University of Wyoming Dorin Blodgett, Kevin Brown, Heather Choi, Ben Lampe Eric Robinson, Michael Stephens, Patrick Weber October 7,

Mission Overview

Scientific Objectives o Capture optical images of the earth. o Collect space dust. o Provide perspective of what is in our atmosphere. o Measure thermal, seismic and pressure effects throughout duration of launch. o Collect data for future projects 3

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. 4

Mission Requirements The payload shall conform to the requirements set forth in the 2011 RockSat-X User Guide 5

TYPEQUANTITATIVE 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 GravityLies 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 VoltageAll payloads utilizing higher voltage (>28V) shall conformal coat all electronics. 6 Specifications: Physical Constraints

Specifications: Performance Parameters KEY PERFORMANCE PARAMETERVALUE 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-Load25 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 7 (Source: RockSat Payload Canister User’s Guide 2010)

Success Criteria o At minimum, the payload shall gather data during launch, at apogee, and during reentry through the use of: o Thermocouples o 3-axis Accelerometers o 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 Earth o Store photographs to on-board SD cards o Capture space dust using AeroGel 8

Expected Results o Space Dust Composition (10^-6) o Rocket Fuel o Meteor/ Metal Fragments o Gases o Earth/Payload Images o Detailed Data through Flight Duration o Thermal Data o Seismic Data o Pressure Data 9

Concept of Operations 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.

Design Overview 11

RockSat 2010 Payload Structure 12 Factor of Safety = 1.5

Payload Functional Block Diagram 13 Power (NASA) Microcontroller X/Y Accelerometer Z Accelerometer Pressure Sensor Thermocouple 1 Thermocouple 2 Thermocouple n … ADC Microcontroller Solid State Storage Device G-SwitchRBF (Wallops) To Wallops Telemetry (10x 0-5V A/D 16-Bit, and Asynchronous) Optical Camera 1 Optical Camera 2 Pressure Sensor Boom Actuator Microcontroller ADC

Design Specifications, Mechanical o Water Shield o Material (weight, thermal conductivity, impact and vibration resistance) o Sealing around data connections o Dynamic sealing around AeroGel following successful data collection o Structure o Able to withstand 25G with 50G+ impulse loads o Harmonic Oscillations o Boom o Telescopic Mechanical Arm o Surviving launch and vibration loads o AeroGel retrieval 14

Design Specifications, Electrical o Automation o Booms, Control Motors o Timed Exposures – Gyroscope and Light sensors o Data 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 o Photo Capture o Optical Camera (~390 – 750nm) o Implementation o Photos stored on redundant SD cards (Multi-GB) o Data sent through NASA telemetry o Payload powered by NASA 15

AstroX Team 16

Management 17

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 18

Conclusions 19 o Mission Recap o Capture optical images of the earth. o Collect space dust via aerogel. o Measure thermal, seismic and pressure effects throughout duration of launch. o Issues o Sufficient funds o Engineering success o Waterproofing payload o Extreme vibrations

Questions? 20