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CanSat 2018 CDR: Team 5278 BUTTER
CanSat 2018 Critical Design Review (CDR)
Version 1.0
Team 5278B.U.T.T.E.R
1
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
Team Organization
3
CanSat 2018 CDR: Team 5278 BUTTER
Acronyms
4Presenter: Anthony McCourt
• 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
CanSat 2018 CDR: Team 5278 BUTTER
System Overview
Anthony McCourt
5
CanSat 2018 CDR: Team 5278 BUTTER
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
6Presenter: Anthony McCourt
CanSat 2018 CDR: Team 5278 BUTTER
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.
7Presenter: Anthony McCourt
CanSat 2018 CDR: Team 5278 BUTTER
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.
Competition Requirement High
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.
Competition Requirement High
SR-05 The probe shall not tumble during any portion of descent. Tumbling is rotating end-over-end.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
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.
Competition Requirement High
SR-07 The probe shall hold a large hen's egg and protect it from damage from launch until landing.
Competition Requirement High
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.
Competition Requirement High
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.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
10
SR-10 The aero-braking heat shield shall be a fluorescent color; pink or orange.
Competition Requirement High
SR-11 The rocket airframe shall not be used to restrain any deployable parts of the CanSat.
Competition Requirement High
SR-12 The rocket airframe shall not be used as part of the CanSat operations.
Competition Requirement High
SR-13 The CanSat, probe with heat shield attached shall deploy from the rocket payload section.
Competition Requirement High
SR-14 The aero-braking heat shield shall be released from the probe at 300 meters.
Competition Requirement High
SR-15 The probe shall deploy a parachute at 300 meters.
Competition Requirement High
SR-16 All descent control device attachment components (aero-braking heat shield and parachute) shall survive 30 Gs of shock.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
11
SR-17 All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock.
Competition Requirement High
SR-18 All electronic components shall be enclosed and shielded from the environment with the exception of sensors.
Competition Requirement High
SR-19 All structures shall be built to survive 15 Gs of launch acceleration.
Competition Requirement High
SR-20 All structures shall be built to survive 30 Gs of shock.
Competition Requirement High
SR-21 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.
Competition Requirement High
SR-22 All mechanisms shall be capable of maintaining their configuration or states under all forces.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
12
SR-23 Mechanisms shall not use pyrotechnics or chemicals.
Competition Requirement High
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.
Competition Requirement High
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.
Competition Requirement High
SR-26 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts.
Competition Requirement High
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.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
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.
Competition Requirement High
SR-29 XBEE radios shall have their NETID/PANID set to their team number.
Competition Requirement High
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.
Competition Requirement High
SR-32 Each team shall develop their own ground station.
Competition Requirement High
SR-33 All telemetry shall be displayed in real time during descent.
Competition Requirement High
SR-34 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.)
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
14
SR-35 Teams shall plot each telemetry data field in real time during flight.
Competition Requirement High
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.
Competition Requirement High
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.
Competition Requirement High
SR-38 Both the heat shield and probe shall be labeled with team contact information including email address.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
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.
Competition Requirement High
SR-40 No lasers allowed. Competition Requirement High
SR-41 The probe must include an easily accessible power switch.
Competition Requirement High
SR-42 The probe must include a power indicator such as an LED or sound generating device.
Competition Requirement High
SR-43 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second.
Competition Requirement High
SR-44 The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
System Requirement Summary
16
SR-45 An audio beacon is required for the probe. It may be powered after landing or operate continuously.
Competition Requirement High
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.
Competition Requirement High
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.
Competition Requirement High
SR-48 Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects.
Competition Requirement High
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
System Concept of Operations
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
CanSat 2018 CDR: Team 5278 BUTTER
System Concept of Operations
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
CanSat 2018 CDR: Team 5278 BUTTER
Payload Physical Layout
20Presenter: Anthony McCourt
• 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
CanSat 2018 CDR: Team 5278 BUTTER
Payload Physical Layout
- 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
21Presenter: Anthony McCourt
CanSat 2018 CDR: Team 5278 BUTTER
Payload Physical Layout
• Deployed Configuration- Heat Shield/Aero-Brake
assembly expands to 260 mm after deployment to maintain desired velocity.
