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University of

Alabama in

Huntsville

NASA SL

Preliminary

Design Review

11/3/2017University of Alabama in Huntsville

USLI PDR1

• Design, fabricate, test and fly a rocket and payload to 1 mile in altitude

• Deploy a rover upon landing to autonomously travel and unfold solar panels

• Conduct STEM outreach with students

*Throughout the presentation, all dimensions are in inches

Mission Summary


USLI PDR2

VEHICLE DESIGN

University of Alabama in Huntsville

USLI PDR311/3/2017

• Launch Vehicle Dimensions– Fairing Diameter: 6 in.– Body Tube Diameter: 4 in.– Mass at lift off: 39.7 lbm. – Length: 96 in.

• Concept– L-Class Solid Commercial Motor– Rover Delivery– Electronic Dual Deployment– Fiberglass Airframe

Vehicle Summary


USLI PDR4

Vehicle System Locations


USLI PDR5

Rover Piston Main

Parachute

Drogue

Parachute

Coupler

12 in.

Tracking/Rover

Deployment

Avionics

Fins (x4)

Recovery

Avionics

Forward

Airframe

24 in.

Aft

Airframe

41 in.

Payload

Fairing

36 in.

CG

51 in.

CP

63 in.

Vehicle CONOPS


USLI PDR6

Powered Ascent:

0 – 3.2 seconds

0 – 1,050 ft.

Deploy Drogue:

19 seconds

5,282 ft.

Deploy Main:

50 seconds

600 ft.

Landing:

100 seconds

0 ft. Deploy Rover:

Team Command

• OpenRocket Sim:

– A 1-D in house Monte Carlo simulation will be used to verify results

– Results will also be compared to flight tests for verification

Flight Simulation


USLI PDR7

Attribute Value

Apogee (ft.) 5282

Length (in.) 96

Max. Mach Number 0.56

Rail Exit Velocity (ft./s) 55.7

Static Stability (cal.) 2.0

Motor Designation AT L1520T - P

Thrust-to-Weight Ratio 8.7

CG 51 in.

CP 63 in.

• Apogee of approximately 5282 ft. at 19 sec.

• Motor burnout at approximately 1050 ft. at 3.2 sec.

Simulation Results


USLI PDR8

50 sec. Main deploy (600 ft.)

Apogee of 5282 ft. (19 sec.)

Burnout at 3.2 sec.

• Stability of 2.06 cal. at rail exit– Calculated with no wind conditions

• Stability of 2.74 cal. at motor burnout

Stability Analysis


USLI PDR9

Takeoff Stability: 2.06

Maximum Stability: 2.74

UPPER AIRFRAME


USLI PDR1011/3/2017

Nose Cone Payload Fairing TransitionForward Body Tube

Objectives• Protect and deploy the payload

• House assembly for tracking vehicle location

• Transition upper airframe to payload fairing

Forward System Overview


USLI PDR11

Payload Piston Avionics Bay

• 3D printed High Strength ABS• Ejected with rover deployment• Room to store ballast for stability• No electronics housed inside• Shear pin interface• Bulkhead at base• 6 in. ellipsoid shape• 2 in. shoulder

Nose Cone and Fairing


USLI PDR12

6.0 in. 2.0 in.

• Responsible for housing the rover and rover deployment system

• Filament wound fiberglass

6.0 in.

24.0 in.

• Used to deploy rover from fairing • Spring driven spike punctures cartridge • Spring released by hotwire upon

command; redundant arming

Piston Overview


USLI PDR13

Plunger

Ø 6.0 in.

Cylinder

Ø 6.0 in.

