and Autonomous IDentification NASA USLI Preliminary Design Review - - PowerPoint PPT Presentation

PLAID: Precision Launch and Autonomous IDentification

NASA USLI Preliminary Design Review Carnegie Mellon Rocket Command

November 17, 2017

Launch Vehicle Design

Overall Design

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Wildman Extreme Darkstar

Why the Darkstar?

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• Starting baseline for our new team
• Includes all main compatible launch vehicle components
• Quality components
• Full fiberglass body, motor mount, and centering rings
• Metal tipped nose cone
• Engine adaptability
• Fits wide range of motors
• 54mm or 75mm
• Cost
• Donated by team mentor

Main Dimensions & Materials

Component Dimensions* Material Lower Airframe 4” D x 52” L Fiberglass (G-12) Recovery Bay (coupler) 4” D x 11” L Fiberglass (G-12) Switch Band 4” D x 2” L Fiberglass (G-12) Upper Airframe 4” D x 24” L Fiberglass (G-12) Nose cone 4” D 5-1(L/D) Fiberglass (G-12) with Aluminum tip Motor Mount 75mm Fiberglass (G-12) Fins 3/16” thick Fiberglass (G-10)

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Total Rocket 4" D 94” L (OpenRocket) *Actual dimensions vary slightly from these manufacturer specifications, e.g. the 4” diameter measurement is used for all components that fit with a 4” airframe.

Material Justification

Material of 4” Diameter Body Tube Cost (per inch length of 4" diameter body tube) Water Effects Ultimate Tensile Strength (ksi) Stiffness (msi) Kraft Paper (Apogee Components) $0.50 Highly Susceptible - weakens and swells as it absorbs water

• Blue Tube 2.0

(Always Ready Rocketry) $0.81 Water-resistant, but not waterproof

• G12 Fiberglass

(Wildman Rocketry) $1.95 Negligible 60-80 5-10 Carbon Fiber (Wildman Rocketry) $4.60 Negligible 240 20-30

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Launch Vehicle Material Comparison

Material Justification (continued)

Carbon Fiber

+ Extremely high strength to weight ratio + Waterproof + Low thermal expansion

• Brittle
• Expensive

Fiberglass

+ Cost-effective + Waterproof + High strength to weight ratio

• Slightly higher thermal

expansion

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Stability Parameters

Stability Parameters

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Mass (lb) Center of Gravity, CG (in. from forward end) Center of Pressure, CP (in. from forward end) Static Stability Margin (cal) Dry 12.25 58.20 76.67 4.55 Wet (with current chosen motor) 16.625 65.09 76.67 2.86

Motor Selection

Selection Criteria

• 1. The motor must be reloadable.
• 2. It must be manufactured by Aerotech, CTI, or Loki
• 3. The output apogee altitude must be within a range of 5,400 to

7,000 ft.

• 4. The motor thrust curve must feature a neutral-regressive burn

profile with a high initial thrust peak.

• 5. The required ballast to lower the apogee under ideal (no wind)

conditions must be less than 10% of the total design weight (motor included).

• 6. Must provide a rail-exit velocity of 52 fps or above
• 7. Must be commercially available with multiple suppliers.

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Selected Motor

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November 17, 2017

Rocket Flight Profile with CTI K650 in 10 MPH winds FLIGHT PROFILE WITH BALLAST CORRECTION

Launch Parameters

Thrust-to-Weight Ratio

• Based on the CTI K650 Smokey Sam:
• 657.68 N of average thrust
• PLAID weight:
• 74 N
• Thrust-to-Weight Ratio
• 8.91
• This is a sufficient thrust-to-weight ratio

for Project PLAID

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Rail Exit Velocity

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• Minimum Required Velocity: 52 ft/s
• Achieved Velocity: 78.9 ft/s
• Based on engine thrust curve of

CTI K650

• Based on OpenRocket flight

simulation

Subsystem Breakdown

Summary

Subsystem Description Mass (lb) Approximate Length (in) Lower Airframe Includes the lower body tube, motor mount, centering rings, thrust plate, retainer, fins, motor adapter and motor 11.3 52 Recovery Includes the electronics bay, parachutes, shock cords, and parachute protectors 2.0 11 Upper Airframe Includes the upper body tube 1.8 24 Payload Includes the nose cone, payload electronics, camera, and camera mounting system 1.5 20

