1 / 8

Summer Projects Review:

Summer Projects Review:. Current Status. 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

aileen
Download Presentation

Summer Projects Review:

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  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 0.0505C. • 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 Review6th Aug. 2008SRC SPACE ACADEMY

  3. 50 nanoseconds of peak current (>400mA) 1.11amps at 4.5Ω (typical) Set/Reset circuit on ADCS Set/Reset strap on HMC1053 Summer Review6th Aug. 2008SRC SPACE ACADEMY

  4. 1U CubeSat Electrical Power Supply from Clyde Space • 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/m2) • Battery capacity 1.25Ah PSU Main Features Summer Review6th Aug. 2008SRC SPACE ACADEMY

  5. Testing of the PSU • 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 Summer Review6th Aug. 2008SRC SPACE ACADEMY

  6. GOALS Test flight and dev board Incomplete Specify physical interfaces Complete Set up and Software Development Environment Complete Write ADCS software Incomplete Fully interface subsystems Incomplete OBDH KEY FACTS Majority of the board runs on 3.3V logic Board includes +5V and +3.3VVCC 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 Review6th Aug. 2008SRC SPACE ACADEMY

  7. Summer Review6th Aug. 2008SRC SPACE ACADEMY

  8. NORMAL OPERATING PROCEEDURE PSU beacon OBDH COMS PAY ADCS CAM SD 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. Sunlight Eclipse Launch Safe Summer Review6th Aug. 2008SRC SPACE ACADEMY

More Related