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SOCD Mission CDR

SOCD Mission CDR. www.kentuckyspace.com. SOCD Mission. S ub- O rbital C ubeSat D emonstration Mission. Wallops Sounding Rocket Launch Vehicles. Altitude versus Payload Weight Performance. Terrier-Malemute.

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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. Trajectory Estimate

  9. 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.

  10. 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

  11. Requirements • 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)

  12. Success Criteria • Minimum Success Criteria • Integration of rail system 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

  13. CubeSat Standard NEEDS THE DRAWING FROM THE CDS Started in 1999 through CalPoly and Stanford Universities. Allows the use of higher risk components and encourages student innovation. Must conform to 10 cm cube and weight less than 1 Kg. Because of relatively cheap launch cost many universities have gained access to space. Much shorter development schedules. Planned missions include the first university payloads to be launch by NASA September 2008

  14. MK III (I’m not sure what to call it) NEEDS DRAWINGS/PICS OF PPODS Adapted from a CubeSat deplorer developed by CalPoly. Has flight heritage from several previous CubeSat missions. 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. September 2008

  15. RailNameHere

  16. 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.

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

  18. CutSat Structural Design

  19. CutSat Block Diagram

  20. 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

  21. 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

  22. Additional Media

  23. Additional Media

  24. Telemetry Format

  25. Flight Communication 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 5 January 2020

  26. Flight Communication 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 5 January 2020

  27. Flight Communication Matching Circuit (either one can be used) Method I ZLOAD = (10.122 – j349.89) Ω L = 0.41 uH C = 44.1 pF Method II ZLOAD = (10.122 – j349.89) Ω L1 = 0.36 uH L2 = 27.56 nH 5 January 2020

  28. 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)

  29. 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

  30. Ground Station Hardware Mobile Ground Station 2 M Arrow antenna Design a CP antenna using 2 arrow antennas mounted perpendicular to each other and combined with a phasing network Kenwood TH-D7A handheld radio with built-in TNC Serial logger to display and store the packets 5 January 2020

  31. Ground Station Hardware Kentucky Space Earth Stations High gain CP Yagi antennas Icom VHF/UHF transceiver Computer controlled rotator PC with automated tracking and radio tuning software Serial loggers and TNC’s to display and store the telemetry 5 January 2020

  32. Ground Station Hardware Running Hyperterminal 5 January 2020

  33. Ground Station Hardware Running Mix-W 5 January 2020

  34. Link Budget @ Wallops 5 January 2020

  35. Link Budget @ Kentucky 5 January 2020

  36. Antenna Pointing angle Bearing Az ~ 87° with respect to North El ~ 10° with respect to Horizon 5 January 2020

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

  38. www.kentuckyspace.com

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