CanSat 2018 Preliminary Design Review (PDR) Version 1.2

Transcription

1 CanSat 2018 Preliminary Design Review (PDR) Version 1.2 Team 5278 B.U.T.T.E.R 1

2 Table of Contents Introduction: Alex Schneider Systems Overview: Alex Schneider Sensor Subsystem Design: Michael Campbell Descent Control Design: Anthony McCourt Mechanical Subsystem Design: Dwight Scott, Lyle Hailey Communication and Data Handling Subsystem Design: Sina Malek Electrical Power Subsystem Design: Mecah Levy Flight Software Design: Vijay Ramakrishna Ground Control System Design: Vijay Ramakrishna CanSat Integration and Test: David Madden Mission Operations and Analysis: Alex Schneider Requirements Compliance: Mennatallah Hussein Management: David Madden Conclusion: David Madden Presenter: Alex Schneider 2

3 Team Organization Presenter: Alex Schneider 3

4 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 Presenter: Alex Schneider 4

5 Systems Overview Alex Schneider 5

6 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 Presenter: Alex Schneider 6

7 System Requirement Summary ID Requirements Rationale Priority SR-01 Total mass of the CanSat (probe) shall be 500 grams +/- 10 grams. Competition Requirement SR-02 The aero-braking heat shield shall be used to Competition Requirement 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 SR-04 The probe must maintain its heat shield orientation in the direction of descent. Competition Requirement SR-05 The probe shall not tumble during any portion of descent. Tumbling is rotating end-over-end. Competition Requirement Presenter: Alex Schneider 7

8 System Requirement Summary 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 SR-07 The probe shall hold a large hen's egg and protect it from damage from launch until landing. Competition Requirement 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 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 Presenter: Alex Schneider 8

9 System Requirement Summary SR-10 The aero-braking heat shield shall be a fluorescent color; pink or orange. Competition Requirement SR-11 The rocket airframe shall not be used to restrain any deployable parts of the CanSat. Competition Requirement SR-12 The rocket airframe shall not be used as part of the CanSat operations. Competition Requirement SR-13 The CanSat, probe with heat shield attached shall deploy from the rocket payload section. Competition Requirement SR-14 The aero-braking heat shield shall be released from the probe at 300 meters. Competition Requirement SR-15 The probe shall deploy a parachute at 300 meters. Competition Requirement SR-16 All descent control device attachment components (aero-braking heat shield and parachute) shall survive 30 Gs of shock. Competition Requirement Presenter: Alex Schneider 9

10 System Requirement Summary SR-17 All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock. Competition Requirement SR-18 All electronic components shall be enclosed and shielded from the environment with the exception of sensors. Competition Requirement SR-19 All structures shall be built to survive 15 Gs of launch acceleration. Competition Requirement SR-20 All structures shall be built to survive 30 Gs of shock. Competition Requirement SR-21 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives. Competition Requirement SR-22 All mechanisms shall be capable of maintaining their configuration or states under all forces. Competition Requirement Presenter: Alex Schneider 10

11 System Requirement Summary SR-23 Mechanisms shall not use pyrotechnics or chemicals. Competition Requirement 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 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 SR-26 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts. Competition Requirement SR-27 Telemetry shall include mission time with one Competition Requirement second or better resolution. Mission time shall be maintained in the event of a processor reset during the launch and mission. Presenter: Alex Schneider 11

12 System Requirement Summary 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 SR-29 XBEE radios shall have their NETID/PANID set to their team number. Competition Requirement SR-30 XBEE radios shall not use broadcast mode. Competition Requirement SR-31 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost. Competition Requirement SR-32 Each team shall develop their own ground station. Competition Requirement SR-33 All telemetry shall be displayed in real time during descent. Competition Requirement SR-34 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.) Competition Requirement Presenter: Alex Schneider 12

13 System Requirement Summary SR-35 Teams shall plot each telemetry data field in real time during flight. Competition Requirement 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 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 SR-38 Both the heat shield and probe shall be labeled with team contact information including address. Competition Requirement Presenter: Alex Schneider 13

14 System Requirement Summary SR-39 The flight software shall maintain a count of Competition Requirement 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 SR-41 The probe must include an easily accessible power switch. Competition Requirement SR-42 The probe must include a power indicator such as an LED or sound generating device. Competition Requirement SR-43 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second. Competition Requirement SR-44 The descent rate of the probe with the heat Competition Requirement shield released and parachute deployed shall be 5 meters/second. Presenter: Alex Schneider 14

15 System Requirement Summary SR-45 An audio beacon is required for the probe. It may be powered after landing or operate continuously. Competition Requirement SR-46 Battery source may be alkaline, Ni-Cad, Competition Requirement Ni-MH or Lithium. Lithium polymer batteries are not allowed. Lithium cells must be manufactured with a metal package similar to 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. Competition Requirement SR-48 Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects. Competition Requirement Presenter: Alex Schneider 15

16 System Requirement Summary SR-49 A tilt sensor shall be used to verify the stability of the probe during descent with the heat shield deployed and be part of the telemetry. Presenter: Alex Schneider Competition Requirement 16

17 System Level CanSat Configuration Trade & Selection Heat Shield/Aero Brake Config 1 Heat Shield/Aero Brake Config 2 This component was the deciding factor for overall system design Directly affected the electrical components required Structural component configuration relied heavily on this component Presenter: Alex Schneider 17

