Hy-V 0.1 Environmental Testing Phillip Jasper Ryan Johnson Mitchell Foral December 2008 Virginia 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 _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 ( |T|)) Probe is 6” Long with wiring, main body is 2”

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: V/PSI Accuracy: +/- 2% Operating Temperature Range: -20 C to +105 C Vibration max: 10G at Hz Shock max: 50G for 11 ms Approximate Price: $25 asheet-09/tnDSA jpg

Accelerometer Freescale Semiconductor MMA3201 Supply Voltage: 4.75V to 5.25V dc Consumption Current: 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

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 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 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% 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  Code  Special 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 Code Splash 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 List PartQuantityCompanyModel CF2 Data Logger1PersistorPERCF21M A/D Board (8ch 12bit) 1PersistorR212 A/D Board (4ch 16bit) 1PersistorAD16S2 RTD2OmegaP-L-1/10-1/8-6-1/8-G-3 Skin Friction Sensor2ATKN/A Inertial Sensor1Analog DevicesADIS16350 Pressure Transducer 1HoneywellASDX Series Accelerometer1FreeScaleMMA3201D Lithium Ion Batt. (9V) 5PowerizerLI-9V400+CH

Rocksat User’s Guide Compliance RequirementMethodStatus Payloads must weigh less than 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 FlemmingMark Paretic Max RuschePreston Cupp Jason HennDmitry Volodin Matt Banks Phil Jasper Ben Leonard Archie Raval Jess Quinlan Naeem AhmedShaun Masavage Management Chris Koehler and Shawn Carroll PM: Ryan Johnson Chris Goyne Advisor SystemsMech and Aero Kevin Shinpaugh PM: Kyle Knight Mitchell Foral Chris Sweeney UVAVT

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) - Ultra_RTD Invensys ASDX100 Pressure Sensor - line.cn/iol_asdx005d44r/pdfview/ htm AS Autosport Pressure Transducer - Transducer.html MMA3201 Accelerometer - pdf/pdf/188041/FREESCALE/MMA3201.html ADIS16355 Inertial Sensor - chip/adis16355/products/product.html