Claude Skills by ashfordeOU

Use when you must assemble the spacecraft pointing error budget for the attitude determination and control system: combine independent 1-sigma error contributors (determination noise, gyro propagation, control deadband, jitter, thermal distortion) by root-sum-square, convert to 3-sigma, check it against the pointing requirement, allocate the remaining budget to a not-yet-sized contributor, and rank error sources by variance share. Produces the RSS pointing error, the requirement verdict, the ...

Use when you must estimate the RCS attitude-hold propellant demand of a reaction-jet limit cycle: the control angular acceleration from the control torque and axis inertia, the angular rate at the deadband crossing, the firing duration of each braking pulse, the delta-V and propellant mass per pulse and per cycle, the aggregate cycle period, the cycle count over the mission life, and the three-axis lifetime propellant total with an activity duty factor. Produces the per-axis limit-cycle state...

Use when you must design the reaction wheel control law for a spacecraft pointing maneuver: command wheel torques from quaternion error feedback and body rate with PD gains, integrate wheel momentum with the body rate transport term, clip torque commands and flag wheel momentum saturation, and compute the momentum desaturation command with its magnetorquer dipole estimate. Produces the commanded wheel torque vector, the accumulated wheel momentum, the saturation verdict, and the desaturation ...

Use when the task is star identification, boresight and field of view selection, lost in space versus tracking mode, cross-boresight versus roll pointing accuracy, or star tracker update rate. Determine star tracker attitude determination for spacecraft ADCS: identify measured star centroids against an onboard star catalog, compute the angular separation between each measured centroid and its catalog star, and return the best match inside the field of view. The logic normalizes unit vectors, ...

Use when you must evaluate spacecraft sun pointing for the ADCS safe hold: compute the angle between the sun vector and the pointing axis, check it against the pointing tolerance, estimate the solar illumination factor at the sun angle, and size the slew rate to acquire the sun. Produces the sun pointing angle, the safe hold verdict, the illumination factor, and the required slew rate that gate sun acquisition. Trigger: sun pointing, safe hold, sun acquisition, solar illumination, slew rate.

Use when plan and execute acceptance proof and leak tests on flight hardware under ECSS-E-ST-32C clause 5.5: determine the required proof pressure for each pressurized assembly from its maximum design pressure and the applicable proof factor, confirm the applied test pressure meets or exceeds the requirement and that the hold duration satisfies the minimum dwell time, evaluate the measured leak rate against the allowable limit for each sealed assembly, and determine overall programme acceptan...

Use when analyze acoustic loading response of spacecraft structural panels under a diffuse acoustic field per ECSS-E-ST-32C clause 4.6.2.6: convert broadband sound pressure levels to acoustic pressure, compute overall sound pressure level from spectral bands, categorize the excitation as low-frequency or high-frequency coupling, compute acoustic force on each panel, verify structural response margins against allowables, confirm the diffuse-field assumption above the Schroeder frequency, asses...

Use when perform acoustic test verification of a spacecraft structure per ECSS-E-ST-32C clause 4.6.3.10: derive the 1/3-octave band test spectrum from the launch acoustic environment, apply the qualification margin to acceptance levels, compute the Overall Sound Pressure Level (OASPL), verify frequency range covers 31.5 Hz to 10 kHz, check test duration against the category minimum, and assess band-by-band spectrum compliance within tolerance. Categorize the test as qualification, acceptance,...

"Use when determine aeroelastic stability margins for aerodynamic surfaces

"Use when plan or verify aerodynamic, aerothermodynamic, and aeroelastic

Use when verify structural materials and passive film coatings for degradation under ageing and contamination exposures per ECSS-E-ST-32C clauses 4.6.3.16–4.6.3.17: categorize each test specimen by type, validate the ageing conditioning regime against the approved test specification, compute mechanical property retention ratios from pre- and post-exposure measurements, assess contamination exposure level against the allowable limit, and determine whether each specimen and the overall test cam...

Use when determine alignment compliance and dimensional stability for spacecraft structural elements per ECSS-E-ST-32C clauses 4.6.2.19–4.6.2.20: inventory alignment contributors (manufacturing tolerance, thermo-elastic deformation, hygrothermal expansion, load-induced displacement, creep), combine systematic contributors by absolute sum and random contributors by root-sum-square, compare the total against the interface alignment requirement, verify hot-case and cold-case and eclipse thermal ...

