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Progress Design Review. Space Cowboys. University of Wyoming Kyle Fox, Sean King, Erich Lichtfuss, Jeff Parkins, Anne-Marie Suriano. Overview. Mission Overview Subsystem Requirements Special Requirements Block Diagrams Schematics Activity Diagram Parts List Test Plans

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Presentation Transcript
space cowboys

Progress Design Review

Space Cowboys

University of Wyoming

Kyle Fox, Sean King, Erich Lichtfuss,

Jeff Parkins, Anne-Marie Suriano

  • Mission Overview
  • Subsystem Requirements
  • Special Requirements
  • Block Diagrams
  • Schematics
  • Activity Diagram
  • Parts List
  • Test Plans
  • Canister Guidance
  • Canister Shared Logistics Plan
  • Management
  • Issues and Concerns
mission overview
Mission Overview
  • Objective
    • Accurately measure flight parameters including ambient and skin temperatures, pressure, acceleration, spin rate, and magnetic field.
    • Gain basic understanding of design requirements and associated hurdles for designing in real-world space applications.
mission overview1
Mission Overview
  • Goal
    • Provide an accurate base of flight parameters to model rocket flight conditions and patterns for assessment of associated affects on other systems.
    • Attain real-world design experience.
mission overview2
Mission Overview
  • Underlying Science/Theory
    • Recognition of magnetic field changes associated with altitude
    • Quantification of varying flight parameters
    • Attempt to determine rocket orientation using post-flight accelerometer data
mission overview3
Mission Overview
  • Previous Related Experimentation
    • Previous flights have included multi-sensor packages
    • Results provide a basis for improvement on future data collection
mission overview4
Mission Overview
  • Mission Requirements
    • Multipoint Temperature Monitoring
    • Pressure Monitoring
    • 3-Axis Accelerometer Monitoring
    • Humidity Monitoring
    • 3-Axis Gauss Meter
mission overview5
Mission Overview
  • Success Criteria
    • No mechanical failure of structure
    • No electrical failures in system
    • Clear and accurate data stored
      • Allows for analysis
      • Easily organized and identifiable
mission overview6
Mission Overview
  • Benefits
    • Other experiments on the rocket
      • Accurate flight data
    • Future rocket flights and teams
      • Accurate flight data
      • Clear identification of extreme parameters for more efficient design
      • Multi-sensor platform that allows for expansion to add future sensors and experiments as desired
subsystem requirements
Subsystem Requirements
  • Subsystems
    • Power
    • Sensors
    • Command & Data Handling
    • PCB
    • Support Structure
subsystem requirements1
Subsystem Requirements
  • Power
    • Payload will consume 1.2 amps under peak conditions
      • See next slide for peak power usage breakdown
    • Batteries will provide peak current for 1.5 hours
    • Two 3.6V Batteries will operate in series to provide 7.2V
    • Voltage regulation will be performed on the main board and will negate effects of temperature and voltage variations of the batteries during discharge
subsystem requirements2
Subsystem Requirements

Peak Power Usage Breakdown

subsystem requirements3
Subsystem Requirements
  • Sensors
    • Main board accelerometer will be located on the center axis of payload canister
    • Each sensor requires specific sampling intervals and returns specific sample sizes
  • Command & Data Handling
    • Code must be extremely robust with excellent error handling capabilities

Subsystem Requirements

  • PCB
    • Multilayer construction focusing on noise mitigation and ease of future expansion
  • Support Structure
    • Maximize strength, minimize mass
special requirements support columns
Special RequirementsSupport Columns

University of Minnesota may only be willing to allow Option 1

block diagrams
Block Diagrams

Main Sensor Board

block diagrams1
Block Diagrams

Peripheral Board #1:

Skin Temperature and Off-Axis Acceleration Measurement

block diagrams2
Block Diagrams

Peripheral Board #2:

