Engineering · Rocketry · Aerospace · Exploration
Vinay.K
B.Tech Mechanical Engineering · Second year · VIT Vellore
Engineering fields
From satellites to propulsion
- Cube satellite
- Rockets
- Drones
- Software
- Graphs
- Astronaut suit
- Nose cone
- Fins
- Aerodynamics
- Parachute
- Heat
- Nozzle
- Thrusters
- Propellers
- Cube satellite
- Rockets
- Drones
- Software
- Graphs
- Astronaut suit
- Nose cone
- Fins
- Aerodynamics
- Parachute
- Heat
- Nozzle
- Thrusters
- Propellers
Education & experience
Learning by building
Education
B.Tech Mechanical Engineering
Second year · VIT Vellore
Team Sammard
Junior Mech Core
Junior Propulsions Core
Vayusastra
Cube Satellites
Built Cube Satellites and Model Rockets
Writing
Latest blogs
What Our First Static Fire Taught Me About Solid Motors
Grain geometry, nozzle erosion and the three things that almost ended the test stand campaign.
9 min · 2026-08-02
Five FEA Sanity Checks Before You Trust A Single Stress Plot
Mesh convergence, boundary conditions and hand calculations that keep you honest.
7 min · 2026-07-21
A Parametric CAD Workflow For Rapid Airframe Iteration
How a handful of driving parameters turned a two-day redesign into twenty minutes.
6 min · 2026-07-04
Video
Latest videos
Static Fire Test #3 — Full Campaign Walkthrough
Rocketry · 14:22
Designing A Rocket Nose Cone In Fusion 360
CAD · 22:05
Day In The Life — Mechanical Engineering Lab Week
College Life · 10:41
Featured
Featured project
Vega-1 Sounding Rocket
Fly a 2.4 m airframe to 1.2 km with dual-deploy recovery and full telemetry.
Our club had no reusable platform to validate recovery and avionics together.
- Timeline
- Jan 2026 — ongoing
- Lessons learned
- Mass margin discipline matters more than any single clever subsystem.
- Next up
- Carbon fin can, redundant altimeter, live LoRa downlink.
Photography
Latest gallery photos
Launch pad
Recent rocketry updates
LOG-014 · Static Fire · 2026-08-02
Static Fire #3 — 4.1 s burn, nominal chamber pressure
Peak 42 bar, throat erosion 0.4 mm, no structural anomalies on the stand.
LOG-013 · Flight Test · 2026-07-15
Vega-1 recovery bench test — dual deploy verified
Ten consecutive ejection cycles with correct main deployment at 150 m setpoint.
LOG-012 · Simulation · 2026-06-28
Nozzle CFD sweep — 6 contours compared
Bell contour at 80% length gave the best thrust coefficient for our chamber.
Archive
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