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AERO3760 Group 4: “ Cubelicious ” CDR

AERO3760 Group 4: “ Cubelicious ” CDR. Alex Bunting Geoff Chang Nathan Wallace Harry Wood Michael Holmes. Mission Objectives. Monitor Earth’s magnetic field over an extended period Perform technology demonstration of USYD Charge Exchange Thruster

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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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