# Engineering boundary and unresolved interfaces / Rev E

This register prevents a completed digital model from being misrepresented as a completed flight program. The delivery is useful for design review, part inspection, interference development and supplier discussions. It is not ready for spacecraft fabrication or launch.

| Item | Actual state | Required closure |
|---|---|---|
| Mission and orbit | Study architecture and power allocations; final mission not frozen | Orbit, beta-angle/eclipse history, lifetime, radiation and debris environment |
| Complete deployment | Separate deployed assembly and unconnected transport inventory | Connected kinematics, restraints, actuators, dampers, latches, cables, testable sequence |
| On-orbit assembly | Separate structure stock is explicitly allocated | Robotic/manipulator design, assembly joints, operations, failure recovery, mass and power |
| Global mechanical joints | Member geometry, seams and some local parts defined | Bolted/welded joint details, certified material/process data, loads and margins |
| Pod support | Finite aperture beams and strut envelopes touch geometrically | Attachment fasteners, thermal isolation, local reinforcement, launch load path |
| RS external circuits | Eight panel-to-pod flexible interfaces remain open | Actual hoses, fittings, endpoint tangency, routing, retained bend radius and full motion |
| Internal hydraulics | Static routes pass the stated collision scope | Recalculate pressure loss and liquid fill from measured routes; select pumps/valves/fluid |
| Trunk length | Actual route about 4.798 m versus Rev D 4.000 m allowance | Update pressure, liquid mass, support, insulation and procurement budgets |
| Pipe terminals | Tangent paths include tight shaped elbows | Manufacturable fittings, wall/process definition, proof/leak/fatigue verification |
| RS pressure assembly | Explicit cavities, stays and local core replacement | Final brazed/welded material union, seam qualification, measured UA, freeze survival |
| Material overlap in RS | Some constituent brazed carrier/header/stay material is deliberately represented as contacting/overlapping fabrication stock | Fuse the final manufacturing union before reporting exact mass or production geometry |
| RC heat transport | Optional segmented chamber model; partial thermal chain remains unclosed | Validated heat transport/spreading, wick/charge, dry-out/startup, pressure and thermal-vacuum tests |
| Thermal views | Real geometry now available for future ray tracing | Quantify Sun/Earth/albedo incidence, mutual blockage, gradients and heater requirements |
| PV power | Proposed 512-cell local arrangement and converter envelope | Selected cell I-V, EOL/radiation, wiring, shadowing and hinge-root cell-mask reconciliation |
| Processor and electronics | Explicit mechanical housing and generic internal envelopes | Selected devices, board layout, package contacts, radiation/SEE, shielding and EMC |
| Battery | Reserved cases and capacity allocations | Selected cells, BMS, busbar design, thermal runaway containment, EOL/cycle qualification |
| High-voltage bus | Geometry does not validate 400 V operation | Plasma arcing, creepage/isolation, grounding, fault energy and connector selection |
| Optical terminals | Proposed head/yoke packaging and clearances | Actual optics, gimbals, boresight, flexible-body jitter, thermal stability and link availability |
| Propulsion and attitude control | Mission-level envelopes/budgets are not final hardware | Torque authority, flexible modes, propellant, tanks, thrusters, collision avoidance and disposal |
| Pod packing | Bare 1,800 x 1,800 x 800 mm allocation; internal cold pipes extend 44 mm below the bare pod | Reconcile protrusions, connectors, removable branches and packed attitude; optical-head removal alone does not close the fit |
| Hinge/harness packing | Not represented in transport inventory | Define restraint hardware, connectors and their separate packing volumes |
| Launch carrier | Study cylinder and preliminary member inventory | Provider-specific dynamic envelope, interface loads, separation, coupled loads and tests |
| Whole-spacecraft mass | Volumes and component data are available; several mass allocations remain unclosed | Unique ownership, exact unions/removals, selected equipment, harness/actuator/shielding mass |
| Qualification | Local geometry and data-file checks only | Independent review, correlated FE, vibration/acoustics, thermal-vacuum, deployment and acceptance campaign |

A zero-collision result for a named subset must not be generalized to the full spacecraft. Press-fit overlap is intentional contact; an unspecified overlapping structural joint is not automatically acceptable. A nominal dimension is not a manufacturing tolerance. A proposal shown in exact CAD is still a proposal.