Claude Skills by ashfordeOU

Use when running element electromagnetic compatibility tests under ECSS-E-ST-10-03C §6.5.5: determine auto-compatibility by verifying that each internal emitter's frequency has sufficient isolation margin against every internal receive band, evaluate passive intermodulation (PIM) products for RF-bearing elements to confirm no odd-order products fall within the receive band, perform residual magnetic dipole moment checks against the element magnetic budget, and identify the correct test mode—s...

Use when run element-level general tests per ECSS-E-ST-10-03C §6.5.1 to verify that all mechanical functions and electrical performance parameters of a space element meet their acceptance requirements: categorize each test item as mechanical-functional (deployment, retraction, separation, latch-release) or electrical-functional (continuity, insulation resistance, bonding); evaluate each measured parameter against its lower and upper acceptance limits; flag any pre-test or post-test inspection...

Use when verify general element test requirements under ECSS-E-ST-10C §6.1: order the test campaign by ascending scope (unit, integration, element), confirm that every declared interface is exercised by at least one passing test, check that all element-level functions are covered by the campaign, and flag missing required test levels before formal acceptance. Trace each test result to its driving requirement and control the test configuration throughout. Trigger: ecss, e-st-10-system-scope, e...

Use when run element-level mechanical tests for a space hardware item under ECSS-E-ST-10C §6.5.2: categorize each test type (physical properties, modal survey, static load, spin, transient/sine-burst, acoustic, random vibration, sinusoidal vibration) into its structural or dynamic family, confirm test levels and durations are within their qualification, protoflight, or acceptance specification, enforce the required test sequence (physical-properties and modal-survey before dynamic tests), and...

"Use when run element mission-specific tests under ECSS-E-ST-10C

Use when run element-level pressure tests for pressurized space hardware under ECSS-E-ST-10C §6.5.3: determine proof pressure from the maximum expected operating pressure and verify the hold duration, cycle pressure between bounds for the required number of fatigue cycles, apply design burst pressure to confirm ultimate structural integrity, and measure leakage against the allowable leak rate. Each test produces a pass/fail verdict with explicit findings. Trigger: ecss, e-st-10-system-scope, ...

Use when define the element protoflight test baseline under ECSS-E-ST-10-03C §6.4: decide whether a space element must follow the protoflight test approach (one hardware model demonstrating both design qualification and flight acceptance, with no separate dedicated qualification model), and derive, for each required test type, the protoflight test level from the Table 6-5 qualification severities and the protoflight test duration from the Table 6-6 acceptance durations. Also flag any protofli...

Use when define the element qualification test baseline for a space hardware item under ECSS-E-ST-10C §6.2: determine the qualification approach (full qualification versus protoflight) from the element category and prototype test history, map the mission environment drivers to the required test types, compute the qualification level by applying the standard margin over the acceptance level for each test type (vibration, acoustic, shock, thermal cycling, thermal vacuum, quasi-static), compute ...

Use when run and validate element-level thermal tests per ECSS-E-ST-10C §6.5.4: thermal vacuum cycling, thermal balance correlation, mission-pressure thermal cases, and Space-Station-specific thermal conditions for a spacecraft element. Checks each test case for conformance with temperature setpoint, soak duration, cycle count, chamber pressure, and margin requirements. Verifies thermal model correlation against balance measurements and confirms the mandatory thermal test campaign is complete...

Use when defining the acceptance test baseline for a piece of equipment under ECSS-E-ST-10-03C: derive per-test-type acceptance levels and durations from the equipment's qualification baseline and its margin/duration reduction rules, guard against an acceptance level or duration that fails to sit below its qualification counterpart, and check the baseline for coverage gaps before it is released to the test programme. Anchor: E-ST-10-03C clause 5.3 + Tables 5-3/5-4. Trigger: equipment acceptan...

Use when scoping and running the ECSS-E-ST-10-03C equipment electrical/RF test set for one equipment item: verify test applicability (EMC, magnetic, ESD, passive intermodulation, multipactor, corona/arc discharge) from equipment risk flags, define each test's status (not applicable, missing, passed, failed), and roll up the campaign disposition (complete, incomplete, failed) before equipment qualification/acceptance sign-off. Anchor: E-ST-10-03C clause 5.5.5. Trigger: equipment electrical tes...