18 System Level CanSat Configuration Trade & Selection Configuration 1 This configuration included a deployable nylon heat shield Spring tension would open the heat shield to act as Aero Brake System CONOPS Variations When stowed, fishing line will be used to retain tensioned rods On payload deployment, a nichrome cutting circuit will release heat shield Presenter: Alex Schneider 18

19 System Level CanSat Configuration Trade & Selection Configuration 1 Problems and Risks Complex design at connection to payload risk of fishing line hanging up on expansion of heat shield Did not comply with requirement S-2 as the heat shield did not fully envelop the payload prior to deployment This design over complicated the design of internal structural components Presenter: Alex Schneider 19

20 System Level CanSat Configuration Trade & Selection Configuration 2 This configuration will consists of a two piece heat shield and aero-brake The aero-brake will be affixed to a fiberglass sleeve surrounding the payload Spring tension will expand the aero-brake CONOPS Variations fishing line will retain the aero-brake in stowed position A nichrome cutting circuit will release heat aero-brake The heat shield will separate into two parts on ejection Presenter: Alex Schneider 20

21 System Level CanSat Configuration Trade & Selection Configuration 2 Benefits Fully envelopes the payload prior to deployment to comply with requirement S-2 Simple release mechanism reduces risk of failure during ejection of heat shield and aero-brake Allows the addition of a camera to complete the bonus objective Presenter: Alex Schneider 21

22 Physical Layout Overall Component Layout Egg centered and well protected by foam walled container Egg container Integrated into capsule Aero-Brake and Heat Shield form and assembly and fully enclose the probe Deployed Configuration shown RBF Pins accessible on exterior of payload Presenter: Alex Schneider FIBERGLASS AERO-BRAKE PARACHUTE EGG 265 mm FOAM RBF Pins HEAT SHIELD 22

23 Physical Layout Probe Component Layout Batteries kept low for to lower COM Electronics kept stowed under batteries and egg compartment Two part capsule for quick disassembly and access to batteries and egg compartment Press Tabs to detach top and bottom capsule sections PRESS TABS BATT COMP CAMERA Presenter: Alex Schneider 170 mm PCB 23

24 Physical Layout Electronics Layout 4 holes evenly spaced for mounting screws All components thru-hole for ease of soldering Contains all sensors and control electronics SD Card Reader TEENSY 3.2 GYRO TEMP Altimeter RADIO GPS Presenter: Alex Schneider 24

25 System Concept of Operations OP # CONOPS Flow Chart Stage 1 Establish Communication Between Probe and Ground Station Pre-Flight 2 Pre-Flight System Check Pre-Flight 3 Mount Payload to Rocket Ascent 4 Launch (Apogee at 600m) Ascent 5 Expansion of Aero-Brake Descent 6 Descend at m/s Until 300m Altitude Descent 7 Eject Heat Shield and Aero-Brake ASSY and Parachute Deployment Descent Presenter: Alex Schneider 25

26 System Concept of Operations OP # CONOPS Flow Chart Stage 8 Descend at 5m/s Descent 9 Landing Ground 10 Recovery Ground Presenter: Alex Schneider 26

27 Launch Vehicle Compatibility Launch Configuration 3mm clearance on overall outer diameter given for payload to allow for easy deployment 5mm clearance on overall height dimension to ensure the payload fits in the rocket, and so the to payload can easily clear the rocket section at apogee All edges are rounded to ensure no sharp surfaces will snag on deployment 295 mm 122 mm Presenter: Alex Schneider 27

28 Sensor Subsystem Design Michael Campbell 28

29 Sensor Subsystem Overview 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 Presenter: Michael Campbell 29

30 Sensor Subsystem Requirements Direct Requirements Requirement Number Requirement Rationale Priority SS-01 Total mass of the CanSat (probe) shall be 500 grams +/- 10 grams Ensure deployment from the launching rocket within a reasonable margin. SS-02 All 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- 03 All 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. SS-05 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost. Competition Requirement. SS-06 A tilt sensor shall be used to verify the stability of Probe orientation cannot easily be CanSat 2017 PDR: Team ### (Team Number andfrom Name) the probe during the descent with the heat shield determined the ground, so deployed and be part of the telemetry. additional sensors are required. Presenter: Michael Campbell Medium 30

31 Probe Air Pressure Sensor Trade & Selection Model Power Usage Mass Dimensions Accuracy Interface BMP V, 32 µa, µw per reading/sec <1 g 3.6 mm X 3.55 mm ±0.25 meters I2C MPL3115A2 3.3V, 40 µa, 132 µw per reading/sec 0.9 g 4.55 mm X 2.55 mm ±0.3 m / ±1 C I2C Selected Air Pressure Sensor MPL3115A2 -Temperature compensated altitude readings versus only pressure, little to no calibration needed -Acceptable accuracy -I2C interface -Secondary temperature sensor Presenter: Michael Campbell 31

32 Probe Air Temperature Sensor Trade & Selection Model Power Usage Mass Dimensions Accuracy Interface TMP36 3.3V, 50 µa, 165 µw 0.2 g 2 mm X 2 mm ±1 C Analog TMP V, 10 µa, 33 µw 0.8 g 14 mm X 14 mm ±0.5 C I2C Selected Air Temperature Sensor TMP36 -Simple interface -Acceptable accuracy -Smaller footprint Presenter: Michael Campbell 32

