking heat shield shall be a fluorescent color; pink or orange. Comply 126

The heat shield is orange in color

11 The rocket airframe shall not be used to restrain any deployable parts of the CanSat. Comply 27

3mm clearance on outer diameter allowing easy deployment

12 The rocket airframe shall not be used as part of the CanSat operations. Comply 22

Payload will completely clear the rocket section at apogee

13 The CanSat, probe with heat shield attached shall deploy from the rocket payload section. Comply 22

CanSat deploys from rocket at apogee

14 The aero-braking heat shield shall be released from the probe at 300 meters. Comply 124

15 The probe shall deploy a parachute at 300 meters. Comply 124

16 All descent control device attachment components (aero-braking heat shield and parachute) shall survive 30 Gs of shock. Comply 118

17 All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock. Comply 118

18 All electronic components shall be enclosed and shielded from the environment with the exception of sensors. Comply 22 each part is fully enclosed

in its holder

19 All structures shall be built to survive 15 Gs of launch acceleration. Comply 118




RqmtNum Requirement Comply / No

Comply / Partial


Compliance


20 All structures shall be built to survive 30 Gs of shock. Comply 118

21 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives. Comply 24

All parts have their own holders

22 All mechanisms shall be capable of maintaining their configuration or states under all forces. Comply 75

23 Mechanisms shall not use pyrotechnics or chemicals. Comply 124

24Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to the outside environment to reduce potential risk of setting vegetation on fire.

Comply 22Nichrome wire is totally enclosed inside.

25During descent, the probe shall collect air pressure, outside air temperature, GPS position and battery voltage once per second and time tag the data with mission time.

Comply 88

26 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts. Comply 88

27Telemetry shall include mission time with one second or better resolution. Mission time shall be maintained in the event of a processor reset during the launch and mission.

Comply 88

28 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. Comply 87

29 XBEE radios shall have their NETID/PANID set to their team number. Comply 87




RqmtNum Requirement


Partial


Compliance


30 XBEE radios shall not use broadcast mode. Comply 87

31 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost. Comply 141 Hardware under $1000

32 Each team shall develop their own ground station. Comply 114GS collects data during

the mission

33 All telemetry shall be displayed in real time during descent. Comply 114

34 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.) Comply 114

35 Teams shall plot each telemetry data field in real time during flight. Comply 114

36The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a handheld antenna.

Comply 107

37The ground station must 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 107

38 Both the heat shield and probe shall be labeled with team contact information including email address. Comply 126

39The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.

Comply 114




RqmtNum Requirement


Partial


Compliance


40 No lasers allowed. Comply 22 Lasers aren’t used

41 The probe must include an easily accessible power switch. Comply 22 RBF pins are used

42 The probe must include a power indicator such as an LED or sound generating device. Comply 84

While powered, the Teensy has a LED that flashes

43 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second. Comply 52

44 The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second. Comply 51

45 An audio beacon is required for the probe. It may be powered after landing or operate continuously. Comply 93

46Battery source may be alkaline, Ni-Cad, Ni-MH or Lithium. Lithium polymer batteries are not allowed. Lithium cells must be manufactured with a metal package similar to 18650 cells.

Comply 94

47An easily accessible battery compartment must be included allowing batteries to be installed or removed in less than a minute and not require a total disassembly of the CanSat.

Comply 55,62

48Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects.

Comply 62

49A tilt sensor shall be used to verify the stability of the probe during descent with the heat shield deployed and be part of the telemetry.

Comply 35


Management

David Madden


CanSat Budget – Hardware

Presenter: David Madden

Component Status Quantity Individual Cost Type

Teensy 3.2 New 1 $17.00 Exact

XBEE Pro 900 New 1 $39.00 Exact

MicroSD Breakout New 1 $4.95 Exact

Pull-pin Alarm New 1 $7.99 Exact

GPS New 1 $39.95 Exact

Altimeter New 1 $29.99 Exact





Camera Reused 1 $35.95 Exact

3.3V Regulator New 1 $0.86 Exact

Parachute Swivel New 1 $7.35 Exact

Parachute New 1 $28.00 Exact

900MHz Antenna New 1 $7.40 Exact

TIP120 3 pack New 1 $2.50 Exact

Accelerometer New 1 $10.95 Exact





120 Springs, 9271K704 (Pack of 6)

New 1 $6.47 Exact

180 Springs: 9271K674 (Pack of 6)

New 1 $6.47 Exact

262-F 4-oz/yd^2 Fiber Glass Fabric 5

YardPackage

New 1 $38.45 Exact

WEST-105A (Quart) New 1 $32.40 Exact





WEST-206A (1/2 pints) New 1 $15.95 Exact

Gyroscope New 1 $14.95 Exact

Application New 1 $100 Exact

Mini Camera New 1 $12.50 Exact

TMP36 New 1 $1.35 Exact


CanSat Budget – Ground Control



Mac Laptop Reused 1 $1000 Estimate

XBEE Pro 900 New 1 $39.00 Exact

Yagi Antenna Reused 1 $15.25 Exact


CanSat Budget – Other Expenses



Prototyping and Testing N/A 1 $100.00 Estimate

Hotel Expenses N/A 8 $100.00 Estimate

Car Rental N/A 1 $400.00 Estimate

Airfare N/A 8 $250.00 Estimate

Gasoline N/A 1 $200.00 Estimate

Team Shirts N/A 10 $20 Estimate


Final Budget

141

Expenses

Expenses of the

CanSat Itself

$315.68

Ground Support

Expenses$1054.25

Other Expenses $3700.00

Total Expenses $5069.93

Income

University Funding $1000.00

Reused Part Savings $1051.20

Other Sources Such as

Reimbursement of Travel

$3018.73

Total Income $5069.93

Final Budget

Income $5069.93

Expenses $5069.93

Net Total $0.00



Program Schedule



Preliminary Design Stage



Critical Design Stage



Final Stage



Conclusion


● Accomplishments- All subsystems have detailed designs- All requirements are met

● Unfinished work- More prototyping of probe design needs to be

completed before full integration of CanSat- Physical testing of assembled CanSat to be done- Test cutting mechanism at heights higher than 100m- PCB fabrication

● Ready for next stage of development- Fully detailed designs- Requirements met- Ready for production of payload

Documents

Preliminary Design Review (PDR) Version 1.2 …cansatcompetition.com › docs › teams › Cansat2018_5278_PDR.pdfengineering units (meters, meters/sec, Celsius, etc.) Competition