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RamRack Preliminary Design Review

RockSat 2008-2009. RamRack Preliminary Design Review. Colorado State University Zach Glueckert Christopher Reed Timothy Schneider Brendan Sheridan Christina Watanuki Advisor: Dr. Azer Yalin November 14, 2008. Overview.

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RamRack Preliminary Design Review

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  1. RockSat 2008-2009 RamRackPreliminary Design Review Colorado State University Zach Glueckert Christopher Reed Timothy Schneider Brendan Sheridan Christina Watanuki Advisor: Dr. AzerYalin November 14, 2008

  2. Overview • Objective: To develop a sounding rocket payload to act as a power bus, data logger, and mounting structure for future scientific payloads • Overview: • Power bus will be programmable to provide varying voltage supplies depending on need. • Data logger will provide a broad range of low level sensor communication and will contain several redundant systems. • Design will incorporate several permanent sensors that can be used to monitor conditions of this and future flights • Success Criteria: On this initial flight sensor data will provide data on conditions in the immediate region of the payload • Benefits: This information will be used to create constraints on future experimental payloads and help characterize the flight dynamics.

  3. Connection Type Electronic Structural System Design RamRack Structure Data Loging/Control Power Sensors

  4. Subsystem - Structural • Requirements • Must utilize the five 8-32 mounting holes available on the can • Highly adaptable mounting points for future payloads • Use as little space as possible while still providing adequate mounting points for future payloads • Non-magnetic • Will not yield under a 40-g acceleration with a 10 pound load • Conform to RocketSat flight requirements • Weigh less than 1lb • Design Drivers • Adaptability • Material Strength versus Weight • Size

  5. Subsystem – Power Supply • Requirements • Minimum supply voltage of 5V • Maximum supply voltage of 15V • Provide 15W for 1hr • Allow for brief but large current loads <5A • Redundant • Adjustable voltage output • Thermal monitoring with shutdown capabilities • DesignDrivers • Future payloads will have diverse power requirements • Trying to allow for a broad range in order to be adaptable • Weight • Size

  6. Subsystem – Data Logger • Requirements • Survive the physical characteristics of flight • Multiple ADC channels capable of 16 bit conversions • Multiple serial input channels • Easy data transfer • Redundancy in case of component failure • Sample Rates of 100Hz or better • Storage for all of the ADC channels at maximum sample rate for one hour. • DesignDrivers • Maximize the amount of ADC Channels for future sensors • Ease of use – no special abilities required for future use • Cost

  7. Subsystem – Sensors • Requirements • Measure G-forces on three axis • Fine measurement for low accelerations (+/-3g) • Gross measurements for large accelerations (+/-40g) • Pressure (15-151 kPa) • Temperature of Operating Components • Vibration (10-300 Hz) • DesignDrivers • Test out our data logging system • Characterize Rocket Flight for future missions • Cost

  8. Block Diagram - Power G - Switch Voltage Regulator Data Logger and Control Circuit Requirements Battery Voltage Regulator Battery Voltage Regulator G - Switch Voltage Regulator Sensor Package Voltage Regulator Voltage Regulator

  9. Block Diagram – Data Logger Temperature Sensor Data Log One Sensor Package Power Temperature Sensor Data Log Two

  10. Block Diagram – Sensors Gross G Sensor Data Logger and Control Circuit Requirements z Gross G Sensor Fine G Sensor y Gross G Sensor Power x Pressure Vibration

  11. Structural Al 6061 T6 Weight Estimate 6 oz Integrates to holes available in can All components attach to frame Electronic Enclosure Battery Pack In RockSat Can Structural

  12. Structural

  13. Structural

  14. Data Logger and Control

  15. Data Logger and Control Top Side Bottom Side

  16. Data Logger and Control

  17. Sensors • Beginning work on mounting and sensor circuitry • Selected the sensors • Verified they will work with data logging unit • Will be mounted on top of the RamRack • Can be placed in many different areas in order to make room for other payloads

  18. Command and Control • In-House Software: Front-End • Development planned in C++ • Data parser for .txt formatted file dump • Generates time-stamps for each reading based on frequency settings and internal clock • Splits data into separate graph-ready files for each input channel • Interface for changing input/frequency settings • Intuitive graphic user interface for ease of use by future groups • Will take advantage of standard C++ GUI libraries (GTK+)‏ • Settings for each input channel saved in txt format and later piped to embedded systems

  19. Command and Control • In-House Software: Back-End • Control unit programmed in a combination of tiny-BASIC and assembly • Software for selecting and piping data from multiple input channels in real-time based on internal clock • Must incorporate input and frequency settings from front-end software • Must handle collisions appropriately

  20. Command and Control • Memory Budget • 4 GB Micro SD Card • Allows for sampling of 50kHz • Stores data from all 10 16 ADC Channels

  21. Test Plan • Subsystem Testing - Benchtop • Test each sensor individually • Integrate and make sure they are all recording data and working • Calibration Testing • May have an opportunity to use the Air Force’s vibration facility • Drop Tests for G testing • Practical Testing • Car Test • Drive around with unit in vehicle and see if the data is reasonable • Allows for a time based test and requires the unit to be self-reliant

  22. Parts List Data Logger Sensors

  23. RockSat 2008-2009 • RockSat Payload Canister User Guide Compliance • Mass: • Estimated use: 2.5lbs • Allotted: 2.5lbs • Volume: • Estimated use: 5.75” x 5.75” x 2” (dependant on sensor mounting) • Allotted: 9” x 2” • Payload activation • G-switch – no voltage running prior to launch. On launch, mechanical G-switches activate powering electronic systems. • Rocket Interface • Complies with no-volt shorting wire setup.

  24. Logistics • Unable to meet with other schools before today • Have been in contact and all schools have agreed to the standard mounting hole pattern. • Latest email mentioned an additional payload

  25. Management Team Leader Zach Glueckert Thermal Structural Systems Engineer Control Systems Chris Reed Christina Watanuki Zach Glueckert Electrical Engineer Tim Schneider Software Engineer Brendan Sheridan

  26. Conclusions: • Concerns • Shared canister integration • How to mount three/four different payloads together • Center of mass/volume with other schools • Mass and volume constraints • Flight Dynamics • Spin Rate of Rocket

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