33 GPS Sensor Trade & Selection Model Power Usage Mass Dimensions Accuracy Interface MTK V, 20mA 8.5g 25.5mm x 35mm x 6.5mm ±3 Meters ±0.1 m/s Tx/Rx Venus638FLPx 3.3V, 67mA 6g 18mm x 29.5mm x 2mm ±2.5 Meters Tx/Rx Selected GPS MTK3339 -Includes built in antenna -10Hz update rate -Reduced power draw and mass Presenter: Michael Campbell 33

34 Probe Power Voltage Sensor Trade & Selection Model Power Usage Mass Dimensions Accuracy Interface Model NCP V,.5μA <1 g 0.4 cm X 0.2 cm 2.0% Analog NCP303 Voltage divider 3.3V, 2mA 0.5 g 0.2 cm X 1 cm 2.0% Analog Voltage divider Selected Voltage Measurement Method Voltage divider -Integrated on the board -Can easily measure voltage before conversion -Acceptable power usage -Easily modified Presenter: Michael Campbell 34

35 Tilt Sensor Trade & Selection Model Power Usage Mass Dimensions Accuracy Interface Adafruit LSM9DS V, 4mA 3g x mm +/- 30 /sec I2C Sparkfun MPU V, 3.2mA 1.5g x mm +/- 5 /sec I2C Selected Tilt Sensor - Sparkfun MPU Small size - Lightweight - I2C interface - Correct operating Voltage Presenter: Michael Campbell 35

36 Bonus Camera Trade & Selection Model Power Usage Mass Dimensions Resolution Interface Adafruit camera #3202 5V 80mA Standby 110mA Active 2.8g 28.5mm x 17mm x 4.2mm 1280x720 Picture 640x480 Video 3.3V Trigger Adafruit camera # V 75mA 20mm x 28mm 640x480 Picture 640x480 TTL Video Teensy RX/TX 3g Selected Camera - Adafruit #3202 -Able to record video -Built in SD memory card -Simple interface Presenter: Michael Campbell 36

37 Descent Control Design Anthony McCourt #slide=i d.p5 37

38 Descent Control Requirements Requirement Description Rationale Competition Requirement 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. DC-02 The probe shall not tumble during any portion of descent. Tumbling is rotating end-over-end. Competition Requirement DC-03 The probe with the aero-braking heat shield shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length. Tolerances are to be included to facilitate container deployment from the rocket fairing. Competition Requirement The probe shall deploy a parachute at 300 meters. Competition Requirement DC-05 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second. Competition Requirement DC-06 The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second. Competition Requirement DC-04 Presenter: Anthony McCourt 38

39 Payload Descent Control Strategy Selection and Trade Parachute CFC-18 Chute (Fruity Chutes) TARC-18 Chute (Fruity Chutes) Area (m2) Shape Shock Force Survival DCS Connections Preflight Review Testability Color Elliptical and hole (10% Area) Good (Flexible) Nylon Lines Good (Drop Test) Orange/ Black Round and hole (10% Area) Good (Flexible) Lightweight Spectra Lines Good (Drop Test) Orange/ Black Mass (g) Both parachutes provided the desired 5 m/s descent rate However, the TARC-18 parachute was decided on due to the g mass versus the CFC-18 Chute with more than double the mass of g. This larger mass detracted from the mass budget for electronics as well as moving the center of mass further aft. Presenter: Anthony McCourt 39

40 Descent Stability Control Strategy Selection and Trade Heat Shield Design & Control System Overview Spherically Blunted Cone (SBC)-Based Design Passive Control Mechanism Mass is kept at the cone-shaped end to keep center of mass below the center of pressure Aerodynamic properties of the body keep it stable with no need of active control system Minimizes need for unnecessary mechanical or electrical systems Frees mass budget for critical components Presenter: Anthony McCourt 40

41 Descent Stability Control Strategy Selection and Trade First Iteration SBC without capsule or skirt Based on the Apollo re-entry vehicles used by NASA (left) Fluid analysis via Solidworks determined that preliminary design would result in unwanted turbulence in the body s wake (right) Presenter: Anthony McCourt 41

42 Descent Stability Control Strategy Selection and Trade First Iteration SBC without capsule or skirt Pros: Passive stability control Mass can be kept at tip of cone to push center of gravity near the nose Simple geometry can be 3D printed at low cost and mass ABS plastic is rough enough to keep falling velocity within limits Cons: Stubby design pushes center of pressure near center of gravity Wake turbulence may result in instability Complicates heat shield and parachute deployment Presenter: Anthony McCourt 42

43 Descent Stability Control Strategy Selection and Trade Second Iteration SBC with capsule Added capsule with deployable heat shield (left) Fluid analysis depicting smoother streamlines with smaller wake vortices than first iteration (right) Presenter: Anthony McCourt 43

44 Descent Stability Control Strategy Selection and Trade Second Iteration SBC with capsule Pros: Center of pressure is pushed away from center of gravity due to elongated body, increasing stability Heat shield is easily detachable from the capsule Cons: Slender profile causes body to fall too quickly due to smaller wetted area Parachute still somewhat difficult to deploy due to solid back-end Presenter: Anthony McCourt 44

45 Descent Stability Control Strategy Selection and Trade Third Iteration SBC with capsule and skirt Added skirt produces skin friction drag which allows for a slower decent (left) Fluid analysis that turbulence develops on either side of the skirt (right) Presenter: Anthony McCourt 45

46 Descent Stability Control Strategy Selection and Trade Third Iteration SBC with capsule and skirt Pros: Added surface area results in more drag, slowing descent Cons: ABS plastic is relatively heavy, resulting in large part of mass budget being reserved for capsule Turbulent flow between capsule and skirt may result in instability Presenter: Anthony McCourt 46

