Transcript Suborbital Rocket Payload - Colorado Space Grant Consortium

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:
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2 – Three axis accelerometers
1 – Humidity sensor
2 – Temperature/Humidity sensors
1 – Three axis Hall-effect sensor
– Additional Electronics:
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Data storage
Microprocessors
Power Supply
PCBs
Design
• Required Hardware
– Mechanical & Structural:
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Support trays
Support columns
Circuit Board Mounting
Sensor Positioning
Design
• Preliminary
Electrical & Data
Block Diagram
Main Sensor Board
G-Switch
RBF Pin
Power Source
(Battery)
Storage
Memory
Main
Microprocessor
• CAN Interface
Between Circuit
Boards
Humidity and
Temp Sensor
3-Axis
Accelerometer
Interface to Peripheral Boards
Peripheral Board #1
Sub
Microprocessor
Interface to Main
Board
Temp Sensor
(for side of can)
3-Axis
Accelerometer
Data
Power
Pressure Sensor
Voltage
Regulator
Color Key
Peripheral Board #2
Sub
Microprocessor
Interface to Main
Board
3-Axis Gauss
Sensor
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