Claude Skills by ashfordeOU

Use when produce the multipactor-verification-plan required by ECSS-E-ST-20-01C clause 4.2.1 and keep it current afterwards: confirm the baseline plan is issued no later than the equipment-qualification-review and carries an approved sign-off rather than a draft state, validate the revision-history for unique identifiers and non-decreasing dates, categorize every configuration-change-event as one that forces a plan-update -- radio-frequency power increase, gap-geometry change, electrode-mater...

Use when derive the worst-case secondary-electron-emission-yield curve that a multipaction assessment has to use under ECSS-E-ST-20-01C clause 9.3: take the set of measured yield-versus-primary-electron-energy curves held for one surface condition, restrict them to the energy interval they all cover, interpolate each curve onto the shared energy grid, take the highest yield value at every primary-electron-energy, and report the resulting envelope with its peak, the first and second crossover-...

Use when verify that the erosion charge-exchange-ions sputter from a spacecraft surface stays inside the agreed allowance, per ECSS-E-ST-20-06C clause 11.2.4: categorize the exposure as direct-beam-impingement, charge-exchange-backflow or no-ion-exposure, convert the collected ion-current-density into an ion-number-flux, evaluate the near-threshold sputter-yield of the surface material at the arrival energy, combine flux, yield and atomic-number-density into an erosion-rate, integrate that ra...

Use when verify that a spacecraft-charging computer model offered as design-acceptance evidence carries the physical content required by ECSS-E-ST-20-06C clause 6.8.4: confirm the simulation represents ambient-electron-collection and ambient-ion-collection, photoemission on sunlit-surfaces, secondary-electron-emission by electrons and by ions, electron-backscatter, surface-conduction and bulk-conduction in dielectrics, radiation-induced-conductivity under penetrating-radiation, illumination-g...

Use when plan the spacecraft-charging protection programme required by ECSS-E-ST-20-06C clause 5: score an early charging-hazard assessment for each item from its orbital-environment severity, its surface-exposure kind and its exposed area, categorize the electrostatic-discharge risk into a band, derive the mitigation measures and the verification-method set that band demands, compare the planned project-review milestone against the latest acceptable one, and report every item with no plan en...

Use when audit the applicable-document tree of a spacecraft-charging activity under ECSS-E-ST-20-06C clause 4.2: parse each ECSS identifier into branch, document kind, discipline, issue and revision, confirm the charging standard sits in the engineering branch under the electrical-and-electromagnetic discipline, map every charging-analysis topic onto the normative reference that governs it, and screen the declared applicable-document list for missing references, malformed identifiers, duplica...

Use when determine whether an external surface has to go to sample testing under ECSS-E-ST-20-06C clause 6.6.1: take each surface item with the status of every material-provision and analysis-provision, downgrade a compliance-claim whose evidence cannot carry it, a bare declaration, an analytical demonstration offered against a measured-property provision, or heritage outside its qualified-envelope, trigger the sample-kind each unmet provision demands, size and sequence the resulting sample-c...

Use when assess the spacecraft-charging concerns a hardware item actually carries under ECSS-E-ST-20-06C clause 4.1.2: compute the differential-potential between an external-surface and its structure reference and against an adjacent surface, compare both and the absolute frame potential with electrostatic-discharge-onset thresholds, derive the bulk electric-field a deposited current density drives through a dielectric from its resistivity, check that field and the deposition rate against bur...

Use when verify that a conductive-coating on an externally exposed spacecraft surface still carries its electrostatic bleed path at end-of-life under ECSS-E-ST-20-06C clause 6.3.3.5: accumulate the depth each erosion mechanism removes across the mission lifetime, atomic-oxygen recession, ion-sputtering, particulate-abrasion and handling-wear, scale the sum by the erosion-uncertainty factor, subtract it from the as-deposited thickness, and check the surviving layer against both the coating con...

Use when verify that an outer spacecraft material conducts well enough to hold its surface potential under the permitted ceiling per ECSS-E-ST-20-06C clause 6.3.3.2: convert bulk-resistivity and coating-thickness into sheet-resistance, compute the through-thickness ohmic-drop and the lateral potential-rise driven by the worst-case charging-current-density, select the governing drain-path, compare the resulting surface-potential against the ceiling, derive the maximum-allowable-resistivity, an...