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Lower Airframe Components

• G12 body tube
• G12 75mm motor mount
• (2) G10 centering rings
• (6) G10 beveled fins
• Aluminum thrust plate and

flanged motor retainer

• Aluminum 54/75mm motor

adapter

• Motor with casing

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Lower Airframe: Fins

• Split fins
• Upper is tapered swept
• Aspect Ratio = 0.929
• Lower is trapezoidal
• Aspect Ratio = 1.192
• Pre-beveled
• Considered tapering trailing

edges

• Fin flutter
• 3/16" thickness

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Upper Fin Lower Fin

Lower Airframe: Thrust Plate and Retainer

• Aluminum vs. plastic retainer
• Kaplow clips and Engine clips

eliminated due to lack of strength

• Aluminum retainer best

practice

• Material strength
• Heat
• Thrust plate recommended by

mentor to distribute motor launch forces

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Lower Airframe: Thrust Plate and Retainer

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75mm Thrust Plate 75mm Motor Retainer

Lower Airframe: Motor Adapter

• Allows flexibility with motor

diameter

• Mates with Aeropack Engine

Retainer

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Recovery Components

• Electronics Bay
• G12 coupler
• G12 switch band
• (4) G10 bulk plates
• 3D printed sled
• (2) PerfectFlite Stratologger CF Altimeters
• (2) Schurter rotary switches
• Other electrical components (wires, JST connectors, battery)
• Fasteners and hardware (screws, threaded rods, eye-bolts,

black powder compartment, etc.)

• Drogue SkyAngle Classic Parachute (24”)
• Main SkyAngle Classic Parachute (60”
• Considering larger for safety factor
• (2) Nomex Parachute Protectors
• (2) Kevlar shock cord
• (2) Nylon schock cord protectors

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Recovery: Circuit Design

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• Two altimeters

provide redundancy for both charges

• Contains both drogue

and main parachute charges

• Altimeters each have

dedicated power supply

• Altimeters each have

dedicated switch

Recovery: Altimeter Selection

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PerfectFlite Stratologger CF Missile Works RRC2+ Missile Works RRC3 Price $58.80 $44.95 $79.95 Dimensions 2"L 0.85"W 0.5"H 2.28"L 0.925"W ~0.5"H 3.92"L 0.925"W 0.563"H Weight (oz) 0.38 0.35

• 0. 59

Altitude Accuracy ± 0.1% Not given Not given Operating Voltage 9V nominal (4V to 16V) 9V(3.5VDC-10VDC) 9V(3.5VDC-10VDC)

Recovery: Altimeter Selection

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Altimeter Pros Cons

PerfectFlite Stratologger CF

• Audibly reports peak altitude & max flight velocity via

beeps

• Up to 100,000’ msl altitude
• Output: drogue/main
• Collects 20 samples/sec
• Stores 16 flights
• (18 min/each) of data
• 2 output channels
• Does not include dt4u data transfer

kit Missile Works RRC2+

• Programmed using a DIP switch configuration
• Up to 100,000 msl altitude
• Programmable High/low audible beep tone
• Output: drogue/main
• Easily mountable
• 16 bit series mCU / altitude sensor has 24 bit ADV
• 2 output channels

Missile Works RRC3

• Reports peak altitude & max flight velocity
• Up to 100,000’ msl altitude
• Programmable High/low audible beep tone
• Altimeter sensor has 24 bit adc
• Stores 15 flights
• (28 min/each) of data
• 3 output channels: drogue/main/auxiliary
• Heavier
• Longer

Recovery: Altimeter Selection

• PerfectFlite StratoLogger CF
• Compact
• Ample performance
• Own already
• Low cost for first year in

competition

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Recovery: Sled Selection

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Recovery: Sled Selection

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Sled Type Pros Cons Plywood

• Cheap (<$5 for material)
• Easily machined/laser cut
• Can create our own custom design or

buy from online

• Time will be spent on

making a custom sled design

• Weakest of all choices

G10/Other Fiberglass

• Strong
• Readily available scraps in our inventory
• Difficult to machine

Additive Aerospace

• Already designed for plug and play use
• More secure housing of battery and

switch

• Can buy universal sled in case of

altimeter change

• Most expensive (~$35)

Self-designed 3D Printed

• Free
• Most customizable
• More time and work

Recovery: Sled Selection

• 98mm SMART Sled from

Additive Aerospace

+ Plug and play + Saves time

• More expensive
• Cannot Customize
• Still considering designing our
• wn
• Free 3D printing

November 17, 2017 31

Recovery: Switch Selection

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Pros Cons Schurter rotary switch

• Switch secured with a small flat blade

screwdriver, to lock position of switch

• Provides vent for pressure altimeters.
• Affordable ($10)

Simple spring- loaded switch

• Affordable ($6)
• Straightforward, functional
• More susceptible to external forces

disrupting the position of the switch

• May be armed or disarmed by accident.