Use when running the general equipment test requirements of ECSS-E-ST-10-03C 5.5.1 within a qualification, acceptance, or protoflight test sequence: run the functional/performance test at each sequence position (baseline and final comprehensive, interim abbreviated unless an anomaly is suspected), evaluate current measurements against the baseline to flag degraded parameters, verify physical configuration (mass properties and visual inspection) at each test point, and confirm the launch confi...

Use when verifying the general equipment-level test requirements under ECSS-E-ST-10-03C clause 5.1, ahead of picking the qualification, acceptance, or protoflight test baseline: confirm the test model carries the correct campaign (qualification/acceptance/protoflight), validate the test configuration is flight-representative or has documented deviations with every required interface simulated, check that mechanical/electrical interface checks bookend the test sequence, and run the functional-...

Use when running equipment-level mechanical tests under ECSS-E-ST-10-03C clause 5.5.2: determine which mechanical tests apply to a given equipment item (physical properties, acceleration by static/spin/sine-burst, sinusoidal vibration, random vibration, acoustic, shock, and micro-vibration for both disturbance-generating and micro-vibration-sensitive equipment), and verify every applicable test is closed with matching evidence before the equipment's mechanical test campaign is declared comple...

"Use when execute equipment mission-specific test verification under

Use when running equipment structural-integrity-under-pressure tests under ECSS-E-ST-10-03C: run the leak, proof pressure, pressure cycling, design burst and burst tests on pressurized space segment equipment, derive which of these tests apply from the test campaign and the item's service profile, select whether burst margin is demonstrated by a physical burst test or a design burst analysis depending on whether the article can be sacrificed, sequence a destructive burst test last, and evalua...

Use when you define the equipment protoflight test baseline under ECSS-E-ST-10-03C clause 5.4: decide whether an equipment item must follow the protoflight test approach (one hardware model demonstrating both design qualification and flight acceptance, with no separate dedicated qualification model), and derive, for each test type, the protoflight test level from the Table 5-5 qualification/acceptance severities and the protoflight test duration from the Table 5-6 qualification/acceptance dur...

Use when defining the equipment qualification test baseline of an ECSS-E-ST-10-03C testing programme: select which test families apply to a piece of equipment and in what sequence (Table 5-1), and derive each applicable test's qualification level and duration from its reference level/duration plus a margin and duration factor (Table 5-2). Trigger: equipment qualification test, qualification baseline, test sequence, Table 5-1, Table 5-2, qualification level, qualification duration, margin fact...

Use when running equipment-level thermal tests under ECSS-E-ST-10-03C clause 5.5.4: select thermal vacuum vs thermal test at mission pressure for a unit based on its vacuum exposure, execute the qualification/acceptance/protoflight thermal cycle plan (cold/hot plateaus, dwell stabilization, functional/performance checks at the extremes), and verify the test as complete only when every required cycle stabilizes and passes. Trigger: thermal vacuum, TVAC, thermal cycling, thermal test at mission...

Use when you need to verify that each test input applied during a space qualification or acceptance campaign falls within the allowable deviation for its input type, as specified in ECSS-E-ST-10C §4.4.2 and Table 4-1. Categorize the input by type (temperature, pressure, supply voltage, frequency, random vibration power spectral density, sine vibration level, acoustic level, humidity, or test duration), compute the actual deviation from the nominal target, and confirm the deviation does not ex...

Use when manage a system-level test campaign under ECSS-E-ST-10C §4.3.1: assign customer and supplier responsibilities to each test event, verify that all mandatory readiness conditions (configuration baseline locked, procedure approved, support-equipment calibrated, personnel qualified, safety clearance granted) are satisfied before authorising a test, sequence campaign phases from planning through closeout, and flag any responsibility gap or unmet readiness prerequisite before the test-read...

