Critical Design Review (CDR) CanSat 2018cansatcompetition.com/docs/teams/Cansat2018_5278_CDR_v01.pdfCritical Design Review (CDR) Version 1.0 Team 5278 B.U.T.T.E.R 1 CanSat 2018 CDR:

CanSat 2018 CDR: Team 5278 BUTTER

CanSat 2018 Critical Design Review (CDR)

Version 1.0

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

1


Presentation Outline

2Presenter: Anthony McCourt

• Introduction: Anthony McCourt.………....…….…………………………………..………..…..1

• Systems Overview: Anthony McCourt.…………………………...……………..………...…...5

• Sensor Subsystem Design: Michael Campbell ...………………….………………….....…23

• Descent Control Design: Frankie Pinon………………....……..……….……...………...….33

• Mechanical Subsystem Design: Lyle Hailey...………….……………………....………...…49

• Communication and Data Handling Subsystem Design: Sina Malek…….……....….…65

• Electrical Power Subsystem Design: Mecah Levy…….....………………………...……...74

• Flight Software Design: Vijay Ramakrishna…………………..…………...………...…..…..83

• Ground Control System Design: Vijay Ramakrishna………………………..….………….94

• CanSat Integration and Test: David Madden…....………………………………………….105

• Mission Operations and Analysis: Mecah Levy….....……………...……….…...………..116

• Requirements Compliance: David Madden………………..….…….…...………...………123

• Management: David Madden…...……………………………………...…………...………...130

• Conclusion: David Madden…...………………………………………..……………………..147


Team Organization

3


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


System Overview

Anthony McCourt

5


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



Summary of Changes Since PDR

• The capsule closure was changed from plastic press tabs to nutplates to attach the capsule pieces.

• Outer diameter was decreased by .5mm for clearance in rocket.

• Thickness was increased on lower section of probe to lower center of gravity.



System Requirement Summary

8

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.




9

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.




10

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.




11

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.




12

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.




13

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.)




14

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.




15

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.




16

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.



System Concept of Operations

17

Altitude [m]

0

300

600

1

2 3

4

5

1. Pre-flight preparations and Launch2. CanSat deployment3. Heatshield deployment and descent4. Parachute deployment and heat shield separation5. Landing and recovery



1. Pre-flight Preparationsa. Final CanSat overview and assemblyb. Flight Readiness Reviewc. Power on CanSatd. Commence ground station-CanSat

communicatione. Integrate CanSat into payload bay of

rocket2. Launch3. Descent Operationsa. Container separation from rocket via

ejection chargeb. Deployment of aerobraking shield

seconds after rocket separationc. Descent at 10-30 m/s to an altitude of

300 md. CanSat utilizes on-board power to

measure required quantities

18

e. CanSat transmits data to ground station

f. Deployment of parachute at 300 m and separation of aerobraking shield

g. Descent at 5 m/s while video taken4. Recoverya. CanSat lands and sounds beaconb. CanSat is localized and recovered5. Data Reductiona. Flight data is saved to onboard SD

card as well as on ground stationb. Flight data is presented to judges in

Post Flight Review



19

Team Roles and Responsibilities

Role Members Responsibilities

Mission Control Officer(MC)

Anthony McCourt● Assists team with launch preparation and oversees the entirety of the mission ● Determines flight readiness● Signals initial launch

Ground Station Crew(GS)

Mecah Levy ● Performs final tests on ground station software, communication with CanSat, and accuracy of data

● oversees transmission during descent ● responsible for sending transmission signal in the case of deployment failure● Responsible for maintenance of antenna used for transmission● Perform data reduction and organize data into charts and graphs for analysis

Michael Campbell

Vijay Ramakrishna

CanSat Crew(PO)

Lyle Hailey ● Perform final assessments of the CanSat to ensure launch readiness (Skirt deployment, Heat shield separation, and structure security)

● Incorporates and secures the egg into the container prior to launch and secures heat shield and skirt with nylon fishing line

