Claude Skills by ashfordeOU

Use when build the operations timeline for a human-rated space system per ECSS-E-ST-10-11C §4.9.3: sequence each crew task in a phased timeline, compute the time-averaged workload index for each hourly assessment window, verify no window exceeds the maximum allowable workload level, confirm mandatory rest gaps are preserved between consecutive high-demand activity clusters, and check that concurrent task counts remain within the cognitive limit specified by the HFE requirement. Trigger: ecss,...

Use when defining the training approach for human operators as required by ECSS-E-ST-10-11C §4.3.5: categorize each operator task by criticality and worst-case error consequence, determine the minimum required training level (awareness, procedural, or expert), select admissible training means (simulation, CBT, classroom, on-the-job, handbook, or briefing), assign a training strategy (initial, recurrent, refresher, or qualification), set the recurrent interval for strategies that repeat, and v...

Use when define training requirements and materials for operator tasks derived from operational products under ECSS-E-ST-10-11C §4.9.5: determine the training need tier for each task from task complexity, procedural novelty, and safety criticality (routine / standard / enhanced / specialized); verify that the minimum required training materials exist for the assigned tier; confirm that every personnel role performing the task holds a training assignment before first operational use; and asses...

"Use when define user populations for a space system under ECSS-E-ST-10-11

Use when define the users manual for a human-rated space system under ECSS-E-ST-10-11C §4.3.4: verify that all required HFE input sections are present (user population, task procedures, interface description, error recovery, mission-phase applicability, training requirements), validate each task procedure's steps against applicable mission phases, confirm that safety-critical steps carry a warning note, verify that every task procedure with safety-critical steps has a linked error-recovery en...

Use when verify Human Factors Engineering (HFE) requirements by analysis or similarity under ECSS-E-ST-10-11 §4.11.2: select the applicable analysis method (task analysis, cognitive workload, workspace envelope, anthropometric analysis, or digital human model simulation), score heritage similarity against the target design to determine whether prior evidence transfers, run DHM simulations and compare joint angles, reach zones, crew forces, and visual fields against acceptance thresholds, and ...

Use when verify human factors engineering requirements for a space system by running crew-in-the-loop simulations under ECSS-E-ST-10-11C §4.11.4: define simulation scope and acceptance criteria, recruit representative and qualified crew participants, execute integrated system simulations, measure task completion, error rate, and workload against thresholds, compare results to acceptance criteria, and produce a simulation-based HFE verification report. Trigger: ecss, e-st-10-system-scope, hfe-...

Use when verify human factors engineering (HFE) requirements for a space system by ground tests and demonstrations per ECSS-E-ST-10-11C §4.11.3 and Annex D: identify each HFE requirement needing ground verification, assign a verification method (test, demonstration, analysis, or inspection), map each test or demonstration method to its Annex D event category, check that all mandatory Annex D ground events are covered, evaluate pre-event readiness criteria, and aggregate pass, fail, and pendin...

Use when assess workstation layout and human-factors design for a crewed spacecraft under ECSS-E-ST-10-11C §4.7.6: verify display placement within acceptable viewing angles from the crew Eye Reference Point, verify controls fall within the reach envelope for their access-frequency zone (primary, secondary, or tertiary), and verify ingress/egress clearance dimensions meet minimum crew-access requirements. Categorize each workstation element by access-frequency zone, flag any element outside it...

Use when compute background radiation from induced radioactive activation of spacecraft materials under ECSS-E-ST-10C §10.4.4: identify target isotopes in the material stack, compute saturation activity from particle flux and activation cross-section, derive build-up activity at end-of-irradiation, apply radioactive decay for the post-irradiation cooling interval, convert activity to background count rate or absorbed dose rate using detector solid angle and efficiency, and aggregate contribut...

Use when define the sensor-background assessment basis for a space instrument under ECSS-E-ST-10-12C §10.1–10.3: identify the relevant natural radiation environments for the target orbit (trapped electrons and protons, galactic cosmic rays, solar energetic particles, albedo neutrons), map the instrument to a sensor-technology family from the standard's Table 10-1 taxonomy (silicon semiconductor, scintillator, proportional counter, solid-state germanium, CdTe/CdZnTe, neutron detector, microcha...

