RamRackPreliminary Design Review
Colorado State UniversityZach Glueckert
Christopher Reed
Timothy Schneider
Brendan Sheridan
Christina Watanuki
Advisor: Dr. Azer Yalin
November 14, 2008
RockSat 2008-2009
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.
Overview
System Design
RamRack
Structure
PowerData Loging/Control
Sensors
ElectronicStructural
Connection Type
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
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
• Design Drivers– Future payloads will have diverse power requirements
• Trying to allow for a broad range in order to be adaptable
– Weight– Size
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.
• Design Drivers– Maximize the amount of ADC Channels for future sensors– Ease of use – no special abilities required for future use– Cost
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)
• Design Drivers– Test out our data logging system– Characterize Rocket Flight for future missions– Cost
Block Diagram - Power
Battery
Battery
Voltage Regulator
Voltage Regulator
Voltage Regulator
Voltage Regulator
Voltage Regulator
Voltage Regulator
G - Switch
G - Switch
Data Logger and Control Circuit Requirements
Sensor Package
Block Diagram – Data Logger
Power Sensor Package
Data Log One
Data Log Two
Temperature Sensor
Temperature Sensor
Block Diagram – Sensors
Power
z
y
x
Gross GSensor
Gross GSensor
Gross GSensor
Fine G Sensor
Pressure
Data Logger and Control Circuit Requirements
Vibration
Structural
• 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
Structural
Data Logger and Control
Data Logger and Control
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
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
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
Command and Control
•Memory Budget•4 GB Micro SD Card
•Allows for sampling of 50kHz•Stores data from all 10 16 ADC Channels
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
Parts List
part # # needed $ min Quant # to order
ATMEGA2561-16AU-ND 3 $15.91 1 3 47.73
ATMEGA8515-16AU-ND 4 $5.16 1 4 20.64
296-9225-5-ND 4 $0.72 1 4 2.88
296-9182-5-ND 2 $0.60 1 2 1.2
ADS7805U-ND 3 $31.07 1 3 93.21
576-1761-5-ND 16 $1.24 25 25 31
0
490-1631-1-ND 3 $0.22 10 10 2.2
399-1097-1-ND 15 $0.08 10 20 1.66
399-4788-1-ND 18 $1.04 10 20 20.8
493-2400-1-ND 6 $0.20 10 10 2
0
576KXBK-ND 3 $0.10 5 6 0.588
33.2KXBK-ND 3 $0.10 5 6 0.6
200XBK-ND 3 $0.10 5 6 0.6
P6.04KCCT-ND 16 $0.09 10 25 2.25
P1.5KDACT-ND 16 $0.20 10 25 5
RHM1.60KCCT-ND 30 $0.03 10 50 1.5
0
3361S-503GLFCT-ND 6 $1.02 1 6 6.12
CAT5113VI-10-T3CT-ND 18 $1.92 25 25 48
0
0
475-2506-1-ND 10 $0.13 1 10 1.33
475-1408-1-ND 10 $0.13 1 10 1.3
475-1196-1-ND 10 $0.13 1 10 1.3
0
A26508-40-ND 3 $2.32 1 3 6.96
929850E-01-36-ND 3 $3.31 1 3 9.93
A26532-40-ND 2 $4.22 1 2 8.44
929852E-01-36-ND 2 $6.33 1 2 12.66
0
HM152-ND 1 $10.94 1 1 10.94
0
http://www.saelig.com/ 0
uALFAT-TF 4 $35.95 1 4 143.8
Total 484.64
Part # # Needed Price Min Quant # Order Total PriceMMA2201D-ND 3 15.34 1 3 46.02ADXL330KCPZ 1 11.71 1 1 11.71MPX4115A-ND 1 12.45 1 1 12.45MSP1006-ND 5 2.4 1 5 12
Total 82.18
Sensors
Data Logger
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.
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
Team LeaderZach Glueckert
Thermal Structural
Systems Engineer
Control Systems
Electrical Engineer Tim Schneider
Zach Glueckert
Software EngineerBrendan Sheridan
Christina WatanukiChris
Reed
Management
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 DynamicsSpin Rate of Rocket
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