Use when verifying that structural components meet alignment accuracy, dimensional stability, and geometrical form requirements per ECSS-E-ST-32C clauses 4.6.3.19–4.6.3.21. Check each component's measured alignment (angular and translational) against its specified tolerance; assess dimensional change from baseline against the stability budget across thermal, hygroscopic, creep, and other drivers; verify geometrical form deviations (flatness, straightness, circularity, parallelism, perpendicul...

Use when document or verify a structural analysis report under ECSS-E-ST-32C clause 5.2 or a Leak-Before-Break (LBB) report under clause 5.3.5: confirm the report covers every required section (objectives, applicable documents, model description, load cases, material properties, analysis methodology, results, margin of safety, and conclusions), compute the margin of safety from applied and allowable loads for each load case, check that each LBB report includes fracture toughness data, crack-g...

"Use when analyze load transfer, bearing stress, bypass ratio, preload,

Use when assess the structural integrity of adhesive-bonded joints per ECSS-E-ST-32C clause 4.6.2.12: apply the Volkersen shear-lag model to determine peak shear stress at overlap ends, compute peel stress from load eccentricity at the adhesive-adherend interface, derive margins of safety against adhesive shear and peel allowables, and flag any joint whose margin falls below zero for both failure modes. Trigger: ecss, e-st-32-structures-scope, adhesive-bonded-joints, peel-stress-bonded-joints...

"Use when verify buckling onset margins for space structure panels,

Use when assess composite structures, bonded joints, and sandwich panels for delamination growth, defect severity, and damage threat compliance under ECSS-E-ST-32C clause 8.4: categorize each detected defect by type (delamination, disbond, core damage, matrix crack, impact damage) and laminate location, determine whether the mixed-mode delamination driving force remains below the critical strain energy release rate envelope, evaluate residual strength against design ultimate load using fractu...

Use when determine composite overwrap and liner material allowables for a pressure-vessel structure per ECSS-E-ST-32C clause 5.6: select the appropriate coupon test programme (fiber tensile and compression, in-plane shear, interlaminar shear strength, open-hole and bearing), verify specimen counts meet CMH-17 statistical basis requirements, compute A-basis or B-basis allowables from test data using the k-factor tolerance-limit method, apply environmental and process knockdown factors, and con...

"Use when verify composite structures under ECSS-E-ST-32C clause

Use when verify all contained and restrained items on a spacecraft structure satisfy ECSS-E-ST-32C clause 6.3.4: categorize each item as container, restrained, latched, or tethered, confirm the load path is defined and sized for static and dynamic load cases, check that limit and ultimate factors of safety meet clause minimums, verify failure modes and their consequences are documented for every item, confirm that catastrophic or critical consequence items carry redundant restraint provisions...

Use when verify a composite overwrapped pressure container (COPC) with metallic liner per ECSS-E-ST-32 clause 4.5.2: confirm the liner remains elastic at proof pressure, compute the margin-of-safety on liner hoop stress at maximum expected operating pressure, validate proof and burst pressure factors against required minimums, demonstrate leak-before-burst by confirming the fracture-mechanics critical flaw depth exceeds the liner wall thickness, and check the fatigue-cycle budget against a cy...

Use when verify structural compliance of a Composite Overwrapped Pressure Container (COPC) fitted with a homogeneous non-metallic liner per ECSS-E-ST-32 clause 4.5.3: categorize the liner material as thermoplastic, thermoset, or elastomer; check proof and burst pressure factors against MEOP minimums; assess liner gas permeation rate against the project allowable limit; compute the load-sharing ratio between liner and composite overwrap; confirm liner-fluid chemical compatibility; and validate...

Use when assess the structural response of a COPS (Composite Overwrapped Pressure Structure) with metallic liner under ECSS-E-ST-32C §4.4.3: compute the hoop strain shared between the liner and composite overwrap via the compatibility condition, determine the stress state in each component at design pressure, check the liner against yielding, verify the composite against its hoop allowable, account for ring stiffener contributions to shell stiffness, and confirm the burst pressure margin sati...