Use when defining the test objectives for a qualification, acceptance or protoflight test campaign under ECSS-E-ST-10-03C clause 4.5: define the demonstrated-margin and workmanship-screen objectives assigned to each campaign type, derive the required test level (qualification level vs acceptance level) and duration class (full vs reduced) that those objectives imply, and validate a proposed test definition against the campaign's assigned objectives before test conditions, levels and durations...

Use when running pre-launch health checks, leak verification, functional tests, and campaign constraint checks at the launch site under ECSS-E-ST-10C §7: categorize each health check as structural, electrical, thermal, propulsion, software, or mechanical; compare measured leak rates against the allowable limit for each pressurized system; evaluate functional test outcomes for critical and non-critical subsystems; and verify every launch campaign environmental and temporal constraint is within...

Use when applying ECSS-E-ST-10-03C clause 4.6 retesting rules to define whether an article must be retested: a design modification made after qualification, storage after a protoflight/acceptance test beyond the qualified shelf life, a previously flown article being prepared for reflight, or a qualification-model article proposed for flight use. Classify each case's required action (no retest, requalification, acceptance-level retest, or disallowed for flight) ahead of test-programme executio...

"Use when determine the tailoring profile of ECSS-E-ST-10-03C for a

Use when define test conditions for a space equipment or system verification campaign under ECSS-E-ST-10C §4.4.1: establish the required ambient environment parameter ranges (temperature, pressure, humidity, EMI environment), the cleanliness class for each test area, the ESD protection measures required for each test item, the unit-under-test configuration state and interface definitions, and the monitoring channel set with recording rates and acceptance limits. Each condition input is catego...

Use when record, reduce, and deliver test measurement data for a spacecraft test campaign under ECSS-E-ST-10C §4.3.5: determine the minimum sampling rate for each channel type (vibration, acoustic, thermal, pressure, electrical, strain), validate that raw data records carry complete metadata (channel ID, calibration coefficients, timestamp, format), compute storage requirements, apply linear calibration to convert raw counts to engineering units, categorize each data channel as primary, secon...

Use when producing the test documentation set required by ECSS-E-ST-10C §4.3.3: draft the Assembly, Integration and Test (AIT) plan, the Test Specification (TSPE), the Test Procedure (TPRO), and the Test Report; verify each document carries the mandatory control fields (type, issue number, date, approval status); confirm the TSPE and TPRO trace every item to a recorded test requirement; check that document sequencing is respected (AIT plan approved before TSPE is released, TSPE approved befor...

Use when define the overall test programme for a space system or subsystem under ECSS-E-ST-10C §4.1: identify each hardware model entering the programme (BB, EM, QM, EQM, PFM, FM), derive its corresponding test level (development, qualification, proto-flight, or acceptance), build and validate the ordered test sequence for each model ensuring positions are unique and consecutive, verify that functional tests bookend the sequence at position 1 and the final position, confirm all required progr...

Use when perform test readiness reviews and close-out reviews for a spacecraft test campaign under ECSS-E-ST-10C §4.3.2: verify each review has defined entry criteria grouped as mandatory or advisory, determine the outcome (pass, conditional pass, or fail) from which criteria are met, confirm all test anomalies carry a disposition before close-out, and ensure every review produces a complete record capturing review type, chair, attendees, criteria verdicts, outcome, and open action items. App...

Use when validate a Test Procedure (TPRO) document against ECSS-E-ST-10C Annex C DRD requirements: confirm the header carries all required identification fields (document ID, title, revision, objective, test level, applicable standard, safety requirements), verify each procedure step is numbered sequentially with an explicit action, expected result, and data-recording entries specifying parameter, unit, and acceptance range, check that pass/fail criteria cover all measured parameters, and sur...

Use when validate or generate a Test Specification (TSPE) document against the ECSS-E-ST-10C Annex B Data Requirement Document: verify the document carries a test identification block (ID, name, and test-type category), a substantive description of the test objective, a conditions block covering environment, configuration, and stimuli, an ordered procedure list with step numbers and actions, and at least one measurable success criterion with parameter, limit, and measurement unit. Flag each a...