● Integrates CanSat into rocket

David Madden

Matthew Meiers

Recovery Crew(R)

Frankie Pinon ● Assist Payload organization team with payload preparation activities ● Locate and recover the CanSat after landing including the main probe, along

with the heat shield● Assess the CanSat for any damage to devices● Open the CanSat to check for any damage to the egg

David Madden

Sina Malek


Payload 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

CAMERAPCB

BATTCOMP

EGGCOMP



- 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

- Heat Shield/Aero-Brake Assembly fully enclose probe pre-deployment




• Deployed Configuration- Heat Shield/Aero-Brake

assembly expands to 260 mm after deployment to maintain desired velocity.



Sensor Subsystem Design

Michael Campbell

23


Sensor Subsystem Overview

24Presenter: 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


Sensor Changes Since PDR

• There have been no changes since PDR



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 Summary


MS5607 Dimensions 2.16cm x 2.08cm

Mass .9g

Power Usage 3.3V1.74mA5.74mW

Accuracy ±0.02m±1℃

Interface Serial (I2C)

Temperature Calibration

Yes

- Provides altitude- Provides backup temperature readings


Probe Air Temperature Sensor Summary


- Outputs power proportional to temperature

- Temperature = Vout / .01 = ℃

Dimensions 2mm x2mm

Mass 0.20g

Power Usage 3.3V50μA165μW

Accuracy ±1°C

Interface Analog

TMP36


GPS Sensor Summary


- Provides Latitude and Longitude- Provides backup altitude readings

Dimensions 18mm x29.5mm x2mm

Mass 6g

Power Usage 3.3V20mA66mW

Accuracy ±3m±0.1m/s

Interface Tx/Rx Lines

MTK 3339


Probe Voltage Sensor Summary


-

-Resistors are 10k Ohm and 22k Ohm-Vin is 3.3V and 6V

Dimensions 6.3mm x2.2mm x4 units

Mass 1g

Power Usage 3.3V.33mA,.15mA6V.6mA,.27mA

Accuracy ±.1V

Interface Analog

Voltage Divider


Tilt Sensor Summary


-Provides current X, Y, and Z angle-Provides X, Y, and Z rotation speed

Dimensions 10.92mm x17.78mm

Mass 1.5g

Power Usage 3.3V3.2mA10.6mW

Accuracy ±5°/sec

Interface Serial (I2C)

MPU-9250


Bonus Objective Camera Summary


-Records 640x480 30fps video-Stores video on a built-in microSD card-Activated by a 3.3V trigger signal

Dimensions 28.5mm x17mm x4.2mm

Mass 2.8g

Power Usage 5V80mA(STBY).4W110mA(RCD).55W

Interface Analog

Adafruit camera #3202


Descent Control Design

Frankie Pinon

33


Descent Control Overview

Probe Descent ControlComponents: Tail, Parachute, Carbon fiber rods, 180° torsion springsDescription: After the probe is ejected from the rocket, springs attached to theback of the probe unwind such that the ripstop nylon-covered tail extend outward. The tail is used to push the aerodynamic center towards the tailas well as inducing more drag on the prode. This extra drag slows the probewithin the designated descent rate. Once the heat shield deploys, the tailwill too which will cause the parachute to deploy. The parachute used was chosen such that it descends at the necessary 5 m/s.

Heat Shield OverviewComponents: 3D ABS printed plasticDescription: The width of the heat shield and the surface roughness of the plastic further slow down the probe such that its descent speed is within thedesignated rate.

34


Descent Control Overview

35

Altitude [m]

0

300

6001 2

3

1. Post-Ejection Configuration - This is the few seconds that the CanSat is in its stored configuration before the skirt is opened

2. Primary Descent Configuration - This is with the skirt fully opened and descending from 10-30 m/s3. Post-Separation Configuration - This is when the parachute is deployed and the aero-braking shield is

released. CanSat will descend at a rate of 5 m/s


Descent Control Changes Since PDR

36

Changes Rationale Benefit

Tail Deployment: using torsional springs attached to the inside of the fiberglass sleeve.