Push-Hold Switch Trigger

• Push switch in ON position for a few seconds

to connect power to altimeter which allows switch not to change position easily.

• Insensitive to resistive or capacitive load
• G-force tested at 300 Gs
• On the expensive side ($20)

Recovery: Switch Selection

• Secure and sturdy connection
• Reduced risk of component failure
• n launch day or during flight
• Access hole provides altimeter

vent

• Mates well with Additive

Aerospace sled

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Recovery: Main Parachute

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• Determined drag force required to

achieve 75 ft-lbf of KE at landing

• Based on terminal velocity equations
• Determine required parachute

area and coefficient of drag

• Based on air resistance equations
• Selected SkyAngle 60" parachute
• Results in 69 ft-lbf of KE at landing
• Considering larger for safety factor
• Recommended by mentor

Recovery: Drogue Parachute

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• Drogue will be deployed at apogee
• Small enough to minimize drift
• Large enough to prevent too much

acceleration

• Solved same equations as for the

main parachute

• OpenRocket Simulations
• Selected SkyAngle 24" parachute

Recovery: Parachute Deployment

• Drogue on aft end of

electronics bay

• Main on forward end of

electronics bay

• Altimeters sense apogee,

trigger first ejection charge

• Deploy drogue
• Altimeters sense main

deployment height, trigger second ejection charge

• Deploy main

November 17, 2017 36

Upper Airframe

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• As discussed in materials section:
• G12 Fiberglass Body Tube
• Very strong, lightweight, and

durable

• Rivets hold the Upper Airframe to

the Recovery Bay

• Nylon shear pins connect the

Upper Airframe to the nose cone

Upper Airframe: Camera Bay

• Camera bay located between the

nose cone and upper air frame

• Walls of clear tubing for camera to

view through

• Tube selected for durability of

flight forces

• Camera mounted on angled

plates for optimal viewing angle

• Design work and materials

selection in process

November 17, 2017 38

Nose Cone/Payload Housing

• The payload is housed by a G-

12 nose cone

• Strong, lightweight, durable
• Metal tip protects from fracture

at weakest point

• Also allows threaded rod to be

inserted

• Experiment payload will be

housed in a sled in the nose cone

November 17, 2017 39

Preliminary Payload Design

Payload Overview

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• Payload housed in a nose

cone bay on a wooden sled

• TDS
• flight computer, sensors,

camera, and battery

• Telemetry System
• GPS, transmitter, and

receiver

• Camera mounted in clear

tube below the nose cone

Telemetry System Target Detection System (TDS)

Payload Components

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Flight Computer Software Sensors Camera GPS Raspberry Pi 3B OpenCV on Python Raspberry Pi SenseHAT Mobius Action Camera Eggfinder GPS Tracking System

System Level Considerations

Computationally Light

• One camera feed
• Standard lens camera
• Mobius Action Camera
• Raspberry Pi 3B sufficient as a

flight computer

• OpenCV and Python sufficient

for image processing

• Proposed design

Computationally Heavy

• Multiple (two) camera feeds
• Wide angle lens
• RunCam Wide Angle Camera
• Nvidia Jetson TK1 required as

a powerful flight computer

• OpenCV and C++ for
• ptimized image processing

November 17, 2017 43

Camera Considerations

Internal Camera

• Located in clear tube below

nose cone + No impact on drag + Simplified wiring to computer

• Clear tube structural integrity
• Chosen Configuration

External Camera

• Located in shroud mounted to

the body tube

• Increases drag
• Wiring to computer becomes

more complex

• Decreased rocket stability

November 17, 2017 44

GPS Considerations

Eggfinder GPS Tracking System

• Accurate up to 2.5 m
• Range up to 8000 ft
• 10 hrs standby, 2 hrs operation
• Uses license-free frequency
• Requires 2S 7.4V LiPo
• Proposed GPS

Beeline 100mW GPS

• Comparable accuracy
• Comparable range
• Comparable battery life
• Requires amateur radio license
• Contains internal battery