Magnetic Field Measurement

operating system
Operating System
  • The Payload will operate with a Real Time Interrupt Driven Operating System
  • The Operating System will have extensive error handling capabilities including multiple sensor failures
  • The Operating System will be constructed to allow easy modification and expansion as required by future missions
can bus interface
CAN bus interface
  • The Main Board will communicate with all satellite boards via a CAN bus Interface
  • CAN has the ability to address over 110 devices
  • CAN provides 1MB/s throughput
  • CAN is commonly available and very inexpensive
microsd main board storage
MicroSD Main Board Storage
  • MicroSD will be implemented for project storage
  • MicroSD is inexpensive and is available in high data densities on a small footprint
  • MicroSD provides 3MB/s throughput
  • MicroSD offers an 8-bit data path over SPI
sensor package
Sensor Package
  • Temperature
    • Sensirion SHT15
    • Temperature is measured on both the Main Board and a single Satellite Board for approximating skin temperature
    • Resolution: 0.01C
    • Accuracy: +/- 0.3C
    • Response Time: 5s
sensor package1
Sensor Package
  • Relative Humidity
    • Sensirion SHT15
    • Humidity is measured on the Main Board
    • Resolution: 0.05 %RH
    • Accuracy: +/- 3.0 %RH
    • Response Time: 8s
sensor package2
Sensor Package
  • Accelerometers
    • VTI SCA3000-E05
    • Three axis acceleration is measured along the center axis and inner edge of payload canister
    • Resolution: 0.002g
    • Accuracy: +/- 2.0 %
    • Response Time: 200Hz
sensor package3
Sensor Package
  • Magnetic Sensor
    • PNI MicroMag 3
    • Magnetic field is measured on peripheral board #2
    • Resolution: 0.015µT
    • Response Time: 500µs
sensor package4
Sensor Package
  • Pressure Sensor
    • Hope RF HP03
    • Pressure is measured on the Main Board
    • Resolution: 0.1 hpa
    • Accuracy: ± 0.5 hpa
    • Response Time: 35ms
  • Structure
    • Developed mathematical models
      • Basis for initial design
      • Reviewed by ME professor
    • Research of Materials
      • Extensive properties list determined
      • Basic materials analysis performed
support column 3d schematic drawings
Support Column3D Schematic Drawings

(Left) Non-deformed 3D Mesh

(Right) Scaled Deformation 3D Mesh (20 G vertical load, 10G Lateral Load)



  • Electrical
    • Code verification will be completed in the CodeWarrior Development Environment
    • Hardware verification will be completed by a series of tests TBD
  • Structure
    • Vibration testing will be completed at a local businesses 2-axis vibration table
    • Spin Stabilization Testing will also be conducted at local business using a spin table
  • Full Package Testing
    • Environmental Testing using previous RockSat flights data as a reference
    • Possible Weather Balloon Launch. Local Civil Air Patrol Squadron has offered to run our package as a payload for a future weather balloon launch.
  • Potential Points of Failure
    • Electrical
      • Contact to data storage card
      • Electrical connection breakage during high Gs
      • Unforeseen code interruption due to interference
    • Mechanical
      • Bolt thread shearing
      • Vertical supports buckling
      • Tray malfunction
major structural components
Major Structural Components
  • Makrolon(Tray Material)
    • Bayer
      • Properties are known (
      • Price & Availability known
  • Aluminum(Support Columns & Circuit Mounts)
    • Provided by University of Wyoming Engineering Machine Shop
      • Properties known
      • Prices & Availability known
major electrical components
Major Electrical Components
  • Parts List
    • See file “Parts List.docx”
  • Lead Times
    • 1.5 Weeks
  • S+H
    • $50 in addition to listed part costs
rocksat payload canister user guide compliance
RockSat Payload Canister User Guide Compliance
  • Mass/Volume
    • Estimate 3lbs
  • Payload Activation
    • G-switch activation
      • Open circuit until g-switch activation
  • Rocket Interface
    • RBF/Shorting wires
shared can logistics plan
Shared Can Logistics Plan
  • University of Wyoming (UW) & University of Minnesota (UMN)
  • UW Missions
    • Multi-sensor: Rocket flight parameter measurements
    • Good Vibrations: Explore rocket flight effects on electrical and crystal oscillators
  • UMN Mission
    • To characterize the flight of the rocket and attempt to record data using techniques untested in suborbital flight.
shared can logistics plan1
Shared Can Logistics Plan
  • Interfacing Collaboration Plan
    • E-mail and phone conferencing
    • Exchange of 3D modeling suggestions
    • Full assessment and agreement on location, structure and interface
  • Structural Interfacing
    • Still to be determined
    • Positioning has been discussed
  • Project Schedule
    • See attachment
  • Preliminary mass/monetary budgets
    • Mass Budget: 3lb (Multi-Sensor)
    • Budget: approx. $750
  • Issues/Concerns
    • Structural Interface with other Payloads within Canister
    • Electrical Interference from Payloads and External Radiation