Use when run radiation background calculations for a spacecraft instrument or detector under ECSS-E-ST-10C §10.4.9: compute the energy-deposition spectrum by applying linear energy transfer to the ambient particle flux in each energy bin, determine the absorbed dose for each particle species, derive nuclear interaction rates from the particle flux, nuclear cross-section, and target areal density, apply Beer-Lambert attenuation to propagate the radiation environment through shielding material,...

Use when predict the sensor background count rate produced by direct ionisation of the active detector volume by charged particles under ECSS-E-ST-10-12C §10.4.2: identify the charged particle populations (trapped protons, trapped electrons, galactic cosmic rays, solar energetic particles) at the target orbit, compute the energy deposited per crossing particle from its linear energy transfer (LET) and sensor geometry, retain only populations whose deposited energy meets or exceeds the detecti...

"Use when assess background radiation using experimental irradiation

Use when estimate radiation-induced noise contributions for a space-based gravity-wave detector test mass under ECSS-E-ST-10-12C §10.4.7: determine the particle-flux-driven charge deposition rate on the test mass, compute the stochastic force noise power spectral density from charge shot-noise coupling and from cosmic-ray momentum-transfer recoil, convert total force noise to displacement noise using the free test-mass transfer function, verify that accumulated charge stays within the charge-...

Use when determine the background count rate produced by nuclear interactions in spacecraft shielding materials under ECSS-E-ST-10-12C §10.4.3: for each shielding layer, compute the nuclear interaction probability from material type and areal density using the nuclear interaction length, estimate the secondary particle yield per interaction as a function of incident particle energy, compute the interaction rate for a given incident flux and detector area, scale by the fraction of secondaries ...

"Use when estimate scintillation and Cerenkov background count rates

"Use when compute the fluorescent X-ray interaction background for

Use when defining the space radiation environments applicable to a crewed mission and verifying crew dose compliance with ECSS-E-ST-10C §11.3–11.4: identify which environments (galactic cosmic rays, solar energetic particles, trapped protons, trapped electrons, secondary neutrons) apply to the orbit profile, determine dose contributions to the blood-forming organ, eye lens, and skin, compare accumulated doses against the short-term (30-day and annual) and career limits for each crew member, a...

"Use when calculate biological effects margins for a crewed mission

"Use when determine dosimetric quantities for a space radiation

Use when run a radiobiological risk assessment for a crewed or uncrewed space mission under ECSS-E-ST-10C §11.5: estimate excess cancer risk from accumulated effective dose, categorize each uncertainty source (dosimetry, biological, model, epidemiological, transport) per the §11.5 uncertainty taxonomy, derive risk bounds using the compound uncertainty factor, and determine whether the risk estimate meets mission-acceptable limits. Trigger: ecss, e-st-10-system-scope, radiobiology, space-radia...

"Use when evaluate uncertainties in a space-radiation biological-effects

Use when assess displacement damage (DD) parameters for a spacecraft device under ECSS-E-ST-10-12C §8.5: determine the total non-ionizing dose (TNID) by summing NIEL-weighted fluence contributions across all particle species and energy bins for the mission environment, convert TNID to the displacement damage equivalent fluence (DDEF) referenced to a standard particle, apply the project radiation design margin (RDM) factor to the DDEF, and compare the margin-adjusted DDEF against the device di...

"Use when determine the end-of-life parametric degradation of a

Use when identify displacement-damage-relevant particle environments and susceptible component technologies for a space mission under ECSS-E-ST-10-12C §8.3–8.4: categorize the orbital environment by DD relevance (trapped protons, solar proton events, galactic cosmic rays), map each candidate technology (solar cells, bipolar devices, CCDs, optocouplers, photonic components) to its DD susceptibility tier, and confirm every DD-susceptible item has an assigned NIEL-based analysis path. Trigger: e...