•Machined from aluminum•Powered by 8 or 12 gram CO2 cartridge•Plunger tethered to base•Standard Operating Procedure in development

• Aerodynamic transition between upper airframe and fairing, load path supplemented with aluminum insert

• 3-D printed with ABS plastic, single piece design

• Threaded rod in tension connecting to aft bulkhead to built in forward coupler

Fairing Transition


USLI PDR14

• Problems with ABS single piece design– Mass: 4.7 lbm

– Complicated FEA

– Structurally weak without aluminum insert

– Aluminum insert could pose manufacturing difficulties

• Other options considered:– Aluminum brace with direct bulkhead connection, purely aerodynamic

cover

Fairing Transition


USLI PDR15

CENTRALSUBSYSTEM


USLI PDR1611/3/2017

• Central Subsystem responsibilities:

– Primary coupler between airframes

– Flight Avionics

– Ejection System

– Tracking and Ground Station

– Recovery System

Central Subsystem Overview


USLI PDR17

Coupler


USLI PDR18

U Bolt(2 Places)

Black Powder Housing (4 Places)

Stratologger CFAltimeter (2 Places)

9V Battery (2 Places)

Switch/Pressure Equalization holes (2 Places)

All-Thread (2 Places)

1 in.Switchband

Aluminum Bulkheads

3D Printed Avionics Sled

9 in.12.5 in.

1 in.

Recovery Avionics Subsystem

• 2 PerfectFlite StratoLoggerCF altimeters; each with a 9V battery and SPDT momentary activation switch

• 4 Safe Touch terminals, E-matches, and black powder charges

• Full redundancy in avionics and ignition

Avionics


USLI PDR19

Recovery Deployment Avionics


USLI PDR20

• Normally Closed SPDT Pull Pin Microswitch– Prevents detonation during

assembly– Helps preserve battery life

• Primary Drogue charge fired at apogee– Secondary fired one second after

• Primary Main fired at 600 ft.– Secondary fired at 550 ft.

• Primary charges are roughly 4 g of black powder

• Secondary charges are 2 g larger than primary

GPS Tracking Subsystem


USLI PDR21

System

• CRW will reuse a previously designed PCB that contains an Xbee Pro-PRO 900HP RF module, and an Antenova GPS Chip

– PCB will includes traces for all relevant connections including battery sources.

• Xbee transmits GPS coordinates to a receiver connected to the ground station laptop.

• Tests will be performed prior to the full scale launch to verify operation success

Structure Integration

• 3D printed mount to secure tracker and its essentials within the transition section of the rocket.

• Three axis security and battery retention to ensure components are kept in tact

• Drogue Parachute Deployment:– Deployment at apogee– Fruity Chute CFC-18 (CD = 1.5)– Shock Cords: 1 inch Nylon (50 ft.)– Connected between forward motor

retention bulkhead in lower airframe and avionics bay housing.

– Descent speed under drogue: 62.2 ft/s

• Main Parachute Deployment:– Deployment at 700 ft. above ground

level– Fruity Chute 60 in. Iris Ultra (CD = 2.2)– Shock Cords: 1 inch Nylon (50 ft.)– Connected between fairing bulkhead

and avionics bay housing. – Descent speed under main: 15.23 ft/s

Recovery System


USLI PDR22

• Open Rocket Simulation between 0 and 20 mph winds showed a maximum drift at 15 mph of about 1,700 ft.

https://fruitychutes.com/buyachute/l3-elliptical-72-to-120-c-8/120-custom-parachute-50lb-20fps-p-6.html

https://www.apogeerockets.com/Building_Supplies/Parachutes_Recovery_Equipment/Parachutes/High_Power/84in_Iris_Ultra_Parachute?zenid=a1aiv1itb71rpsg0g4pb66elc2

• Required that each individual section will have a maximum kinetic energy of 75 ft-lbf

• For initial calculations, a conservative estimate of 75 ft-lbf was used for the heaviest section

• 𝐾𝐸 =1

2𝑚𝑣2

– m = mass of the section, lbm

– v = velocity, ft/s

• The largest independent section is 15 lbm, so the safe descent speed was determined to be 17.9 ft/s

• 𝐷 =8𝑚𝑔

𝜋𝜌𝐶𝐷𝑣2

– D = diameter of parachute, ft.

– m = mass of vehicle, lbm

– g = force of gravity, ft/s2

– 𝝆 = density of the air, lbm/ft3

– CD = Coefficient of Drag

– v = previously calculated velocity, ft/s

• Minimum Diameter must be 93.3 inches

Recovery System Calculations


USLI PDR23

• The load in 1, 2, and 3 are causing tension under Drogue and Main. Shock cord applies load to eyebolt in the coupler bulkhead.

