Space Cowboys

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 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 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 Overview• Previous Related Experimentation

– Previous flights have included multi-sensor packages

– Results provide a basis for improvement on future data collection

Mission Overview• Mission Requirements

– Multipoint Temperature Monitoring– Pressure Monitoring – 3-Axis Accelerometer Monitoring– Humidity Monitoring– 3-Axis Gauss Meter

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 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

Design• Required Hardware

– Sensors:• 2 – Three axis accelerometers• 1 – Humidity sensor• 2 – Temperature/Humidity sensors• 1 – Three axis Hall-effect sensor

– Additional Electronics:• Data storage• Microprocessors• Power Supply• PCBs

Design• Required Hardware

– Mechanical & Structural:• Support trays• Support columns• Circuit Board Mounting• Sensor Positioning

Design• Preliminary

Electrical & Data Block Diagram

• CAN Interface Between Circuit Boards

Peripheral Board #1

Main Sensor Board

Power Source (Battery)

Voltage Regulator

Main Microprocessor

Storage Memory

3-Axis Accelerometer

Humidity and Temp Sensor

Pressure Sensor

Interface to Peripheral Boards

3-Axis Accelerometer

Sub Microprocessor Temp Sensor

(for side of can)

RBF PinG-Switch

Interface to Main Board

Peripheral Board #2

Sub Microprocessor 3-Axis Gauss

Sensor

Interface to Main Board

Color KeyData

Power

Data + Power

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• University of Wyoming (UW) & University of

Minnesota (UMN)• UW Missions

– Multi-sensor: Rocket flight parameter measurements– 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 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

Management

Management• Project Schedule

– See attachment

• Preliminary mass/monetary budgets– Mass Budget: 3lb (Multi-Sensor)– Budget: approx. $500

Conclusions• Issues/Concerns

– Structural Interface with other Payloads within Canister

– Electrical Interference from Payloads and External Radiation