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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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Aero3760 group 4 cubelicious cdr

AERO3760 Group 4: “Cubelicious” CDR

Alex Bunting

Geoff Chang

Nathan Wallace

Harry Wood

Michael Holmes


Mission objectives

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


Mission requirements

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


Structure

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


Component layout

Component Layout


Assembly plan

Assembly Plan


Power components

Power Components

  • Components:

  • PCB

  • 2xLithium Ion Batteries

  • 4x2U solar panels

  • Zero Voltage Switching (ZVS) Flyback Driver and Cockcroft Walton (CW) Generator


Zvs flyback driver and cw generator

ZVS Flyback Driver and CW Generator


Power consumption

Power Consumption

  • Maximum Margin: 87.61% per cycle in Safe Mode

  • Minimum Margin: 14.19% per cycle in Thrust Mode


Communications

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.


Transceiver board

Transceiver Board

  • Compact Layout

  • On-board 5v-3.3v Regulator

  • Extensive Decoupling Capacitors

  • MOLEX Antenna Interface


On board computer

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)


On board computer1

On-Board Computer


On board computer2

On-Board Computer


Payload magnetometer

Payload - Magnetometer


Module interconnections

Module Interconnections

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


Attitude control

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


Charge exchange thruster

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


Fuel tank

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


Piping

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


Valves

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


Overview of test plans

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


Any questions

Any Questions?


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