22Presenter: Anthony McCourt
CanSat 2018 CDR: Team 5278 BUTTER
Sensor Subsystem Design
Michael Campbell
23
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
Sensor Changes Since PDR
• There have been no changes since PDR
25Presenter: Michael Campbell
CanSat 2018 CDR: Team 5278 BUTTER
Sensor Subsystem Requirements
26Presenter: Michael Campbell
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
CanSat 2018 CDR: Team 5278 BUTTER
Probe Air Pressure Sensor Summary
27Presenter: Michael Campbell
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
CanSat 2018 CDR: Team 5278 BUTTER
Probe Air Temperature Sensor Summary
28Presenter: Michael Campbell
- Outputs power proportional to temperature
- Temperature = Vout / .01 = ℃
Dimensions 2mm x2mm
Mass 0.20g
Power Usage 3.3V50μA165μW
Accuracy ±1°C
Interface Analog
TMP36
CanSat 2018 CDR: Team 5278 BUTTER
GPS Sensor Summary
29Presenter: Michael Campbell
- 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
CanSat 2018 CDR: Team 5278 BUTTER
Probe Voltage Sensor Summary
30Presenter: Michael Campbell
-
-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
CanSat 2018 CDR: Team 5278 BUTTER
Tilt Sensor Summary
31Presenter: Michael Campbell
-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
CanSat 2018 CDR: Team 5278 BUTTER
Bonus Objective Camera Summary
32Presenter: Michael Campbell
-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
CanSat 2018 CDR: Team 5278 BUTTER
Descent Control Design
Frankie Pinon
33
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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.
CanSat 2018 CDR: Team 5278 BUTTER
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.
Competition Requirement
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.
Competition Requirement
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.
Competition Requirement
DC-06The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second.
Competition Requirement
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
Descent Rate Estimates
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
CanSat 2018 CDR: Team 5278 BUTTER
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
44
Descent Rate Estimate of CanSat “Primary Descent”
CanSat 2018 CDR: Team 5278 BUTTER
Descent Rate Estimates
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.
CanSat 2018 CDR: Team 5278 BUTTER
Descent Rate Estimates
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
CanSat 2018 CDR: Team 5278 BUTTER
Descent Rate Estimates
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
CanSat 2018 CDR: Team 5278 BUTTER
Descent Rate Estimates
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
CanSat 2018 CDR: Team 5278 BUTTER
Mechanical Subsystem Design
Lyle Hailey
49
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
Requirement Number Requirement Rationale Priority
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.
Competition Requirement High
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.
Competition Requirement High
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
CanSat 2018 PDR: Team 5278 BUTTER 53
Mechanical Sub-System Requirements
Direct Requirements
Requirement Number Requirement Rationale Priority
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.
Competition Requirement High
M-10All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock.
Competition Requirement. High
Presenter: Lyle Hailey
CanSat 2018 PDR: Team 5278 BUTTER 54
Mechanical Sub-System Requirements
Direct Requirements
Requirement Number Requirement Rationale Priority
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
Competition Requirement. High
Presenter: Lyle Hailey
CanSat 2018 PDR: Team 5278 BUTTER 55
Mechanical Sub-System Requirements
Direct Requirements
Requirement Number Requirement Rationale Priority
M-16Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.
Competition Requirement High
M-17Both the heat shield and probe shall be labeled with team contact information including email address.
Competition Requirement. High
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.
Competition Requirement. High
Presenter: Lyle Hailey
CanSat 2018 PDR: Team 5278 BUTTER 56
Mechanical Sub-System Requirements
Direct Requirements
Requirement Number Requirement Rationale Priority
M-21The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second.
Competition Requirement High
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.
Competition Requirement. High
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.
Competition Requirement High
M-24Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects
Competition Requirement High
Presenter: Lyle Hailey
CanSat 2018 CDR: Team 5278 BUTTER
Payload Mechanical Layout of Components
57Presenter: Lyle Hailey
CanSat 2018 CDR: Team 5278 BUTTER
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.
58Presenter: Lyle Hailey
CanSat 2018 CDR: Team 5278 BUTTER
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.
59Presenter: Lyle Hailey
TWIST LOCK LID
FOAM LINED CONTAINER
118mm
80mm
CanSat 2018 CDR: Team 5278 BUTTER
Heat shield Release Mechanism
60Presenter: Lyle Hailey
• 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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 PDR: Team 5278 BUTTER 64
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
Presenter: Lyle Hailey
CanSat 2018 CDR: Team 5278 BUTTER
Communication and Data Handling (CDH) Subsystem Design
Sina Malek
65
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
CDH Changes Since PDR
• There were no changes since PDR
67Presenter: Sina Malek
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Sina Malek
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Sina Malek
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Sina Malek
CanSat 2018 CDR: Team 5278 BUTTER
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.