PDR design did not provide a concrete method of deployment of aero-brake.

The tail can be contracted to fit inside of the rocket and automatically deploy once the probe exits the rocket.


Descent Control Requirements

37

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


DC-03The 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-04The probe shall deploy a parachute at 300 meters. Competition

Requirement

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


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



Payload Descent Control Hardware Summary

Payload Descent Control HardwareTorsion Springs with Carbon Fiber Rods: When placed in a closed space orheld together, the aero-brake can be retracted to fit small spaces. This wasnecessary so the probe could fit inside of the rocket. However, once free of the rocket, the retaining nylon cord will release, the springs would contract, and the nylon skirt expands as shown below.

38


Payload Descent Control Hardware Summary

Passive ComponentsHeat shield: Heat shield induces necessary drag, but sizing was constrained by the capsule size.Skirt: An expandable skirt was used to help increase drag during descent.CFD was used to help predict correct sizing of skirt. Parachute: Slows down the probe to fit descent rate constraint; spill hole on the top maintain stability for the probe.

Active ComponentsNichrome Wire Circuit: Release the heat shield and parachute. Circuit was tested to find the time it takes to cut and release the line to deploy chute so correct deployment time can be achieved; delay time was estimated to be about 4 seconds, which will have to be considered in flight.

39


Descent Stability Control Design

Mitigating Tumbling• For the sake of simplicity, the probe’s aerodynamic shape is used to create

stability.• Simulation using Matlab shows that while the probe is within 10°, a moment will

try to push the probe nose-up; however, when the probe rotates to 10°, a moment will push the probe nose-down again. The moments that push nose-down are significantly larger than that of the nose-up moments, thereby resisting tumbling

• Simulation was run using:– Center of gravity located 100 mm from the tip of the heat shield– Lift generated by slender body and cross-flow drag per CanSat geometry– Moment about the center of gravity

• This suggests that regardless of probe speed, the aerodynamic center will be:– forward the center of gravity while the probe is within 10°– aft the center of gravity when the probe is at or passed 10°

• The plot shows that the aerodynamic properties of the probe will correct itself during descent to prevent tumbling.

40


Descent Stability Control Design

The figure below shows that the aerodynamic forces acting on the probe will keep it from tilting more than 10° with respect to a vertical axis normal to the ground.

41


Descent Rate Estimates

Assumptions: ● Conditions are steady (no sudden gusts of wind)● probe will exit rocket between -30° and 30° with respect to the ground ● CanSat is symmetrical about center axis of rotation● Drag coefficient is 1 about a cylinder for given Reynold’s number ranges

Calculations: ● Lift from Slender-body theory:

● Alpha - Angle of attack● q_x - dynamic pressure in the x-direction● Delta S - Change in cross-sectional area

● Lift from cross-flow drag:

● Cd - Drag coefficient of shape● q_y - dynamic pressure in the y-direction● r - radius of CanSat● Delta x - length of section of CanSat being analyzed

42

Descent Rate Estimate of CanSat Pre-Deployment



43

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



Assumptions: ● Conditions are steady (no sudden gusts of wind)● probe will exit rocket between -30° and 30° with respect to the ground ● CanSat is symmetrical about center axis of rotation● Drag coefficient is 1 about a cylinder for given Reynold’s number ranges

Calculations: ● Lift from Slender-body theory:

● Alpha - Angle of attack● q_x - dynamic pressure in the x-direction● Delta S - Change in cross-sectional area

● Lift from cross-flow drag:

● Cd - Drag coefficient of shape● q_y - dynamic pressure in the y-direction● r - radius of CanSat● Delta x - length of section of CanSat being analyzed

44

Descent Rate Estimate of CanSat “Primary Descent”



45

Descent Rate Estimate of CanSat “Primary Descent”

• 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.



