Xcelerator · Digital Thread Demonstrator

FlyNow

It starts with a customer RFP — modeled on real U.S. Air Force solicitations — and ends with a flight-verified design. In between, an AI carried a single idea, the QX-250 quadcopter, unbroken through every discipline of a modern engineering enterprise: requirements, reliability and 6-DOF simulation, logical and electrical architecture, mechanical CAD, a managed program, the EBOM / MBOM and quality, and verification — inside the real Siemens Xcelerator tools — every tool operated autonomously by the AI, with no human hands on the tools. The AI Lifecycle Harness is what will steward that loop; this weekend a human still directed each step — but never operated a tool.

RFP → flight-verified · grows through the weekend Stewarded by the AI Lifecycle Harness 51 requirements · 53-part NX build MADe · Amesim · Capital · NX · Teamcenter

The moment

“Watson, come here — I want to see you.” In 1876 one sentence proved a whole new medium was real. This is that kind of threshold — the first time an AI carried a single design idea, unbroken, through every discipline of a modern engineering enterprise and committed it to the system of record.

The digital thread's ambition is to collapse the distance between a customer's requirement and the as-built, flight-verified configuration — across reliability, systems, electrical, software, manufacturing and quality engineering — so nothing is lost in translation between tools or teams. What follows is that thread, authored end-to-end by an agent and materialized in the live Teamcenter.

Where it begins

It starts with a customer RFP

Every engineering program starts with a need. This one begins with a request for proposal modeled on real U.S. Air Force solicitations — a full acquisition document with a 41-page system spec — that the QX-250 is built to answer.

Grounding the story in a real RFP is the point: it makes the whole thread accountable. Every requirement derives from it, every design decision serves it, and verification proves the answer against it. The RFP & proposal is the origin; the AI Lifecycle Harness is what carries it forward — decomposing the RFP into a structured program of work and driving it across the tools to a flight-verified design.

The arc. RFP → requirements → simulate → design → build → verify → fly. This weekend the AI walked that arc with a human prompting each step; the harness is the bet that it can be stewarded end-to-end. See the AI Lifecycle Harness.

Why the order matters

Simulate before you cut metal

The single most important decision in this program was sequence: run the reliability and system-performance simulations first, and let them drive the design.

By the time late analysis finds a problem, the mechanical, electrical and software designs are already committed and every fix is a rework loop. On the QX-250 the analysis ran up front — and it materially changed the design in all three domains before any were frozen:

→ Electrical

MADe found 24 order-1 cut sets — every single fault drops the aircraft. Redundancy went onto the electronics: a 2nd battery, 2nd flight controller and a BMS/OR-ing block were added. Cheaper parts, yet more reliable (R = 0.9999784).

→ Software

The Amesim 6-DOF model showed the attitude loop recovers fast but is lightly damped — it rings (ζ ≈ 0.15) and holds attitude only. A control-law finding: it wants more rate-damping and an outer position/heading loop.

→ Mechanical

The sweeps proved geometry and control are coupled: shrinking the arm to 125 mm without re-tuning the controller destabilises hover (roll diverges to 67°). Geometry can't be changed in isolation.

The thesis. Reliability and performance simulation are not a late verification gate — they are the first design authority. Running them early is what let their conclusions flow into the mechanical, electrical and software designs while those were still cheap to change.

The aircraft

QX-250 at a glance

A 5-inch freestyle-class quadcopter — the vehicle the whole thread describes.

All-up weight500 g

single-string design point · ~650 g as-built (dual-battery redundancy, right-sized packs) · ≤ 700 g limit ✓

Thrust : weight~5 : 1

at the 500 g design point · 3.83:1 as-built (650 g, flight-verified) · ≥ 2:1 required at WOT

Mission reliability0.9999784

with redundancy, MTTF 4673 h (MADe)

Attitude recovery~0.86 s

lightly damped, ζ≈0.15 (Amesim 6-DOF)

Explore the thread

The whole program, by phase

Every page — grouped the way the work actually flows, from the customer RFP through to a flight-verified design. The top menu carries the same groups.

Origin — the customer RFP

Analyze — simulate first

Architecture

Engineering — mechanical · electrical · compute · software

Deliver — program & build

Verify — against the RFP

The meta-layer — the harness that stewards it