University of Hawaii: Community Colleges Team Team Overview 3 - - PowerPoint PPT Presentation

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University of Hawaii: Community Colleges Team Team Overview 3 - - PowerPoint PPT Presentation

Dec 18, 2022 45 likes •778 views

University of Hawaii: Community Colleges Team Team Overview 3 Changes Since PDR 4 Vehicle Design 5 Payload Design 32 Safety 46 Testing 49 Project Plan 58 High Power Rocketry Certifications Dr. Jacob Hudson Jr. (Team Mentor) -

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University of Hawai’i: Community Colleges Team

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Team Overview 3 Changes Since PDR 4 Vehicle Design 5 Payload Design 32 Safety 46 Testing 49 Project Plan 58

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High Power Rocketry Certifications

  • Dr. Jacob Hudson Jr.

(Team Mentor) - Level 3 Katherine Bronston (Team Lead) - Level 2 Matthew Nakamura (Vehicle Engineer) - Level 2 Lauren Grzegorczyk (Vehicle Engineer) - Level 1

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  • Tracker

○ GPS ○ Microcontroller

  • Retention and Ejection Design Changes

○ URLSS

  • Deployment Trigger

○ Current ○ Shields

  • Rover Design Changes

○ Sensor ○ Motor ○ Microcontroller

  • SSRS

○ Umbrella Design

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Length 116 inches Weight/Mass 32.2 lbs/1 slug Motor Selection Aerotech K1050W Number of Sections 2 Target Altitude 4700 feet AGL Main Chute Deployment 500 feet AGL

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Main Chute 12’ Rocketman Payload Chute - 5’ Rocketman Drogue Chute - 3’ Rocketman

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Determination of Center of Pressure Determination of Center of Gravity

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CP 96.3’’ below the nosecone CG 68.4’’ below the nosecone CG and CP are 27.9’’ apart

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Descent Time: 96 s

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Wind Velocity (ft/sec) Wind Velocity (mph) Doptimistic (ft) Dpessimistic (ft) 7.33 5 561.2 701.8 14.6 10 1117.8 1397.2 22 15 1684.3 2105.4 29.3 20 2343.2 2804

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Wind Speed (ft/sec) Simulated Drift (ft) 3.00-7.33 214 7.34-14.66 1010 14.67-22.00 1263 22.01-29.33 2323

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q CD

  • Est. Altitude

+/- 0o 0.89 4109.3’ 20.3’ 5o 0.89 4110.0’ 20.2’ 10o 0.92 4067.8’ 20.1’ 15o 0.97 3997.8’ 20.0’ 20o 1.07 3865.7’ 19.7’ 25o 1.12 3804.2’ 19.5’ 30o 1.18 3735.7’ 19.3’

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  • Scaling Factor 1:4
  • Jolly Logic Altimeter 3
  • Motor: B6-4
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Altitude above sea-level: 90 m Relative humidity: 50% Temperature: 80 F Latitude: 21 Wind: 8-14 mph Variability: Some (0.04) Weather: Partly Cloudy

VDA Deployment Angle

0° 11° 45° 90° Failure Mode (0°/90°)

Apogee Height (ft)

182 205 179 142 145

Flight Conditions Recorded Altitude

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Linear Actuator: PQ12-R

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Soil Collector: Umbrella Design

Soil Collector Closed Soil Collector Open

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TABLE 5.4 SUMMARY OF HAZARDS PRE-MITIGATION Probability Severity 1 Catastrophic 2 Critical 3 Marginal 4 Negligible A - Frequent B - Probable 1 1 C - Occasional 8 4 4 1 D - Remote 14 11 4 E - Improbable

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TABLE 5.5 SUMMARY OF HAZARDS POST-MITIGATION Probability Severity 1 Catastrophic 2 Critical 3 Marginal 4 Negligible A - Frequent B - Probable C - Occasional D - Remote 1 E - Improbable 18 14 9 6

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Name Description Requirement Verified Status VEHICLE 1 - Subscale Testing

  • Test. The subscale model will be flown with

different angles of the VDA to test the predicted correlation between the deployment angle and maximum altitude. 2.19 Compete VEHICLE 2 - Inverted-Y Harness Testing