Assumptions: ● Conditions are steady (no sudden gusts of wind)● Parachute will fully-deploy● Complete separation of aero-braking system

Calculations: ● Taken from manufacturer “FruityChutes” calculator, shown on next slide

46

Descent Rate Estimate of CanSat Post-Separation



47

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



48

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-Ejection 32.5+ m/s

Primary Descent 10-30 m/s

Post-Separation 5.04 m/s


Mechanical Subsystem Design

Lyle Hailey

49


Mechanical Subsystem Overview

• Capsule– The capsule containing the egg and electronics will be

made of ABS plastic and two parts (upper and lower). Lower will contain electronics, upper will contain a container for the egg and chute deployment.

• Heat-Shield– Heat shield will be made of ABS plastic, and attached

using fishing line, and tabs.• Sleeve

– The outer sleeve will be made of fiberglass with rip-stop nylon fabric skirt connected by torsion springs.

• Electronics– PCB will be mounted using M3 screws and jam nuts

mounted in base of lower capsule.

50


Mechanical Subsystem Changes Since PDR

• Changes since PDR– No major changes to the design since PDR– Slight increase of tolerances between anular interfaces

of upper and lower capsule design.– Slight increase in thickness of bottom plate to lower CG,

and improve impact loading stresses.

51

CanSat 2018 PDR: Team 5278 BUTTER 52

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

Presenter: Lyle Hailey



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




Payload Mechanical Layout of Components

57Presenter: Lyle Hailey


Payload Mechanical Layout of Components

● Structural material selection● The capsule and heat shield were 3D printed using ABS

because of it was readily available, financially possible, light weight, and could fulfil the missions requirements.

● The sleeve was chosen to be made of fiberglass because of availability of fiberglass from last year’s competition and its weight saving attributes.

● Chute and skirt were chosen to be made of rip-stop nylon fabric for its strength and light weight.



Egg Protection Mechanical Layout of Components

● Material selection(s)● The material used for the egg protections structure is

simply a 3D printed area within the upper capsule, and memory foam to lower the impulse of the egg during landing.


TWIST LOCK LID

FOAM LINED CONTAINER

118mm

80mm


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

FISHING LINENICHROME WIRE


Probe Parachute Release Mechanism

• The parachute is attached to the probe with I bolts attached to the aft section

• The parachute bundle will by stowed under the Aero-Brake assembly

• Deployment of the parachute will be triggered by the release of the Aero-Brake, which will expand the parachute as it slides off of the probe body.

61

RELEASE STRING


Structure Survivability

• As applicable for the Payload, discuss:– Electronic component mounting methods– Electronic component enclosures– Acceleration and shock force requirements and testing– Securing electrical connections (glue, tape, etc.)

• Consider required judge verification during pre-flight check in– Descent control attachments

62Presenter: Name goes here


Structure Survivability

• As applicable for the Payload, discuss:– Electronic components will be mounted using four M3 screws

located at the corners of the PCB. These screws will thread into pressure fit jam nuts pressure fit into cylinders at the bottom of the lower capsule.

– Electronic component enclosures– For acceleration testing FEA was used to determine the

viability of the structure, and a physical centrifugal test was done to verify the design.

– Shock loading was solely physically tested by drop testing.– Securing electrical connections (glue, tape, etc.)

• Consider required judge verification during pre-flight check in

– Descent control attachments63Presenter: Lyle Hailey


Mass Budget

ComponentEstimated

Weight (grams)

Source of Estimate/

Uncertainty

Structural Elements 110±10 From CAD

Estimates

Egg 61±7From

Competition Guidelines

Parachute 60±2 From Data Sheets

Electronic Components 112±3 From Data

Sheets

Probe Final Weight 343±22

ComponentEstimated

Weight (grams)

Source of Estimate/

Uncertainty

Probe Weight 343±22 From Table

to Left

Heat Shield 95±14 From CAD Estimates

Margin

WorstCase: 26

BestCase: 98

Remaining Mass Budget.

