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Critical Design Review Heavens Bound Halibut (HBH) February 8, 2012 1.

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Presentation on theme: "Critical Design Review Heavens Bound Halibut (HBH) February 8, 2012 1."— Presentation transcript:

1 Critical Design Review Heavens Bound Halibut (HBH) February 8,

2 Changes Made Since PDR Changes made to vehicle criteria: – Rocket is 133 inches – The main parachute and drogue parachute have switched places. – Payload is located in the nose cone. – Rocket separates into four pieces – Fuselage weighs lbs – ACDS separated from parachute deployment – ACDS controller switched to BeagleBone Changes made to payload criteria: – None Changes made to activity plan: – None 2

3 Budget 3 DescriptionCostNumberSub CostRunning Tally Fiberglass Nosecone, 24/6$ Bluetube Body 6", length 48"$66.953$200.85$ Blue Tube 54mm$ $ Thrust Ring Retainer, 54mm$ $ /2" 9-Ply Birch Centering Rings, 54mm$8.673$26.01$ /2" 9-Ply Birch Bulkhead Plates$6.344$25.36$ ft. Rocketman Main Parachute$ $ ft. Rocketman Drogue Parachute$ $ L2200G-P reload kit (propellant)$ $1, RMS-75/5120 reload casing$ $1, Carbon fiber kits$ $1, Stratologger$69.994$279.96$1, GPS Tracker$ $2, linear actuator$ $2, processor$ $2, air speed sensor$ $2, analog device IMU sensor$ $3, siren$ $3, rocket beeper$ $3, XL Variable-Capacity Ejection Canister$9.993$29.97$3,837.90

4 Timeline 4 February 1 st -30 th : Component testing February 3 rd -28 th : Rocket Assembly February 14 th – March 26 th : Full Scale Launch February 14 th – March 24 th : Parachute Tests March 26 th : Deliver FRR on Website

5 Vehicle Dimensions 5 Electronics and ACDS Payload Vehicle Properties Diameter (in) 6 Length (in)133 Gross Liftoff Weight (lb) Launch Rail Size (in) 1.0 Motor Retention thrust ring

6 Fins 6

7 CP and CG analysis 7  The center of pressure (CP) is located inches from the nose cone.  The center of gravity (CG) is located inches from the nose cone.  The stability margin has increased to Total Mass (Lbs)54.64 Nose Cone0.22 Payload1.5 Parachute Bays4.34 Main Parachute8.14 Drogue Parachute5.57 ACDS Tube17.25 Motor Tube17.62

8 Flight Simulations 8

9 Scale Model Results 9

10 10 High Risks Low Risks Moderate Risks Consequence Categories Risk Type 1 Very Low 2 Low 3 Moderate 4 High 5 Very High Technical No impact to full mission success criteria Minor impact to full mission success criteria Moderate impact to full mission success criteria. Minimum mission success criteria is achievable with margin Major impact to full mission success criteria. Minimum mission success criteria is achievable Minimum mission success criteria is not achievable Schedule Negligible or no schedule impact Minor impact to schedule milestones; accommodates within reserves; no impact to critical path Impact to schedule milestones; accommodates within reserves; moderate impact to critical path Major impact to schedule milestones; major impact to critical path Cannot meet schedule and program milestones Cost <2% increase over allocated and negligible impact on reserve Between 2% and 5% increase over allocated and can handle with reserve Between 5% and 7% increase over allocated and can not handle with reserve Between 7% and 10% increase over allocated, and/or exceeds proper reserves >10% increase over allocated, and/or can’t handle with reserves TechnicalSchedule Likelihood Categories 5 Very High No understanding of design or no experience implementing similar designs. No one is working on the subsystem 4 High Little understanding of design or little experience implementing similar designs Only one student working on this who will graduate before it is expected to be done. 3 Moderate Some understanding of design or some experience implementing similar designs Only one student working on this who has many classes this semester. 2 Low Great understanding of design or good experience implementing similar designs There are two (or more students working in this 1 Very Low Previously implemented design or extensive experience implementing similar designs Subsystem almost done and a clear path to finalization is determined FROSTE System Risk Matrix

11 FROSTE System: Risk Analysis Approach M – Mitigate W – Watch A – Accept R – Research Criticality High Med Low L x C Trend  Decreasing (Improving)  Increasing (Worsening)  Unchanged * New since last month TrendRankAppRisk Title  1M Development Delays  2M Motor Shipping Issues  3M Funding  4AMaterial Acquisition  5WFacilities Schedule Conflicts  6WStudent Schedule Conflicts  7RFAA Waiver Issues 2 LIKELIHOODLIKELIHOOD CONSEQUENCES

12 Component testing The testing will be done in house Blue tube and carbon fiber are the primary materials The materials will have four tests: compression, tensile, torsion, and bending. The ACDS linkages will be compressed to find point of highest strength vs. weight 12

