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SOCD Mission CDR

The purpose of this mission is to demonstrate launching CubeSats from the Wallops 17” sounding rocket form-factor. Once ejected, the CubeSats will conduct experiments and transmit data to mobile ground stations at Wallops and in Kentucky. Key partners include Cal Poly and Kentucky Space, leveraging the P-POD standard. The payload, based on CP4, aims to test the C&DH board. The mission involves successful ejection of CubeSats and data reception at ground stations. Mechanical details include RailNameHere and Pedestal design for payload alignment. The ADAMASat payload features an antenna deployment test and radio link overview. Success relies on integration, testing, and data reception criteria. California Polytechnic University's PolySat program background is also outlined in the mission details.

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SOCD Mission CDR

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  1. SOCD Mission CDR www.kentuckyspace.com

  2. SOCEM • Sub- • Orbital • CubeSat • Experimental • Mission

  3. SOCEM Experiment Concept

  4. Trajectory Estimate

  5. SOCEM Purpose • The purpose of this mission is to demonstrate the feasibility of launching CubeSats from the Wallops 17” sounding rocket form-factor. • Once ejected, the CubeSats will carry out experiments and return data via telemetry to mobile ground stations deployed at Wallops and existing ground stations in Kentucky.

  6. Partners • Cal Poly partnering to provide RailNameHere and a CubeSat Experiment • Kentucky Space: CubeSat, Sounding Rocket, High-Altitude Balloon Programs • NASA Wallops Flight Facility Sounding Rockets Program

  7. Assumptions • Blow-off door 6”x6” • Deck ½” below door opening • Remove-Before-Flight Pin removed once satellites integrated into RailNameHere • 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)

  8. Success Criteria • Minimum Success Criteria • Integration of RailNameHere in Malemute payload section • Delivery and Integration of CubeSats into rail system • Acceptance testing of complete payload • Comprehensive Success Criteria • Successful ejection of CubeSats • Reception of telemetry data from CubeSats on portable ground stations at Wallops and stations in Kentucky • Successful actuation with monofilament cutter system

  9. CubeSat Background Developed in 1999 by Cal Poly and Stanford Universities 10 cm cube and 1 Kg “1U” standard “High risk” mission Student innovation Leverage COTS technologies Short Development cycles Access to space for Universities International standard with many programs developing

  10. CubeSat Form Factor

  11. P-POD 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-T73 Aluminum and anodized with Teflon impregnation.

  12. PPOD Mechanical Detail

  13. Footprint

  14. RailNameHere • Description of the rail system that will be used for this mission goes here

  15. Pedestal Design • Pedestal provides alignment of CubeSat center-line with blow-off door center. • Provide mechanical interface to deck and RailNameHere. • Designed to provide overall centerline balance for the payload.

  16. Mass Budget and Balancing on Rocket Centerline • Balance Payload by adjusting mass properties of the Pedestal • RailNameHere mass properties and solid model in process

  17. Mechanical Interface:RailNameHere to Deck 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 RailNameHere bolt pattern Pedestal bottom designed to interface directly with payload deck via brackets with .2”-dia holes. Tapping of the deck will be necessary.

  18. Mechanical Interface:Blow-off door and CubeSats 2U KY Space Payload will interface directly with the inner surface of the rocket, via a rapid-prototyped polymer. 1U Cal Poly payload will sit behind the KY Space Payload, at the back of the P-POD

  19. Kentucky Space ADAMASat • Antenna Deployment and Mono-filament Actuator Test • 2U (10cmx10cmx20cm) form factor • Interface to rocket door • Nichrome and monofilament actuator experiment • 2m amateur band telemetry downlink

  20. Radio Link Overview • ADAMASat • 1/2 wavelength dipole antenna; tape measure folded to sides of ADAMASat • 300 mW Transmitter at 144.39 MHz • Ground Stations: • Deployed at Wallops: • Custom designed CP yagi antennas • Standard 3dB arrow antennas • Kentucky: 10dB CP yagi antennas, full ground station.

  21. Flight Comm - Transmitter • Micro-Trak 300 operates on 144.39 MHz • Transmit power : 300mW (24.7dBm) • Current consumption : 180mA • Data rate : 1200 Baud AFSK • PCB dimensions : 1 X 3.3 Inches • Weight : < 1 ounce • Connector : SMA Female

  22. ADAMASat ConOps • T+x: Satellite Ejection • 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)

  23. California Polytechnic UniversityPolySat Program Four Orbital Satellites CP1, 2, 3, and 4 CP1 and 2 were lost due to launch vehicle failure CP3 is currently operational in orbit CP4 is semi-operational in orbit and experiencing C&DH lockup issues SOCEM Payload is based on CP4 Mission to test the C&DH board

  24. Mobile Ground Stations • Deployed at Wallops • 2 meter CP antenna using 2 perpendicular Arrow antennas combined with a phasing network • Kenwood TH-D7A handheld radio with built-in TNC • Log and display packet data • Dual Redundant Stations deployed at Wallops

  25. Kentucky Space Stations Lexington and Morehead • High gain CP Yagi antennas • Icom VHF/UHF transceiver • Computer controlled rotator • Automated tracking and radio tuning • Loggers and TNC’s for telemetry

  26. Link Budget @ Wallops • Summary: • 6dB Arrow Antennas • Maximum expected range: 450 km • Link Margin: 24.6 dB

  27. Link Budget @ Kentucky • Summary: • 10dB Antennas – Circular polarization • Maximum expected range: 1100 km • Link Margin: 20.9 dB • Bearing: Azimuth: ~ 87°, Elevation: 10° (Based on STK simulations)

  28. Antenna Pointing angle • Bearing • Az ~ 87° with respect to North • El ~ 10° with respect to Horizon

  29. www.kentuckyspace.com

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