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SOCD Mission CDR

SOCD Mission CDR. www.kentuckyspace.com. SOCEM. S ub- O rbital C ubeSat E xperimental M ission. SOCEM Experiment Concept. Trajectory Estimate. SOCEM Purpose.

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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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