SOCD Mission CDR www kentuckyspace com SOCEM

SOCD Mission CDR www. kentuckyspace. com

SOCEM o Subo Orbital o Cube. Sat o Experimental o Mission Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 2

SOCEM Experiment Concept Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 3

Trajectory Estimate Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 4

SOCEM Purpose o o The purpose of this mission is to demonstrate the feasibility of launching Cube. Sats from the Wallops 17” sounding rocket form-factor. Once ejected, the Cube. Sats will carry out experiments and return data via telemetry to mobile ground stations deployed at Wallops and existing ground stations in Kentucky. Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 5

Partners o o o Cal Poly partnering to provide Rail. Name. Here and a Cube. Sat Experiment Kentucky Space: Cube. Sat, Sounding Rocket, High. Altitude Balloon Programs NASA Wallops Flight Facility Sounding Rockets Program Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 6

Assumptions o o Blow-off door 6”x 6” Deck ½” below door opening Remove-Before-Flight Pin removed once satellites integrated into Rail. Name. Here Foot switches on each satellite will inhibit the satellite power system until ejection (Satellites will be self contained and will require no electrical interface with the rocket) Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 7

Success Criteria o Minimum Success Criteria n n n o Integration of Rail. Name. Here in Malemute payload section Delivery and Integration of Cube. Sats into rail system Acceptance testing of complete payload Comprehensive Success Criteria n n n Successful ejection of Cube. Sats Reception of telemetry data from Cube. Sats on portable ground stations at Wallops and stations in Kentucky Successful actuation with monofilament cutter system Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 8

Cube. Sat Background o o o o Developed in 1999 by Cal Poly and Stanford Universities 10 cm cube and 1 Kg “ 1 U” standard “High risk” mission Student innovation Leverage COTS technologies Short Development cycles Access to space for Universities International standard with many programs developing Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 9

Cube. Sat Form Factor Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 10

P-POD o o o Poly Picosatellite Orbital Deployer (P-POD) Flight heritage and qualification for a variety of launch vehicles Robust rail and spring system that assures operation in space environment Third generation has larger access ports Made of 7075 -T 73 Aluminum and anodized with Teflon impregnation. Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 11

PPOD Mechanical Detail Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 12

Footprint Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 13

Rail. Name. Here o Description of the rail system that will be used for this mission goes here Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 14

Pedestal Design o o o Pedestal provides alignment of Cube. Sat center -line with blow-off door center. Provide mechanical interface to deck and Rail. Name. Here. Designed to provide overall centerline balance for the payload. Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 15

Mass Budget and Balancing on Rocket Centerline o o Balance Payload by adjusting mass properties of the Pedestal Rail. Name. Here mass properties and solid model in process Draft 26 March 2009 Draft V 4 Component Mass (lb) CG Location (in) Torque (ft*lb) KY Space Payload 4. 41 -4. 09 -1. 51 Cal. Poly Payload 2. 20 2. 09 0. 38 Rail System 3. 86 0. 00 Pedestal 6. 85 1. 97 1. 13 Total 17. 33 Kentucky Space Proprietary Information 0. 00 16

Mechanical Interface: Rail. Name. Here to Deck o o o Pedestal sits between P-POD and payload deck, and elevates the P-POD 1”, thereby centering it on the 6” x 6” rocket door. Pedestal top designed to interface directly with Rail. Name. Here bolt pattern Pedestal bottom designed to interface directly with payload deck via brackets with. 2”-dia holes. Tapping of the deck will be necessary. Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 17

Mechanical Interface: Blow-off door and Cube. Sats o o 2 U KY Space Payload will interface directly with the inner surface of the rocket, via a rapid-prototyped polymer. 1 U Cal Poly payload will sit behind the KY Space Payload, at the back of the P-POD Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 18

Kentucky Space ADAMASat o o o Antenna Deployment and Mono-filament Actuator Test 2 U (10 cmx 20 cm) form factor Interface to rocket door Nichrome and monofilament actuator experiment 2 m amateur band telemetry downlink Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 19

Radio Link Overview o ADAMASat n n o 1/2 wavelength dipole antenna; tape measure folded to sides of ADAMASat 300 m. W Transmitter at 144. 39 MHz Ground Stations: n Deployed at Wallops: o o n Custom designed CP yagi antennas Standard 3 d. B arrow antennas Kentucky: 10 d. B CP yagi antennas, full ground station. Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 20

Flight Comm - Transmitter o Micro-Trak 300 operates on 144. 39 MHz n n n Transmit power Current consumption Data rate PCB dimensions Weight Connector Draft 26 March 2009 Draft V 4 : : : 300 m. W (24. 7 d. Bm) 180 m. A 1200 Baud AFSK 1 X 3. 3 Inches < 1 ounce SMA Female Kentucky Space Proprietary Information 21

ADAMASat Con. Ops o T+x: Satellite Ejection n n o o o Antennas Deployed (held passively by PPOD frame) Foot switch energizes satellite power buses Ejection + 5 s: Telemetry Beacon Begins Ejection + 280 s: Cutter Experiment Begins Ejection + 290 s: Telemetry updated with experiment results (continues until impact) Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 22

California Polytechnic University Poly. Sat Program o Four Orbital Satellites n n o o CP 1, 2, 3, and 4 CP 1 and 2 were lost due to launch vehicle failure CP 3 is currently operational in orbit CP 4 is semi-operational in orbit and experiencing C&DH lockup issues SOCEM Payload is based on CP 4 Mission to test the C&DH board Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 23

Mobile Ground Stations o o o Deployed at Wallops 2 meter CP antenna using 2 perpendicular Arrow antennas combined with a phasing network Kenwood TH-D 7 A handheld radio with built-in TNC Log and display packet data Dual Redundant Stations deployed at Wallops Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 24

Kentucky Space Stations Lexington and Morehead n n n High gain CP Yagi antennas Icom VHF/UHF transceiver Computer controlled rotator Automated tracking and radio tuning Loggers and TNC’s for telemetry Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 25

Link Budget @ Wallops Summary: • 6 d. B Arrow Antennas • Maximum expected range: 450 km • Link Margin: 24. 6 d. B Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 26

Link Budget @ Kentucky Summary: • 10 d. B Antennas – Circular polarization • Maximum expected range: 1100 km • Link Margin: 20. 9 d. B • Bearing: Azimuth: ~ 87°, Elevation: 10° (Based on STK simulations) Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 27

Antenna Pointing angle o Bearing n n Az ~ 87° with respect to North El ~ 10° with respect to Horizon Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 28

www. kentuckyspace. com Draft 26 March 2009 Draft V 4 Kentucky Space Proprietary Information 29