Geometry & exchange
Eight native/STEP states, nominal assembly/motion checks and native mass properties.
Inspect evidenceEvidence / methods and sources
Trace a claim to its inputs.
The evaluated configuration is VOLLEY-G5-ACR1. Geometry, motor/circuit behavior and orbital delivery use explicitly identified models and source files.
Evidence map
Four connected records.
Coupled shot & resources
Finite motor geometry, source/current/voltage model, arrest and explicit installed allocation.
Inspect evidenceHost-assisted mission
Frozen synthetic target states, release recoil, continuous host arcs and native Orekit replay.
Inspect evidenceAcademic record
Exact report plus original scientific figures and controlled Blender views.
Inspect evidenceMotor / coupled model
Release and recovery share one energy account.
Extended engineering analyses
From native dynamics to first measurements.
Structural dynamics
Forty elastic modes, finite forcing, phase-dependent normal reaction and conditional clearance.
Methods and native results ↗Release and arrest
Forty-two native runs with local egress, contact/refinement and keeper-catch sensitivity.
Histories and interpretation ↗Thermal operating envelope
CAD-based radiation, repeated duty, regulated host heat paths and a separately identified voltage-derated source.
Conditions and computed limits ↗Lunar campaign
Finite host authority, release policy, covariance, native orbit lifetimes and independent engine-only disposal.
Campaign and resource study ↗These separately identified supplements preserve the accepted ACR1 core and ED1 document identities. Numerical output, proposed fixture geometry and physical measurements are distinct evidence classes.
26 October / mission supplement
One machine, different manifest sizes.
Two- and four-payload campaigns extend the retained twelve-payload reference: 28 finite-force candidates and 17 native Orekit replays, with full hardware mass retained.
Methods, full-state results, native replay and resource comparison ↗
Independent static solver comparison
The same chassis. A second solver.
The primary ANSYS bare-chassis result gives 0.286392 mm paired closure under matched 3.01048 kN opposed-patch loads: 0.143% above the CalculiX reference. Three mesh levels and 11,448 independently read primary samples accompany the comparison.
Read the inputs, mesh sensitivity, clearance-budget effect and source data →
Method boundary
Read each result in its declared model.
Geometry and mechanisms
Native solid geometry, nominal motion, interface retention and declared analytical sizing. Reference actuator envelopes and allocations are identified in the source; manufacturing and instrumented hardware correlation follow.
Motor and release
Finite geometry and coupled computational source/motion models. The 1–3 m/s command band is the supported study range; no hardware rating or flight capability is asserted.
Orbital delivery
Fixed-axis J2 point masses, synthetic preplanned full-state targets, constant inertial host force and Isp 220 s. Drag, higher gravity, attitude/plume allocation, navigation and finite exit geometry are outside the mission model.
Numerical agreement
Independent replay and step refinement assess numerical consistency. They do not establish physical delivery accuracy, measured reliability or payload compatibility.
Installed allocation
149.55672 kg computed CAD mass + 7 kg power/control allowance = 156.55672 kg retained device allocation; + 48 kg payloads = 204.55672 kg loaded device. The generic wet host is 500 kg including its 20 kg fuel once, so the mission begins at 704.55672 kg.
Provenance
Inspect the original output.
