We publish the limits before the beauty

Operating Philosophy

We publish the limits before the beauty renders

Every subsystem here is stated as a claim, its supporting data, and its documented boundary — in the same breath. Where a capability is qualified, we name the standard. Where it is not yet qualified, we say so plainly. Moon Buggies is a fictional lunar mobility studio; nothing on this page implies flight or test heritage. What it does imply: architecture you can self-qualify against, interfaces drawn as hard boundaries, and margins carried as fact, not confidence. Read the subsystems below. If your mission profile fits the boundaries — and only then — open an engineering conversation.

Review qualification posture

Platform Architecture

The platform architecture, drawn as an exploded diagram

Seven subsystems, one integration boundary. This diagram labels mobility, positioning, power, thermal management, dust tolerance, avionics interfaces, and redundancy — each with its documented limit attached, not implied. Moon Buggies is a fictional design studio; no flight or test heritage is claimed. Every subsystem below states what is qualified, to what standard, and what is not yet qualified.

Mobility
Traction and suspension sized to the stated regolith slope case. Documented limit: slope margin at the abrasion-loaded wheel bearing, not the nominal case.
Positioning
GNSS-denied navigation as the design baseline. Drift bounded by the stated sensor-fusion assumptions; the limit is disclosed, not averaged away.
Thermal
Both are stated on the margin tables above.
Dust tolerance
Seals and interfaces rated against a stated abrasion and ingress case. Tolerance is a bounded number, with the failure mode named.
Avionics interfaces
Mechanical, electrical, thermal, and data interfaces defined at the integration boundary. What crosses the boundary is drawn, not assumed.
Redundancy
Fault tolerance shown as decisions in the redundancy tree — which faults are covered, which are accepted, and why.

Evidence before render

Evidence first. The render comes after the margins.

This is a fictional-project studio. We publish qualification posture, documented margins, and explicit not-yet-qualified boundaries before any beauty render. Every number above carries a unit and a margin, with stated assumptions attached. Read the tables, self-qualify your mission profile, then open an engineering conversation — not a sales call.

Documented margins

Power, thermal, and dust margins — with assumptions

Stated margins with the load case and worst-case assumption behind each number. Where an item is not yet qualified, it is labelled as such.

Thermal budget, lunar noon

Margin

18% at 393 K

Assumption / load case

Illustrative lunar-noon radiator case.

Power, lunar-night survival

Margin

6% reserve

Assumption / load case

Baseline survival heater draw only. No traverse capability during night without external power. Stated plainly: not yet qualified for continuous night operations.

Dust tolerance, regolith abrasion

Margin

12% seal-wear margin

Assumption / load case

Illustrative 10 µm mare-fines abrasion case.

Power, daylight traverse

Margin

24% reserve

Assumption / load case

Excludes contingency egress or tow scenarios.

Thermal, shadowed-crater ingress

Margin

Not yet qualified

Assumption / load case

Permanently shadowed region thermal loads unmodelled beyond survival case. No documented margin — flagged as an open integration boundary.

If your mission profile sits outside these assumptions, the margins do not apply. Bring your load case and we will walk it against the qualification data.

Discuss your load case

Failure-mode reasoning

Avionics redundancy, drawn as decisions

Each branch states a primary path, fallback, and covered failure mode. Single-string subsystems remain visible. Voting logic and assumptions travel with each figure. This fictional architecture claims no flight or test heritage.

Redundancy tree

Each branch documents a failure mode and the design decision that bounds it.

Flight computer
Dual redundant with cross-monitor; reversion to a degraded-mobility safe state on divergence. Not yet qualified for autonomous crewed egress.
GNSS-denied positioning
Primary inertial plus visual odometry, fused. Single-string star-tracker aid; drift bounded by documented margin, not eliminated.
Power bus
Dual-bus with isolated fault domains; load-shed table defines which subsystems drop first under undervoltage.
Motor drive controllers
Per-wheel controllers, independently addressable. Loss of one wheel enters documented reduced-traction limp mode.
Data network
Redundant deterministic links; failover verified in analysis only. Latency budget stated with its assumptions.

Review a mission profile with engineering

Operational limits, bounded by their conditions

Parameter

Documented limit

Condition / margin basis

Slope traverse

Bounded by regolith bearing strength

Documented for stated wheel-loading assumptions; not qualified beyond nominal grade case

Thermal survival duration

Set by thermal budget margin

Illustrative 18% steady-state; 0% eclipse-transition margin.

Dust ingress tolerance

Bounded by seal design case

Qualified against defined abrasion cycles; not yet qualified for extended regolith immersion

GNSS-denied positioning drift

Bounded per traverse distance

Documented under stated terrain-feature density; degrades in low-feature regions

Fault tolerance depth

Single-fault operable

Redundancy documented at subsystem level; dual-fault cases stated as not-yet-qualified

Landing-load survival

Margin case-dependent

Illustrative landing-load margin: 0%; boundary remains open.

Parameter

Slope traverse

Documented limit

Bounded by regolith bearing strength

Condition / margin basis

Documented for stated wheel-loading assumptions; not qualified beyond nominal grade case

Parameter

Thermal survival duration

Documented limit

Set by thermal budget margin

Condition / margin basis

Illustrative 18% steady-state; 0% eclipse-transition margin.

Parameter

Dust ingress tolerance

Documented limit

Bounded by seal design case

Condition / margin basis

Qualified against defined abrasion cycles; not yet qualified for extended regolith immersion

Parameter

GNSS-denied positioning drift

Documented limit

Bounded per traverse distance

Condition / margin basis

Documented under stated terrain-feature density; degrades in low-feature regions

Parameter

Fault tolerance depth

Documented limit

Single-fault operable

Condition / margin basis

Redundancy documented at subsystem level; dual-fault cases stated as not-yet-qualified

Parameter

Landing-load survival

Documented limit

Margin case-dependent

Condition / margin basis

Illustrative landing-load margin: 0%; boundary remains open.

Provide your mission profile to check it against these documented bounds. What is not yet qualified is stated as such.

Discuss Your Limits