Use when evaluate a Composite Overwrapped Pressure System (COPS) with a homogeneous non-metallic liner, or an all-composite Pressure System (CPS) with no liner, under ECSS-E-ST-32 clause 4.4.4: determine the system variant (non-metallic-liner COPS or all-composite CPS), verify proof and burst pressure margins against ECSS safety factors, check liner permeation and buckling allowables for non-metallic variants, confirm pressure-cycle fatigue life meets the design service life multiplied by the...

Use when verify a Composite Overwrapped Pressure Vessel (COPV) with metallic liner under ECSS-E-ST-32-02C §4.3.3: determine liner hoop stress at MEOP, confirm proof and burst pressure factors meet minimum requirements, evaluate fatigue-life of the metallic liner against scatter-factored design cycle count, assess composite overwrap fiber stress at burst via netting theory, and check liner yield limits at proof. Covers titanium, aluminium, and Inconel liners, autofrettage detection, margin-of-...

Use when assess a composite overwrapped pressure vessel (COPV) with a homogeneous non-metallic liner, or an all-composite pressure vessel (CPV), under ECSS-E-ST-32C clause 4.3.4: categorize the vessel configuration, compute the sustained stress ratio (SSR) for each operating phase, accumulate composite-fiber stress rupture damage via a power-law model and verify the Miner-rule analogue damage sum against the allowable limit, check non-metallic liner hoop stress against the liner allowable, an...

"Use when evaluate metallic-liner COSPE structural and pressure

Use when assess the structural integrity of a composite overwrapped pressure vessel with a homogeneous non-metallic liner per ECSS-E-ST-32C clause 4.6.3: categorize the liner material family, verify the proof pressure and burst pressure factors against the maximum allowable working pressure, check liner strain at proof pressure against the liner allowable strain, validate the overwrap fiber volume fraction, and apply environmental degradation to the effective burst margin. A vessel assessment...

Use when calculate crack growth life, margins, and scatter factors for a fracture-critical structural component under ECSS-E-ST-32-01C §7.2.8: determine the critical crack size from fracture toughness and applied stress, integrate the crack growth rate law (Paris, Walker, or Forman) from the initial assumed flaw to the critical size, apply a life scatter factor (x3 with material-specific test data, x5 with handbook data only), and compute the margin of safety on life against the required serv...

Use when determine the critical crack size at limit-load and assess residual-strength margin for a structural component per ECSS E-ST-32C clause 7.3: apply linear elastic fracture mechanics to compute the critical crack half-length from material fracture toughness, a stress-intensity geometry factor, and the applied limit stress; derive the part residual-strength at the assumed crack size; compute the margin-of-safety against limit-load failure; and flag any crack at or beyond the critical si...

Use when determine the most critical crack location and orientation for a structural item under ECSS-E-ST-32C clause 7.2.2: enumerate candidate crack initiation sites (stress concentrations, fastener holes, weld toes, surface defects), pair each site with all plausible crack orientations (axial, circumferential, radial, oblique, transverse), compute the stress intensity factor for each pair using net-section stress and a geometry correction factor, evaluate the fracture margin against materia...

Use when assess damage-tolerance design intent for a structural element under ECSS-E-ST-32C clause 4.3.8: categorize the structure into the safe-life or fail-safe approach, bound crack growth against the critical flaw size across the design service life, verify that a damaged structure retains sufficient residual strength, and determine whether the applied stress-intensity ratio triggers mandatory fracture control per ECSS-E-ST-32-01C. Apply after the load environment is established and befor...

Use when determine the correct design allowable basis (A-basis or B-basis) and verify structural margins for spacecraft structural members under ECSS-E-ST-32C clause 4.5.8: assign A-basis to single load-path members and B-basis to redundant (multiple load-path) members, retrieve the allowable stress value from the applicable material database (MMPDS for metals, CMH-17 for composites, supplier data for non-metals and adhesives), compute the margin of safety as (allowable / applied_stress) − 1,...

Use when determine the structural alignment budget for a spacecraft or instrument mounting interface under ECSS-E-ST-32C Annex L: identify every contributor to alignment error — manufacturing tolerances, thermoelastic distortion, gravity-release deformation, load-induced deflection, and measurement uncertainty — assign sensitivity coefficients, combine contributions by root-sum-square or worst-case arithmetic, and verify the resulting total against the pointing or interface alignment requirem...

