CUAVA-2
Status
Operational
Flight time
Last comms
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Note: ISS trajectory information shown until commissioning is complete.
Location
n/a
Speed
n/a
Altitude
n/a
Inclination
n/a
Next pass (SYD)
Spacecraft subsystems
Note: synthetic data below until commissioning is complete.
Battery power
OK
15.1 VSolar panel current
OK
1.6 A
Power consumption
HIGH
5.6 W (avg 3.0 W)
On-board computer
OK
Payload computer
OK
S-band radio
OFF
VHF/UHF radio
OFF
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Attitude control
The spacecraft's attitude determination and control system (ADCS) uses a magnetorquer developed by Deneb Space.
Yaw
0.1°
target: 0°
Δ 0.0°/min
Pitch
37°
target: 40°
Δ 1.2°/min
Roll
–19°
target: –19°
Δ –0.1°/min
Payloads
Payload schedule (nominal)
Electron Density & Debris Instrument (EDDI)
By continuously measuring Earth’s plasma properties, the EDDI instrument is providing valuable data for developing the first accurate and globally varying dataset for the cold plasma in Earth’s ionosphere.
Flight model EDDI held by Quinn Musulin
EDDI Antenna
Electro Permanent Magnetorquer (EPM)
The Electro Permanent Magnetorquer (EPM) is a CubeSat-compatible device used for attitude determination and control on the spacecraft, developed by a team at the University of Sydney’s School of Aerospace, Mechanical and Mechatronic Engineering (AMME). Unlike traditional magnetometers, this magnetorquer uses hard magnetic materials for its core.
In 2023, Deneb Space acquired the intellectual property from the University of Sydney for the EPM design. Subsequently, it was included as a backup payload on WS-1.