• The load in 4 is transferred through the all thread and down to the motor casing then back up the tube.

represents force due to drag

represents the force due to mass

Load Path (Drogue and Main)


USLI PDR24

1

2

3

4

AFT SUBSYSTEM


USLI PDR2511/3/2017

• Objectives/Responsibilities

– Fin Design

▪ Optimize dimensions and materials for flight stability

– Centering Ring/Thrust Plate

▪ Carry load path from the vehicle

▪ Centering and fin integration ability

– Forward/Recovery Retention

▪ Provide method for recovery attachment

▪ Carry thrust through the vehicle via forward retention

Aft SystemObjectives


USLI PDR26

• Design Overview

– Through the wall design/slotted body tube

▪ Slots allow for fin mounting integration

– G10 Fiberglass fins attached with seven 4-40 bolts per fin

▪ Fins will be mounted to centering ring

– 3-D printed centering ring/fin mounting bracket

▪ Can be removed from body tube for repair/inspection

– Aluminum Forward/Recovery retention bulkhead

▪ Uses U bolt for recovery system

▪ Motor case tapped to allow for forward retention

Aft System Components


USLI PDR27

Fin Can/Centering Ring

Motor/Motor CasingThrust Ring

Trapezoidal Fin(s) (4)

Forward/Recovery Retention Bulkhead

Secondary Centering Ring

Motor Selection


USLI PDR28

Aerotech L1520R-P Specifications

Motor Designation L1520T-P

Apogee 5,282 ft.

Stability 2.0 cal.

Ballast 51 in.

Diameter 75 mm. (3 in.)

Length 25.7 in.

Propellant Mass 8.0 lbm

Total Impulse 835 lbf.-s

Max Acceleration 289 ft./s2

Velocity off the Rail 55.7 ft./s

Burn Time 2.5 sec

• Other motors considered:– L1150

▪ Too little total impulse– L850

▪ Too slow off the rail– L1390

▪ Too much total impulse

Motor Retention

• Forward Retention Bulkhead

– Screwed onto top of motor

– Recovery retention is fixed on U-bolt

– 3.9 in. diameter

– 0.5 in. thick Aluminum

– Fixed to body tube with four ¼-20 screws


USLI PDR2911/3/2017

• Requirements fulfilled by part: motor centering, fin mounting, thrust takeout from motor

• Material: 3D printed high strength ABS plastic

• Location: inserted in the bottom of the aft body tube

Fin Can


USLI PDR 30

Fin Can

Fin Can Dimensions


USLI PDR31

• Purpose: align motor as it is inserted into the rocket• Bolted to the aft body tube using 4-40 bolts• Material: Polycarbonate

Secondary Centering Ring


USLI PDR32

• Trapezoidal Fin Design– Allows more freedom in fin design

– Adjust fin shape to shift CP

• Fin Dimensions– 8 in base

– 3.5 in height with extended base for body tube insertion

– Seven holes allow integrated mounting to centering ring located inside body tube

– Rounded leading edge

• Fin Material– G10 Fiberglass

– Will be fabricated/designed in house

• Fin Mounting– Fins mounted through the body tube to centering ring

– Replaceable upon breakage/damage

• Flutter speed– Calculated to be 1444.76 mph (Mach 1.88)

Fin Design


USLI PDR33

• Fins made out of G-10 fiberglass

• This material was chosen for its high strength to weight ratio

• Tensile Strength:– Crosswise: 38 ksi– Lengthwise: 45 ksi

• Flexural Strength:– Crosswise: 65 ksi– Lengthwise: 75 ksi

Fin Material


USLI PDR34

• Flexural Modulus:

– Crosswise: 2400 ksi

– Lengthwise: 2700 ksi

• Compressive Strength: 65 ksi

• Its density is 0.065 lbm/in^3.