Use when compute the displacement damage (DD) dose for a spacecraft device under ECSS-E-ST-10-12C §8.2: identify all contributing particle types and energy bins from the mission radiation environment, retrieve the Non-Ionizing Energy Loss (NIEL) value for each bin, multiply each bin fluence by its NIEL to obtain the partial DD contribution, sum all partial contributions to obtain the total DD dose in MeV/g, convert to a reference-particle equivalent fluence using the DD equivalence relation (...

Use when determine displacement damage (DD) assessment uncertainty factors for a spacecraft radiation analysis under ECSS-E-ST-10-12C §8.7: identify each uncertainty source (environment model, NIEL scaling, shielding transport, and device response data), assign a numeric factor to each source, combine the factors into an overall uncertainty multiplier using either the multiplicative or root-sum-square method, apply the combined factor to the nominal proton-equivalent fluence to obtain the des...

"Use when assessing radiation dose-effects margin compliance for electronic

Use when compute deposited dose with margin split across environment, shielding, and susceptibility uncertainties per ECSS-E-ST-10-12C §5.4: derive the nominal absorbed dose from the environment model, apply the three independent uncertainty factors (environment, shielding, susceptibility) to obtain the design dose, compute the margin ratio against the component lot-testing threshold, and determine whether each part meets the required design margin. Trigger: ecss, e-st-10-system-scope, dose-m...

"Use when apply environment-driven margins for a spacecraft radiation

Use when establish project-phase radiation hardness margins for a space mission under ECSS-E-ST-10-12C §5.6: determine the required radiation design margin (RDM) at each review milestone (pre-PDR, PDR-to-CDR, post-CDR), verify that the RDM for total ionising dose and displacement damage meets or exceeds 2.0 relative to the predicted mission environment, confirm phase-appropriate hardness assurance activities are scoped, and validate that post-CDR test methods (cobalt-60, proton, heavy-ion, or...

"Use when assess radiation effects on space components or systems

Use when define the radiation design margin (RDM) requirement basis for a spacecraft component from the mission radiation environment specification (ECSS-E-ST-10-12C §5.1.1): take the total ionising dose, proton fluence, and electron fluence from the environment model, apply the minimum RDM factor to each parameter to derive the required component withstand level, verify the factor meets the ECSS minimum threshold, and flag any component whose radiation tolerance falls short of the required l...

Use when compute the radiation design margin (RDM) in the general dose-effects case under ECSS-E-ST-10-12 §5.1.2/§5.2: determine the mission total ionizing dose at the component shielded location, obtain the component's lot-qualified failure dose, derive the design dose by applying an uncertainty factor to the mission dose, calculate the RDM as the ratio of failure dose to design dose, and verify that each component's RDM meets or exceeds the minimum required margin for its application catego...

Use when determine the radiation design margin for single-event effects (SEE) on spacecraft EEE parts under ECSS-E-ST-10-12C §5.1.3: categorize each SEE-sensitive device as subject to destructive effects (latchup, burnout, gate rupture) or non-destructive effects (upset, functional interrupt, transient), compute the LET-threshold margin for destructive parts and the upset rate margin for non-destructive parts, verify each margin meets the required RDM factor, and flag any part with insufficie...

"Use when compute in-orbit single-event-effect rates and degradation

Use when define SEE-relevant mission orbit environments and electronic technology susceptibility profiles under ECSS-E-ST-10-12C §9.2–9.3: categorize the mission orbit as LEO, MEO, GEO, HEO, interplanetary, or lunar to determine the dominant particle population (trapped protons, heavy ions, galactic cosmic rays, solar particle events), map each candidate technology (CMOS, BiCMOS, SRAM, DRAM, Flash, FPGA, power MOSFET, linear bipolar) to its applicable SEE types (SEU, SET, SEFI, SEL, SEB, SEGR...

Use when run SEE hardness assurance for a space electronic device under ECSS-E-ST-10-12C §9.5: determine the device's susceptibility to ion-induced and proton/neutron-induced single-event effects, predict the on-orbit SEE rate using device cross-section parameters and the mission particle spectrum, compare the predicted rate against the allowed-error-rate requirement, and assign the hardness assurance category that sets acceptance testing and lot-screening obligations. Trigger: ecss, e-st-10-...

