Claude Skills by ashfordeOU

Use when run the simplified shielding analysis for a sensitive component under ECSS-E-ST-10-12C §6.2.2: model the shield as a planar slab, a spherical shell, or a set of solid-angle sectors, compute the areal density of each layer as thickness × density, invert that relation to derive the thickness needed for an areal-density budget, flux-weight the mean areal density across sectors, verify the sector set covers the full 4π sphere within tolerance, and report the minimum and maximum shielded ...

"Use when run detailed 1-D, 2-D, or 3-D radiation transport calculations

Use when determine shielding calculation uncertainties for a spacecraft radiation analysis under ECSS-E-ST-10C §6.4: identify each uncertainty contributor as model (transport-code assumptions and dose-conversion factors), geometry (simplified mesh versus as-built structural detail), or cross-section (nuclear reaction data spread), assign a fractional uncertainty to each contributor, combine them by RSS or linear worst-case summation, apply a k-sigma margin to the nominal computed dose or flue...

Use when assess radiation design margins for EEE components where susceptibility test data carries uncertainty—small sample counts, single-lot characterization, non-equivalent radiation sources, or absent test data entirely. The procedure categorizes the data quality for each radiation effect type (TID, SEE, NIEL, displacement damage), selects an uncertainty multiplication factor proportional to the data shortfall, applies that factor on top of the base radiation design margin, and checks tha...

"Use when calculate total ionising dose (TID) damage for spacecraft

Use when determine the TID assessment basis for a spacecraft electronics programme under ECSS-E-ST-10-12C §7.1–7.4: identify every orbit environment that contributes to total ionising dose (trapped protons, trapped electrons, solar energetic protons, galactic cosmic rays, bremsstrahlung), categorize each device technology against the TID sensitivity spectrum per Table 7-1 (high/moderate/low), flag bipolar linear technologies that require low dose-rate ELDRS testing, and derive the minimum TID...

Use when determine the total ionizing dose (TID) degradation of a component or material from experimental test records under ECSS-E-ST-10-12C §7.6–7.7: extract the dose-response curve from laboratory TID test measurements, interpolate the parameter value at the mission design dose, apply an enhanced low dose-rate sensitivity (ELDRS) correction factor when bipolar semiconductor devices are present to account for greater on-orbit degradation at lower dose rates, apply a lot-variability margin t...

"Use when evaluate TID assessment uncertainties for space electronic

Use when assess interface baseline control and change approval under ECSS-E-ST-10C §5.5: establish an approved baseline from candidate interface documents, categorize each change request as minor (no functional impact) or major (affecting interface definition, timing, or physical properties), verify Interface Change Board quorum before voting, evaluate vote outcome by simple majority, confirm all required stakeholders have formally agreed to the interface document, and maintain an auditable c...

Use when define interfaces for a space system element by establishing the geometry, signals, protocols, and allocated budgets at each interface end in the IDD or single-end ICD, following ECSS-E-ST-10-24C §5.4: identify every interface end, assign the required geometric envelope and mounting constraints, document signal types and electrical characteristics or communication protocols, allocate per-end resource budgets and verify margin against capacity, and confirm the interface-definition rec...

"Use when produce EICDs for space segment elements under ECSS-E-ST-10-24C

Use when produce an Equipment-level Interface Control Document (EICD) for a space-segment equipment item per ECSS-E-ST-10-24C §5.8.1: inventory all equipment interfaces, categorize each as electrical (pin/signal/connector), mechanical (envelope/attachment/mass), or thermal (dissipation/contact resistance/temperature range), validate pin-level signal data per connector, detect duplicate pin assignments, confirm mechanical and thermal field completeness, and flag any interface category absent f...

Use when produce EICDs at the space segment subsystem level per ECSS-E-ST-10-24C §5.8.2: identify all inter-subsystem interfaces by type (mechanical, electrical, thermal, data, RF, fluid, optical, pyrotechnic), verify each interface record carries every required field, confirm that requirement references trace to the system-level requirement registry, flag records where subsystem identifiers are not distinct, and detect duplicate or contradictory interface definitions for the same subsystem p...

Use when generate and validate an Interface Control Document (ICD) against ECSS-E-ST-10-24C Annex B DRD criteria: identify both sides of each interface pair, assign each interface to a recognized type (mechanical, electrical, thermal, data, RF, optical, fluid), confirm all mandatory DRD sections are present (scope, reference documents, interface description, verification requirements), trace every interface requirement to a parent IRD or system-level requirement, and verify that each interfac...