Fin Retention

• Each fin mounted with seven 4-40 bolts; normal to fin face

• Four sets of ten 4-40 bolts normal to body tube surface used to maintain body tube shape under motor thrust


USLI PDR3511/3/2017

• Approximately half-scale – 4 in. body → 2.125 in. body– 6 in. fairing → 3 in. fairing– Mach 0.56 → 0.49

Subscale Rocket


USLI PDR36

Subscale Rocket

Full-Scale Rocket

– 3 in. motor → 1.5 in. motor

– 96 in. length→ 49 in. length

– 9.0 G → 15.2 G

3.0 in

6.0 in

PAYLOAD DESIGN


USLI PDR3711/3/2017

• Objective: Design an autonomous rover that will deploy from the interior of the rocket, move a minimum of 5 ft. away from the rocket, and deploy solar panels

• The rover’s design consists of a rectangular chassis, two expandable wheels, and a stabilizing arm

• The rover measures temperature, pressure, location, and transmits this data with images to a ground station

Payload Summary


USLI PDR38

Rover Assembly


USLI PDR39

• The tail will be wrapped around the chassis while inside the fairing.• Rover will be kept collapsed passively by the fairing.• The collapsed diameter is 5.7 in with 0.15 in of clearance.

Rover Assembly


USLI PDR40

• Rover wheels will expand to 14.24 in. diameter when deployed

• Wheels rotate independently. Allows for steering via differential

• Lid will slide open via linear gear driven by a DC motor

• Solar panel will increase its effective area from 0 to 100%

• Solar panel will charge battery for distance extension

• Aluminum Unibody selected– Highest strength to weight design– Resistant to drastic changes in temperature– Least deflection under load protects motors and electronics

• 3D Printed ABS Unibody is secondary selection– Will be used if aluminum unibody is too difficult to manufacture

Rover Chassis Trade Study


USLI PDR41

Aluminum Unibody3D Printed ABS

Unibody

Aluminum Base/3D

Printed ABS Walls

Ease of Manufacturing 2 5 4

Strength to Weight 5 2 3

Environmental

Protection5 2 1

Total Score 12 9 8

• The chassis will be milled out of a single block of 6061-T6 aluminum• The chassis will house all electronics• The drive motors will be mounted directly to the sidewalls• The tail will be mounted to the bottom of the chassis

Rover Chassis Design


USLI PDR42

• The chassis can sustain a 30G (210 lbf) load to the sidewall, simulating a load from the wheel during adverse deployment conditions (left)

• The chassis can sustain a 30G (210 lbf) load to the base, simulating loading from inside the rocket upon landing (right)

Rover Chassis Stress Analysis


USLI PDR43

• Measuring Tape selected– Ease of manufacturing– Results in a longer tail and moment arm

• Sideways Hinged Aluminum is secondary selection– Will be used if measuring tape fails integration and deployment

tests

Rover Tail Trade Study


USLI PDR44

18 inch

Measuring

Tape (Wrapped

around)

11 inch

Sideways

Hinged

Aluminum Tail

Ease of

Manufacturing5 2

Strength 3 5

Tail Length 5 3

Total Score 13 10

Wheel Rotation

Counter moment from tail

• Main Goals for design: Expanding wheels– 6 in. diameter constraint while inside rocket

– > 6 in. diameter desired for handing terrain

• Chosen Design: Umbrella wheel– Desired for handling terrain

– All designs similarly decent in other categories

Trade Study: Wheel Design


USLI PDR45

Telescoping

WheelsFoam Umbrella wheel

Cost 3 4 3

Design Complexity 2 4 3

Low Risk of Damage 4 5 4

Terrain Effectiveness 4 1 5

Total 13 14 15

• Main Considerations:– Pushing wheels out of rocket without taking damage

– Ease of manufacturing wheel shapes

• Chosen Material: Aluminum– Highest strength while maintaining low weight

– Easiest to manufacture wheels

Trade Study: Wheel Material


USLI PDR46

Aluminum ABS Polycarbonate

Cost 4 3 3

Design Complexity 5 4 4

Weight 3 5 4

Strength of Material 5 3 4

Total 17 15 15

• Current Chosen Design: Umbrella Wheel – 0.703 lbm– 5.7 in. diameter wheel expands to 14 in.

