Senior Structural Analyst

Sophia Space•Pasadena, CA

9d•$100,000 - $175,000•Hybrid

About The Position

Sophia Space is hiring a Senior Structural Analyst to own structural analysis for its first flight demonstration and subsequent missions. The role covers coupled loads analysis (CLA), dynamics test predictions and model correlation, piece-part stress analysis, and vibration and shock analysis of avionics boxes and circuit boards. The analyst will turn analysis results into design and test decisions, defend methodologies with launch providers and customer reviewers, and work as a peer with Thermal, Mechanical, and Avionics engineers. The near-term focus is carrying the first flight demonstration from finite element model development through CLA delivery, environmental testing, and flight. The analyst will later help establish structural architecture for larger Modules built from multiple TILE units. The work emphasizes engineering judgment, hand calculations, classical solutions, and risk-conscious use of detailed finite element models. The role also includes close partnership with the Senior Thermal Engineer on thermal-structural coupling, ownership of Sophia Space’s structural analysis toolchain and methods documentation, and mentorship of junior analysts. Expect 1–3 weeks of travel per year for launch provider CLA reviews and environmental test facilities. Candidates with 8 or more years of experience and a record as CLA lead may be considered at the Staff level. The position is primarily in-person in Pasadena, California, with occasional hybrid flexibility based on business needs. It may require access to technology governed by U.S. export-control laws; applicants may need to qualify as a U.S. Person under applicable ITAR and EAR regulations.

Requirements

B.S. in Aerospace Engineering, Mechanical Engineering, or Engineering Mechanics.
Typically 5–8 years of post-degree spacecraft structural analysis experience.
At least one program carried from finite element model development through CLA delivery, dynamics test correlation, and flight.
Documented CLA contribution with a launch service provider.
Extensive NASTRAN experience, including SOL 101, 103, 105, 108, 109, 111, and 112; bulk data fluency; and superelement and component mode synthesis reduction for CLA handoff.
FEMAP and Siemens NX Simcenter or NX Nastran experience, including pre- and post-processing, CAD-to-FEM integration, and traceability from CAD to the finite element model.
Hands-on dynamics testing experience, including pre-test predictions, modal survey, sine, random, and shock testing, and post-test correlation with model updating.
Piece-part detailed-design analysis experience with a stated margin policy and applicable standards.
Avionics box-level dynamics and PCB-level analysis experience, including chassis modal, mounting and isolation, board modal, component natural frequencies, and solder-joint and lead-wire fatigue.
Working knowledge of Steinberg methods and JEDEC JESD22-B103 and B104, with experience correlating PCB-level analysis to board-level vibration tests.
Ability to partner with the Senior Thermal Engineer on thermal-structural coupling, including orbital thermal environments, thermal expansion mismatch, gradient distortion, and joint preload at temperature.
Ability to read exports from thermal tools such as Thermal Desktop, Sinda/Fluint, or equivalent, interpret thermal results, and partner on coupled trades.
Strong command of statics, dynamics, strength of materials, vibration, contact mechanics, fatigue, and fracture.
First-principles engineering approach, including hand calculations, classical solutions, and dimensional analysis, with judgment about when a full finite element run is warranted.
Clear technical writing and ability to defend methodology before launch provider and customer reviewers.
Comfort using AI tools in day-to-day work, interest in adopting AI assistants and agents, and sound judgment about their appropriate use and limitations.

Nice To Haves

M.S. or Ph.D. in a relevant field; this may shift placement toward the Staff level.
Eight or more years of experience and a documented record as CLA lead; candidates may be considered at the Staff level.
Lead-of-analysis history on a flown spacecraft program.
Experience with nonlinear analysis (NASTRAN SOL 400 or NX Advanced Simulation), explicit dynamics (LS-DYNA or Abaqus Explicit), multibody dynamics (Adams or RecurDyn) for deployment kinematics, or acoustic and vibroacoustic analysis (Wave6, VA One, or NASTRAN SEA).
Composites analysis experience.
Small-sat, ESPA-class, CubeSat, or commercial demonstration mission experience, including launch campaign and on-orbit anomaly support.
Python or MATLAB scripting for post-processing and CLA case automation, with exposure to pyNastran, NX Open, or the FEMAP API.
Demonstrated experience applying AI tools and agents, such as LLM assistants like Claude, to structural analysis work, including load case automation, analysis documentation, data reduction, or decision support.

Responsibilities

Own mission CLA, including spacecraft finite element model build and reduction, launch vehicle integration, transient response, and load-cycle delivery to the launch provider.
Coordinate CLA cycles with the launch provider, including model exchange, review participation, anomaly resolution, and reruns when configurations change.
Lead pre-test predictions for modal, sine, random vibration, shock, and acoustic tests, and post-test correlation, including MAC and orthogonality checks, model updating, and design-load reruns using correlated models.
Specify instrumentation with the Integration & Test team and coordinate fixture stiffness and boundary conditions with test facilities.
Perform static, modal, random vibration, sine, and shock analyses of components and primary and secondary structures, including brackets, fittings, mounts, panels, deployables, and mechanisms.
Establish and defend margins for yield, ultimate, buckling, fatigue, and fracture using applicable standards.
Own avionics chassis dynamics analysis, including modal, mounting, isolation, and random vibration and shock response of enclosed electronics.
Analyze printed circuit boards, including board modal frequencies, component natural frequencies, and solder-joint and lead-wire fatigue; apply Steinberg-class methods and relevant JEDEC standards, and correlate against board-level vibration tests.
Partner with the Avionics Lead and Manufacturing Engineer on layout, placement, staking, and mounting decisions affecting vibration and shock margins.
Lead thermal-structural coupling with the Senior Thermal Engineer, including thermal-induced loads, distortion from thermal expansion mismatch, gradient effects, and bolted-joint preload.
Support payload structural accommodation and deployment kinematics with relevant leads.
Own Sophia Space’s structural analysis toolchain and methods documentation, aligned with NASA-STD-7009 model-validation expectations.
Mentor junior analysts as the team grows.