  • Demonstration. To demonstrate

functionality of the inverted-Y harness, the subscale’s forward/payload section will be closely monitored during flight to ensure horizontal orientation during descent and landing. Recovery 1 Complete VEHICLE 3 - Drop Tests

  • Demonstration. To ensure the strength of

the shear pins, the rocket will be drop tested to ensure the nosecone does not prematurely separate. Safety Concerns Scheduled for January 24, 2019

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Name Description Requirement Verified Status VEHICLE 4 - Parachute Deployment Tests

  • Demonstration. To Demonstrate

functionality of the parachute deployment, the team will prepare the proper pyrotechnic charge and demonstrate that the sections separate and chute deploy while on the ground. 3.1 3.2 Scheduled for February 9, 2019 VEHICLE 5 - Avionics and Electronics Performance Tests

  • Demonstration. The Avionics and

Electronics will be turned on and ran on the ground to ensure the devices’ functionality. 2.11 3.11.2 Recovery 3 Complete VEHICLE 6 - Motor Retainer Stress Test

  • Demonstration. Motor retainer will

experience intense stress levels to ensure it is durable enough to withstand the launch day conditions. Safety Concerns Scheduled for January 26, 2019

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Name Description Requirement Verified Status RETENTION-1: Motor Test

  • Demonstration. Show that the motor is

able to be turned on when the signal to deploy is received by the XBee receiver. 4.3.2 Complete RETENTION-2: URL Test

  • Demonstration. Test full URL system and

ensure it will be able to deploy the rover. 4.3.2 In Progress RETENTION-3: URLSS Fit Test

  • Demonstration. Fit test of URL with URLSS. 4.3.2

In Progress RETENTION-4: Drop Test

  • Demonstration. Drop Retention and

Ejection Subsystem from a height of 19.7 cm. 4.3.2 In Progres

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Name Description Requirement Verified Status DEPLOYMENT-1: Current Test

  • Test. Determine optimal amount of

current for XBee Pro. 4.3.3 Complete. DEPLOYMENT-2: Obstruction Test

  • Demonstration. Ensure that the XBee

Pro is able to receive the deployment signal from within the payload tube. 4.3.3 In progress DEPLOYMENT-3: System Demonstration

  • Demonstration. Utilizing all intended

components for final design of nosecone, demonstrate that system works. 4.3.3 In progress

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Name Description Requirement Verified Status ROVER-1: Coding Movement

  • Demonstration. Arduino code governing basic

movement was tested on a pre-built rover. The code demonstrates the rover can move forward, turn left and turn right. 4.3.1, 4.3.4 Complete ROVER-2: Coding Detection

  • Test. Arduino code for ultrasonic sensors was
  • tested. The code demonstrates the sensors

can detect various types of obstacles from various distance 4.3.1, 4.3.4 In progress ROVER-3: Distance Determination

  • Test. The rover will record the distance it

traveled and angle it turned while it traverses a clear flat surface. 4.3.1, 4.3.4 In progress

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Name Description Requirement Verified Status ROVER-4: Terrain Traversal

  • Demonstration. The rover will demonstrate it

can drive over various types of soil and

  • terrain. It will record the distance it traveled

during movement. 4.3.1, 4.3.4 In progress ROVER-5: Obstacle Avoidance

  • Test. The rover will use its forward ultrasonic

sensor to detect obstacles in the way. It will turn to avoid the object. 4.3.1, 4.3.4 In progress ROVER-6: Outside Obstacle Avoidance

  • Demonstration. The rover will use its

sensors to navigate through obstacles. It will record the distance it travelled during the experiment. 4.3.1, 4.3.4 In progress ROVER-7: Subsystem Demonstration

  • Demonstration. The rover will use its

sensors to navigate at least 10 feet away from its starting position over an obstacle course. 4.3.1, 4.3.4 In progress

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Name Description Requirement Verified Status SOIL-1: Linear Actuator Motion

  • Test. Run arduino code and verify it’s

able to actuate to position specified. 4.3.5 Complete SOIL-2: Umbrella Collector

  • Demonstration. Verify collector

expands and contracts as intended. 4.3.5, 4.3.6 In progress SOIL-3: SSRS and Sample Size Verification