diameter wheel

– Linear extension spring for compression and expansion

– Keeps compressed while in rocket, expands naturally once out

– Spring located on the exterior, pulls in to bring spoke vertical

– Rod used for assembly of main wheel to spokes

Wheel Design


USLI PDR47

• Made of Aluminum 6061 – T6

• Eight notches for eight spokes, holes for attaching spokes with rod

Wheel DesignMain Wheel


USLI PDR48

• 6061 – T6 Aluminum

• 0.75 in. extrusion for grip with expanded wheel

• Circular piece for attaching to wheel base

Wheel DesignSpoke


USLI PDR49

• 6061 – T6 Aluminum

• Attaches to wheel base

Wheel DesignMotor Mount


USLI PDR50

• Can withstand 120 lbf before yielding

• Load: Pushed out by piston, no more than few pounds

• Will likely be more distributed to entire wheel base

Main Wheel


USLI PDR51

• Can withstand 35 lbf before yielding to 40 ksi

• Max Stress – 15 ksi– Full weight of rover and motor torque

Spoke


USLI PDR52

• Can withstand 900 lbf before yielding

• Load: Pushed out by piston, absorbed by other parts

• Max load by piston no more than a few pounds

Motor Mount


USLI PDR53

• Sliding solar panel lid utilizing remote servo gear

• Solar panels will remain static

• Solar panels recharge battery

Solar Deployment


USLI PDR54

Gear System Hinge

Simplicity 3 4

Functionality 5 3

Weight 2 2

Cost 1 1

Total Score 11 10

• Two different designs considered for solar panel deployment mechanism

Gear system lid Hinged lid

• Lid with gear system was selected– Hinge mechanism would be harder to

close once opened– Gear system would be easier to bring the

cover back over the solar panels

Rover Mass Budget

• The mass of all components totaled 6.4 lbm.

• A 10% Margin was added to the total weight to account for fasteners, adhesives, and design changes


USLI PDR5511/3/2017

Component Mass (lbm)

Chassis 2.5

Wheel Assembly 1.4

Lid/Solar Deployment 1.0

Tail 0.1

Electronics 1.4

10% Margin 0.6

Total 7.0

Li-Ion 18650 CR123A SurefireEnergizer Recharge Power

Plus

Power 4 3 4

Capacity 5 4 4

Weight 4 3 2

Safety 3 5 5

Reusability 5 5 5

Power Density 5 3 2

Total 26 23 22

Battery Trade Study


USLI PDR56

• Three different batteries considered– 3x Li-Ion 18650 in series– 4x CR123a Surefire in series– 8x Energizer Recharge Power in series

• Trade studies conducted by rating each battery’s benefits on a scale of 1 – 5 • Li-Ion 18650 was selected based on criteria

MCU Trade Study


USLI PDR57

Arduino Mega Arduino Uno PCB with ATMega 2560

Beaglebone Raspberry Pi 3

Clock Speed 3 3 3 5 5

I/O Pins 5 3 5 3 4

Operating Voltage

4 3 4 2 4

Power Draw 4 4 4 3 1

Complexity 4 4 2 5 2

Volume 3 4 3 4 3

Mass 4 5 4 4 3

Cost 4 4 2 2 4

Total 31 30 28 28 28

Component Selection


USLI PDR58

Component Selection Features

MCU Arduino Mega• (7 – 12) Vin

• I2C, SPI, UART, GPIO• 16 MHz

IMUAdafruit LSM9DS0

• Accelerometer • Gyroscope

• Magnetometer • 3 Axis• I2C, SPI

Temperature and Pressure Sensor

Adafruit BMP280• Press range: (300 – 1100) hPa• Temp range: (-40 – 85) °C

• SPI, I2C• 0.8" x 0.7" x 0.1"

MotorCytron DC Geared Motor

SPG30-300K

• 12 V • At load 410 mA

• Stall torque 1.18 Nm • Mass: 160 g • Brushed

Selection cont.


USLI PDR59

Component Selection Features

Solar Cell OSEPP Monocrystalline Solar Cell• 100mA• 5 V• 4” x 3” x 0.2”

GPS Adafruit MTK3339

• 5V• 20 mA• 10 Hz updates• -165 dBm sensitivity

Radio X-Bee PRO

• 28 mile range (with high gain antenna)• 900 MHz• Data rate 200 kbps• UART, SPI

Lid Motor NMB Technologies PPN7PA12C1• 5V DC• Brushed• 0.022 lbm

DC/DC converter LM3671 Buck Converter• 3.3 V output• 600mA draw• 0.6" x 0.4" x 0.1"

