Sakshham R Sahai

I design, analyze, and test structures and mechanical systems, from first-principles load analysis and CAD (SolidWorks, Fusion 360) to vibration analysis, controls, and wind tunnel experiments (MATLAB, LabVIEW). Looking for mechanical design, structural analysis, and test engineering full-time roles, internships, and co-ops (up to 12 months), including advanced air mobility, autonomous delivery systems, and launch vehicles.

Available to start immediately · full-time roles, internships & co-ops (up to 12 months)

6engineering projects

5reports & decks to read

B.S. Aerospace Engineering, 2026 · Department of Mechanical and Aerospace Engineering, University of California San Diego

Where I've worked and studied

Teaching, hands-on vehicle design, and my degree.

MAR 2026 – JUN 2026

Course Reader, MAE 104: Aerodynamics

University of California San Diego

Evaluated work from 82 upper-division students on flow physics, performance, and computational methods; gave written feedback.

SEP 2023 – SEP 2024

Mechanical Engineer, Triton Solar Car

University of California San Diego

Designed and assembled the driver pedal assembly for a 450 lb single-seat solar race car using first-principles load analysis for reliable force transfer.

SEP 2022 – JUN 2026

B.S. Aerospace Engineering

Department of Mechanical and Aerospace Engineering, University of California San Diego · Specialization: Astrodynamics & Space Applications

Coursework: Aerospace Structures, Aerospace Materials, Solid Mechanics, Aerodynamics, Fluid Mechanics, Space Propulsion, Computational Methods.

Design, analysis, and test

Each project links to its write-up. Reports open right here on the page.

Concept render

MATLAB · OpenVSP/VSPAero · SolidWorks · Jan – Jun 2026

WHOVER: Winged Hovering Electric Rotorcraft

Defined the structure of a 460 kg single-seat eVTOL: aluminum frame (spars, ribs, landing struts) with CFRP shell (fuselage, rotor ducts, ailerons), benchmarked against Joby S4 and Archer Midnight.
Closed a 35 kWh mission energy budget with a 6.5 kWh (19%) reserve by sizing two tilting 1.7 m rotors with momentum theory across hover, climb, transition, and cruise.
Justified a fixed-wing hybrid over multirotor (wings carry at least 40% of cruise lift) and held predicted noise to 70.8 dB at 300 ft with owl-inspired serrations and tip winglets.

460 kg MTOW35 kWh70.8 dB

As built

Test stand · IMU · Raspberry Pi Pico · MAE 155B

Ducted Coaxial PAV: Propulsion & Attitude Control

Verified propulsion by measuring 4.3 N thrust per rotor near 10,000 RPM at over 60 W (matching the 4.4 N manufacturer spec) on a test stand with 7-in propellers and 2300 KV motors.
Quantified vehicle inertia (Ixx, Iyy, Izz = 0.0057, 0.0055, 0.0102 kg·m²) with swing and bifilar pendulum tests; traced the mass overrun to wiring, adhesive, and mounting hardware.
Lifted off several inches at about 95% of available power using an IMU/Pico closed-loop attitude controller driving duct vanes.

4.3 N / rotor0.8 kg~95% power

MATLAB · Python · 2025

Wing & Spar Structural Analysis Tool

Built a MATLAB tool that computes cross-section stiffness (EA, EIyy, EIzz, EIyz, GJ) for single-cell wings and spars using thin-wall beam theory.
Cut spar mass 80.7% (62.7 to 12.1 lb) and wing mass 88.2% in an aluminum-to-CFRP trade study across five critical V-n load cases.

Wind tunnel test section and instrumentation

MATLAB · LabVIEW · MAE 175A

Wind Tunnel Testing: Clark Y-14 Airfoil

Calibrated fan power to airspeed with under 0.004% velocity uncertainty using a Pitot-static probe and weighted regression.
Measured lift, drag, and moment at 20–50 m/s (Re about 50,000–120,000) with pressure taps, a wake-survey rake, and a sting balance; the three methods agreed within 2σ.
Found stall onset shifting from 6° to 12° as speed rose, and center of pressure moving from 0.35c to 0.25c.

Measured versus modeled frequency response

MATLAB · Accelerometers · Digilent AD2 · MAE 175A

Structural Vibration & Modal Analysis

Characterized three modes (10, 17.3, 28 Hz) of a 3-story shear building, with floor amplification ratios and phase lags from FFT, PSD, and the Hilbert transform.
Derived H21 and H31 transfer functions with a 0.073 damping estimate, validated against Bode plots averaged over three trials.
On a rotor blade, measured a 179° root-to-tip phase reversal and 1.3× mid-span amplification, repeatable across three trials.

Helicopter pitch and yaw tracking response

MATLAB · Simulink · MAE 175A

Multivariable Control: 2-DOF Helicopter

Modeled a coupled pitch/yaw helicopter as a first-order MIMO system; verified PID loops with Nyquist and Bode margins.
Tracked ±5° pitch and ±20° yaw references with a 6-state LQR and decoupling pre-compensator, then traced residual oscillation to a loose stand, slip-ring friction, and wall downwash.

Tools and methods

What I use to design, simulate, and verify.

Software & CAD

MATLABSimulinkPythonSolidWorksFusion 360OnshapeANSYS (FEA)OpenVSP/VSPAero

Analysis & Controls

Structural AnalysisComposite/Metallic StructuresV-n LoadingAerodynamicsPropulsion SizingModal AnalysisSystem IDPIDLQR

Test & Instrumentation

Strain-Gage BalanceAccelerometersPressure TapsIMULabVIEWDigilent AD2

Licenses & certifications

Online coursework in programming and mathematics.

Python Data Structures

Coursera

Issued Sep 2023 · ID 8ZY4TBYBEHYH

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Programming for Everybody (Getting Started with Python)