Hy-V 0.1Hy-V 0.1Environmental Testing
Phillip Jasper
Ryan Johnson
Mitchell Foral
December 2008Virginia Tech and University of Virginia
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
• 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• 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: $25
http://www.datasheetarchive.com/Thumbnails/Datasheet-09/tnDSA00145182.jpg
Accelerometer
• Freescale Semiconductor MMA3201• Supply Voltage: 4.75V to 5.25V dc• Consumption Current: 6 - 10 mA• Sensitivity: 50 mV/g• Operating Temperature Range: -40 C to +125 C• Vibration max: 45g
Inertial Sensor
• Analog Devices High Precision Tri-Axis Inertial Sensor ADIS16355
• Operating Temperature Range: -40 C to +85 C• Tri-axis gyroscope with digital range scaling• 14-bit resolution• +/- 10 g measurement range• Supply Voltage 4.75 – 5.25 V• 2000 g Shock Qualified• Size: 23 mm X 23 mm X 23 mm
http://www.soel.ru/cms/i/?/360241$[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:
oAnalog signal outputoSmall footprintoLow weightoLow 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):– 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:• 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 sensoro Activated by G-switcho 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% VT: 75%
•Two Skin Friction sensors
•Largest sensors
•Location: irrelevant
•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 CodeSpecial needs (IE voltage requirements)
Shared Can Logistics(cont)-Mech and Aero
• VT and UVA will collaborate on structure design• 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)-Management
• 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
Ignition of Rocket
Tripping of G-Switch
Board Turns on
Sensors Power on
Code Execution Begins
Is memory Full?
Yes
No
Keep Executing Code
Stop CodeSplash Down
Recovery of Rocketv
Recovery of DATA
Assessment of Test
Deintegrate
Block Diagram
Structural Diagrams
Subsystem Overview
• 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 ListPart 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 Status
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
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.
Sean Flemming Mark Paretic
Max Rusche Preston Cupp
Jason Henn Dmitry Volodin
Matt Banks
Phil Jasper
Ben Leonard
Archie Raval Jess Quinlan
Naeem AhmedShaun Masavage
Management
Chris Koehler and Shawn Carroll
PM: Ryan JohnsonChris Goyne
Advisor
SystemsMech and Aero
Kevin Shinpaugh
PM: Kyle Knight
Mitchell Foral
Chris Sweeney
UVA VT
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
• 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=P-Ultra_RTD
Invensys ASDX100 Pressure Sensor - http://www.ic-on-line.cn/iol_asdx005d44r/pdfview/2840599.htm
AS Autosport Pressure Transducer - http://www.sensorsone.co.uk/products/0/36/AS-Autosport-Pressure-Transducer.html
MMA3201 Accelerometer - http://www.alldatasheet.net/datasheet-pdf/pdf/188041/FREESCALE/MMA3201.html
ADIS16355 Inertial Sensor - http://www.analog.com/en/other/multi-chip/adis16355/products/product.html