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TDS Program Logic

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• Autonomous initiation of

TDS

• Analyze images based on

expected RGB, size, and shape of targets

• Interface with SenseHAT

for acceleration data

• Label and store all

identified targets

Requirement Compliance Plan

General Requirements

November 17, 2017 48 Requirement Currently Met and Evidence? Plan to Meet Students on the team will do 100% of the project, including design, construction, written reports, presentations, and flight preparation with the exception of assembling the motors and handling black powder or any variant of ejection charges, or preparing and installing electric matches (to be done by the team’s mentor). Yes; Authors of the project report, Authors of documents tracking calculations and design of rocket Continue to work independently of

• utside resources apart from

guidance. The team will provide and maintain a project plan to include, but not limited to the following items: project milestones, budget and community support, checklists, personnel assigned, educational engagement events, and risks and mitigations. Yes; presence of a project timeline, budget, and team member records. Continue to meet project deadlines as provided by both NASA and the CMRC The team will engage a minimum of 200 participants in educational, hands-on science, technology, engineering, and mathematics (STEM) activities, as defined in the Educational Engagement Activity Report, by FRR. An educational engagement activity report will be completed and submitted within two weeks after completion of an event. No, but progressing; Records of CMU Society of Women Engineers High School Day Continue progress on STEM

• utreach activities through

participating with the local YMCA as well as the CMU community. Each team must identify a “mentor.” A mentor is defined as an adult who is included as a team member, who will be supporting the team (or multiple teams) throughout the project year, and may or may not be affiliated with the school, institution, or organization. The mentor must maintain a current certification, and be in good standing, through the National Association of Rocketry (NAR) or Tripoli Rocketry Association (TRA) for the motor impulse of the launch vehicle and must have flown and successfully recovered (using electronic, staged recovery) a minimum

• f 2 flights in this or a higher impulse class, prior to PDR.

Yes, John Haught is the mentor for the CMRC Team. With a Level 3 HPR certification, he has done a minimum of 2 flights in the K or above class. John Haught will remain our mentor for the duration of Project PLAID and will maintain his current certification.

Vehicle Requirements

November 17, 2017 49 Requirement Currently Met and Evidence? Plan to Meet The vehicle will deliver the payload to an apogee altitude of 5,280 feet above ground level (AGL) No, but plan to meet The two separately wired altimeters will work as redundant systems to record information and cross check data to find the most precise altitude, with less than a foot of error. The launch vehicle will be designed to be recoverable and reusable. Reusable is defined as being able to launch again on the same day without repairs or modifications. No, but plan to meet The rocket will be designed with reusability in mind. The rocket components and recovery system will ensure the rocket is reusable. The launch vehicle will have a maximum of four (4) independent sections. An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute. No, but plan to meet PLAID will have 3 sections: the nose cone, the electronics bay, and the body. The launch vehicle will be capable of being prepared for flight at the launch site within 3 hours of the time the Federal Aviation Administration flight waiver opens. No, but plan to meet PLAID will be constructed at Carnegie Mellon University, and final preparations such as parachute preparations, will be able to be completed in less than 3 hours. The launch vehicle will be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board components. No, but plan to meet The construction of PLAID will be strong enough to withstand direct sunlight for at least an hour. All electronics will remain functional for over one hour of standby.

Vehicle Requirements (cont.)

November 17, 2017 50 Requirement Currently Met and Evidence? Plan to Meet The launch vehicle will be capable of being launched by a standard 12-volt direct current firing system. The firing system will be provided by the NASA-designated Range Services Provider. No, but plan to meet PLAID will be designed to launch based off of this standard system. The total impulse provided by a College and/or University launch vehicle will not exceed 5,120 Newton-seconds (L-class). No, but plan to meet The motor, CTI 1750-K650-16A, has a maximum measured impulse of 1749.5 Newton-seconds. The launch vehicle will have a minimum static stability margin of 2.0 at the point of rail exit. Rail exit is defined at the point where the forward rail button loses contact with the rail. No, but plan to meet The static stability is designed to be about 4 at the point of rail exit. The launch vehicle will accelerate to a minimum velocity of 52 fps at rail exit. No, but plan to meet The planned exit rail velocity will be 80.6 ft/s. Teams will launch and recover subscale model of rocket before CDR, carrying an altimeter capable of reporting model’s apogee altitude No, but plan to meet An altimeter will be onboard the subscale rocket, and will record live peak altitude and max velocity. All teams will successfully launch and recover their full-scale rocket prior to FRR in its final flight configuration. The rocket flown at FRR must be the same rocket to be flown on launch day. If the payload is not flown, mass simulators must be used in approximately the same location as the payload would have been. No, but plan to meet CMRC will launch the final rocket prior to FRR in as full of a configuration as possible.