47 Descent Stability Control Strategy Selection and Trade Fourth Iteration Fiberglass SBC with capsule and spoked-skirt Fourth Iteration and current model of CanSat (left) Flow simulation shows smooth streamlines leaving the body (right) Presenter: Anthony McCourt 47

48 Descent Stability Control Strategy Selection and Trade Fourth Iteration Fiberglass SBC with capsule and spoked-skirt Pros: Parachute can be easily deployed through the hollow tail Fiberglass is lighter than ABS plastic resulting in less mass needed for capsuled Fiberglass has a higher structural integrity than ABS plastic ABS plastic heat shield slows capsule down until detachment Cons: Less surface roughness than ABS plastic Presenter: Anthony McCourt 48

49 Descent Rate Estimates Methodology A code was written inside of MatLab in order to estimate the Lift produced by the CanSat in both configurations by using the Slender-Body Theory and Cross-Flow Drag. The CanSat Profile was cut up by 1 mm slices and the change in radius, along with the oncoming velocity and Reynolds Number at each slice Integrating all the pieces produced a total Lift that could be run several times at varying angles of attack (AoA) and oncoming velocities Assumptions: The altitude of Stephenville, TX was used for air density calculations CanSat is perfectly cylindrical about center Plot descriptions: Top-Left - Lift produced by Cross-flow drag Top-Right - Profile of CanSat Bottom-Left - Slender Body Lift Bottom-Right - Total Lift Presenter: Anthony McCourt 49

50 Descent Rate Estimates Descent Rate Estimate of CanSat Pre-Deployment This configuration did not produce sufficient lift within the 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 Presenter: Anthony McCourt 50

51 Descent Rate Estimates Descent Rate Estimate of CanSat Post-Deployment This configuration is after the skirt of the CanSat is released shortly after ejection from the rocket. This configuration falls within the acceptable window of required descent rate. The plot on the bottom shows the steady-state velocity of the CanSat in this configuration at a varying AoA. Even at a small AoA, the CanSat will be producing enough lift to stay within the maximum 30 m/s descent rate. Presenter: Anthony McCourt 51

52 Descent Rate Estimates 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 Presenter: Anthony McCourt Shown above is a plot of the descent rate versus mass for the selected TARC-18 parachute 52

53 Descent Rate Estimates 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 Presenter: Anthony McCourt CanSat Configuration Calculated Descent Rate Range Pre-Deployment m/s Post-Deployment m/s Post-Heat Shield Separation 5.04 m/s Shown above is the summary of the estimated descent rates of the CanSat for their respective Configurations 53

54 Mechanical Subsystem Design Lyle Hailey and Dwight Scott #slide=id.p5 54

55 Mechanical Subsystem Overview 3D PRINTED CAPSULE TOP FIBERGLASS SLEEVE 3D PRINTED CAPSULE BOTTOM 3D PRINTED HEAT SHIELD FOAM PADDING NYLON RIPSTOP DROGUE EGG CONTAINER LID E-STACK PRESS TABS X4 Presenter: Lyle Hailey & Dwight Scott 55

56 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 M-2 The probe shall hold a large hen's egg and protect it from damage from launch until landing. Competition Requirement 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 M-4 The rocket airframe shall not be used to restrain any deployable parts of the CanSat. Competition Requirement M-5 The rocket airframe shall not be used as part of the CanSat operations. Competition Requirement Presenter: Lyle Hailey & Dwight Scott 56

57 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 M-7 The aero-braking heat shield shall be released from the probe at 300 meters. Competition Requirement. M-8 The probe shall deploy a parachute at 300 meters. Competition Requirement M-9 All descent control device attachment components (aero-braking heat shield and parachute) shall survive 30 Gs of shock. Competition Requirement M-10 All descent control devices (aero-braking heat shield and parachute) shall survive 30 Gs of shock. Competition Requirement. Presenter: Lyle Hailey & Dwight Scott 57

58 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 M-12 All structures shall be built to survive 30 Gs of shock. Competition Requirement. M-13 All mechanisms shall be capable of maintaining their configuration or states under all forces. Competition Requirement M-14 Mechanisms shall not use pyrotechnics or chemicals. Competition Requirement 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. Presenter: Lyle Hailey & Dwight Scott 58

59 Mechanical Sub-System Requirements Direct Requirements Requirement Number Requirement M-16 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost. Competition Requirement M-17 Both the heat shield and probe shall be labeled with team contact information including address. Competition Requirement. M-18 No lasers allowed. Competition Requirement M-19 The probe must include an easily accessible power switch Competition Requirement M-20 The descent rate of the probe with the heat shield deployed shall be between 10 and 30 meters/second. Competition Requirement. Presenter: Lyle Hailey & Dwight Scott Rationale Priority 59

60 Mechanical Sub-System Requirements Direct Requirements Requirement Number Requirement M-21 The descent rate of the probe with the heat shield released and parachute deployed shall be 5 meters/second. Competition Requirement 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 cells. Competition Requirement. 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 M-24 Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects Competition Requirement Presenter: Lyle Hailey & Dwight Scott Rationale Priority 60

61 Probe Mechanical Layout of Components Trade & Selection Probe Design 1: Glued Assembly Configuration 3d Printed ABS Structure Circular Heat Shield Attachment points Electronics mount into bottom of Probe ELECTRONICS MOUNTING AREA HEAT SHIELD ATTACH POINTS Presenter: Lyle Hailey & Dwight Scott AERO FIN TAPERED THROUGHOUT 61

