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Magnetorquers offer a method of controlling the attitude of a spacecraft. This can be achieved either directly, by interacting with the local Earth’s magnetic field, or more usually in combination with reaction wheels where they allow a method of dumping excess momentum in the wheels without the need for a complex propulsion system.

The use of a magnetic alloy rod produces an amplification effect over an air cored magnetorquer. This allows a system that uses less power and is less susceptible to magnetic torque variations due to temperature.

Each rod is typically bifilar wound for redundancy, or the windings can be activated together to increase the torque produced. Drive circuits for the rods can be supplied if required, but they typically run directly from a switched power output from the on-board power control system.

The Qualification of the magnetorquer rods comes from flight heritage on the BADR-B, Fedsat and MicroLabSat missions.

FUNCTIONAL CHARACTERISTICS

Magnetic moment: from 1Am2 up to 100Am2
Linearity: +/- 5% across operating design range
Residual moment: <0.1Am2
Power: typically 1W from 5Volt supply
Operating range: -35oC to +75oC
Random Vibration: tested to 15g rms
Lifetime: >10years

PHYSICAL CHARACTERISTICS

Length:8cm to 60cm available
Rod core: 6 or 12mm diameter
Mounting feet: 2, 3 or 4 depending on length
Mass: Approx 55g/cm length (12mm core)
Tube finish can be Alochrom or black anodized

INTERFACES

9-way D-type Male connector
Dual pins per winding
Redundant winding

FEATURES

High torque for low power
Small size
Adaptable for size, torque and power to meet optimal system requirements
Redundant windings
Flight heritage

APPLICATIONS

Active damping for spin stabilised, momentum biased and gravity gradient controlled satellites
Momentum dumping of reaction wheels in three axis stabilised spacecraft

Click on the image to download the datasheet.



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Products	Magnetorquer Rod

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	Overview Technical Details Photo's Datasheet Magnetorquers offer a method of controlling the attitude of a spacecraft. This can be achieved either directly, by interacting with the local Earth’s magnetic field, or more usually in combination with reaction wheels where they allow a method of dumping excess momentum in the wheels without the need for a complex propulsion system. The use of a magnetic alloy rod produces an amplification effect over an air cored magnetorquer. This allows a system that uses less power and is less susceptible to magnetic torque variations due to temperature. Each rod is typically bifilar wound for redundancy, or the windings can be activated together to increase the torque produced. Drive circuits for the rods can be supplied if required, but they typically run directly from a switched power output from the on-board power control system. The Qualification of the magnetorquer rods comes from flight heritage on the BADR-B, Fedsat and MicroLabSat missions. FUNCTIONAL CHARACTERISTICS Magnetic moment: from 1Am2 up to 100Am2 Linearity: +/- 5% across operating design range Residual moment: <0.1Am2 Power: typically 1W from 5Volt supply Operating range: -35oC to +75oC Random Vibration: tested to 15g rms Lifetime: >10years PHYSICAL CHARACTERISTICS Length:8cm to 60cm available Rod core: 6 or 12mm diameter Mounting feet: 2, 3 or 4 depending on length Mass: Approx 55g/cm length (12mm core) Tube finish can be Alochrom or black anodized INTERFACES 9-way D-type Male connector Dual pins per winding Redundant winding FEATURES High torque for low power Small size Adaptable for size, torque and power to meet optimal system requirements Redundant windings Flight heritage APPLICATIONS Active damping for spin stabilised, momentum biased and gravity gradient controlled satellites Momentum dumping of reaction wheels in three axis stabilised spacecraft Click on the image to download the datasheet.