1. Summer Projects Review: Current Status

2. ADCS ADCS calibrated in uniform magnetic field using support hardware to mimic the computer onboard the satellite. The mV/gauss change is now known: 1-3mV/gauss for the y axis 30-52mV/gauss for the x axis 34-53mV/gauss for the z axis Pointing variation for the z axis has been calculated, α=2.891° or 0.0505 C. Current passing through the Set/Reset strap on the HMC1053 as its resistance changes due to the ambient temperature has been calculated. This is directly linked to how much power the Set/Reset will draw. Summer Review 6 th Aug. 2008 SRC SPACE ACADEMY

3. 1.11amps at 4.5Ω (typical) Set/Reset circuit on ADCS Set/Reset strap on HMC1053 50 nanoseconds of peak current (>400mA) Summer Review 6 th Aug. 2008 SRC SPACE ACADEMY

4. up to 6 solar arrays 3 battery charge regulators (BCRs) 3 power buses, 2 regulated (3.3V and 5V) and a raw battery bus Bus over-current protection Battery under-voltage protection; if the battery voltage drops below 6.5V, the output buses are disable until the battery voltage reaches 7.5V Telemetry and telecommand via an I2C bus Power consumption <0.1W and weight 152.96g Estimation of power produced when in sunlight 2.11W (solar array efficiency 17%, AM0 = 1.35kW/m 2 ) Battery capacity 1.25Ah 1U CubeSat Electrical Power Supply from Clyde Space PSU Main Features Summer Review 6 th Aug. 2008 SRC SPACE ACADEMY

5. Current Status Solar array equivalent circuit and battery simulator connected successfully I2C bus has been used successfully BCR1 has been damaged – testing has been suspended Testing of the PSU Summer Review 6 th Aug. 2008 SRC SPACE ACADEMY

6. GOALS Test flight and dev boardIncomplete Specify physical interfacesComplete Set up and Software Development EnvironmentComplete Write ADCS softwareIncomplete Fully interface subsystemsIncomplete OBDH KEY FACTS Majority of the board runs on 3.3V logic Board includes +5V and +3.3V VCC power buses Clock speed of MCU is 7.378 MHz Power consumption is around 0.01 W Mass (with physical interfaces) is 90g Tolerances are -40 to +85 ° C Summer Review 6 th Aug. 2008 SRC SPACE ACADEMY

7. Summer Review 6 th Aug. 2008 SRC SPACE ACADEMY

8. Interfacing Physical interfaces are via the cubesat kit system bus Multiplexing and a PowerFET are needed for the ADCS interface. Transceiver does not plug into the cubesat kit bus. Modes outlined. PSU OBDH COMS PAY SD CAM NORMAL OPERATING PROCEEDURE ADCS beacon Summer Review 6 th Aug. 2008 SRC Sunlight Eclipse Launch Safe SPACE ACADEMY