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SOCD Mission CDR

The CubeSat Demonstration Mission aims to demonstrate the feasibility of launching CubeSats from the Terrier-Malamute rocket. The mission will carry out experiments and return data via telemetry to ground stations in Kentucky. This mission is a high-risk, student-led project leveraging COTS technologies.

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SOCD Mission CDR

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  1. SOCD Mission CDR www.kentuckyspace.com

  2. SOCD Mission • Sub- • Orbital • CubeSat • Demonstration • Mission

  3. Wallops Sounding Rocket Launch Vehicles

  4. Altitude versus Payload Weight Performance

  5. Terrier-Malemute The Terrier-Malamute is a two-stage, solid fuel rocket consisting of a Terrier 1st stage and a Malamute 2nd stage. It is capable of lifting a 200 lb payload to an apogee of approximately 700 km or a 500 lb payload to approximately 400 km.

  6. Experiment Concept

  7. Trajectory Estimate

  8. SOCD Mission Purpose • The purpose of this “path finder” 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.

  9. 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

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

  11. 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

  12. CubeSat Standard Developed in 1999 by CalPoly 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

  13. CubeSat Form Factor

  14. MK III (I’m not sure what to call it) Adapted from a CubeSat deplorer developed by CalPoly. Flight heritage Simple design with rail and spring system that assures insertion into space environment. Has three iterations of the initial design with the third, and revision that will fly, having larger access ports to the payloads. Made of 7075-T73 Aluminum and anodized with Teflon impregnation.

  15. PPOD Mechanical Detail

  16. Footprint

  17. RailNameHere

  18. Pedestal Design • Pedestal provides alignment of CubeSat center-line with blow-off door. • Provide mechanical interface to deck and RailNameHere system. • Machined to provide balance on the center-line of the rocket.

  19. Mass Budget and Balancing on Rocket Centerline • Balanced through machining of the Pedestal CG • RailNameHere mass properties and solid model in process

  20. 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 P-POD Mk 3 bolt pattern Pedestal bottom designed to interface directly with payload deck via L-brackets with .2”-dia holes. Tapping of the deck will be necessary.

  21. 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

  22. Kentucky Space “CutSat” • 2U (10cmx10cmx20cm) form factor • Interface to rocket door • Nichrome and monofilament actuator experiment • 2m amateur band telemetry downlink

  23. CutSat Structural Design

  24. Antenna System Drawings • Left: 2u cubesat without antennas • Center: antennas wrapped around 2u cubesat • Right: 2u cubesat with antennas deployed

  25. Antenna Mounting Plate • Antenna mounting plate made of epoxy fiberglass circuit board material • Copper strips on board allow attachment of tape antenna elements • Back side of board available for matching circuits, if needed

  26. CutSat Block Diagram

  27. Payload Mass Budget

  28. Design Decisions Cutter Circuit Baseline of one cutter circuit Multiple cutter circuits added in a later rev Payload Layout Layout boards on bottom face of cube Use stack implementation if time permitting

  29. Antenna Deployment MechanismControl Circuit Circuit is protected against fail-open and fail-closed Current path through two IC’s in series Two current paths in parallel intersecting in the middle Circuit is protected during processor startup Active High Enable Active Low Enable Adjustable Current Limit Adjustable from 600mA to 1.2A Current limit set via an I2C Potentiometer

  30. Antenna Deployment MechanismHardware Payload Interface Module Custom board to be used on KySat-1 Contains ADM control circuit and interface Nichrome Cutter Built in house to be used on KySat-1 22 turn coil of 36 Ga Nichrome wire ~5.5 Ohms Housed in a glass tube • Insert Antenna Cutter Pic

  31. Additional Media

  32. Additional Media

  33. Telemetry Format (I don’t think we made final decisions on that yet. – Samir) • FSK data packets • Short CW Morse Code beacons with experiment results (easier to decode)

  34. Radio Link Overview • CutSat • ¼ wavelength dipole antenna; tape measure folded to sides of CutSat • 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.

  35. 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

  36. Flight Comm - Radiation • 2M Rocket antenna • λ/4 dipole antenna oriented along 0° – 180° axis • Width of the antenna (printed/measuring tape) :11/16” • 2 arms of the dipole are λ/8 each @ 2m • Reasonably omni-directional pattern • 3 dB Beam width ~ 40° • Linearly polarized antenna • Gain ~ 1.82 dB • Zin ~ (10.122 – j349.89) Ω

  37. CutSat Concept of Operations • T+x: Satellite Ejection • Antennas Deployed (held passively by PPOD frame) • Foot switch energizes satellite power buses • Ejection + 20 s: Telemetry Beacon Begins • Ejection + 280 s: Cutter Experiment Begins • Ejection + 290 s: Telemetry updated with experiment results (continues until impact)

  38. California Polytechnic UniversityPolySat Program Launched 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 Payload is representative of CP4 Mission to test the C&DH board A 1kg mass model will be used if the launch deadline cannot be met

  39. 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

  40. 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

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

  42. 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)

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

  44. Risks • Major Risks and Mitigation Plans described here….

  45. www.kentuckyspace.com

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