"Use when apply generic Interface Control Document (ICD) structure

Use when generate or validate an Interface Definition Document (IDD) or single-end ICD under ECSS-E-ST-10-24C Annex C: confirm each interface record carries a recognized type and status, verify that every record names its mating item and supplies non-empty interface characteristics, flag any agreed interface that lacks a bilateral ICD reference, surface superseded entries without a successor reference, tally interfaces by status, and decide whether the IDD is complete. Trigger: ecss, e-st-10-...

"Use when identify interfaces for a space system under ECSS-E-ST-10-24C

Use when draft an Interface Identification Document (IID) for a space system or equipment item under ECSS-E-ST-10-24C Annex D: inventory every interface of the item, categorize each interface by type (physical, electrical, data, RF, thermal, optical, fluid), assign a maturity level (proposed, agreed, or baselined) to each interface, record the responsible party for each interface side, verify that every interface links to a controlling Interface Control Document, and aggregate completeness ga...

Use when generate or validate an Interface Requirements Document (IRD) for a space system element pair under ECSS-E-ST-10-24C Annex A: identify both interface parties, categorize each interface requirement by type (mechanical, electrical, thermal, data, rf, environmental, human), assign a unique verifiable identifier to every requirement, confirm each requirement carries a verification method (T/A/I/R/D), check that no duplicate requirement IDs exist, and flag any missing mandatory document-l...

Use when run the interface management life cycles for a space project under ECSS-E-ST-10C §4.3: determine required lifecycle activities per project phase for generic, space-element–launch-segment, space–ground-segment, and OTS-product interface types; check that phase-gate agreements are in place; and verify interface documentation has reached the expected maturity level. Covers all four lifecycle streams and OTS-product involvement agreements. Trigger: ecss, e-st-10-system-scope, interface-m...

Use when produce mechanical interface control documents (MICDs) under ECSS-E-ST-10-24C §5.11: categorize each mechanical interface as structural, kinematic, thermal-mechanical, electrical-mechanical, fluid-mechanical, or optical-mechanical; verify the MICD carries required fields (interface identifier, provider and receiver elements, registered coordinate frame, six-component interface loads, and mass properties); validate that mass is non-negative and all six load components are numeric; fla...

Use when define the Interface Management Plan (IMP) for a space project under ECSS-E-ST-10C §5.1: establish IMP scope and purpose, assign team responsibilities for interface identification, documentation, review, approval, baseline, and change control, specify the IM process steps from identification through verification, schedule IM milestones against project lifecycle phases (phases 0 through F), and integrate the IMP with the System Engineering Plan (SEP) by linking the SEP IM section and ...

"Use when define the interface reference data list for a space system

"Use when structure interface requirements for an Interface Requirements

Use when produce test interface control documents (TICDs) for ground test interfaces under ECSS-E-ST-10-24C §5.10: identify every electrical, mechanical, data, and power interface between the unit under test and ground support equipment, define each signal's type, direction, connector, and pin assignment, verify pin assignments are unique, confirm a ground reference signal is present, and check that all required interface categories are covered before the test campaign begins. Trigger: ecss, ...

Use when produce TM/TC interface control documents (ICDs) for a spacecraft following ECSS-E-ST-10-24C §5.9: register CCSDS application process identifiers (APIDs), define PUS-based telemetry and telecommand packet structures with service and subservice assignments, validate packet field ranges against CCSDS and PUS-C conventions, check APID registration completeness, and verify the ICD includes at least one TM downlink and one TC uplink definition. Trigger: ecss, e-st-10-system-scope, tmtc-ic...

"Use when verify and validate interfaces under ECSS-E-ST-10-24C §5.6:

Use when define the antenna design-baseline that has to be fixed early in the design cycle under ECSS-E-ST-20C clause 7.2.2.1: categorize the declared build into its antenna family (reflector, lens, array, horn, wire), confirm every mandatory element role of that family is present and that no element belongs to another family, check each selected technology is an admissible implementation of its element role and carries enough technology-readiness at the baseline-freeze review, verify the fix...

Use when structure the antenna engineering steps of ECSS-E-ST-20C clause 7.2.1.2.2, from mission-transmission-reception-analysis through to the antenna design decision: validate that a step is entered only once its predecessors are complete and its entry data is on record, derive the antenna-gain that the required-effective-isotropic-radiated-power leaves after transmitter output and feeder-loss, turn the coverage footprint at the orbit altitude into an edge-of-coverage half-angle, convert th...