Use when verify that the environments a spacecraft sees do not interrupt or degrade a bonding current path under ECSS-E-ST-20-06C clause 6.8.3: categorize each exposure as random-vibration, sine-vibration, mechanical-shock, acoustic-noise, thermal-cycling, thermal-vacuum or humidity-and-corrosion, confirm the exposure set required for the path class is complete, check each run reached the qualification level in the right unit and was held long enough, require live continuity-monitoring while ...

Use when determine how a deliberately biased external surface disturbs the electrostatic potential around the vehicle under ECSS-E-ST-20-06C clause 6.5: inventory every commanded-bias element, a high-voltage-array string end, an electric-propulsion grid, a plasma-contactor, a biased-plasma-probe or a tether-anode, with its bias-offset and its exposed conductive area, evaluate the plasma current each element exchanges at a trial frame potential, solve the vehicle floating-condition by bisectio...

Use when evaluate whether a mission holds differential-charging and stored-discharge-energy below its acceptable levels under ECSS-E-ST-20-06C clause 6.1.2: take the predicted absolute potential of each adjacent surface-pair, derive the differential-potential across the dielectric gap, compute the pair capacitance from coated-area, dielectric-thickness and relative-permittivity, convert it into the stored-discharge-energy an electrostatic-discharge would release, grade each pair against the m...

Use when map an electric-propulsion unit onto its thruster family and the spacecraft-charging interactions its operation drives under ECSS-E-ST-20-06C clause 11.1.1: sort each designation into the electrostatic, electromagnetic or electrothermal family, derive exhaust-velocity, propellant mass-flow and extracted beam-current from thrust, specific-impulse and propellant ion-mass, decide whether the unit ejects a net charged beam and so needs an electron-emitting neutralizer, enumerate the char...

Use when allocate every electric-propulsion requirement to the standard that owns it and confirm the charging provisions of ECSS-E-ST-20-06C clause 11.1.2 sit correctly alongside the propulsion standard governing performance, interfaces and verification-of-requirements: resolve each requirement-topic to its owning standard, flag a misallocated owner, demand an explicit cross-reference on a jointly-governed topic, reject an unrecognised verification-method, detect duplicate identifiers and con...

Use when determine whether the surface electrical-continuity rules of ECSS-E-ST-20-06C clause 6.3.3.1 govern a spacecraft outer item: walk the applicability decision-diagram in order — plasma-exposure, deliberately-biased and high-voltage-surface routing, conductive versus dielectric material-family, the small-isolated-conductive-part waiver sized from stored-discharge-energy, and the severity of the mission charging-environment — then record the governing rule, the route taken, and every ung...

Use when structure and check the electrical-hazard mitigation-plan annex of ECSS-E-ST-20-06C Annex A: confirm the document carries every required section, categorize each declared hazard into an electrostatic, propulsion-interaction, power-distribution or grounding-and-bonding family, score its assessment outcome on the severity-by-likelihood grid, credit only the mitigations whose verification-status has actually progressed, recompute the residual-risk band per hazard, and decide release rea...

Use when determine whether the Lorentz-force interaction on a deployed electrodynamic-tether can pump a dynamic instability, under ECSS-E-ST-20-06C clause 10.2.6: build the mode table from the orbital mean-motion (gravity-gradient libration, taut-string transverse and axial longitudinal modes), assemble the forcing spectrum from orbital harmonics of the geomagnetic-field variation and from the current-modulation rate, categorize every forcing line as libration-resonance, transverse-string-res...

Use when determine which arcing provisions extend to the exposed elements of the power-chain beyond the solar-array under ECSS-E-ST-20-06C clause 7.3: categorize each element as drive-mechanism, rotary-transfer, conductor-run or conditioning-unit, compute the largest conductor-to-conductor differential it presents and its most negative exposed potential relative to the ambient plasma, derive the arcing regime from those two against the primary-arc-inception and sustained-arc thresholds, expan...

Use when determine whether an isolated conductive part may stay ungrounded under ECSS-E-ST-20-06C clause 6.3.2: compute its capacitance to the structural reference from the exposed-area and dielectric-standoff geometry, estimate the floating-potential it reaches under the charging environment or through its leakage-resistance, evaluate the stored electrostatic-energy and the peak discharge-current that energy could deliver, and grant the small-isolated-conductor exception only when exposed-ar...

