MOTS Platform › Power Converters

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Power Converters

For space and aviation

The MOTS Platform of Power Converters is tailored for high-reliability applications in the aerospace industry. Engineered for efficiency and dependability, our converters can be customized to include features such as high efficiency, minimal ripple, and precise regulation. We can cater designs to meet the specific needs of your vehicle or application. With a flexible design approach, our converters adapt to a diverse environments, offering stable power for critical systems. 

Products built

Note: these are past examples of how MOTS Power Converter IP blocks have been used. All specifications can be customized.

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Description

A stackable power converter system for space and aviation. Designed to support a range of applications and power requirements, including: space stations, electric aircraft, GEO/MEO/LEO satellites, scientific payloads, and more.

  • Radiation tolerant
  • Power dense and efficient
  • Stackable for high-voltages (>1 kV)
  • Customizable
  • Designed for high-reliability

Specifications

Description

The product is a GaN-based SpaceVPX power supply for New Space. The power supply featured: 1) a fully analog discrete PWM controller from logic gates, op amps, and comparators. This makes component sourcing easier, as the design is not dependent on a single PWM controller IC, 2) varying power conversion topologies: phase shifted full-bridge with synchronous rectification, multi-output and split-rail flybacks, and synchronous buck converters, and 3) an onboard microcontroller with a digital interface allows for software configurable setpoints. Physical switches allow for software lockout and uses predefined setpoint configurations.


Description

The application is a satellite plasma thruster that can be powered by a variety of fuels, including: water, nitrogen, iodine, xenon, or krypton. SOE developed: 1) a propellant controller responsible for controlling valves, driving heating elements, and monitoring telemetry to be streamed back to the data bus; and 2) a thruster controller (ie a power processing unit (PPU)) steps up the bus voltage, which in turn biases the RF amplifier used to excite electrons in the gas.

Description

The application is for a satellite that will be part of a constellation. The design uses: 1) a fully analog discrete PWM controller from logic gates, op amps, and comparators, as previously developed and tested by SOE. A discrete approach provides flexibility for component swaps based on the radiation environment of the program or supply chain shortages, and 2) dual redundant boost converters to meet the vehicle’s fault tolerance architecture.


Interested?

Interested in solving your problems with Second Order Effects?

Email or call us at:

connect@soeffects.com

424.290.0617