Vehicle Requirements (cont.)

November 17, 2017 51 Requirement Currently Met and Evidence? Plan to Meet If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle, those systems will be active during the full-scale demonstration flight. No, but plan to meet The payload is not designed to manage the total energy of the vehicle and it does not change the external surface of the rocket. If the full-scale motor is not flown during the full-scale flight, it is desired that the motor simulates, as closely as possible, the predicted maximum velocity and maximum acceleration of the launch day flight. No, but plan to meet Full Scale test flight will include full scale motor. The vehicle must be flown in its fully ballasted configuration during the full- scale test flight. No, but plan to meet If the vehicle design needs any ballast, the vehicle will be flown fully ballasted. The launch vehicle will not exceed Mach 1 at any point during flight. No, but plan to meet PLAID will remain subsonic at all points in flight. Vehicle ballast will not exceed 10% of the total weight of the rocket. No, but plan to meet Any added ballast will be weighed and compared with the total weight to ensure this standard is not exceeded.

Recovery Requirements

November 17, 2017 52 Requirement Currently Met and Evidence? Plan to Meet The launch vehicle will stage the deployment of its recovery devices, where a drogue parachute is deployed at apogee and a main parachute is deployed at a lower altitude. No, but plan to meet PLAID will deploy a drogue parachute, located above the electronics bay, at apogee, while deploying the main parachute at an altitude of 700ft. Each team must perform a successful ground ejection test for both the drogue and main parachutes. This must be done prior to the initial subscale and full-scale launches. No, but plan to meet CMRC plans to perform a ground ejection test on November 19th. At landing, each independent sections of the launch vehicle will have a maximum kinetic energy of 75 ft-lbf. No, but plan to meet The maximum kinetic energy at landing, with the current calculations, will be 56.26 ft-lbf— well under the maximum 75 ft- lbf. The recovery system electrical circuits will be completely independent of any payload electrical circuits. No, but plan to meet The payload circuits will be located in the nose cone, while the recovery electronics will be placed in a separate electronics bay located between the nose cone and the body. The recovery system will contain redundant, commercially available

• altimeters. The term “altimeters” includes both simple altimeters and more

sophisticated flight computers. No, but plan to meet PLAID will contain two PerfectFLite StratoLogger CF altimeters. Removable shear pins will be used for both the main parachute compartment and the drogue parachute compartment. No, but plan to meet Removable shear pins will be used in the specified locations.

Recovery Requirements (cont.)

November 17, 2017 53 Requirement Currently Met and Evidence? Plan to Meet Recovery area will be limited to a 2500 ft. radius from the launch pads. No, but plan to meet The recovery area will be limited to the specified radius. The dual deploy recovery system will allow the rocket to be recovered in this radius. An electronic tracking device will be installed in the launch vehicle and will transmit the position of the tethered vehicle or any independent section to a ground receiver. No, but plan to meet The GPS system will be located in the avionics payload. Any rocket section, or payload component, which lands untethered to the launch vehicle, will also carry an active electronic tracking device. No, but plan to meet No components will land untethered to the launch vehicle. The electronic tracking device will be fully functional during the official flight

• n launch day.

No, but plan to meet Functionality of the GPS system will be checked before and on launch day. The recovery system electronics will not be adversely affected by any other

• n-board electronic devices during flight (from launch until landing).

No, but plan to meet The payload will be RF shielded so it will not affect any other

• n-board electronic devices.

Recovery system altimeters will be located in a separate location than any radio frequency transmitting device and/or magnetic wave producing

• device. Recovery system electronics will be shielded from all onboard

transmitting devices, to avoid interference (including generators, solenoid valves, and Tesla coils) No, but plan to meet The Recovery system altimeters will be located in a different bay than the electronics bay. No other electronic devices will be within the same region as the recovery system and its

• altimeters. In addition, a type of Faraday’s cage will be arranged

so no charge will affect the inside of the cage, including the

• ther onboard transmitting devices.

Experiment Requirements

November 17, 2017 54 Requirement Currently Met and Evidence? Plan to Meet Each team will choose one design experiment option from the following list. Yes CMRC has chosen Target Detection for the 2017-18 NASA USLI Competition Additional experiments (limit of 1) are allowed, and may be flown, but they will not contribute to scoring. Yes No other experiments will be flown. If the team chooses to fly additional experiments, they will provide the appropriate documentation in all design reports, so experiments may be reviewed for flight safety. N/A N/A Teams will design an onboard camera system capable of identifying and differentiating between 3 randomly placed targets. No, but plan to meet The avionics bay will accomplish this task. Data from the camera system will be analyzed in real time by a custom designed on-board software package that shall identify, and differentiate between the three targets. No, but plan to meet The data will be analyzed during flight by a Raspberry Pi or similar processor. Teams will not be required to land on any of the targets. No, but plan to meet No plans have been made to land on the targets.