13 Physical Payload Integration 13 Payload is in P-POD shell Slides into nose cone Secured by 8 quarter inch bolts

14 Payload 14 The Alaska Research CubeSat (ARC)

15 ARC Mission Objectives 15 Education Mission Objective 1 (EMO1): Provide an authentic, interdisciplinary, hands-on student experiences in science and engineering through the design, development, operation of a student small satellite mission. Science Mission Objective 1 (SMO1): Characterize thermal and vibration environment inside the launch vehicle from ignition to orbit insertion. Science Mission Objective 2 (SMO2): Validate a novel low power Attitude Control and Determination Systems (ACDS). Science Mission Objective 3 (SMO3): Validate a high bandwidth communication system by obtaining images of changing snow/ice coverage in arctic regions.

16 16 ARC Launch Environment Data Logger (LEDL): Risk Analysis Approach M – Mitigate W – Watch A – Accept R – Research Criticality High Med Low L x C Trend  Decreasing (Improving)  Increasing (Worsening)  Unchanged * New since last month LIKELIHOODLIKELIHOOD CONSEQUENCES TrendRankAppRisk Title  1RLaunch Detect  2WSoftware / testing  3AMemory  4M / RSensor Header Failure

17 Deployment Charges and Shear Pins The modules are held together by 2-56 nylon shear pins, each having a shearing force of 25 pounds. Each module will be held in place by 4 shear pins, totaling 100lb of force needed for separation. To separate the modules, 4F black powder will be used. 17

18 Parachute System Dual Deployment Method Main Parachute switched with Drogue Drogue has 5’ diameter Main has 20’ diameter Terminal Velocity: 68.3 ft/s Impact velocity: 16.7 ft/s Max impact energy 74.7 ft-lb 18

19 Parachute Performance 19

20 Parachute: Risk Analysis Approach M – Mitigate W – Watch A – Accept R – Research Criticality High Med Low L x C Trend  Decreasing (Improving)  Increasing (Worsening)  Unchanged * New since last month TrendRankAppRisk Title  1R/MParachute folding technique  2M Air Brake interference with parachute deployment  3MBulkhead attachment strength  4A Altimeter failure  5M Deployment accelerations on rocket body LIKELIHOODLIKELIHOOD CONSEQUENCES 3 5 1

21 AirBrake Linkage Four-Bar-Linkage – Flap – Link – Slider – Rocket (ground linkage) 3 six inch long flaps One link per flap

22 AirBrake Linkage 1.Linear actuator drives slider down guide shaft 2.Links are forced out of rocket body 3.Flaps open up

23 Linkage Dimensions AirBrake compartment length is 15in Flaps are 6in long Connecting links are 6.52in long Slider sleeve length is 6.125in Guide shaft length is 3.5in Slider displacement is 2.35in which allows flaps to open 56 degrees

24 ACDS: Electrical Diagram 24

25 ACDS Control 25 ACDS uses a proportional navigation algorithm in conjunction with a PID controller. ACDS controller determines the altitude and orientation of the rocket by filtering and combining sensor data with an Unscented Kalman filter. SensorManufacturerModelRange -Range +Accuracy +-Drift +- AccelerometerBoschBMA18016 g512 LSB/g +-3.0%0.01 %/K GyroscopeSTMicroelectronicsL3G4200D2000 dps70 mdps/digit0.04 dps/C Differential Pressure Sensor Honeywell24PCDFA6D-3030 PsiN/A BarometerBoschBMP hPa1100 hPa1.0 hPa 1.0 hPa in 12 months TemperatureBoschBMP C1.0 CN/A

26 Unscented Kalman Filter Block Diagram 26

27 ACDS: Risk Analysis Approach M – Mitigate W – Watch A – Accept R – Research Criticality High Med Low L x C Trend  Decreasing (Improving)  Increasing (Worsening)  Unchanged * New since last month TrendRankAppRisk Title  1R/M Kalman filter implementation and tuning issues  2M Erroneous control loop commands  3M INS Drift  4R/MI2C Implementation  5MLinear actuator weight limitations  6RLinear actuator force limitations  7R Unpredicted flight characteristics with airbrake use 2 LIKELIHOODLIKELIHOOD CONSEQUENCES

28 Educational Engagement & Outreach OUTREACH GOALS: Reach kids in Alaska’s interior & groups underrepresented in STEM outreach. Show kids that they possess the skills to become future engineers and innovators and inspire them to pursue a STEM career. Make a difference in Alaska’s interior schools and to enrich STEM education. OUTREACH ACTIVITIES: Rocketry Presentations Hybrid Motor Demonstration Rocket Building Workshops Launch at Poker Flat Rocket Range

29 Educational Engagement & Outreach (Cont.) SCHEDULE: BUDGET:


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