Use when determine whether a spacecraft antenna retained without redundancy is a single-point-failure item under ECSS-E-ST-20C clause 7.2.1.3, and whether its failure-rate is agreed with the customer, specified in the requirement-baseline and demonstrated by evidence: categorize the redundancy-scheme (none, cold-standby, hot-standby, cross-strapped), confirm a numeric failure-rate in failures-per-billion-hours is on record, check that the demonstrated failure-rate does not exceed the specifie...

Use when verify the guided-wave interfaces on an antenna port under ECSS-E-ST-20C clause 7.2.3.1: categorize each port as a coaxial-connector or a waveguide-flange, convert the declared voltage-standing-wave-ratio into reflection-coefficient, return-loss and mismatch-loss, check the operating-frequency against the rectangular-waveguide cutoff-frequency and single-mode-band or against the coaxial higher-order-mode-onset and characteristic-impedance tolerance, derate the interface rf-power-rati...

Use when determine the antenna characterisation parameter-set demanded by ECSS-E-ST-20C clause 7.2.2.5: confirm every mandatory radiative parameter is declared for the antenna-function at hand, sort each declared entry into its beam-coverage, directivity-and-antenna-gain, polarisation-purity, boresight-pointing or port-matching family, derive directivity from the half-power-beamwidth pair, convert directivity into antenna-gain through radiation-efficiency, translate axial-ratio into cross-pol...

Use when evaluate the radiative interaction between an antenna and its surrounding spacecraft-structure under ECSS-E-ST-20C clause 7.2.3.2, from phase B onward: place each appendage (solar-array-wing, thermal-radiator, deployable-boom, neighbouring radiating-port) in the reactive-near-field, radiating-near-field or far-field zone, categorize its interaction-path as main-beam-blockage, near-field-coupling, side-lobe-scattering or port-to-port-coupling, convert the item radar-cross-section and ...

Use when verify the antenna engineering provisions of ECSS-E-ST-20C clause 7.2.4: assign each antenna requirement a verification method its characteristic can actually evidence, check the planned closure gate is neither earlier than that method can physically close nor later than the gate the antenna category is held to, confirm every closed requirement names a well-formed antenna verification record and every waived one carries a reference and a rationale, and compute the verification-covera...

Use when evaluate the feed-chain of a spacecraft antenna as a circuit in its own right under ECSS-E-ST-20C clause 7.2.2.3.5: categorize every stage as a waveguide-run, filter, diplexer, orthomode-transducer, rotary-joint, directional-coupler, polariser or switch, sum the cascaded-insertion-loss against its allocation, refer each stage dissipation back through the Friis cascade into a chain noise temperature, turn the stage return losses into adjacent-interface mismatch ripple and a worst-case...

Use when compute the support-structure-scattering assessment of ECSS-E-ST-20C clause 7.2.2.3.6: categorize every feed-support-strut, subreflector tripod-leg and rim-fitting by the field-region it intercepts, separate plane-wave-scattering in the collimated aperture-field from spherical-wave-scattering in the diverging feed-wave and from rim edge-diffraction, magnify each feed-region shadow onto the reflector, sum the projected aperture-blockage-area, derive the blockage-efficiency antenna-gai...

Use when verify that one recognised source of antenna terminology governs every project document under ECSS-E-ST-20C clause 7.2.1.2.1: confirm exactly one terminology-source is declared and that it is a recognised vocabulary, resolve each term used in a specification, drawing or report against the canonical-term registry, rewrite a deprecated-synonym onto its canonical form, flag an uncategorized term and a term whose defining vocabulary differs from the declared one, check each project-gloss...

Use when judge whether a spacecraft function interrupted by an electrostatic arc returns to its specified performance under ECSS-E-ST-20C clause 6.3.4.3: categorize the event as a self-extinguishing primary discharge or a power-fed sustained secondary arc, derive the outage from arc onset to restored service and check it against the allowance the function holds, compare every post-arc parameter against its specified level in the correct direction of merit, quantify the residual shortfall that...

Use when compute the element-to-element mutual-coupling of a spacecraft phased-array antenna under ECSS-E-ST-20C clause 7.2.2.2.3: build the pair coupling matrix from the lattice spacing in wavelengths and the E-plane, H-plane or diagonal pair orientation, categorize every pair as strong, moderate, weak or negligible, combine the commanded element excitations with that matrix into the active-reflection-coefficient and active-standing-wave-ratio of each radiator, sweep the scan volume for a sc...