62 Probe Mechanical Layout of Components Trade & Selection Probe Design 2: Press Tab Configuration (Chosen Configuration) 3d Printed ABS Structure E-Stack included for mounting PCB and Batteries ELECTRONICS STACK TAPERED SECTION HEAT SHIELD ATTACH POINTS STRAIGHT SECTION PRESS TABS FOR DISASSEMBLY Presenter: Lyle Hailey & Dwight Scott 62

63 Probe Mechanical Layout of Components Trade & Selection Overview Both configurations were designed for 3d printing. This was chosen as material because of the ease of adding mounting structures to the probe 4 heat shield attachment points were included in Design 2: Press Tab Config to hold securely Electronics mounting for both designs was nearly identical Design 2 included an egg container as part of the capsule body Design 1 included a fin for aerodynamic properties Presenter: Lyle Hailey & Dwight Scott 63

64 Probe Mechanical Layout of Components Trade & Selection Selection Justification Design 2: Press Tab Configuration was chosen This design allow for easier disassembly than design one because of the press tabs. The straight section on Design 2 made manufacturing and assembly simple Design 2 allows for access to both batteries and egg compartment in under 1 minute The fin on Design 1 proved to be too flimsy to last under defined loading and shock conditions Heat shield detachment on Design 2 has less contacting surface area for a smooth release, while still having better mechanical properties than Design 1 Presenter: Lyle Hailey & Dwight Scott 64

65 Payload Pre Deployment Configuration Trade & Selection Design 1: Inverted Umbrella Uses a torsion spring tensioned rod to hold in stowed configuration. Fishing line used to connect tensioned rod to nichrome cutting circuit Nichrome circuit used to cut FISHING fishing line and release LINE aero-brake Outward facing to allow for easy expansion Presenter: Lyle Hailey & Dwight Scott NICHROME CIRCUIT TORSION SPRINGS 65

66 Payload Pre Deployment Configuration Trade & Selection Design 2: Aero-Brake Drogue (Chosen Configuration) Uses a torsion spring tensioned rod to hold in stowed configuration. Fishing line used to connect tensioned rod to nichrome cutting circuit Nichrome circuit used to cut fishing line and release aero-brake Fishing line tied to ends of rods for more torque Presenter: Lyle Hailey & Dwight Scott TORSION SPRINGS FISHING LINE NICHROME CIRCUIT 66

67 Payload Pre Deployment Configuration Trade & Selection Selection Justification Design 2: Aero-Brake Drogue was chosen This design used the same mechanism as Design 1, but the moving parts were more concealed The Brake facing inward pre-deployment eliminated risk of sharp edges snagging on inside of rocket section. The inward angle also meant that the fishing lines would have less stress on them to hold the payload in the stowed configuration Design 1 did not fully cover the probe pre deployment Presenter: Lyle Hailey & Dwight Scott 67

68 Heat shield Deployment Configuration Trade & Selection Deployment Options Passive (using force from surrounding air Active (using spring tension) Passive Pros: The idea of this method was to allow the air to push open the heat shield into deployed configuration Requires no electronic control circuitry or power The weight would be considerably less Cons: Unreliable Unstable Aerodynamic properties Presenter: Lyle Hailey & Dwight Scott 68

69 Heat shield Deployment Configuration Trade & Selection Active (chosen option) Pros: Reliable Much less risk of payload becoming unstable on descent Solid construction Can ensure expansion of Aero-Brake on deployment from rocket Cons: More complicated design Requires more more electronics More costly on mass budget Presenter: Lyle Hailey & Dwight Scott 69

70 Heat shield Deployment Configuration Trade & Selection Selection Justification Maintaining stability and the proper descent rate was vital to the mission operations The reliability of the payload deployment far outweighed the effect this had on the mass budget The Payload was light enough to allow for flexibility in choosing this option Nichrome circuits have been proven to work, and are an effective way to release a deployable structure Presenter: Lyle Hailey & Dwight Scott 70

71 Heat shield Mechanical Layout of Components Trade & Selection Position of Heat Shield Aero-Braking Assembly was a major factor in design. 3 Design configurations were considered Major Selection Criteria: Weight: location and material will factor into the overall mass of the payload Material: considered both weight and strength of material Requirement compliance: needed to comply with all mission requirements Ease of Assembly: Need quick access to Egg and Batteries Strength: Considered structure and material properties Deployment Reliability: Ability to release from rocket Presenter: Lyle Hailey & Dwight Scott 71

72 Heat shield Mechanical Layout of Components Trade & Selection Heat Shield Mechanical Layout Design 1 (Upside Down LAUNCH CONFIG Umbrella) Criteria Weight Score (1-10) PROBE 6 Material 10 Requirement Compliance 4 TORSION SPRINGS HEAT SHIELD DEPLOYED CONFIG Ease of Assembly 6 Structural integrity 6 Deployment Reliability 6 Presenter: Lyle Hailey & Dwight Scott 72

73 Heat shield Mechanical Layout of Components Trade & Selection Heat Shield Mechanical Layout Design 2 (Fiberglass LAUNCH CONFIG Sleeve Aero-Brake Assembly) Criteria Weight Score (1-10) TORSION SPRINGS 9 PROBE Material 10 Requirement Compliance 10 Ease of Assembly 9 Structural integrity 8 Deployment Reliability 8 Presenter: Lyle Hailey & Dwight Scott HEAT SHIELD DEPLOYED CONFIG AEROBRAKE 73