Presenter: Sina Malek
CanSat 2018 CDR: Team 5278 BUTTER
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]
Presenter: Sina Malek
CanSat 2018 CDR: Team 5278 BUTTER
Electrical Power Subsystem Design
Mecah Levy
74
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
EPS Changes Since PDR
• Since PDR there have been no changes to EPS
77Presenter: Mecah Levy
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Mecah Levy
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Mecah Levy
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Mecah Levy
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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%
Presenter: Mecah Levy
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
Presenter: Vijay Ramakrishna
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
Presenter: Vijay Ramakrishna
ID Requirement Rationale
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.
CanSat 2018 CDR: Team 5278 BUTTER 8888
FSW Requirements
Presenter: Vijay Ramakrishna
ID Requirement Rationale
MISSION
FSW-08 (MISSION-39)
FSW-09 (MISSION-40)
CanSat 2018 CDR: Team 5278 BUTTER 8989
FSW Requirements
Presenter: Vijay Ramakrishna
ID Requirement Rationale
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.
CanSat 2018 CDR: Team 5278 BUTTER 9090
FSW Requirements
Presenter: Vijay Ramakrishna
ID Requirement Rationale
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>
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER 9292
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)
Presenter: Vijay Ramakrishna
CanSat 2018 CDR: Team 5278 BUTTER
Software Development Plan
• Timeline:– April: Finish all Subsystems + Test Individually– May: Integrate Subsystems into FSW for the Can Sat +
Test
93
CanSat 2018 CDR: Team 5278 BUTTER
Ground Control System (GCS) Design
Vijay Ramakrishna
94
CanSat 2018 CDR: Team 5278 BUTTER
GCS Overview
9595
GCS Overview
Presenter: Vijay Ramakrishna
CanSat 2018 CDR: Team 5278 BUTTER
GCS Changes Since PDR
• Determined and added antenna mounting design and description of antenna usage
96
CanSat 2018 CDR: Team 5278 BUTTER
GCS Requirements
97Presenter: Name goes here 97
GCS Requirements
Presenter: Vijay Ramakrishna
ID Requirement Rationale
GCS-01 (MISSION-28) XBEE shall be used to communicate with the probe
GCS-02 (MISSION-29)
GCS-03 (MISSION-30)
CanSat 2018 CDR: Team 5278 BUTTER 9898
GCS Requirements
Presenter: Vijay Ramakrishna
ID Requirement Rationale
GCS-04 (MISSION-32)
GCS-05 (MISSION-35)
GCS-06 (MISSION-36)
CanSat 2018 CDR: Team 5278 BUTTER 9999
GCS Requirements
Presenter: Vijay Ramakrishna
ID Requirement Rationale
GCS-07 (MISSION-37)
CanSat 2018 CDR: Team 5278 BUTTER 100
GCS Design
Laptop (>=two hour battery life)
XBee Pro S3B
900 MHzTrue Gain Antenna
DATA
GCS Desktop GUI Sparkfun XBee Explorer Dongle
Presenter: Vijay Ramakrishna
CanSat 2018 CDR: Team 5278 BUTTER 101
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
Presenter: Vijay Ramakrishna
CanSat 2018 CDR: Team 5278 BUTTER 102102
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
Presenter: Vijay Ramakrishna
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
CanSat 2018 CDR: Team 5278 BUTTER 103
GCS Software
103Presenter: Vijay Ramakrishna
CanSat 2018 CDR: Team 5278 BUTTER
GCS Bonus Wind Sensor
• We are not pursuing the bonus objective
104
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 PDR: Team 5278 BUTTER
Subsystem Level Testing Plan
• 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
107Presenter: David Madden
CanSat 2018 PDR: Team 5278 BUTTER
Subsystem Level Testing Plan
• 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
108Presenter: David Madden
CanSat 2018 PDR: Team 5278 BUTTER
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
109Presenter: David Madden
CanSat 2018 PDR: Team 5278 BUTTER
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.
110Presenter: David Madden
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
Test Procedures Descriptions
112
Test ID Test Description Requirements Pass Fail Criteria
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
CanSat 2018 CDR: Team 5278 BUTTER
Test Procedures Descriptions
113
Test ID Test Description Requirements Pass Fail Criteria
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.