Use when verify that a spacecraft bonding-and-grounding provision is closed under ECSS-E-ST-20-06C clause 6.8.1 through inspection evidence combined with an electrical continuity measurement: categorize each provision as a structure-bond, equipment-chassis-bond, harness-shield-termination or static-dissipative-bleed-path, confirm the inspection record carries surface-preparation, fastener-installation, corrosion-protection and conductor-routing evidence with no open nonconformance, check the ...

Use when compute the plasma-interaction behaviour of a high-voltage solar-array or other deliberately biased external surface in the dense low-orbit plasma of ECSS-E-ST-20-06C clause 8.1: validate the ambient electron-density and electron-temperature, derive the electron-thermal and ram-ion current densities, solve the two-area current-balance that fixes how much of the string-voltage floats positive of the plasma and where spacecraft-ground settles, categorize each biased surface as exposed-...

Use when compute the electric field standing inside a solid insulating material and check it against the internal-dielectric-field cap of ECSS-E-ST-20-06C clause 9.2.3: derive the field from the applied potential and the insulator geometry -- planar wall thickness or coaxial inner and outer radii -- apply the material and temperature derating that the insulator is qualified for, then compare the derated field with the default internal-field cap unless a higher application-specific level is de...

Use when assess internal parts and materials exposed to deep-dielectric-charging for internal-electrostatic-discharge, under ECSS-E-ST-20-06C clause 9.1: attenuate the energetic-electron-flux through the local shield thickness, screen out items below the internal-charging screening threshold, categorize every remaining item as a bulk-dielectric, an ungrounded-conductor or a grounded-conductor, then check its steady-state buried-charge-field against the dielectric-field limit, its stored disch...

Use when audit a structure-and-harness grounding inspection campaign under ECSS-E-ST-20-06C clause 9.3 and prove that no internal metallic item was left ungrounded: build the inventory of internal-metallic-items from the structure and harness build records, match each item to an inspection record, check the record used a method valid for that item family -- visual-bond-inspection, bond-resistance-measurement or shield-continuity-check -- read the measured bond-resistance against the item limi...

Use when verify that every internal metallic item of a spacecraft -- harness-shield, equipment-enclosure, connector-backshell, internal-bracket, secondary-structure -- carries two independent grounding routes under ECSS-E-ST-20-06C clause 9.2.2: categorize each internal-metallic-item into its bonding family, build every candidate grounding-route from its bond segments, total the segment bond-resistance and check it against the family route cap, then prove two surviving routes are genuinely in...

Use when verify that a spacecraft-charging qualification campaign exercises every material and every assembly under both the normal-gradient and the inverted-gradient potential condition of ECSS-E-ST-20-06C clause 6.6.3: derive the gradient polarity from the measured dielectric-surface and structure potentials, compute the qualification stress from the worst-case predicted differential-potential and the qualification factor, categorize each run as qualifying or non-qualifying against campaign...

Use when determine whether individual material-characterization testing of a spacecraft-charging material may be waived because an assembly-level-qualification test already bounds it, under ECSS-E-ST-20-06C clause 6.6.2: categorize every charging-relevant material parameter, confirm the material sits inside the assembly in its as-flown-configuration, check that the assembly test-envelope bounds the worst-case flight exposure in electron-energy, particle-flux, temperature and exposure-duration...

Use when verify that the electrical material properties behind a spacecraft-charging decision rest on measured data under ECSS-E-ST-20-06C clause 6.8.2: categorize each parameter record by provenance (selection-campaign-measurement, maker-declared-measurement, generic-reference-value, unsubstantiated-estimate), check bulk-resistivity, surface-resistivity, relative-permittivity, secondary-emission-yield-peak, photoemission-yield and dielectric-thickness against physically admissible ranges and...

Use when compute the maximum permitted resistivity of a spacecraft external dielectric under ECSS-E-ST-20-06C clause 6.2.2: derive the bounding charging-current-density from the electron-flux, secondary-emission and photoemission balance, convert an allowable differential-potential into a bulk-resistivity ceiling through the material thickness and into a sheet-resistivity ceiling along the bleed-path length, compare each declared material resistivity against its ceiling with an explicit margi...

