Preliminary Design Review

Preliminary Design Review Patrick Weber, Eric Robinson, Dorin Blodgett, Michael Stephens, Heather Choi, Kevin Brown, Ben Lampe November 1, 2010

Mission Overview 3 4 2 5 1 6

Scientific Mission Overview Primary: Collect space dust. • Provide a perspective of what is in our upper atmosphere. Secondary: • Capture optical images of the Earth. • Measure thermal, seismic, and pressure effects throughout the duration of the launch. • Collect data for future projects. Presenter: Eric Robinson

Engineering Mission Overview Engineer an extendable boom to mount a dust collector. Use aerogel tablet as dust collector. • Engineer a water shield to protect dust collector. Engineer modular electronic systems for: • Capturing and storing images from optical devices. • Recording thermal, seismic, and pressure data in real time throughout launch using sensors and transferring recording data via provided NASA Wallops Telemetry. Presenter: Eric Robinson

Theory and Concepts Underlying Science and Theory • Attempt to capture space particles using telescoping boom and aerogel. • Quantification of varying flight parameters. Presenter: Eric Robinson

Theory and Concepts Previous Experimentation • Previous flights have included multi-sensor packages. • Temperature, Humidity, and Pressure Sensors • Accelerometers / Seismic Sensors • Magnetometers • Data Storage (SD Cards) • Results provided a basis for improvement on future data collection and retrieval. • SD Cards impervious to low exposure to salt water • Payload orientation Presenter: Eric Robinson

Concept of Operations t ≈ 1.7 min Shedding of Skin Boom Extends t ≈ 4.0 min Boom Retracts t ≈ 2.8 min Apogee t ≈ 0.7 min End of Orion Burn t ≈ 8.2 min Chute Deploys t ≈ 15 min Splash Down t ≈ 0 min Launch Presenter: Eric Robinson

Expected Results Successfully collect space dust • Space Dust Composition(10-6) • Exhausted Rocket Fuel • Meteor / Metal Fragments • Other Miscellaneous Gases • Earth images • Detailed data throughout flight duration • Thermal Data • Seismic/Vibration Data • Atmospheric Pressure Data Presenter: Eric Robinson

System Overview 3 4 2 5 1 6

Subsystem Definitions TB: Telescopic Boom OC: Optical Camera IS: Integrated Sensors EPS: Electrical Power System STR: Structure MCU: Micro Controller Units Presenter: Eric Robinson

Subsystem Overview Presenter: Eric Robinson

System Level Block Diagram STR EPS Buck Converter Microcontroller WFF Power Interface Boost Converter Wallops PT Interfaces Motor Controller OC Legend IS Camera Pressure S. Data/ Control TB Accelerometer High Voltage WFF Telem. Interface Thermal Sensor Low Voltage Presenter: Eric Robinson

Critical Interfaces Presenter: Eric Robinson

System/Project LevelRequirement Verification Plan Presenter: Eric Robinson

User Guide Compliance Presenter: Eric Robinson

Sharing Logistics Who are we sharing with? • University of Northern Colorado • Re-entry Experiment Sat: Recover a reusable deployable, attempt to dynamically control the descent of the payload, and gather data during the return trip. • The possibility of a communication system between the AstroX payload and the UNC Re-entry Experiment Sat payload is being considered. Plan for collaboration? • Email, phone, road-trips to Greeley and Boulder • Communication with Max Woods on a weekly basis. • Grant UNC access to the AstroX private website. Presenter: Eric Robinson

Subsystem Overview 3 4 2 5 1 6

Subsystem A: Telescopic Boom Presenter: Patrick Weber

Subsystem A: Telescopic Boom Functional Block Diagram Presenter:

Subsystem A: Telescopic Boom Telescopic Boom, Spring Loaded • Safe • Inexpensive • Reliable • Strong Presenter: Patrick Weber

Subsystem A: Water Shield Presenter: Patrick Weber

Subsystem A: Water Shield Aluminum • Easily machined • Inexpensive • Reliable (no surprises) Presenter: Patrick Weber

Subsystem B: Power System (EPS) Presenter: Michael Stephens

Subsystem B: Power System (EPS) NASA Power • Reliable • Inexpensive • No weight penalty • Safe Presenter: Michael Stephens

Subsystem C: Integrated Sensors • SD Cards • Reliable / Redundant • Solid State • Impervious to salt water • Lightweight • Can handle large data Telemetry • Reliable • Least Expensive • No weight penalty • Least Complex • Cannot handle large data Presenter: Michael Stephens

Subsystem C: Integrated Sensors Presenter: Michael Stephens

Subsystem D: Optical Camera Optical Still Camera • Least Expensive (already own) • Lightweight • Least complex (circuits pre-engineered) Presenter: Michael Stephens

Mathematical Models 3 4 2 5 1 6

Telescopic Boom Launch/Reentry • Centrifugal Loading • Static Tension Assumptions • The maximum centrifugal force will occur directly before Orion burn out. • Internal forces are equal to zero. • Centrifugal masses are treated as point masses at their COG. Presenter: Patrick Weber

Telescopic Boom Apogee • Spring Force • Friction • Dynamic Tension Assumptions • The maximum frictional force will occur between the base and mid sections. • Internal forces are zero. • Gravity at apogee will be negligible, beam theory does not apply. Presenter: Patrick Weber