Cases determined

from uncertainties

CanSat Final

Weight500

Including Margin into Calculation



Communication and Data Handling (CDH) Subsystem Design

Sina Malek

65


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

66Presenter: Sina Malek


CDH Changes Since PDR

• There were no changes since PDR

67Presenter: Sina Malek


CDH Requirements

68

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

Presenter: Sina Malek


Probe Processor & Memory Trade & Selection

69

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

70

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 Selection

71

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

72

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

73

• 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 Design

Mecah Levy

74


EPS Overview

75Presenter: 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

76

RBF Switch

3.3V Regulator

Nichrome Cutting Circuit

Sensors

Microcontroller4x

AAAAPack A

Micro-USB Power

4x AAAAPack B

RBF Switch

5V Regulator Camera

Presenter: Mecah Levy


EPS Changes Since PDR

• Since PDR there have been no changes to EPS



EPS Requirements

78

ID Requirements Rationale Compliance

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

79

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 Source

80

Model Capacity Nominal Voltage Mass Dimensions

Energizer E96 AAAA Alkaline

Battery550 mAh 1.5V 6.5g 40.7mm x 8mm

- 4x Energizer AAAA - Small Profile - High capacity- Past success



Probe Power Budget

81

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 3.3 0.99 Data sheet

Audio Beacon Piezo Buzzer 12% 0.035 3.3 0.1155 Data sheet

Total A 0.657963 2.1712779Power 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 18.4Presenter: Mecah Levy


Probe Power Budget

82

Battery Pack A Power Available: 3300 mWh

Sensor Power Consumption: 1478.2203 mWh

Battery A Power Margin: 56%

Battery Pack B Power Available: 3300 mWh

Sensor Power Consumption: 293.7633 mWh

Battery B Power Margin: 91%



Flight Software (FSW) Design

Vijay Ramakrishna

83

CanSat 2018 CDR: Team 5278 BUTTER 84Presenter: Name goes here 84

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 Changes Since PDR

• Major Design Modifications:– One additional state added to states list, representing

deployment of the parachute and the release of the heat shield, to more precisely model the sequence of events during flight• This was originally (implicitly) represented as an event in the

transition between the ascending and descending states.• Minor Design Modifications:

– More specificity added to subsystem design plans- Every subsystem should be able to handle its own dependencies (acquisition and processing)

85

CanSat 2018 CDR: Team 5278 BUTTER 86Presenter: Name goes here 86

FSW Requirements


ID Requirement Rationale

FSW-01 (MISSION-14) 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 (MISSION-05) 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 (MISSION-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

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

CanSat 2018 CDR: Team 5278 BUTTER 8787

FSW Requirements



FSW-04 (MISSION-26) 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 (MISSION-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

Data collected by the probe must be accurate.

FSW-06 (MISSION-33) All telemetry shall be displayed in real-time during the descent

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


FSW Requirements



MISSION

FSW-08 (MISSION-39)

FSW-09 (MISSION-40)


FSW Requirements



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

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.


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>


Probe CanSat FSW State Diagram

91Presenter: Name goes here

Recovery- Non-volatile EEPROM

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

Power- Power management is

handled via Arduino 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– Modify subsystem software so as to individually handle dependencies and

data extraction for each subsystem• Progress Since PDR

– reworked parser scheme for GPS packets (custom)– new gyroscope class– various updates to software subsystems (core, log, communications,

nichrome, altimeter, buzzer, temperature, voltage)



Software Development Plan

• Timeline:– April: Finish all Subsystems + Test Individually– May: Integrate Subsystems into FSW for the Can Sat +

Test

93


Ground Control System (GCS) Design

Vijay Ramakrishna

94


GCS Overview

9595

GCS Overview



GCS Changes Since PDR

• Determined and added antenna mounting design and description of antenna usage

96


GCS Requirements

97Presenter: Name goes here 97

GCS Requirements



GCS-01 (MISSION-28) XBEE shall be used to communicate with the probe

GCS-02 (MISSION-29)

GCS-03 (MISSION-30)


GCS Requirements



GCS-04 (MISSION-32)

GCS-05 (MISSION-35)

GCS-06 (MISSION-36)


GCS Requirements



GCS-07 (MISSION-37)