  • Demonstration. Demonstrate linear

actuator and umbrella collector work in unison to collect 10 mL of sample. 4.3.5, 4.3.6 In progress

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Name Description Status PF-1: Rover and Retention and Ejection Fit Test

  • Demonstration. Ensure rover is able to be mounted

securely to URL. This demonstration is scheduled for February 1, 2019. In progress PF-2: Tracker and Bulkhead Fit Test

  • Demonstration. Ensure tracker is able to fit through

hole for motor in bulkhead. This demonstration is scheduled for February 8, 2019. In progress PF-3: Motor and Bulkhead Fit Test

  • Demonstration. Ensure motor fits within bulkhead
  • hole. This demonstration is scheduled for February

8, 2019. In progress PF-4: URLSS and Payload Tube Fit Test

  • Demonstration. Ensure URLSS fits within Payload

Tube securely. This demonstration is scheduled for February 15, 2019. In progress VPDF: Vehicle and Payload Demonstration Flight

  • Demonstration. Ensure that the Launch Vehicle and

Payload perform as designed. Scheduled for February 17, 2019

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Vehicle Vendors

  • Hawk Mountain Enterprises
  • Altus Metrum
  • PerfectFlite
  • Rocketman Parachutes
  • Aerotech
  • Max Q Aerospace
  • Paracord Planet
  • City Mill

Payload Vendors

  • ServoCity
  • Adafruit
  • SparkFun
  • Actuonix
  • Arduino
  • Advanced Circuits
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General Requirements

  • Team organized into four teams
  • Roles assigned to specific students
  • Identified proper rail size: 12 foot 1515 rail
  • Team Mentor: Dr. Jacob Hudson
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Vehicle Requirements

  • Design meets SLP Requirements
  • Target Altitude: 4700 ft AGL
  • Motor Selection: Aerotech K1050W
  • Vehicle Testing

○ Subscale ○ Demonstration Flight

  • Pre-flight checklist

Recovery Requirements

  • Design meets SLP Requirements
  • Main Chute Deployment: 500 ft AGL
  • Descent Time: 95 seconds
  • Drift within 2500 ft recovery zone in

winds below 19 mph

  • Design protects Avionics section
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Safety Requirements

  • Safety Team identified

○ Safety Officer: Leomana Turalde

  • Hazards Analysis
  • Team Safety Code

○ Adherence to NAR and TRA Codes

  • Launch Procedures Checklist
  • 4 HPR certified members

Payload Requirements

  • Design meets SLP requirements
  • Rover Retention

○ URL & URLSS

  • Autonomously Deploy

○ Deployment Trigger

  • Rover Automation
  • Soil Collection

○ SSRS

  • Batteries clearly marked
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Name Requirement Description Vehicle 1 The launch vehicle must have detachable fins. Vehicle 2 The vehicle must fly on a motor with an average thrust of around 1100 N. Vehicle 3 The vehicle must contain a piston in the forward section. Vehicle 4 The bottom of the payload section must be clear of any obstructing materials. Vehicle 5 The forward section must be above 40 inches in length.

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Name Requirement Description Recovery 1 The nosecone/payload section must land with the nosecone tip parallel to the ground. Recovery 2 All parachutes utilized by the launch vehicle must be of standard sizes. Recovery 3 The launch vehicle must contain two active tracking devices. Recovery 4 The recovery system electronics must function at a frequency that does not require any licensing.

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Name Requirement Description Payload 1 The maximum weight of the payload cannot exceed 6.6 lbs. Payload 2 The payload section and its contents will be required to endure 6Gs during take-off and 10Gs during deployment of the recovery system. Payload 3 The combined dimensions of the rover and soil sample recovery system maximum size cannot exceed a height of 3.6”, a width of 3.6”, and a length of 8.0”. Payload 4 The batteries to be used must be lithium ion. Payload 5 The microcontrollers for deployment and the rover must be motor shield compatible.

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Students Reached: 201

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Future Events

Date Event Location Expected Participants Total Participants (incl. 201 as of Dec. 1) TBA Girl Scouts HI Fundraiser ~50 251 2/1/2018 Center for Aerospace Education (CAE) 20 271 2/5/2018 CAE 24 295 2/8/2018 CAE 11 306 2/15/2018 CAE 14 320

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Any questions?