CanSat 2018 CDR: Team 5278 BUTTER
Test Procedures Descriptions
114
Test ID Test Description Requirements Pass Fail Criteria
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
CanSat 2018 CDR: Team 5278 BUTTER
Test Procedures Descriptions
115
Test ID Test Description Requirements Pass Fail Criteria
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.
CanSat 2018 CDR: Team 5278 BUTTER
Mission Operations & Analysis
Mecah Levy
116
CanSat 2018 CDR: Team 5278 BUTTER
Overview of Mission Sequence of Events
117Presenter: Mecah Levy
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
CanSat 2018 CDR: Team 5278 BUTTER
Overview of Mission Sequence of Events
118Presenter: Mecah Levy
Key:(G) Ground Station Crew (R) Recovery Crew(C) Container Crew (M) Mission Control Officer
CanSat 2018 CDR: Team 5278 BUTTER
Field Safety Rules Compliance
119Presenter: Mecah Levy
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 2018 CDR: Team 5278 BUTTER
CanSat Location and Recovery
120Presenter: Mecah Levy
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
Requirements Compliance
David Madden
123
CanSat 2018 PDR: Team 5278 BUTTER 124
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
CanSat 2018 PDR: Team 5278 BUTTER
Requirements Compliance Overview
125Presenter: 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
CanSat 2018 PDR: Team 5278 BUTTER
Requirements Compliance Overview
126Presenter: David Madden
RqmtNum Requirement
Comply / No Comply /
Partial
X-Ref Slide(s) Demonstrating
Compliance
Team Commentsor Notes
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
CanSat 2018 PDR: Team 5278 BUTTER
Requirements Compliance Overview
127Presenter: David Madden
RqmtNum Requirement Comply / No
Comply / Partial
X-Ref Slide(s) Demonstrating
Compliance
Team Commentsor Notes
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
CanSat 2018 PDR: Team 5278 BUTTER
Requirements Compliance Overview
128Presenter: David Madden
RqmtNum Requirement
Comply / No Comply /
Partial
X-Ref Slide(s) Demonstrating
Compliance
Team Commentsor Notes
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
CanSat 2018 PDR: Team 5278 BUTTER
Requirements Compliance Overview
129Presenter: David Madden
RqmtNum Requirement
Comply / No Comply /
Partial
X-Ref Slide(s) Demonstrating
Compliance
Team Commentsor Notes
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
CanSat 2018 CDR: Team 5278 BUTTER
Management
David Madden
130
CanSat 2018 CDR: Team 5278 BUTTER
Status of Procurements
131Presenter: David Madden
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
CanSat 2018 CDR: Team 5278 BUTTER
Status of Procurements
132Presenter: David Madden
Component Status Quantity Date Arrived
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
CanSat 2018 CDR: Team 5278 BUTTER
Status of Procurements
133Presenter: David Madden
Component Status Quantity Date Arrived
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
CanSat 2018 CDR: Team 5278 BUTTER
Status of Procurements
134Presenter: David Madden
Component Status Quantity Date Arrived
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 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
CanSat Budget – Hardware
136
Component Status Quantity Individual Cost Type
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
CanSat 2018 CDR: Team 5278 BUTTER
CanSat Budget – Hardware
137
Component Status Quantity Individual Cost Type
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
CanSat 2018 CDR: Team 5278 BUTTER
CanSat Budget – Hardware
138
Component Status Quantity Individual Cost Type
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 2018 CDR: Team 5278 BUTTER
CanSat Budget – Ground Control
139
Component Status Quantity Individual Cost Type
Mac Laptop Reused 1 $1000 Estimate
XBEE Pro 900 New 1 $39.00 Exact
Yagi Antenna Reused 1 $15.25 Exact
CanSat 2018 CDR: Team 5278 BUTTER
CanSat Budget – Other Expenses
140
Component Status Quantity Individual Cost Type
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
CanSat 2018 CDR: Team 5278 BUTTER
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
CanSat 2018 CDR: Team 5278 BUTTER
Program Schedule
142Presenter: David Madden
CanSat 2018 CDR: Team 5278 BUTTER
Preliminary Design Stage
143Presenter: David Madden
CanSat 2018 CDR: Team 5278 BUTTER
Critical Design Stage
144Presenter: David Madden
CanSat 2018 CDR: Team 5278 BUTTER
Final Stage
145Presenter: David Madden
CanSat 2018 CDR: Team 5278 BUTTER
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
146Presenter: David Madden
CanSat 2018 CDR: Team 5278 BUTTER
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
147Presenter: David Madden