Use when prepare the material and mechanical-part allowables document required by ECSS-E-ST-32C Annex H (MMPA DRD): identify every structural material and fastener in scope, assign each an allowable basis (A-, B-, S-, or typical), retrieve governing allowable values from MMPDS or CMH-17 for composites, apply environmental and statistical knockdown factors, verify that all required mechanical properties are present for the applicable temperature range, and confirm full source traceability befo...

Use when determine the structural buckling capacity of load-bearing members for an ECSS-E-ST-32C Annex M buckling report: categorize each member by geometry (column, flat plate, or shell), resolve the effective length factor from its boundary conditions, compute the critical buckling stress using the Euler formula for slender columns or the Johnson parabolic formula for intermediate columns, apply a knock-down factor for initial geometric imperfections, evaluate the margin of safety against t...

Use when validate a CAD model and drawing description document (CADMDD) for structural design delivery under ECSS-E-ST-32C Annex A: confirm the model format is an accepted exchange or native type, verify the coordinate system definition (origin, axes, handedness), check assembly tree completeness and component identification, validate drawing title block required fields, assess mass property completeness (mass, centre of gravity, inertia tensor), confirm interface definitions carry type and m...

Use when determine design loads for a space structure under ECSS-E-ST-32C Annex B: enumerate all load cases by type (static, quasi-static, dynamic-sine, dynamic-random, dynamic-shock, thermal, acoustic, pressure, inertia, combined), assign a Limit Load to each, apply partial safety factors to derive Design Limit Loads (DLL), compute Design Yield Loads (DYL = DLL × yield factor), and compute Design Ultimate Loads (DUL = DLL × ultimate factor). Flag any load case with a missing limit load, a sa...

"Use when prepare a dimensional stability analysis (DSA) report for a

Use when determine the content and completeness of a fatigue analysis report deliverable under ECSS-E-ST-32C Annex D (DRD-FA): verify the report defines all required load spectra, applies Miner's rule damage summation over rainflow-counted cycle blocks, adjusts predicted fatigue life by the required scatter factor, and confirms a positive life margin at each fatigue-critical location. Categorize each load event by spectrum type, sum fractional damage across stress amplitudes, and flag any loc...

Use when build the Annex G fracture-critical item register for a structure assessed under ECSS-E-ST-32C: screen each structural item against fracture-criticality criteria, assign each item to the Primary Fracture Critical Item List (PFCIL), Fracture Critical Item List (FCIL), or Fracture Limited Life Item List (FLLIL), validate entry fields and numeric bounds, compute the fracture life margin of safety, and verify that both the PFCIL and FLLIL are proper subsets of the FCIL. Trigger: ecss, e-...

"Use when determine the content of a fracture control analysis report

"Use when draft a fracture control plan (FCP) per ECSS-E-ST-32C Annex F:

Use when produce a structure mass summary (SMS) document per ECSS-E-ST-32C Annex N: enumerate every structural component with its dry mass and design maturity code, apply the maturity-dependent margin to each entry to obtain the component mass-with-margin, sum the contributions to derive total dry mass and total mass-with-margin, compare the total against the allocated mass budget, and flag any component missing a recognized maturity code or a valid mass value. Trigger: ecss, e-st-32-structur...

Use when draft the Mathematical Model Description Document (MMDD) for a structural mathematical model under ECSS-E-ST-32C Annex I and clause 32-03: categorize the model as finite-element, analytical, or hybrid, verify all required MMDD documentation fields are present and non-empty, check eigenfrequency correlation against the ±5 % tolerance and modal assurance criterion (MAC) values against the minimum threshold, assess delivery-package completeness against the MMDD checklist, and flag any m...

"Use when prepare the modal and dynamic response analysis report

"Use when produce a structural stress and strength analysis report

"Use when produce a test-analysis correlation report under ECSS-E-ST-32C

Use when evaluate test results against predictions for a structural test campaign under ECSS-E-ST-32C Annex P: verify each test objective is met, compare measured responses to predicted values within the approved tolerance, assess all anomalies encountered and confirm their disposition, check post-test article condition, and produce the pass/reject conclusion for the test evaluation report. The procedure covers static, dynamic, acoustic, and thermal test types. Trigger: ecss, e-st-32-structur...