LIMITATIONS — rocket-24-month-plan

Every incomplete, simulated, or out-of-scope element, disclosed plainly. These are DISCLOSED_SEAMs — not hidden in footnotes.

DISCLOSED_SEAM: Fictional company

"Apogee Launch Co." does not exist. There is no real funding round, no staff, no suppliers, no facility, no hardware, and no launch. Every name, date, and figure is invented for the purpose of the plan.

DISCLOSED_SEAM: Planning artifact, not hardware

This deliverable plans a program; it does not build, test, or fly anything. Verification proves the plan is consistent, complete, and deterministic — it does not prove that a rocket was produced or that any test or flight occurred.

DISCLOSED_SEAM: Scope is suborbital only

"Earth to space" is interpreted as a single-stage suborbital flight crossing the Kármán line (100 km). Orbital flight is out of scope at this budget and headcount and is not planned here.

DISCLOSED_SEAM: Schedule feasibility is unverified

Reaching space within 24 months of incorporation with 5 core staff is at the extreme edge of historical precedent. The schedule assumes heavy contractor and vendor leverage, leased test stands and launch range, and no major redesign loop after CDR. Whether this is achievable in reality is not established by this artifact; it is disclosed as the program's top risk.

DISCLOSED_SEAM: Budget is an illustrative model

The $200M allocation and the 24-month cumulative-spend curve are planning figures derived from a model, not real quotes, bids, supplier pricing, or earned-value data. Actual costs would differ.

DISCLOSED_SEAM: No live systems

There is no backend, database, scheduling/ERP system, supplier tracker, FAA status feed, or telemetry. The website is a static, self-contained presentation of the static plan model. A real program would integrate live data sources that do not exist here.

DISCLOSED_SEAM: Engineering parameters are notional

Phase durations, the workstream breakdowns, the budget split, and the milestone dates are reasoned planning judgments, not the output of detailed engineering analysis (no real loads, CFD, trajectory, or propulsion sizing was performed).