Transcript Hy-V CDR v2

Hy-V 0.1
Environmental Testing
Phillip Jasper
Ryan Johnson
Mitchell Foral
Virginia Tech and University of Virginia
December 2008
Overview
• Objective:
– Test the vibration, external and internal
temperature, and pressures experienced in flight
– Flight qualify the five sensors and Persistor
DataLogger
– Students to gain experience in several areas of
engineering by engaging in a student run
sounding rocket experiment
• Expected to prove:
– Prove the equipment are viable for the Hy-V
Project to be launched in 2010/2011
– Measured values match predicted values of
vibration, pressure, and temperature
Importance of Hy-V 0.1
• Act as a Preliminary Flight test:
– Students already involved in Hy-V scramjet flight
experiment
– Hy-V is an experiment executed between UVA
and VT
• Flight will give UVA and VT a chance to work together to
achieve a successful flight prior to the flight experiment
– These students will be able to advise faculty and
peers on the sounding rocket process
– Important for students to broaden their knowledge of
instrumentation
• Given experience with instrumentation, students will be
able to advise on sensor function for the future
Science and Theory
• Vibration,
Temperature, and
Pressure profiles must
be known for Hy-V
Project to be
successful
• Certain pieces of
equipment unique to
this project are
sensitive to these
parameters
http://upload.wikimedia.org/wikipedia/commons/5/55/X-43A_(Hyper__X)_Mach_7_computational_fluid_dynamic_(CFD).jpg
Temperature Sensor
• Omega P-L Series 100 Ohm Platinum RTD
• Operating Temperature: -100 C to +400C
(dependent on cable covering)
• 1/8” Mounted Thread
• Accuracy Available up to 10 DIN (δT = +/- 0.1
X (0.3+0.005 |T|))
• Probe is 6” Long with wiring, main body is 2”
http://www.omega.com/ppt/pptsc.asp?ref=P-Ultra_RTD
Pressure Transducer
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Honeywell ASDX100
Supply Voltage: 4.75V to 5.25V dc
Max Supply Voltage: 6.50V dc
Consumption Current: 6 mA
Lead Temperature: 250 C
Pressure Range: 0 – 100 PSI
Sensitivity: 0.040 V/PSI
http://www.datasheetarchive.com/Thumbnails/Dat
asheet-09/tnDSA00145182.jpg
Accuracy: +/- 2%
Operating Temperature Range: -20 C to +105 C
Vibration max: 10G at 20-2000 Hz
Shock max: 50G for 11 ms
Approximate Price: $25
Accelerometer
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Freescale Semiconductor MMA3201
Supply Voltage: 4.75V to 5.25V dc
Consumption Current: 6 - 10 mA
Sensitivity: 50 mV/g
Operating Temperature Range: -40 C to +125 C
Vibration max: 45g
Inertial Sensor
• Analog Devices High Precision Tri-Axis Inertial Sensor
ADIS16355
• Operating Temperature Range: -40 C to +85 C
• Tri-axis gyroscope with digital range scaling
• 14-bit resolution
• +/- 10 g measurement range
• Supply Voltage 4.75 – 5.25 V
• 2000 g Shock Qualified
• Size: 23 mm X 23 mm X 23 mm
http://www.soel.ru/cms/i/?/360241$[200x0].jpg
UVA Skin Friction Sensor
Skin friction sensor specifications:
• Operates in excess of 1000 degrees C.
• Between 4 and 10 mm^2 in surface area.
• Frequency response in the kHz range.
• Power in: 3-20V
• From the manufacturer:
o Analog signal output
o Small footprint
o Low weight
o Low power consumption
Current Board Options
• Persistor DataLogger CF2
– Motorola 68332 based single board computer
– ADC: 8 Channels at 12-bit, 4 channels at 16
bit
– Accepts 3.6 to 20 Volt power input
– Draws 5 to 50 mA current at 3.3 VCurrently
• RockON! Board (fall back):
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Voltage Range: 0-5V
8 Channels
10 Bit Resolution
16 MB Data capacity
50 Hz sampling rate
30 minutes of data
• PC/104+
– Currently owned by VT
– Minimum boot time 5-15 secs
– Experienced boot time at VT – a few minutes
Concept of Operations:
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Shortly after T-zero, G-Switch Closes
Data logger boots, Sensors turn on
CF2 computer begins executing code
Logging software is interrupt-driven
Data is sampled over SPI bus
Data is written directly to Compact Flash
Compact Flash card recovered with payload
UVA Concept of Operations
• Skin friction sensor
o Activated by G-switch
o Takes readings from inside payload bay, sends
them to processor to store into memory until
memory is exhausted
o Instead of storing data directly, take running
averages over periods of time so less memory is
needed
Shared Can Logistics
UVA: 25%
•Two Skin Friction
sensors
•Largest sensors
•Location: irrelevant
VT: 75%
•5 Sensors
•Smaller sensors
•Positioning
somewhat relevant
•Circuit board
Shared Can Logistics-Systems (cont)
• UVA will make several trips to VT
• systems integration
• substructure integration
• DILT collaboration
• UVA subsystem team will assist VT’s System
team
• Supply with adequate experimental component
 Sensors
 Code
Special needs (IE voltage requirements)
Shared Can Logistics(cont)-Mech and Aero
• VT and UVA will collaborate on structure
design
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Solid modeling
Material Selection
Fabrication
Element analysis (determine structural integrity)
• VT and UVA will divide aero analysis
 Expected instrumentation reading
 Expected rocket loads
Shared Can Logistics(cont)-Managemen
• UVA and VT teams will collaborate on weekly
basis next semester
• Management- Weekly meetings
• Systems and Mech- meet every other week
• UVA and VT will work over the next month to:
• Delegate specific duties
• Arrange travel
• More in-depth system analysis
Flow Chart Diagram for Flight Test
Board Turns
on
Assessment
of Test
Sensors
Power on
Ignition
of Rocket
Recovery of
DATA
Tripping of
G-Switch
Code Execution
Begins
Recovery of
Rocketv
Yes
Is memory
Full?