GCS Design

Laptop (>=two hour battery life)

XBee Pro S3B

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



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


Mounting and usage: Data interface:

- the True Gain shall interface with the XBee module

Physical interface:- the True Gain shall be

handheld by the GS operator


GCS Software

103Presenter: Vijay Ramakrishna


GCS Bonus Wind Sensor

• We are not pursuing the bonus objective

104


CanSat Integration and Test

David Madden

105

CanSat 2018 PDR: Team 5278 BUTTER

Subsystem Level Testing Plan

• Aeronautics Subsystem– 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

106Presenter: David Madden



• Mechanical Subsystem– 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




• Electrical Subsystem– Nichrome Wire cutting circuit

testing from ground level, cutting a taunt fishing line.

– GPS testing individually 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



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 the egg

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

• Test of Communications such as the ground station subsection along with telemetry by placing objects a long range but not in flight



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 during transport.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.Dimensions Verification• Check of dimensions utilising different sources such as multiple scales to confirm CanSat meets requirements.



Test Procedures Descriptions

111

Test ID Test Description Requirements Pass Fail Criteria

1 Test of Heat Shield deployment at ground level to confirm functionality 2

To Pass the Heat Shield must fully deploy and seperate from the probe.

2 Test of Heat Shield while in free fall to confirm that CanSat will function under specified environment 2,4

To Pass the Heat Shield must fully deploy and seperate from the probe.

3 Test of Parachute from a height of 10m to confirm functionality 15

To Pass the Parachute must fully deploy from a stowed configuration.

4 Test of Parachute from a height of 10m with egg inside casing attached to confirm egg survivability 7,8

To Pass the Parachute must fully deploy from a stowed configuration and the egg must survive impact

5 Drop Test of payload due to string impulse force above 30g’s to insure egg survivability inside casing. 7,8,16,17

To pass the egg must survive over the duration of the test



112


6 Drop test of final design without egg needed to ensure functionality of design 2,4,5

To Pass the Heat Shield must fully deploy and seperate from the probe. Also the Parachute must deploy successfully

7 Drop test of final design with egg needed to confirm egg survivability 2,4,5,7,8

To Pass the Heat Shield must fully deploy and seperate from the probe. Also the Parachute must deploy successfully and the egg must survive the duration of the test

8 Nichrome Wire cutting circuit tested at ground level to test functionality 24,25,26

To Pass the Nichrome Wire circuit must cut a taunt fishing line given the computer command



113


9 Test of GPS via physical displacement 25,26

To Pass the GPS must successfully connect to the computer and give accurate data

10 Test of XBees by configuration with other proven electronics 25,26,28,29,30,36

To Pass the XBee must give accurate data from the proven hardware to the computer

11 Range test of radio communications at a distance of 500 meters 25,26,33,34,35

To Pass the Radio must successfully transmit data

12 Sensor data test by giving the sensors a known value and ensuring the data is passed to the computer 25,26,34,35

To Pass the data transmitted to the computer must match the known value.



114


13 The gyroscope will undergo random motion test to ensure functionality 25,26,49

To Pass the Gyroscope must give accurate data to the computer

14 Test of full CanSat Integration by dropping the CanSat from a quadcopter at or above 300m 2,4,5,7,8,33,43,44

To Pass the all subsystems must successfully deploy and the egg must survive for the duration of the test

15 Full test of CanSat by launching the CanSat in a rocket up to 670m-725m for a full test of every subsystem

2,4,5,7,8,9,12,13,14,19,20,33,43,44

To Pass the all subsystems must successfully deploy and the egg must survive for the duration of the test



115


16 Test of full communications, ground system, and sensors via displacement of 500m

26,27,33,34,3539

To Pass all subsystems must transmit accurate data between them.

17Termal Test by insulating the CanSat from the outside environment and then using a heat gun to maintain a high temperature for an hour.