Camera ArduCam CMOS OV7670• 640×480 VGA• 3.3V supply needed

ComponentCurrent

(mA)

Voltage

(V) Time (hr)

Duty

Cycle (%)

Efficiency

(%)

Necessary Capacity

(mAhr)

Arduino Mega 50.0 5.00 1.00 100 100 22.5

Pressure/

Temp1.12 5.00 0.25 100 100 0.13

IMU 6.10 5.00 1.00 100 100 2.75

Wheel Motors 820 11.1 0.17 100 100 136

Lid Motors 96.0 5.00 0.01 100 100 0.43

Radio 210 3.30 1.00 100 80.0 78.0

Camera 20.0 3.30 0.25 100 80.0 1.86

GPS 20.0 5.00 0.25 100 100 2.25

Voltage

Regulator600 5.00 1.00 100 100 270

Power Budget


USLI PDR60

Required battery capacity = 𝐼 𝑚𝐴 ∗𝑉 𝑉 ∗𝐷𝐶 ∗𝑇𝑖𝑚𝑒 ℎ𝑟

𝐸𝑓𝑓𝑖𝑐𝑖𝑒𝑛𝑐𝑦 ∗11.1 𝑉

Required Capacity

(mAhr)

Available Capacity

(mAhr)Safety Factor

514 2600 5.06


USLI PDR61

Component Block Diagram

Payload Software Flow Diagram


USLI PDR62

Remove RBF; Payload detects

launch via acceleration

Takes acceleration data throughout flight, calculates

changes

Once acceleration is zero for several

iterations, waits for deployment signal from ground station

Rover transmits acknowledgement,

waits for confirmation signal

Receives confirmation signal; Delays 30 seconds

Supplies power to motor, begins taking

temperature, pressure, and IMU

data

Get position data via GPS and

accelerometer; Sample 2 times per

second

Transmit data back to ground station, save on board to

eeprom

If position change by a certain margin,

back up, turn motor, begin moving again

Once distance traveled, deploy solar panels, end

data collection

Measure battery voltage

Transmit data back to ground station, save on board to

eeprom

REQUIREMENTS COMPLIANCE


USLI PDR6311/3/2017

Requirements Compliance Plan


USLI PDR6411/3/2017

• Demonstration– System verification through repeatable

exhibition of the design feature

– Pre-determined pass/fail criteria

– Parachute deployment, repeat flight tests, capability to launch within an hour

• Testing– Demonstration of system with known

input and output values

– Numerical data feedback as well as demonstrative verification

– Static motor fire, flight test with altimeters, recovery location tracking

• Inspection– Nondestructive/passive examination of

the system

– No numerical data collected

– Design components present, use of checklists, follow safety guidelines

• Analysis– Calculation of performance prior to any

physical testing

– Completely theoretical based on expected performance

– Simulation software, FEA, hand calculations, CAD

• All requirements, both USLI and derived, will be complied with, and verified using the following methods

• The requirements may be found in the PDR Document

• Test launches will only occur at NAR or TRA sponsored launch events.

• Only the mentor is allowed to handle rocket motors

• The rocket will use an L motors and will not exceed the impulse limit set by NASA

NAR and FAA Compliance


USLI PDR65

Launch Vehicle Verification


USLI PDR66

Recovery Ejection

Coupler Strength

Motor Thrust/ Load Path

Simulation/ Aerodynamics

Overall System Performance

Will the parachutes

eject properly with the planned

explosives?

Will the rocket

buckle at the coupler under max.

thrust?

Is the load path sufficiently

strong/how does the motor behave

when fired?

Is the simulation accurate/is the rocket stable?

Does the rocket reach the expected altitude/does

every component

work properly?

Multipleground

ejections of each

component

Apply calculated moment to

coupler

Static fire of the motor, measuring thrust through the high-risk loadpath

components

Launch a subscale version

of the rocket multiple times

Launch the full-scale (final) rocket multiple

times

General Requirements Compliance

• Most of the General Requirements are fulfilled through inspection of the schedule and design documents

• The TRA Mentor’s (Jason Winningham) credentials have been confirmed

• Outreach will be demonstrated through the Outreach Reports

• The team will demonstrate the ability to teleconference during the review

• Rocket rail launch capability, reusability, and readiness will be demonstrated at the test flight


USLI PDR6711/3/2017

SAFETY


USLI PDR6811/3/2017

• Training and Communications are key– Weekly Safety Briefings on relevant current activities

– Create Hazard analysis and Standard operating procedures

• Team work and proper supervision are how risks and hazards can be minimized– No team member shall work alone when manufacturing and testing the

rocket and its components.

