Revolutionary Fixed Tail Plate Aerodynamic Breakthrough Explained! #velocidrone #drone #diydrone

Full technical concept and prototype plan (PDF):
https://drive.google.com/file/d/1xomvCNrbcFr-b63D4lA8x3bbEJN9mvb3/view?usp=sharing

Sponsor Information Page:
https://drive.google.com/file/d/16NS9BvZq2fCkz6x0fQJsgsbk70OBF5KW/view?usp=drive_link

A sub‑55‑pound wingborne VTOL built for the DARPA Lift Challenge — simple, efficient, and engineered for one purpose: to demonstrate VTOL, transition, and wingborne cruise under the 55‑lb limit.

The M235DLC uses four large‑diameter propellers for low disk loading and a high‑lift wing for efficient cruise. The goal is clear: build the prototype, fly it, and prove the concept before the DARPA deadline.

If you want the full mission requirements, airframe layout, disk loading and wing lift equations, control logic, and the complete prototype test plan, download the M235DLC Concept Paper & Prototype Development Plan above.

Sponsors and collaborators:
Your support accelerates the build of the first flight‑ready prototype. Contact information is inside the PDF and on the Sponsor Information Page.

Note:
A Clear, Strong Explanation of the Two M235 Configurations

Two Configurations, One Mission
For the DARPA Challenge program, two propulsion architectures were developed for the M235 platform:
1. Pure Battery Electric
Simplest architecture
Lowest integration risk
Fastest to prototype
Ideal when schedule pressure is extreme
Limited endurance, but excellent instantaneous power delivery

2. Hybrid Genset + Buffer System
Small LiPo buffer handles transients and peak loads
Genset provides sustained cruise power and in‑flight recharge
More complex integration (thermal, vibration, power electronics)
Higher endurance and mission flexibility
Better long‑term growth path

Why the Pure Battery System Is the “Schedule‑Safe” Choice
When the timeline is compressed — as it is for the DARPA Lift Challenge — the pure battery configuration becomes the least difficult system to bring to prototype readiness. It minimizes:
subsystem interactions
tuning complexity
failure modes
integration time

It’s the configuration that lets you fly sooner, gather data sooner, and de‑risk the airframe and control laws while the hybrid system matures in parallel.

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