Safety Requirements

November 17, 2017 55 Requirement Currently Met and Evidence? Plan to Meet Each team will use a launch and safety checklist. The final checklists will be included in the FRR report and used during the Launch Readiness Review (LRR) and any launch day operations. No, but plan to meet Preliminary checklists have been developed and will be used for the launch of the subscale model. SO will monitor activities, with an emphasis on safety Yes SO monitors design and fabrication procedure. SO will oversee all testing and launches. SO has outlined proper safety practices for CMRC to follow at all times, including in his absence. SO will implement procedures developed by the team for construction, assembly, launch, and recovery activities. Yes, SO currently performs these tasks. SO will enforce the established safety procedures. Manage and maintain current revisions of the team’s hazard analyses, failure modes analyses, procedures, and MSDS/chemical inventory data. No, but plan to meet. SO currently creating repository of such data. During test flights, teams will abide by the rules and guidance of the local rocketry club’s RSO. No, but plan to meet Will communicate with our respective NAR and TRA chapters before launch day to ensure we are allowed to launch our rocket. Teams will abide by all rules set forth by the FAA. Yes, CMRC currently abides by these rules. CMRC will continue to abide by all FAA rules and regulations

Internal Goals

November 17, 2017 56

Requirement Currently Met and Evidence? Plan to Meet Win the Rookie Award No, but plan to meet CMRC will attempt for maximum points in all aspects of the competition Reach within 300 feet of the goal apogee of 5,280 feet No, but plan to meet CMRC will test multiple motors for the full scale flight and select the motor with the best apogee results Main parachute will be deployed at 700 feet above the ground No, but plan to meet Signal from preprogrammed altimeter will be sent to ejection charge and deploy main parachute All team members will be concerned with safety first Yes The SO will create a culture of safe practices for Project PLAID, and all CMRC members will mutually enforce these practices

Thank You

Questions?

Special thanks to John Haught, Rod Schafer, and John Brohm!

References

Cipolla, John. “Fin Flutter and Loads Analysis Software.” AeroFinSim, AeroRocket and Warp Metrics, www.aerorocket.com/finsim.html. “Wing Geometry Definitions.” NASA, Glenn Research Center, 5 May 2015, www.grc.nasa.gov/www/k-12/airplane/geom.html. “Elastic Constant Converter.” Calculator for Exploring Relations Among the Elastic Constants, EFunda Inc., www.efunda.com/formulae/solid_mechanics/mat_mechanics/calc_elastic_constants.cfm. Benson, Tom. Velocity During Recovery. NASA, https://www.grc.nasa.gov/WWW/k-12/VirtualAero/BottleRocket/airplane/rktvrecv.html. Howard, Zachary. “Apogee Components Peak of Flight Newsletter.” 19 July 2011. Hennin, Bart. “Apogee Components Peak of Flight Newsletter.” 19 October 2010. Hunter, John D. “Matplotlib: A 2D Graphics Environment.” Computing in Science & Engineering, vol. 9, no. 3, 2007, pp. 90–95., doi:10.1109/mcse.2007.55. Van Milligan, Tim. “Apogee Components Peak of Flight Newsletter.” 18 December 2012. Van Milligan, Tim. “Apogee Components Peak of Flight Newsletter.” 2 May 2017. Tola, Ceyhun, and Melik Nikbay. “Investigation of the Effect of Thickness, Taper Ratio and Aspect Ratio on Fin Flutter Velocity of a Model Rocket Using Response Surface Method.” Research Gate, 7th International Conference on Recent Advances in Space Technologies , June 2015. “Shape Effects on Drag.” NASA, Glenn Research Center, 5 May 2015, www.grc.nasa.gov/WWW/k-12/airplane/shaped.html. “G10 Fiberglass Epoxy Laminate Sheet.” Material Property Data, MatWeb, www.matweb.com/search/DataSheet.aspx?MatGUID=8337b2d050d44da1b8a9a5e61b0d5f85. Niskanen, Sampo "OpenRocket technical documentation", 10 May 2013.

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