74 Heat shield Mechanical Layout of Components Trade & Selection Heat Shield Mechanical Layout Design 3 (Side Wall Heat LAUNCH CONFIG Shield) Criteria Score (1-10) Weight 8 Material 10 Requirement Compliance 8 Ease of Assembly 5 Structural integrity 8 Deployment Reliability 8 Presenter: Lyle Hailey & Dwight Scott PROBE TORSION SPRINGS DEPLOYED CONFIG HEAT SHIELD 74

75 Heat shield Mechanical Layout of Components Trade & Selection Overview and Selection: Layout Design 2 was chosen Bringing the deployment structure away from the internal components allowed for lowest overall weight Fulfilled all mission requirements regarding heat shield Best deployment reliability due to inward facing stowed configuration, which meant less obstructions and no sharp surfaces on outside of payload Similar structural integrity to Design 3, but far better than Design 1 due to mounting structures and springs being covered by the heat shield All designs combined 3d printed structures, with a spring tensioned Nylon Ripstop Aero-Brake Presenter: Lyle Hailey & Dwight Scott 75

76 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 to both the heat shield & Fiberglass sleeve for simultaneous deployment Fishing line is cut with nichrome cutting circuit RELEASE POINTS Presenter: Lyle Hailey & Dwight Scott 76

77 Probe Parachute Release Mechanism Probe Parachute will be stowed on top of probe, under pre deployed Aero-Brake in the launch configuration A wrap will be wound up on parachute and fixed to the fiberglass sleeve portion of the Aero-Brake This will unwind and deploy the parachute when the heat shield and Aero-Brake are released. RELEASE STRING Presenter: Lyle Hailey & Dwight Scott 77

78 Egg Protection Structure Foam was chosen as the primary egg protection Design of probe includes a container for the egg with foam lining to provide protection The egg container lid features a twist-locking mechanism that is easily accessible, but also securely holds the egg in place during flight FOAM LINED CONTAINER TWIST LOCK LID Presenter: Lyle Hailey & Dwight Scott 78

79 Electronics Structural Integrity Electronics will be connected using screws and threaded inserts Inserts will be fixed in bottom surface of satellite No separate enclosure will be used for the pcb board, but all structures above the pcb will be secured to the body of payload fully enclosed by the capsule M3 screws will be used to affix the pcd to the fixed inserts Descent control attachments will be deployed using nichrome wire The nichrome wire will activate the deployable aerobrake A separate nichrome circuit will detach both the heat shield and aerobrake from the satellite at the 300m altitude 79 Presenter: Lyle Hailey & Dwight Scott

80 Mass Budget Component Estimated Weight (grams) Sources Structural Elements 110 From Estimates 68 From Competition Guidelines Egg Parachute Electronic Components Probe Final Weight Presenter: Lyle Hailey & Dwight Scott Component Estimated Weight (grams) Sources Probe Weight 350 From Table to Left Heat Shield 100 From Estimates Margin 50 Remaining Mass Budget CanSat Final Weight 500 From Estimates Data Sheets 80

81 Communication and Data Handling (CDH) Subsystem Design Presenter: Sina Malek #slide=id.p5 81

82 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 Presenter: Sina Malek 82

83 CDH Requirements ID Requirement Rationale Priority CDH-01 During descent, the probe shall collect air pressure, outside air temperature, GPS position, and battery voltage once per second and time tag the data with mission time. Probe data must be collected for transmission to monitor its status. HIGH CDH-02 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts. Live feed of collected probe data. HIGH CDH-03 During 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 83

84 Probe Processor & Memory Trade & Selection Board Processor Teensy bit ARM Cortex 72Mhz Arduino Nano 16Mhz Memory I/O Power Dimensions 256K Flash 64K RAM 2K EEPROM Serial (3) SPI (1) I2C (2) 3.3V (5V Tolerant) 3.5cm x 1.8cm 32K Flash 2K RAM 1K 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 84

85 Probe Real-Time Clock 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 85

86 Probe Antenna Trade & Selection Model Gain VSWR Dimensions Interface 900 MHz Rubber Duck Antenna 2 dbi 2.0:1 Height: 160mm RP-SMA LCOM patch HG902PU 2 dbi 2.0:1 40x8mm x 53.6mm U.FL Selected: 900Mhz Duck antenna Appropriate interface for selected XBee 900 MHz modules Smaller size suitable radiation pattern Presenter: Sina Malek 86

87 Probe Radio Configuration Radio Selection: XBEE-PRO 900-HP Frequency: 900 Mhz Configured in Transparent (AT) Mode NETID: Team 5278 Transmission Control Continuous 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 87

88 Probe Telemetry Format The probe telemetry consists of ASCII comma separated fields followed by a carriage return. Data will be transmitted once per second at 9600 baud in continuous mode. Sensor data as well as mission time, packet count, and the current software state will be transmitted. The data format is as follows: <TEAM ID>,<MISSION TIME>,<PACKET COUNT>,<ALTITUDE>, <PRESSURE>,<TEMP>,<VOLTAGE>,<GPS TIME>,<GPS LATITUDE>,<GPS LONGITUDE>,<GPS ALTITUDE>,<GPS SATS>,<TILT X>,<TILT Y>,<TILT Z>,<SOFTWARE STATE> Example data: [5278,60,40,1000,1013,20,3.3,123.5,33.5,-111.9,1410,3,0.01,0.0,0.3,3] Presenter: Sina Malek 88

