university of wyoming dorin blodgett, kevin brown, heather choi, ben lampe

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University of Wyoming

Dorin Blodgett, Kevin Brown, Heather Choi, Ben LampeEric Robinson, Michael Stephens, Patrick Weber

October 7, 2010

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Mission Overview

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Scientific Objectives

oCapture optical images of the earth.

oCollect space dust.

o Provide perspective of what is in our atmosphere.

oMeasure thermal, seismic and pressure effects throughout duration of launch.

o Collect data for future projects

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Engineering Objectives

o Engineer electronics systems for capturing and storing images from optical devices.

o Create extendable booms to mount imaging equipment and dust collector.

o Use AeroGel to collect space dust.

o Create protective water shield for housing data storage devices and encasing AeroGel collector during reentry and splashdown.

o Record thermal, seismic and pressure data in real time throughout launch using electronic sensors and transmit recorded data via provided Wallops telemetry.

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Mission Requirements

The payload shall conform to the requirements set forth in the 2011 RockSat-X User Guide

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TYPE QUANTITATIVE CONSTRAINT Physical Envelope

Cylindrical**: Diameter: ~12 inches Height: ~12 inches ** Deployables and booms are permitted once skin has been ejected

Weight Payload shall be: 30±1 lbf

Center of Gravity Lies within a 1 inch square in the plane of the RockSat-X plate.

Power and Telemetry

Telemetry Ten (10) 0 – 5V 16 bit A/D Lines One (1) parallel line One (1) asynchronous line Power One (1) redundant power line (28V) Three (3) non-redundant power lines (28V) 1 Ah capacity

High Voltage All payloads utilizing higher voltage (>28V) shall conformal coat all electronics.

Specifications: Physical Constraints

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Specifications: Performance Parameters

KEY PERFORMANCE PARAMETER VALUE Altitude (km) ≈ 160 km

Spin Rate (Hz) at Burn-Out ≈ 1.3 Hz at Terrier burn out; ≈ 4.8 at Orion burn out

Maximum Ascent G-Load 25 G (Sustained) (50+ G Impulses Possible)

Rocket Sequence (Burn Timing) 5.2 s Terrier burn—9.8 s coast—25.4 s Orion burn

Chute Deploy (seconds) 489.2 s

Splash Down (seconds) 933 s

(Source: RockSat Payload Canister User’s Guide 2010)

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Success Criteria

o At minimum, the payload shall gather data during launch, at apogee, and during reentry through the use of:

o Thermocoupleso 3-axis Accelerometerso Gyroscopes o Absolute Pressure Sensors

o Ideally, the payload should also extend telescopic booms outside of the payload and:

o Gather optical images of the Eartho Store photographs to on-board SD cardso Capture space dust using AeroGel

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Expected Results

oSpace Dust Composition (10^-6)

oRocket FueloMeteor/ Metal FragmentsoGases

oEarth/Payload Images

oDetailed Data through Flight Duration

oThermal Data oSeismic DataoPressure Data

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Concept of Operations

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Circuits initialize and begin collecting and transmitting data.

Data continues to be transmitted.

Rocket skins are shed, pressure within canister drops, boom is extended and begins to collect samples/take photographs.

Power and telemetry is shut down and data collection and transmission ceases. Splashdown.

Payload hits atmosphere, pressure within canister rises, boom is retracted and AeroGel is sealed within shield. Data is still being collected and transmitted over telemetry.

Samples/photographs continue to be collected/taken during descent.

T = 0 min.

T = 1.3 min.

T = 2.8 min.

T = 4.5 min.

T = 5.5 min.

T = 15 min.

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Design Overview

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RockSat 2010 Payload Structure

Factor of Safety = 1.5

AerogelCamera

Electronics

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Payload Functional Block Diagram

Power (NASA)

Microcontroller

X/Y Accelerometer

Z Accelerometer

Pressure Sensor

Thermocouple 1

Thermocouple 2

Thermocouple n

…

ADC

Microcontroller

Solid State Storage Device

Solid State Storage Device

Solid State Storage Device

Solid State Storage Device

G-Switch RBF (Wallops)

To Wallops Telemetry (10x 0-5V A/D 16-Bit, and Asynchronous)

Optical Camera 1 Optical Camera 2

Pressure Sensor

BoomActuator

Microcontroller

ADC

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Design Specifications, Mechanical

oWater Shield

o Material (weight, thermal conductivity, impact and vibration resistance)o Sealing around data connectionso Dynamic sealing around AeroGel following successful data collection

oStructure

o Able to withstand 25G with 50G+ impulse loadso Harmonic Oscillations

oBoom

o Telescopic Mechanical Arm o Surviving launch and vibration loadso AeroGel retrieval

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Design Specifications, Electrical

oAutomation

o Booms, Control Motorso Timed Exposures – Gyroscope and Light sensors

oData Acquisition

o Thermal (Thermocouples)o Seismic (Multi-Axis Accelerometers)o Pressure Measurements (Piezoelectric Strain Gage, Absolute)o Send Measurements through 10x 0-5V 16-bit A/D lines

oPhoto Capture

o Optical Camera (~390 – 750nm)

oImplementation

o Photos stored on redundant SD cards (Multi-GB)o Data sent through NASA telemetryo Payload powered by NASA

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AstroX Team

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Management

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Management

o Schedule

o See Attachment

o Budget

o Mass (15-30lbs)o Boom (7 lbs)o Circuits (1 lb)o Water Shield (2 lbs)o Camera (4 lbs)o Other Sensors (1 lb)

o Monetary Budget

o $850

12%12%

18%12%12

%

35%

Monetary Budget

Optical EquipmentShieldExtendableMaterialsElectronicsAerogel

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Conclusions

oMission RecapoCapture optical images of the earth.oCollect space dust via aerogel.oMeasure thermal, seismic and pressure effects

throughout duration of launch.

oIssueso Sufficient funds oEngineering successoWaterproofing payloadoExtreme vibrations

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Questions?