Use when derive the maximum permitted surface potential of an external spacecraft surface under ECSS-E-ST-20-06C clause 6.2.1: look up the material-family ceilings for absolute-surface-potential, differential-surface-potential and dielectric-breakdown-field, convert the field ceiling into the equivalent potential the dielectric-thickness allows, take the binding ceiling as the lower of the two, apply the mission safety-factor and any mission-specific override, compare the predicted worst-case...

Use when evaluate a spacecraft-external assembly that combines dissimilar ungrounded materials against ECSS-E-ST-20-06C clause 6.3.3.4: categorize every constituent as grounded-conductor, floating-conductor or exposed-dielectric from its surface-resistivity and bonding state, decide whether the stack qualifies as a mixed-material-assembly, quantify the resistivity decade-span between exposed ungrounded constituents that drives differential-charging across the interface, and confirm the verifi...

Use when estimate the induced plasma-density around a vehicle caused by propulsion gas release under ECSS-E-ST-20-06C clause 11.3.5: expand every release into the free-molecular far field with a cosine-law plume model, evaluate the neutral-number-density at each observation point, convert the electron-impact ionized share into an induced electron-density, add the ambient-plasma background, and check the resulting electron-plasma-frequency and Debye-length against the plasma-density-limit and ...

Use when assess whether neutral-gas released close to a spacecraft can trigger a gas-discharge on a high-voltage-surface under ECSS-E-ST-20-06C clause 6.9: inventory every release path (propulsion-plume, propellant-leak, pressurant-leak, commanded-vent, material-outgassing, water-desorption, sublimation), compute the local neutral-density and neutral-pressure each one produces at the exposed hardware, form the pressure-gap product, evaluate the Paschen-breakdown voltage for the released speci...

Use when determine the extra electrostatic-cleanliness provisions a science spacecraft owes its plasma-measurement instruments under ECSS-E-ST-20-06C clause 6.7: categorize each instrument by the lowest particle-energy it measures, compute the measurement distortion that the spacecraft-floating-potential and the local differential-potential impose on that energy, check the conductive-surface coverage and potential uniformity of the exposed outer skin, size the boom that places a field probe b...

Use when compute the parasitic leakage-current that exposed conductors drain out of the ambient-plasma and confirm the resulting power-loss is acceptable, under ECSS-E-ST-20-06C clause 8.3: validate the plasma-environment, categorize each exposed element as electron-collecting, ion-collecting or non-collecting from its bias relative to plasma potential, scale the thermal-current-density by the orbit-limited-motion sheath enhancement for its geometry, apply the snapover multiplier where an ele...

Use when establish the vacuum-chamber effects that distort a ground firing of an electric-propulsion thruster and their influence on the measured results, under ECSS-E-ST-20-06C clause 11.3.1: derive the facility background-pressure from propellant mass-flow and pumping-speed, size the pumping-speed a target background-pressure demands, quantify the charge-exchange enhancement along the plume path, decide whether the chamber wall intercepts the divergence-cone, estimate back-sputtered wall-ma...

Use when verify that a spacecraft-propulsion-interaction simulation represents every model element ECSS-E-ST-20-06C clause 11.3.2 enumerates: categorize each declared element into its family - outer-geometry, thruster-source, power-subsystem or grounding-reference - list the required elements no declaration covers, check the computational-mesh cell-size against the Debye-length of the modelled plasma, reconcile the declared beam-current with the thrust and beam-voltage the thruster model asse...

Use when compute the particle deposition an electric-propulsion plume leaves on a spacecraft surface and hold it under the limit the customer agreed, per ECSS-E-ST-20-06C clause 11.2.3: categorize every efflux source as neutral-efflux or charged-efflux, resolve its transport path as direct plume-cone impingement, charge-exchange-backflow, neutral-scatter-backflow or no-transport-path, propagate the source rate through cone solid-angle, inverse-square distance and incidence-cosine into an area...

Use when determine whether a restricted insulating material may be carried on a spacecraft external surface under ECSS-E-ST-20-06C clause 6.3.3.6: match every externally exposed item against the restricted-dielectric register and against the bulk-resistivity and surface-resistivity thresholds that make an unregistered material restricted in its own right, exempt only a negligible exposed area, then permit the item solely on a three-dimensional charging-simulation waiver that models the item g...