– CRW members double and triple check each other’s work to ensure that all steps of manuals and standard procedures are followed

– Supervision from experienced mentors and staff ensures all procedures are done correctly.

CRW Safety Commitment


USLI PDR69

• Rocket motors, e-match, igniters are purchased by the mentor or appropriate PRC staff with the proper license to ensure legality and compliance.

• Motors will be stored in Type 2 Magazine and transported in Type 3 magazines.

ATF, DOT, and NPFA Compliance


USLI PDR70

• Hold weekly Safety Briefings with the entire CRW team

• Each sub-team will designate a Safety Representative to work with the

• Safety Officer

– Aid in Hazard and failure mode analysis for their respective sub-section of the rocket

• A Component Description Sheet will be created for each component used in the rocket

– Analyze failure modes

– Track evolution of the component to aid in verification process

• CRW has identified the required success criteria and a method of verification for each (as outlined in the PDR report)

• A Test Plan has been created based on the verification of all identified success criteria (as outlined in the PDR report)

Safety Plan


USLI PDR71

Safety Representatives


USLI PDR72

Bao H.

Safety Officer

Davis H.Launch

Vehicle Lead

Andrew W.

Payload Lead

• The Safety Officer will be responsible for the overall safety outlined by the SLI Handbook

• The Launch Vehicle lead and the Payload lead will be responsible for the reliability and risk assessment of their systems.

Safety Briefings and Trainings

Training Activity Date

Red Cross First Aid CPR/AED/FA 10/13/2017

Basic Emergency Procedures 10/17/2017

Process Hazard Analysis 10/18/2017

Safe Testing Procedures 10/24/2017

Root-Cause Analysis 10/24/2017

Outreach Safety Procedures 11/7/2017

Sub-scale Launch Safety Procedures

11/14/2017

Hazardous Material Handling/Disposal

11/21/2017

Fire Extinguisher training 11/21/2017

TBD TBD

• The Red Team have completed training for First Aid and CPR/AED

• Additional training content will be added based on relevance to the stages in the development cycle.


USLI PDR7311/3/2017

Launch and Assembly Procedures

• The Test Plan and Verification Processes will be used to optimize the final design, assembly, and launch procedures

• Final rocket assembly procedures have been developed to fit the design concept

• Any changes to the design that require updating the assembly or launch procedures will be coordinated through the team safety officer

• Simulated runs of all procedures will take place at least one week prior to any launch


USLI PDR7411/3/2017

• For the convenience of all team members, the following items will be located on the CRW team website:– Material Safety Data Sheets

– Operators Manuals

– CRW Safety Regulations

– Safety Briefing slides

– Standard Operating Procedures

• The Safety Officer will work to keep this information relevant and up to date

Published Information


USLI PDR75

PROGRAM MANAGEMENT


USLI PDR7611/3/2017

CRW

Management

• Website Updates

• Outreach Coordination

• Schedule and budget tracking

• Requirements Verification

• Interface management

Safety

• Risk Identification and Analysis

• Mitigation Strategy Development

• Safety Briefing

• Manufacturing and Testing supervision

Launch Vehicle

• Aft

• Motor Selection

• Fins

• Lower Body Tube

• Simulation

• Central

• Avionics

• Recovery

• Forward

• Upper Body Tube

• Nosecone

• Payload Fairing

Payload

• Mechanical Structure

• Wheel Design

• Chassis Design

• Vehicle fabrication

• Electrical Design

• Component Selection

• Schematic Development

• Software

• Rover software

• Ground Station

Work Breakdown Structure


USLI PDR77

• Schedule Philosophy– Work around finals and Winter Break

– Internal deadlines 2 weeks ahead of NASA deadline for all documents

– Identify backup dates for critical test launches

• Upcoming Events– Launch Opportunities: Nov 18, Dec 16, Jan 20, Feb

17

– CDR Internal due date: Dec 22

Schedule


USLI PDR78

Budget/Funding Summary

• Launch vehicle- two subscales (6 flights) and two full scales (6 flights) - $5,760