No
Keep Executing
Code
Stop Code
Splash
Down
Deintegrate
Block Diagram
Structural Diagrams
Subsystem Overview
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Electrical and Power Supply (EPS)
– EPS subsystem will provide power to all sensors.
– EPS subsystem will remain between 20 and 40 Degrees Celsius at all times
– Design wiring scheme
Communication and Data Handling
– Handle the transfer and storing of data from sensors to the CF2
Thermal and Environment
– Track temperature profiles and requirements
– Track pressure expectations and component requirements
– Track vibration levels and component limitations
Systems
– Track mass and power budgets
– Integration of payload into the can (support from structures)
Structures
– Design interior structure of the canister and provide necessary support and
vibration resistance for payload
Parts List
Part
Quantity
Company
Model
CF2 Data Logger
1
Persistor
PERCF21M
A/D Board (8ch 12bit)
1
Persistor
R212
A/D Board (4ch 16bit)
1
Persistor
AD16S2
RTD
2
Omega
P-L-1/10-1/8-6-1/8-G-3
Skin Friction Sensor
2
ATK
N/A
Inertial Sensor
1
Analog Devices
ADIS16350
Pressure
Transducer
1
Honeywell
ASDX Series
Accelerometer
1
FreeScale
MMA3201D
Lithium Ion Batt. (9V)
5
Powerizer
LI-9V400+CH
Rocksat User’s Guide Compliance
Requirement
Method
Payloads must weigh less than 12.75 lbs (5.75 kg).
Design,
Test
Payloads must fit in cylindrical can with a diameter of 9.2
inches and height of 9.4 inches.
Design
The payload’s center of gravity (CG) shall be within a 1x1x1
inch envelope of the geometric centroid of the can.
Design,
Test
No volt requirement: Payload may not have current passing
through it before activated at launch.
Design,
Test
Communication systems are prohibited. All data must be
stored on on-board memory.
Design
Payload must withstand G-forces around 25 Gs on the
positive z-axis and endure large vibrations in all directions.
Design,
Test
The payload must be capable of meeting all mission
objectives.
Design,
Test
Status
Special Mission Requirements
• VT would like to measure
temperature and pressure near
the surface of the rocket.
– This requires access to a static
port near the wall of the rocket
– If impossible to integrate pressure
sensor near the rocket skin, the
sensors will simply be placed in
the RockSat canister.
Management
Chris Koehler and
Shawn Carroll
Chris Goyne
UVA
PM: Ryan Johnson
Advisor
Mech and Aero
Archie Raval
Shaun Masavage
VT
PM: Kyle Knight
Systems
Jess Quinlan
Mitchell Foral
Naeem Ahmed
Chris Sweeney
Kevin Shinpaugh
Sean Flemming
Mark Paretic
Matt Banks
Max Rusche
Preston Cupp
Phil Jasper
Jason Henn
Dmitry Volodin
Ben Leonard
Schedule
Test Plans
• Required tests include:
– Structural testing
• To ensure the payload will survive takeoff (i.e. vibration testing)
– Environment Testing
• Running full simulations for Temperature, Pressure, and
Vibration levels
– Day In The Life (DITL) Testing
• At least two full simulations to exhibit the functionality of the
payload. This will entail the payload being operated on a bench
as an integrated payload for the entire mission life (less than 30
minutes)
• Tests will also be done on each piece of equipment
to ensure they are operative.
Conclusion
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We have a plan to place multiple sensors on
board
• These sensors will be flight qualified for Hy-V
• The information gathered will help the Hy-V
team plan their components and mission
profile
• Information of sensors’ performance will be
used on later flight experiments:
• UVA shear sensor experiment
• Hy-V
Appendix
Temperature Sensor (RTD) - http://www.omega.com/ppt/pptsc.asp?ref=PUltra_RTD
Invensys ASDX100 Pressure Sensor - http://www.ic-online.cn/iol_asdx005d44r/pdfview/2840599.htm
AS Autosport Pressure Transducer http://www.sensorsone.co.uk/products/0/36/AS-Autosport-PressureTransducer.html
MMA3201 Accelerometer - http://www.alldatasheet.net/datasheetpdf/pdf/188041/FREESCALE/MMA3201.html
ADIS16355 Inertial Sensor - http://www.analog.com/en/other/multichip/adis16355/products/product.html