Use when verify that an array-fed reflector antenna satisfies both provision families of ECSS-E-ST-20C clause 7.2.2.2.4 at once: confirm the dossier declares and verifies a reflector provision and a radiating-array provision, categorize each beam as single-feed-per-beam or multiple-feed-per-beam, turn the reflector profile error into a ruze-surface-efficiency, trade the feed-cluster edge-taper between illumination and spillover, fold in the feed-cluster excitation efficiency, convert a latera...

Use when derive a spacecraft magnetic cleanliness requirement from the attitude control need under ECSS-E-ST-20C clause 6.3.7.3: evaluate the ambient geomagnetic field at the orbit, convert the control system's allowable magnetic disturbance torque into an allowable spacecraft residual dipole moment, split that allowance across the steady, switching-transient and long-term-drift contributions, categorize every contributor into exactly one of those three families, grow the drifting ones to end...

Use when define the maximum cell ratings that ECSS-E-ST-20C clause 5.6.3 requires a battery design to hold, and verify a duty profile against them: hold a temperature window, a charge ceiling and a discharge floor voltage, and charge, discharge and storage current limits for every operating mode; tighten the whole set through a derating policy of voltage and current factors plus a thermal margin; then examine each declared operating point mode by mode, name the parameter with the least normal...

Use when verify that a spacecraft battery charger can bring a deeply discharged pack, including one taken all the way to zero volts, back into service under ECSS-E-ST-20C clause 5.7.3: categorize the cell terminal state from its measured voltage, select the charge stage that state permits, derive each stage current limit from the rated capacity, time the recovery trickle against its budget, and report a commanded current, cell voltage, charge temperature, depth of discharge or end-of-discharg...

Use when determine whether the ECSS-E-ST-20C clause 5.6.1 battery provisions reach a given on-board energy store: categorize every item as a secondary rechargeable electrochemical battery, a primary non-rechargeable electrochemical battery, an electrochemical converter that holds no internal reactants, or a non-electrochemical store; resolve the declared cell assembly into nominal voltage, ampere-hour capacity and stored energy; select the provision groups that follow from the category; and r...

Use when plan, verify and record the pre-launch removal, replacement or storage of a spacecraft battery module under ECSS-E-ST-20C clause 5.6.4: categorize the module access path (direct-hatch-access, panel-removal, harness-demate, stack-teardown or non-removable), project the open-circuit state of charge a stored module reaches from its temperature-corrected self-discharge rate, screen the storage envelope for temperature excursion, deep-discharge, shelf-life and humidity breaches, derive th...

Use when manage the safety case for a spacecraft battery under ECSS-E-ST-20C clause 5.6.5.2 and the product assurance space-safety route: categorize each battery hazard by severity and likelihood, scale the control strategy it earns (independent inhibit count, containment provision, cell-to-cell propagation barrier), count only the inhibits that are genuinely independent and verifiable towards the achieved failure tolerance, compute the thermal margin between the predicted cell temperature an...

Use when size a spacecraft secondary battery so that the ECSS-E-ST-20C clause 5.6.2 energy balance closes in every declared mission phase: convert each phase into produced, consumed and net energy over its duration, divide the phase discharge by the discharge-path efficiency and the allowable depth of discharge to obtain the capacity it demands, carry the driving phase back to a beginning-of-life rating through capacity fade, confirm the charge window restores what the discharge window drew, ...

Use when verify that a battery-user-manual carries the content required by the ECSS-E-ST-20C Annex D data-requirement: check each mandated chapter (cell-and-battery identification, operating-envelope, charge-and-discharge-control, ground-handling-and-storage, safety-and-hazard-precautions, life-and-degradation-data, transport-and-shipping), reject an uncategorized chapter, prove the declared operating-envelope is self-consistent and that the charge-termination-voltage sits inside it, check th...

Use when compute the independent circuit characterisation of a spacecraft antenna beam-forming-network under ECSS-E-ST-20C clause 7.2.2.3.4: categorize the network topology as corporate, series, matrix or switched, turn commanded element excitations plus per-path insertion-loss, amplitude-error and phase-error entries into the realized element excitations, separate that departure into a linear phase-gradient that shifts the boresight and a residual scatter that costs aperture-efficiency, add ...

Use when verify that a spacecraft electrical subsystem stays robust when a protection device clears a fault and when the primary bus voltage leaves its normal band, under ECSS-E-ST-20C clause 5.7.4: categorize each protection device, check its rating against the derated steady current and the fault current available to clear it, compare the let-through energy with the harness withstand and with the downstream device for coordination, categorize each bus excursion by magnitude and duration, an...