• Payload- two fully operation rovers -$1,010

• $750 margin for shipping/unexpected expenses

• Proposed to ASGC and UAH Propulsion Research Center for funding and

Rover Frame4% Rover

Electronics11%

Airframe13%

Motors50%

Recovery22%

Rover Frame Rover Electronics Airframe Motors Recovery


USLI PDR

• Girls Science and Engineering Day

– Before project started, but good practice

– 80 middle school girls participated

• FIRST Robotics

• Boy Scout STEM Winter Camp

– Invited to teach space, robotics, and maker culture

• Science Olympiad at UAH, February 2018

Outreach


USLI PDR80

Web Presence

• Website updated and reformatted to highlight current content while preserving 2017 team documents

• Facebook and Instagram kept current

• Press release posted

• www.chargerrocketworks.com


USLI PDR8111/3/2017

http://www.chargerrocketworks.com/

Questions


USLI PDR82


USLI PDR83

• NASA USLI

• https://www.nasa.gov/audience/forstudents/studentlaunch/handbook/index.html

• Wikipedia

• https://upload.wikimedia.org/wikipedia/commons/d/dc/PIA16239_High-Resolution_Self-

Portrait_by_Curiosity_Rover_Arm_Camera.jpg

• NASA

• https://www.nasa.gov/sites/default/files/images/640942main_orion_chute_full.jpg

• Thrustcurve.org

• http://www.thrustcurve.org/simfilesearch.jsp?id=1898

• Wonderfulengineering.com

• http://cdn.wonderfulengineering.com/wp-content/uploads/2015/03/NASA-Tests-Mars-Rocket-Booster-6.jpg

• Professionalgrantwriter.org

• https://www.professionalgrantwriter.org/wp-content/uploads/2016/03/shutterstock_127266677.jpg

• National Association of Rocketry

• http://www.nar.org/wp-content/uploads/2014/05/Logo.gif

• Youtube

• https://i.ytimg.com/vi/i3T9Hps3iqs/maxresdefault.jpg

• Emotionalhealth.net

• http://emotionalhealth.net.au/wp-content/uploads/2013/05/question-marks.jpg

Picture Credits

https://www.nasa.gov/audience/forstudents/studentlaunch/handbook/index.html

https://upload.wikimedia.org/wikipedia/commons/d/dc/PIA16239_High-Resolution_Self-Portrait_by_Curiosity_Rover_Arm_Camera.jpg

https://www.nasa.gov/sites/default/files/images/640942main_orion_chute_full.jpg

http://www.thrustcurve.org/simfilesearch.jsp?id=1898

http://cdn.wonderfulengineering.com/wp-content/uploads/2015/03/NASA-Tests-Mars-Rocket-Booster-6.jpg

https://www.professionalgrantwriter.org/wp-content/uploads/2016/03/shutterstock_127266677.jpg

http://www.nar.org/wp-content/uploads/2014/05/Logo.gif

https://i.ytimg.com/vi/i3T9Hps3iqs/maxresdefault.jpg

http://emotionalhealth.net.au/wp-content/uploads/2013/05/question-marks.jpg

Component Mass (g) Number per rover Total Mass (g) Total Mass (lbm)

Arduino Mega 37.0 1 37.0 0.08

BMP280 1.30 1 1.30 0.00

SPG30 geared

motor160 2 320 0.71

Motor Shield 30.0 1 30.0 0.07

LSM9DS0 2.30 1 2.30 0.01

Solar cell 8.50 3 25.5 0.06

Camera 10.0 1 22.5 0.05

900 MHz Xbee 8.50 1 6.50 0.01

Brushed DC motor 9.98 2 20.0 0.04

Battery 150 1 150 0.33

GPS 8.50 1 8.50 0.02

Voltage regulator 0.90 1 0.90 0.00

Total mass - - 625 1.38

Appendix A:Electronics Mass Budget


USLI PDR84

nasa sl preliminary design review - wordpress.comrecovery avionics subsystem • 2 perfectflite...

Documents