89 Electrical Power Subsystem (EPS) Design Mecah Levy #slide=id.p5 89

90 EPS Overview 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 Presenter: Mecah Levy 90

91 EPS Overview Diagram 4x AAAA Pack A RBF Switch 3.3V Regulator Microcontroller Micro-USB Power Sensors 4x AAAA Pack B RBF Switch Nichrome Cutting Circuit 5V Regulator Presenter: Mecah Levy Camera 91

92 EPS Requirements ID EPS-01 EPS-02 EPS-03 EPS-04 EPS-05 Requirements The probe must include an easily accessible power switch. The probe must include a power indicator such as an LED or sound generating device. 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 cells. Rationale To easily restrict power to the probe To easily indicate if the probe is on/off To comply with competition rules on power supplies An easily accessible battery compartment must be included allowing batteries to be installed or removed in less than a minute and not require a Easily access power supply total disassembly of the CanSat. Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects. Presenter: Mecah Levy Priority For no loss of power 92

93 Probe Electrical Block Diagram 4x AAAA Alkaline Batteries 6V RBF Switch ~2.7-6V 3.3V Regulator Micro-USB Power *Umbilical Power Microcontroller 3.3V Gyroscope Temperature XBEE Pro CR2032 4x AAAA Alkaline Batteries 6V RBF Switch ~2.7-6V 5V Regulator Nichrome Cutting Circuit Presenter: Mecah Levy Audio Beacon GPS Micro SD Altimeter RTC 5V Camera Power will be controlled by an external switch. Will verify battery voltage using voltage divider reading from microcontroller 93

94 Probe Power Trade & Selection Model Capacity Nominal Voltage Mass Dimensions Energizer E96 AAAA Alkaline Battery 550 mah 1.5V 6.5g 40.7mm x 8mm Powerizer 123A Li-ion battery 650 mah 3.7V 18g 36mm x 17mm Energizer E92 AAA Alkaline Battery 500 mah 1.5V 11.5g 44.5mm x 10.5mm Selected Battery - 4x in Series Energizer AAAA - Small Profile - capacity - Past success Presenter: Mecah Levy 94

95 Probe Power Budget Component Model Duty Cycle Current (A) Voltage (V) Power (W) Microcontroller Teensy % Estimated Radio XBEE Pro 900 Hp 100% Data sheet GPS FGPMMOPA6H 100% Data sheet Memory micro SD card 30% Estimated Altimeter MS % Data sheet Temperature TMP36 100% Data sheet Gyroscope MPU % Data sheet 3.3V Regulator L % Data sheet Audio Beacon Piezo Buzzer 12% Data sheet Total A Source Power supply B Camera (Standby) Adafruit # %-98% use 98% Data sheet Camera (Operating) Adafruit # %-3% used 3% Data sheet 5V Regulator L7805CV 100% Data sheet Cutting Circuit Nichrome wire 1% Calculated Total B Presenter: Mecah Levy

96 Probe Power Margin Battery Pack A Power Available: 3300 mwh Sensor Power Consumption: mwh Battery A Power Margin: 55% Battery Pack B Power Available: 3300 mwh Sensor Power Consumption: mwh Battery B Power Margin: 91% Presenter: Mecah Levy 96

97 Flight Software (FSW) Design Vijay Ramakrishna #slide=i d.p5 97

98 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 98

99 FSW Requirements ID Requirement Rationale FSW-01 The aero-braking heat shield shall be released from the probe at 300 meters. The probe will have already entered the atmosphere, and so drag will be less of an issue. A parachute will provide better slowing of the descent at this phase. FSW-02 The probe shall not tumble during any part of the descent. Tumbling is rotating end-over-end. Tumbling can potentially throw off or damage sensors, other electronic components, and the payload contained in the probe. FSW-03 During descent, the probe shall collect air pressure, outside air temperature, GPS position, and battery voltage once per second and time tag the data with mission time Telemetry from the probe must be collected and time-stamped in order to determine the current status of the probee. Presenter: Vijay Ramakrishna 99

100 FSW Requirements ID Requirement Rationale FSW-04 During descent, the probe shall transmit all telemetry. Telemetry can be transmitted continuously or in bursts. The probe must be able to communicate with the ground station in order to relay information about the probe s status FSW-05 Telemetry shall include mission time with one second or better resolution. Mission time shall be maintained in the event of a processor reset during the launch and mission Data collected by the probe must be accurate. FSW-06 All telemetry shall be displayed in real-time during the descent The probe must provide recent data samples to the ground station. Presenter: Vijay Ramakrishna 100

101 FSW Requirements ID Requirement Rationale FSW-07 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.) Required in order to ensure the accuracy and understandability of the data. FSW-08 The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets. Ensures that accurate telemetry is transmitted even if the processor is reset mid-flight. FSW-09 No lasers allowed. Lasers pose a threat to the flora and fauna of the launch site! Presenter: Vijay Ramakrishna 101

102 FSW Requirements ID Requirement Rationale FSW-10 (MISSION-45) An audio beacon is required for the probe. It may be powered after landing or operate continuously. The probe must be able to be easily located after flight. FSW-11 (MISSION-49) A tilt sensor shall be used to verify the stability of the probe during descent with the heat shield deployed and be part of the telemetry. The probe must remain stable in order to ensure the safety of the payload. Stability must be verifiable for this purpose. Presenter: Vijay Ramakrishna 102