To Pass the CanSat and its subsystems must function properly after being removed from thermal isolation

18 Shake-table test to ensure structure survivability on launch and landing

To Pass all subsystems must be functional after the sake table trial has stopped. The egg must survive for the duration of test

19The CanSat will be inspected with different tools to ensure dimension requirement compliance. This includes testing it on various scales and measuring size dimensions multiple times.

2,6,9,18

To Pass all CanSat dimensions must meet the requirements specified in the mission guidelines.


Mission Operations & Analysis

Mecah Levy

116


Overview of Mission Sequence of Events


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

– Anthony McCourt• Ground Station crew (G)

– Mecah Levy– Michael Campbell– Vijay Ramakrishna

• Recovery crew (R)– Frankie Pinon– David Madden– Sina Malek

• Cansat Crew (C)– Lyle Hailey– David Madden– Matthew Meiers


Overview of Mission Sequence of Events


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


Field Safety Rules Compliance


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


Mission Rehearsal Activities

● Up to this point we have rehearsed the following launch activities:○ Integration of the egg into the probe○ Mounting of the aero-breaking shield to probe○ Mounting of sleeve with skirt○ Wrapping of parachute for deployment○ Loading of CanSat into payload bay of rocket○ Powering of sensors and data processing○ On-board camera imaging and transmission○ Cutting of nylon fishing line with nichrome cutting circuit○ Ground station radio link with CanSat

121


Mission Rehearsal Activities

● Mission Flight Procedure Manual○ The flight procedure manual contains all of the flight-day

pre-flight, launch, and post-flight procedures○ These procedures have been outlined in the “System

Overview” and current section○ Manual will be printed and contained in a 1” portfolio

and brought to Texas■ Mission Control Officer will oversee procedures during the

competition and verify that all steps of the Manual are completed on time

122


Requirements Compliance

David Madden

123


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: David Madden




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. Comply 117

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

130


Status of Procurements


Component Status Quantity Date Arrived

Teensy 3.2 Procured 1 2/16/18

XBEE Pro 900 Procured 1 2/16/18

MicroSD Breakout Procured 1 2/16/18

Pull-pin Alarm Procured 1 3/1/18

GPS Procured 1 3/1/18

Altimeter Procured 1 3/1/18





Camera Procured 1 11/5/17

3.3V Regulator Procured 1 2/1/18

Parachute Swivel Procured 1 3/7/18

Parachute Procured 1 3/7/18

900MHz Antenna Procured 1 2/1/18

TIP120 3 pack Procured 1 1/17/18

Accelerometer Procured 1 11/9/17





120 Springs, 9271K704 (Pack of 6) Procured 1 10/30/17

180 Springs: 9271K674 (Pack of 6) Procured 1 10/30/17

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

Package Procured 1 2/1/18

WEST-105A (Quart) Procured 1 1/7/18





WEST-206A (1/2 pints) Procured 1 1/7/18

Gyroscope Procured 1 11/25/17

Mini Camera Procured 1 10/30/17

TMP36 Procured 1 2/15/18

Mac Laptop Procured 1 Previously Owned

XBEE Pro 900 Procured 1 3/7/18

Yagi Antenna Procured 1 3/7/18


CanSat Budget – Hardware

135

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



136


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



137


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



138


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

139


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

140


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



Shipping and Transportation

• The CanSat itself will be transported to the launch site via a Pelican Case. It will be brought onboard the plane with the team so that the CanSat will not be lost.

• Tools and other required materials not allowed as Carry-ons will be checked. If any materials are lost, replacements will be bought in Texas as soon as possible



Conclusions

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

● Unfinished work- Further testing of CanSat prototype components- Final testing of CanSat prototype fully integrated- Flight Software needs to be debugged- Analysis of prototype testing- Construction of Final CanSat

● Ready for next stage of development- Finalize designs after further testing analysis- Start manufacturing process of final components


Documents

Critical Design Review (CDR) CanSat 2018cansatcompetition.com/docs/teams/Cansat2018_5278_CDR_v01.pdfCritical Design Review (CDR) Version 1.0 Team 5278 B.U.T.T.E.R 1 CanSat 2018 CDR: