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AERO3760 Group 4: “ Cubelicious ” CDR

The Cubelicious mission aims to monitor Earth's magnetic field over an extended period while demonstrating the USYD Charge Exchange Thruster (CXT) technology for satellite station keeping in low Earth orbit (300 km). Key mission requirements include launching by 2018, utilizing an ISIS 2U model, and equipping the satellite with advanced sensors and communication systems. This mission involves meticulous testing of various components, including the onboard computer, antennas, and power systems, to ensure optimal function and performance in a sun-synchronous orbit.

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AERO3760 Group 4: “ Cubelicious ” CDR

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  1. AERO3760 Group 4: “Cubelicious” CDR Alex Bunting Geoff Chang Nathan Wallace Harry Wood Michael Holmes

  2. Mission Objectives • Monitor Earth’s magnetic field over an extended period • Perform technology demonstration of USYD Charge Exchange Thruster • CXTs used for station keeping to extend orbit life

  3. Mission Requirements • Launch and Orbit • 2018 to allow for CXT development. • LEO Sun Synchronous 300km • Attitude and Position Determination • Required to map magnetic field • Surrey Technology GPS and ISIS Sun-Sensor • Magnetic field measurements • ISIS Magnetometer • Thruster for station keeping • Custom high voltage 15kV power supply • Custom argon gas propellant tank

  4. Structure • A standard ISIS 2U Model • Shock and vibration tested • Easy component mounting • Component Layout • Minimise centre of gravity through symmetrical design • Minimise moments of inertia through clustering at centre

  5. Component Layout

  6. Assembly Plan

  7. Power Components • Components: • PCB • 2xLithium Ion Batteries • 4x2U solar panels • Zero Voltage Switching (ZVS) Flyback Driver and Cockcroft Walton (CW) Generator

  8. ZVS Flyback Driver and CW Generator

  9. Power Consumption • Maximum Margin: 87.61% per cycle in Safe Mode • Minimum Margin: 14.19% per cycle in Thrust Mode

  10. Communications • The Texas Instruments CC1120 UHF Band RF Transceiver. • Operating half-duplex on the 433 MHz Bandwidth. • Low power output: ~100mW, requires power amplifier. • Mission-tested: CAPE-1 (University of Louisiana) and CP4 (California Polytechnic Institute) missions. • SPI Interface, dual buffer system. • Transmission via the ISIS Deployable UHF/VHF antenna system in Dipole-Dipole configuration. • Utilising the ISIS antenna's integrated 2W power amplifier configured to output at 1W. • Operating on 3.3v Logic and Power levels. • Second dipole antenna is wired as backup.

  11. Transceiver Board • Compact Layout • On-board 5v-3.3v Regulator • Extensive Decoupling Capacitors • MOLEX Antenna Interface

  12. On-Board Computer • The on-board computer for the satellite will be a custom-made PCB consisting of the following components: • Texas Instruments MSP430F2419 Microprocessor[3] • Texas Instruments UA78L02A 3-terminal 2.6V voltage regulator [4] • Microchip 25AA1024 Serial EEPROM Module [5] • Multicomp SDMBF-00915B0T2 Push-Push SD Memory Card Connector (Type B) [6] • Intersil HIN208ECBZ RS-232 transmitter/receiver interface circuit chip [7] • Samtec TSW-107-02-S-D 14-pin terminal strip (debug header port) [8] • IQD Frequency 12SMX B 16MHz crystal oscillator [9] • CNR9F: DB9 Port (for RS-232 Driver) • 2 x 18pF Capacitors (for oscillator) • 5 x 100nF Capacitors (for RS-232 Driver)

  13. On-Board Computer

  14. On-Board Computer

  15. Payload - Magnetometer

  16. Module Interconnections • Module interconnections are shown below. The red lines are power connections and the blue lines are the control wiring.

  17. Attitude Control • Most components designed by hand • Refinement critical when CXT is fully developed • Reaction Wheels • Blue Canyon Technologies • Torque: 0.6 mN.m • Power usage: 0.1 W • Size: 43x43x18 mm • Total of 3 used

  18. Charge Exchange Thruster • Developed by University of Sydney • Total of 12 used, in sets of 6 • Still in development • Fuel: Argon gas or Iodine solid • Thrust: Approx. 0.08 mN • Specific Impulse: Approx. 15,000 s • Fuel rate: Unknown

  19. Fuel Tank • Operating fuel rate, pressure and fuel type not confirmed • Designed for Argon gas • Made of aluminium • Leaks before fracture • Inner radius: 23.5 mm • Outer radius: 27 mm • Safety factor to yielding: 2

  20. Piping • Same pressure as tank • Aligned with the tank’s brace • Designed for Argon gas • Made of aluminium • Inner radius: 5.2 mm • Outer radius: 6 mm • Safety factor to yielding: 2

  21. Valves • Highly dependent on fuel rate and pressure • Design not possible until CXTs confirmed • Likely to use a piezoelectric actuator, similar to that shown on the right • Uses high voltage, similar to CXTs • May need to adjust pressure to operate correctly Source: M.C. Louwerse, H.V. Jansen, M.C. Elwenspock, “Modular Thruster and Feeding System for Micro-Satellite”, University of Twente

  22. Overview of Test Plans • Unit Testing of individual hardware modules with associated software. • Bus Testing of SPI and I2C busses with simulation of hardware loss. • Radiation Testing during operation • Thermal Shock Testing • Power Load Testing • Recovery Mode Testing Abstract Integration Plan: Structure -> EPS -> OBC -> Transceiver -> Antenna -> Reaction Wheels -> Sensory Suite -> Thruster Tank -> Thrusters and Power Board -> Solar Cells

  23. Any Questions?

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