103 FSW Requirements 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: The telemetry data from the probe must be structured in order to be easily understandable. <TEAMID>,<MISSION TIME>,<PACKET COUNT>,<ALTITUDE>,<PRE SSURE>,<TEMP>,<VOLTAG E>,<GPS TIME>,<GPS LATITUDE>,<GPS LONGITUDE>,<GPS ALTITUDE>,<GPS SATS>,<TILT X>,<TILT Y>,<TILT Z>,<SOFTWARE STATE> Presenter: Vijay Ramakrishna 103

104 Probe FSW State Diagram Recovery - Non-volatile EEPROM is used on reset to determine state, packet count, and initialize MET Power - Power management is handled via Teensy 3.2 Presenter: Vijay Ramakrishna 104

105 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 Presenter: Vijay Ramakrishna 105

106 Ground Control System (GCS) Design Vijay Ramakrishna #slid e=id. p5 106

107 GCS Overview Presenter: Vijay Ramakrishna 107

108 GCS Requirements ID Requirement Rationale GCS-01 XBEE radios shall be used for telemetry. 2.4 GHz Series 1 and 2 radios are allowed. 900 MHz XBEE Pro radios are also allowed. XBEE shall be used to communicate with the probe GCS-02 XBEE radios shall have their NETID/PANID set to their team number. The telemetry must be identifiable to a specific team. GCS-03 XBEE radios shall not use broadcast mode. The XBEE radios must not be allowed to broadcast data over to other teams during competition. Presenter: Vijay Ramakrishna 108

109 GCS Requirements ID Requirement Rationale GCS-04 Each team shall develop their own ground station. The ground station must be GCS-05 Teams shall plot each telemetry data field in real time during flight. The ground station must be aware of the current state of the probe at any time, to within a 1Hz resolution. GCS-06 The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a handheld antenna. The ground station must be able to fit in the allotted space during competition. Presenter: Vijay Ramakrishna custom, and cannot be shared between teams. 109

110 GCS Requirements ID Requirement Rationale GCS-07 The ground station must be portable so the team can be positioned at the ground station operation site along the flight line. AC power will not be available at the ground station operation site. The ground station must be able to continue to collect data for the duration of the mission. Presenter: Vijay Ramakrishna 110

111 GCS Design GCS Desktop GUI Sparkfun XBee Explorer Dongle Laptop (>=two hour battery life) DATA 900 MHz True Gain Antenna Presenter: Vijay Ramakrishna XBee Pro 900HP 111

112 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 112

113 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-Y dBi 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 113

114 GCS Software Example Telemetry Data: <5278>,<48.325>,<48>,<235>,<1013>,<14.86>,<22.8>,<3.5>,<128.4>,<DESCENT> COTS software packages: Arduino IDE - board programming C# - real-time plotting, sending of serial commands via Winforms, GBee libraries XCTU - Configuring XBee radios Real-time plotting Using C# libraries to process and display telemetry Data archiving saved on GS and onboard payload.csv file created by GC software from received data Commands over C#: Mission start, override parachute deployment/heat shield release, override audio beacon Presenter: Vijay Ramakrishna 114

115 GCS Bonus Wind Sensor Our team is not pursuing this bonus objective at this time Presenter: Vijay Ramakrishna 115

116 CanSat Integration and Test David Madden 116

117 Subsystem Level Testing Plan Aeronautics Subsystem Windtunnel test. Testing of heat shield deployment at ground level Testing of heat shield deployment while in free fall. Completed Parachute Test of 10 meters Completed Parachute and Egg Test of 10 meters Successfully Presenter: David Madden 117

118 Subsystem Level Testing Plan Mechanical Subsystem Drop test of payload with parachute from 10 meters completed successfully Drop test of payload with 30g s of impulse from string completed successfully Drop test of final design without egg Drop test of final design with egg Drop test of all parts integrated Presenter: David Madden 118

119 Subsystem Level Testing Plan Electrical Subsystem Nichrome Wire cutting circuit testing from ground level, cutting a taut fishing line. GPS testing individually by physical displacement. GPS testing while integrated into the CanSat by physical displacement XBees testing through configuration and set up with other proven electronics Range test for radio communication Sensor data collection prototypes have been tested. Gyroscope to be tested through random motion Remainder tests scheduled for completion at ground level and during test launch in March Presenter: David Madden 119

120 Integrated Level Functional Test Plan Drop container with payload from quadcopter at a height above 300m to test full parachute deployment, nichrome wire cutting circuit, heat shield release, and the survival of an Drop container with payload from quadcopter at a height above 300m to test full sensors, communications, the camera, and electronics integration and range. Full drop test of payload in container from rocket launch. To be deployed at competition height (670m-725m) for full testing of every subsystem. Presenter: David Madden 120

121 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 high temperature 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. Presenter: David Madden 121

122 Mission Operations & Analysis Mecah Levy 122

123 Overview of Mission Sequence of Events Team Member Roles and Responsibilities Mission control officer (M) Alex Schneider Ground Station crew (G) Mecah Levy Vijay Ramakrishna Sina Malek Recovery crew (R) Lyle Hailey Anthony McCourt Mennatallah Hussein Cansat Crew (C) Frank Pinon David Jack Madden Michael Campbell Presenter: Mecah Levy 123

124 Overview of Mission Sequence of Events Key: (G) Ground Station Crew (C) Container Crew Presenter: Mecah Levy (R) Recovery Crew (M) Mission Control Officer 124