Integration Boundary Diagram
Where systems meet: integration boundaries
- 01
Mechanical interface
Standardized quick-disconnect payload mounting. Attachment points, shear limits, and cable routing defined in assembly drawings. Margin documented for vibration and thermal cycling stress.
- 02
Power distribution
Battery-to-load voltage rails and peak current limits specified per subsystem. Fault detection and load-shedding thresholds stated with timing. No surprise resets in the mission profile.
- 03
Thermal handoff
Heat rejection capacity and operating-envelope limits published. Your payload thermal load must remain within stated bounds. Mitigation strategies documented if your system approaches margin.
- 04
Positioning and comms
GNSS-denied navigation interfaces and avionics data bus protocols defined. Latency, update rate, and accuracy limits are explicit. No black-box sensor fusion.
- 05
Redundancy architecture
Critical subsystems include documented backup paths and failure modes. Single-point failures flagged where they exist. Your integration must account for the redundancy posture we publish.
- 06
Dust and environmental spec
Regolith abrasion tolerance and seal-life assumptions published. Your sealed components must meet the same environmental class or mitigation is required.
Interface definitions and mechanical boundaries
Mobility interface
Regolith interaction: abrasion testing ongoing; current dust mitigation includes elastomer lip seals and labyrinth packing.
Electrical interfaces
Distribution: three independent circuit branches with isolated return paths. No flight heritage; qualification posture is breadboard and integration-lab testing. Production connectors TBD.
Thermal management
Internal battery pack thermal budget: heater power TBD pending final cell selection. Dust accumulation effects on radiator emissivity under investigation.
Navigation and positioning
Absolute positioning at return: manual waypoint confirmation required. No autonomous orbit-determination or lunar-reference-frame aiding.
Structural and load case
Documented margin on landing-load case: margin calculation ongoing; preliminary data under external review. Vibration isolation: elastomer mounts (durometer TBD) on motor assembly. Long-term fatigue testing at thermal extremes: planned for next phase.
Documentation at handoff
- 01
Interface control document
Mechanical, electrical, thermal, and avionics boundaries, including attachment, power, and data definitions.
- 02
Qualification summary
Subsystem posture with the governing analysis, stated assumptions, and every not-yet-qualified boundary.
- 03
Operational limits specification
Performance-case margins for mobility, thermal cycling, dust exposure, positioning, and redundancy.
- 04
Integration boundary drawing
Annotated power, data, mounting, thermal-coupling, and fault-isolation connection points.
- 05
Failure mode and mitigation register
Known failure modes by subsystem, detection strategy, operational consequence, and mitigation approach. Redundancy decisions and fault-tolerance architecture explained.
- 06
Mission-profile template
Standard spreadsheet for documenting your operational scenario: duty cycle, thermal environment, dust exposure, positioning accuracy requirement, mission duration, abort criteria.
Self-assessment
Self-qualify against platform boundaries
Criteria your mission profile satisfies. Any unchecked line is a boundary to raise before integration.
This checklist is not a qualification record. Checked lines indicate profile fit against documented boundaries only; formal interface verification is scoped during integration review.