Electrical Engineer (EPS), Spacecraft

Katalyst Space Technologies•Broomfield, CO

2d•Onsite

About The Position

Katalyst builds robotic spacecraft that enable dynamic space operations, creating a future where maneuvering, upgrading, refueling, and exploration are as routine as they are on Earth. We are developing the foundational capabilities that make sustained, responsive operations possible, enabling a new era of space activity that strengthens national security and ensures freedom of action in an increasingly contested domain. Working at Katalyst is intense, hands-on, and deeply rewarding. You’ll take real ownership and see your work move from concept to operations in an environment where the problems are hard and the impact is real. We value humility, craftsmanship, and doing things the right way, even when it’s harder. You’ll work closely with thoughtful, driven teammates who push each other to do their best.

Requirements

Bachelor’s degree in electrical engineering or equivalent field.
3+ years of experience designing, testing, or integrating power electronics, spacecraft EPS hardware, battery/solar power interfaces, or closely related high-reliability power systems.
Strong understanding of switch-mode power supply design, DC/DC converter architectures, compensation/stability, magnetics selection, protection circuitry, and practical power electronics debugging.
Experience designing or modifying schematics and PCB layouts for power electronics, including high-current routing, grounding, thermal considerations, creepage/clearance, current sensing, and EMI/EMC-aware layout practices.
Proficiency in Altium or a similar ECAD tool for schematic capture, PCB layout review, design release, and documentation.
Exposure to spacecraft or embedded-system power architectures, including power distribution, load switching, battery management interfaces, solar array regulation, or power telemetry.
Exposure to common digital communication standards (SPI, I2C, UART, CAN, Ethernet) and mixed-signal design best practices for telemetry, control, and power-system interfaces.
Hands-on experience with hardware bring-up, bench testing, and debugging using oscilloscopes, electronic loads, power supplies, DMMs, logic analyzers, and related lab equipment.
Experience writing or executing test procedures, documenting results, and driving board- or component-level troubleshooting through root cause and corrective action.
Must be willing to work extended hours and weekends as needed.

Nice To Haves

Experience integrating power electronics with other spacecraft or embedded subsystems; exposure to environmental testing such as thermal vacuum or vibration is a plus but not required.

Responsibilities

Contribute to the design, iteration, and qualification of Katalyst’s spacecraft Electrical Power System (EPS), including power conversion, power distribution, battery interface electronics, solar array interfaces, protection circuitry, and subsystem power interfaces.
Design, modify, and review schematics, PCB layouts, interface definitions, and analysis packages for spacecraft power electronics, with emphasis on switch-mode power supplies, DC/DC converters, load switching, current sensing, fault protection, and EMI-aware layout practices.
Support integrated operation of EPS hardware during functional, performance, and qualification testing, working directly with test engineers to execute bench, thermal vacuum, vibration, and other qualification test campaigns.
Own integrated functional testing of EPS hardware with avionics, flight software, mechanisms, payloads, and other spacecraft subsystems, ensuring power interfaces behave correctly across nominal, off-nominal, and fault cases.
Plan and execute targeted stress, margin, and performance testing, exercising hardware across design extremes such as input voltage range, load transients, thermal limits, startup sequencing, fault response, and converter stability.
Define design changes and architecture improvements for future spacecraft power systems, including EPS feature upgrades, power budget impacts, redundancy considerations, telemetry needs, and mission-specific power requirements.