Use when verifying that a demonstrated test margin under ECSS-E-ST-10-03C still holds once measurement uncertainty is taken into account: compute the effective margin by subtracting the applicable measurement/instrumentation uncertainty (Table 4-2 typical values, overridable by project-specific characterization) from the demonstrated margin, assess whether the result is still positive, and flag any project-specific uncertainty that exceeds its Table 4-2 typical value for justification. Trigge...

Use when assembling the natural electromagnetic radiation and solar/geomagnetic index reference dataset from ECSS-E-ST-10-04C Annex A for a mission design case: determine which quantities (TSI, EUV/XUV band irradiance, Earth albedo, Earth IR emission, F10.7, F10.7A, geomagnetic index) apply, verify each quantity's solar-cycle phase tagging and that phase-dependent values ordered minimum/mean/maximum, and flag missing quantities, missing phases, or phase-tagging errors before the dataset feeds...

Use when computing meteoroid background flux and meteor-shower stream enhancement for a space mission per ECSS-E-ST-10-04C Annex C: apply the Grün interplanetary flux model, add meteor-stream enhancement tables for known shower epochs, and apply Earth shielding and gravitational focusing corrections for near-Earth orbits to produce the meteoroid environment input for impact risk assessment. Trigger: meteoroid flux, Grün model, meteor stream, shower enhancement, Earth shielding, gravitational ...

Use when defining the neutral atmosphere environment for a mission under ECSS-E-ST-10-04C: select the applicable neutral-atmosphere density model (NRLMSISE-00 for general-purpose drag and lifetime work, JB-2006 for precision analyses) based on the case's precision need, verify the analysis altitude falls within the model's valid range, classify the solar activity level from the F10.7 solar flux index, apply solar/geomagnetic scaling to the reference density, select a wind model (HWM-type) whe...

Use when implementing the IGE-2006 geostationary trapped-electron flux model under ECSS-E-ST-10-04C Annex B.2: look up the differential electron flux at a requested energy and L-shell by log-linear interpolation between the model's tabulated energy and L-shell nodes, resolve the requested confidence level (mean or a worst-case percentile) to its flux scale factor, assemble a full energy-spectrum table for a request, and flag any energy or L-shell query that falls outside the tabulated node ra...

Use when implementing the ONERA MEOv2 trapped-electron flux model for GNSS/navigation-orbit (MEO) radiation analyses under ECSS-E-ST-10-04C Annex B.3: represent the model's flux-versus-energy spectral form as a function of McIlwain L-shell, interpolate the model's L-shell reference grid to an arbitrary L-shell (including along a full mission orbit's L-shell trace), and compute per-energy, orbit-averaged, and worst-case-L-shell flux outputs for the orbit. Trigger: MEOv2, ONERA, GNSS orbit radi...

Use when implementing the FLUMIC outer/inner radiation belt worst-case trapped electron model under ECSS-E-ST-10-04C Annex B.4: select the belt region (inner belt, outer belt, or both for a belt-crossing orbit), apply the confidence (percentile) level and the worst-case exposure-duration class the analysis purpose requires, evaluate the resulting electron energy spectrum, and integrate the flux above a shielding-relevant threshold energy for internal (deep-dielectric) charging design. Trigger...

Use when implementing the NASA worst-case geosynchronous (GEO) electron environment spectrum per ECSS-E-ST-10-04C Annex B.5: select the applicable energy band of the two-population exponential spectral fit (a lower-energy population associated with spacecraft surface charging and a higher-energy, penetrating population associated with deep-dielectric/internal charging), compute the differential and integral electron flux at a given energy, derive the worst-case fluence for a stated exposure d...

Use when generating the Annex B.6 Emission of Solar Protons (ESP) worst-case fluence spectra for a mission under ECSS-E-ST-10-04C: build the reference annual integral fluence spectrum, apply the confidence-level scale factor for the required design percentile, apply the mission-duration scale factor for the exposure period, assemble the resulting fluence-above-energy spectrum, and verify the selected confidence level meets the mission's worst-case design threshold. Trigger: ESP, emission of s...

