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