Use when identify which family a secondary-arc on a photovoltaic solar-array belongs to and how far the clause-7 provisions of ECSS-E-ST-20-06C reach: separate a non-sustained flashover of stored surface-charge from a temporary-sustained and a permanent-sustained arc using the event duration and how it ended, determine whether an array site (cell-to-cell-gap, string-to-string-gap, cell-interconnect, coverglass-edge, array-bus-bar) is plasma-exposed and generator-fed enough for the provisions ...

Use when verify the pass conditions of a secondary-arc qualification-campaign on a solar-array coupon under ECSS-E-ST-20-06C clause 7.2.3.3: confirm the campaign envelope bounds the worst-case string-voltage, string-current, primary-arc population and bias-dwell, categorize every recorded discharge event as non-sustained, temporary-sustained or permanent-sustained from its duration, its peak arc-current and how it terminated, reject any sustained event against the no-sustained-arc condition, ...

Use when verify that a secondary-arc campaign on array coupon samples is laid out and graded as ECSS-E-ST-20-06C clause 7.2.3.2 requires: check each coupon against the flight article for conductor-gap, coverglass-thickness, interconnect-type, adhesive-type, harness-routing and string-count representativeness, lay out the voltage-by-current campaign matrix, size the triggered primary-arc budget per point with a doubled count inside the band around the expected sustained-arc boundary, categoriz...

Use when evaluate whether a photovoltaic array may omit the secondary-arc test campaign under ECSS-E-ST-20-06C clause 7.2.3.1: build the worst-case string-to-string potential term by term from the open-circuit operating point, the cold-temperature excursion and the regulation transient, derive the sustained-arc onset voltage for the actual conductor-gap and insulating-material at the arc site, check the potential against that onset with the required margin, check the current the parallel-stri...

Use when verify that on-board equipment cannot feed a self-sustained-discharge after an electrostatic-discharge is triggered, under ECSS-E-ST-20-06C clause 8.2: categorize each adjacent-conductor pair by gap, barrier material, steady potential-difference and the fault-current its source can deliver; derive the secondary-arc sustaining-voltage and sustaining-current thresholds for that gap; decide whether the pair quenches, flickers as a temporary-sustained-arc, or latches as a permanent-susta...

Use when determine whether a photovoltaic solar-array design triggers the arc-characterization obligation of ECSS-E-ST-20-06C clause 7.2.2: categorize every exposed array surface element as conductive or dielectric, check each one against the surface-grounding provisions (bond-path resistance to structure, conductive-coating surface-resistivity, ungrounded dielectric exposed-area allowance), compute the triple-junction primary-arc inception threshold from coverglass-thickness, interconnect-ga...

Use when evaluate the space-plasma-environment a spacecraft flies through under ECSS-E-ST-20-06C clause 4.1.1 and the spacecraft-charging risks it creates: compute the debye-length and the electron-thermal-flux from ambient electron-density and electron-temperature, categorize the ambient population as cold-ionospheric, warm-magnetospheric, hot-substorm or energetic-electron, decide whether the body sits in a thin-sheath or a thick-sheath regime against its characteristic-length, derive the s...

Use when compute sputter erosion of spacecraft external surfaces from simulated ion trajectories under ECSS-E-ST-20-06C clause 11.3.4: categorize every simulated ion population as primary-beam, beam-wing, charge-exchange or backflow, decide whether its trajectory crosses the angular span a surface subtends from the thruster exit-plane, evaluate the energy-dependent and incidence-angle-dependent sputter-yield of the target material against its sputter-threshold, integrate the removed thickness...

Use when compute the vehicle-wide surface-potential-analysis required by ECSS-E-ST-20-06C clause 6.4: assemble the external-material-inventory row by row, categorize every exposed item as charge-dissipating or charge-storing from its sheet-resistivity and its bonding-path, check the inventoried area against the declared external-area so no exposed item escapes the assessment, evaluate the secondary-emission-yield and backscatter-yield at the worst-case plasma-temperature, solve each item's eq...

Use when compute the floating potential of a spacecraft external surface under ECSS-E-ST-20-06C clause 4.1.3: categorize every current contributor as ambient-plasma collection or surface emission, evaluate the potential-dependent electron-collection, ion-collection, secondary-electron-emission, backscattered-electron and photoemission-current terms, solve the current-balance by bisection for the equilibrium potential of a sunlit or eclipsed surface, categorize the resulting surface-charging r...