Use when deriving solar energetic particle (SEP) heavy-ion energy spectra with Z-dependent elemental abundances for single-event-effects (SEE) analysis under ECSS-E-ST-10-04C Annex B.7: derive each species' differential flux spectrum from a reference element (oxygen) spectrum, classify the SEP event type (gradual/shock-associated vs impulsive/flare-associated) from its iron-to-oxygen abundance ratio, apply the event type's elemental abundance table to scale species spectra, verify heavy-ion s...

Use when computing the Størmer vertical cutoff rigidity for a spacecraft location under ECSS-E-ST-10-04C Annex B.8: apply the dipole-field Størmer formula scaled by an epoch-dependent geomagnetic dipole moment coefficient to derive the cutoff rigidity at a geomagnetic latitude and radial distance, verify whether a given charged-particle rigidity penetrates the geomagnetic field at that location, and roll per-orbit-sample penetration results into a geomagnetic-shielding assessment for low-incl...

Use when characterizing the directional transmission of galactic cosmic ray (GCR) and solar energetic particle (SEP) flux through the geomagnetic field under ECSS-E-ST-10-04C Annex B.9: compute the local vertical Stormer-type geomagnetic cutoff rigidity from geomagnetic latitude, apply the Mobius-class Directional Intensity Change (DIC) correction for a given arrival zenith angle and azimuth to obtain the directional cutoff rigidity (capturing the east-west asymmetry between eastward- and wes...

Use when assessing on-orbit contamination of a spacecraft external surface under ECSS-E-ST-10-04C clause 11.2: classify each contamination source as molecular (outgassing, venting, propulsion effluent, leak) or particulate (debris, MLI fragment, handling residue, paint flake), determine the molecular transport path (direct line-of-sight vs. LEO ram/wake return flux), compute the deposited molecular mass and compare it against the surface's allowable budget, and verify every particulate-genera...

Use when a space project must define which space debris flux model (MASTER-class or ORDEM-class) to select and apply, under ECSS-E-ST-10-04C clause 10.2.2.1, for a mission's orbit and analysis epoch: validating that a candidate model's declared altitude/inclination/epoch/diameter envelope actually covers the mission envelope, building a complete model run request, and determining when a prior result needs re-assessment. Trigger: space debris flux, debris environment model, MASTER model, ORDEM...

Use when you must define a mission's natural electromagnetic radiation environment per ECSS-E-ST-10-04C clause 6.2: assemble the solar spectrum bands (XUV through IR and solar radio), scale total solar irradiance (TSI) to the mission's heliocentric distance, and combine planetary albedo and infrared emission into the incident EM flux a spacecraft must design against. Trigger: electromagnetic radiation environment, solar spectrum, TSI, total solar irradiance, solar radio, planetary albedo, pla...

Use when specifying the galactic cosmic ray (GCR) radiation environment for a mission under ECSS-E-ST-10-04C: select the applicable GCR reference model (heavy-ion energy spectra for single-event-effects analyses, integral LET/dose spectra for total-dose analyses) based on the analysis type and required ion species coverage, classify the solar activity condition from a solar modulation potential, apply solar modulation to scale the reference solar-minimum energy spectra to the mission epoch, a...

Use when computing GEO trapped energetic-electron flux and mission fluence for a geostationary spacecraft per ECSS-E-ST-10-04C Annex B.2: interpolate an IGE-2006-style local-time and energy spectral model at fixed L ~= 6.6, apply local-time sector weighting, and produce the differential and integral electron fluence inputs for internal charging and dose analysis. Trigger: GEO trapped electrons, IGE-2006, geostationary, L-shell 6.6, local-time spectrum, electron fluence, internal charging, e-s...

Use when defining the geomagnetic field environment model for a mission under ECSS-E-ST-10-04C: select the applicable geomagnetic field model (an IGRF-class internal field model alone at low/mid geocentric distance, or that model combined with an external/magnetospheric field model at high geocentric distance) from the mission orbit's geocentric distance, determine the correct IGRF epoch and apply secular variation to update the reference internal field for the mission's target date, verify t...