Use when evaluate single event effects (SEE) margin compliance for space electronics under ECSS-E-ST-10C §5.5.3: categorize each event type as soft (SEU, SET, SEFI) or potentially destructive (SEL, SEB, SEGR), compute the predicted event count over the mission duration, apply the required margin factor, compare the margined total against the mission allowable, and flag any device that exceeds the allowable or lacks current-limiting protection for a destructive-category event. Trigger: ecss, e...

Use when estimate destructive heavy-ion, proton, and neutron Single Event Gate Rupture (SEGR) and Single Event Burnout (SEB) rates for power devices in a space radiation environment per ECSS-E-ST-10-12C §9.4.1.6: categorize the component as power MOSFET (susceptible to both SEGR and SEB) or bipolar transistor (SEB only), fit a Weibull cross-section model to device heavy-ion test data, integrate the fitted cross-section against the orbit LET spectrum, apply the bias-derating condition appropri...

Use when compute the SEHE (single event housekeeping and functional interrupt) rate for a spacecraft device under ECSS-E-ST-10-12C §9.4.1.8: fit the device's measured cross-section versus LET data to a Weibull model (LET threshold, width parameter, shape exponent, saturation cross-section), integrate that curve against the mission heavy-ion LET spectrum using the trapezoidal rule to obtain the unshielded event rate, apply a shielding attenuation factor to produce the shielded rate, and verify...

Use when compute heavy-ion and proton/neutron single-event latch-up (SEL) and single-event snapback (SESB) rates for a spacecraft electronic device under ECSS-E-ST-10-12C §9.4.1.4–9.4.1.5: fit a Weibull cross-section curve to heavy-ion test data, integrate it against the mission LET spectrum, apply the Bendel two-parameter model to proton cross-section data and integrate over the proton energy spectrum, sum both contributions into a combined rate, and categorize the result as acceptable, moni...

Use when assess radiation-induced sensor background margins for space detector systems under ECSS-E-ST-10C §5.5.4: identify each contributing particle population (trapped protons, trapped electrons, galactic cosmic rays, solar energetic particles), compute the raw background count rate at the sensor sensitive area from each population flux and conversion efficiency, sum all contributions over the exposure duration, apply the required radiation design margin to account for environment model un...

Use when compute Single Event Transient (SET) rates for a spacecraft device population under ECSS-E-ST-10C §9.4.1.7: identify each sensitive device and its cross-section model (Weibull for heavy ions, threshold/saturation for protons, effective cross-section for neutrons), integrate each cross-section against the mission particle environment (heavy-ion LET spectrum, proton energy spectrum, ambient neutron flux) to derive per-device rates for all three particle families, sum the three contribu...

Use when calculating heavy-ion-induced single-event upset (SEU), multiple-cell upset (MCU), and single-word multiple-bit upset (SMU) rates for a space-qualified device under ECSS-E-ST-10-12C §9.4.1.2: fit the device cross-section versus LET curve with a Weibull model (LETth, W, s, σsat), integrate over the mission LET spectrum using the rectangular parallelepiped (RPP) method, optionally apply the integral RPP (IRPP) chord-length correction for sensitive-volume geometry, derive MCU and SMU ra...

Use when predict proton- and neutron-induced single-event upset (SEU) and multiple-cell upset (MCU) rates for space electronic devices under ECSS-E-ST-10C §9.4.1.3: identify the direct-ionization and nuclear-reaction transport paths, apply the Weibull cross-section model over the trapped-proton and free-proton/neutron flux spectra for each path, sum the path contributions to derive the total SEU rate, compute expected upsets over mission duration, compute MCU rate from the MCU fraction, and c...

"Use when build the radiation shielding geometry model for a component

"Use when execute the spacecraft shielding calculation process under

Use when run detailed sector shielding calculations for a spacecraft component under ECSS-E-ST-10-12C §6.2.3: discretize the surrounding 4π steradians into directional sectors, ray-trace each direction through the spacecraft mass model to accumulate areal shielding density (g/cm²), apply dose-depth attenuation curves to derive the ionising dose contribution from each sector, and aggregate across all sectors to obtain total TID at the point of interest. Apply a radiation design margin (RDM) to...