Payload Structure Launch • Uniform Thrust Loading • Vibrations • Impulse • Fatigue (~0.7 minutes) • Pressure Vessel Effects (neg.) Assumptions • Loading can be applied as body forces. • Payload internal supports are fixed connections. • Payload has uniform material properties. • Vibrations treated as static loads at peak amplitude. Presenter: Patrick Weber

Payload Structure Reentry • Impact • Pressure Vessel • Shear Loading (Plate Lip) Assumptions • Perfectly rigid and joints have no clearance • Uniform material properties • Gravity is constant Presenter: Patrick Weber

Finite Element Analysis Simplified Governing Equations Presenter: Patrick Weber

Finite Element Analysis Launch Assumptions • Vibration loads will be treated as static loads at peak amplitude. • Base of each longeron is fixed and immovable. • No surface forces are present other than contact forces. • Vibration and thrust loads are applied as body forces. • Loading conditions are continuous over each part. • All materials are linear isotropic. Presenter: Patrick Weber

Finite Element Analysis Reentry Assumptions • Payload falls directly onto surface. • Surface is perfectly rigid. • Payload can deform. • No surfaces forces are present other than part contact forces and surface/payload contact force at impacting location. • Drag and impact loads are applied as body forces. • All materials are linear isotropic. Presenter: Patrick Weber

Prototyping Design 3 4 2 5 1 6

Subsystem: Risk Matrix/Mitigation Risk Matrix / Mitigation • STR/TB.RSK.1: Canister seals failat splashdown and aerogel issaturated with water. • TB.RSK.2: Boom jams when skinsare shed. Boom fails to open andmission objectives are not met. • IS.RSK.1: Telemetry or SD cards fail and data to be collected for next year’s team is lost. Secondary mission objectives are not met. • EPS.RSK.1: Should the NASA telemetry or Timed Event circuits fail, the boom may prematurely extend causing failure of the UW payload as well as possible damage to the rocket. Presenter: Patrick Weber

Prototyping Plan Most mechanical prototyping will be done and tested using Finite Element Analysis. • Drop tests • Launch simulations Once the payload is manufactured, extensive testing will be performed on the payload as it is assembled. • Circuits tests • Pool submersion tests on the canister as well as drop deflection tests on the sealing around the boom. Presenter: Patrick Weber

Project Management Plan 3 4 2 5 1 6

Organizational Chart Project Manager Shawn Carroll Engineering Faculty Advisor Dr. Carl Frick Physics Faculty Advisor Dr. Paul Johnson Team Leader Patrick Weber Telescopic Boom (TB) Patrick Weber Eric Robinson Dorin Blodgett Electrical Power System (EPS) Michael Stephens Ben Lampe Integrated Sensors (IS) Michael Stephens Heather Choi Optical Camera (OC) Kevin Brown Nick Roder Charles Galey Presenter: Patrick Weber

Mechanical Schedule Major Mechanical Milestones: • Design Freeze at CDR (Friday, November 19, 2010) • Blueprints submitted for manufacturing by CDR • Mechanical prototype constructed mid-January, 2011 • Mechanical prototype fully tested by end of January, 2011 • Impact and submersion testing • Aerogel testing Presenter: Patrick Weber

Electrical Schedule Major Electrical Milestones: • Electrical Schematics completed by CDR • Components ordered by end of Fall Semester (December, 2010) • Electrical assembly and testing done by Mid February • Control function test • Telemetry and SD card output test • Fully functioning payload by end of February Presenter: Patrick Weber

Budget Mass Budget (15±0.5 lbs) • Structure (9 lbs) • Boom (2 lbs) • Water Shield (4 lbs) • NASA Structure (3 lbs) • Camera (1 lb) • Other Sensors (1 lb) • Modular Electrical System (1 lb) • Ballasting (~3 lbs) Presenter: Patrick Weber

Budget Monetary Budget (~$1300) • Structure ($600) • Boom ($200) • Aerogel ($300) • Water Shield ($100) • Camera ($100) • Other Sensors ($110) • Modular Electrical System ($200) • Correcting Factor (+$25%) Presenter: Patrick Weber

Work Breakdown Structure Telescopic Boom (TB) Electrical Power System (EPS) • Finalize Schematics • Design Freeze at CDR • Order Parts by End of Fall Semester • Build Circuits • Program Microcontrollers • Test Systems • Integrate with Boom • Finalize Design • Design Freeze at CDR • Submit Work Request • Manufacture Boom Parts • Assemble Boom and Structure Integrated Sensors (IS) Optical Camera (OC) • Finalize Schematics • Design Freeze at CDR • Order Parts by End of Fall Semester • Build Circuits • Program Microcontrollers • Test Systems • Recover previous year’s camera • Test functionality of camera • If functional: • Integrate with Electrical Power System and Integrated Sensors • If non-functional: • Assess alternatives and proceed in the most appropriate path Presenter: Patrick Weber

Conclusions 3 4 2 5 1 6

Scientific Mission Overview Primary: Collect space dust. • Provide a perspective of what is in our upper atmosphere. • Engineer a water shield to protect dust collectors. Secondary: • Capture optical images of the Earth. • Measure thermal, seismic, and pressure effects throughout the duration of the launch. • Collect data for future projects. Presenter: Patrick Weber

Engineering Mission Overview Engineer an extendable boom to mount imaging equipment and dust collector. Use aerogel to collect space dust. Engineer modular electronic systems for: • Capturing and storing images from optical devices. • Recording thermal, seismic, and pressure data in real time throughout launch using sensors and transferring recording data via provided NASA Wallops Telemetry. Presenter: Patrick Weber

Preliminary Design Review