ashfordeOU

@ashfordeou source repo

671 skills
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23 hours ago last updated

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Sandwich Panels · ashfordeou bundle
Use when the task is sandwich panel sizing or analysis, honeycomb or foam core selection, face sheet stress or core shear failure checks, face wrinkling, or sandwich bending stiffness and deflection. Design and analyze aerospace sandwich panels: compute the equivalent bending stiffness from the face modulus, face thickness, and core thickness, the face sheet stresses from a bending moment, the core shear stress from a shear load, the face wrinkling stress from the face and core moduli, and the total deflection of a sandwich beam or panel including the core shear contribution. Trigger: sandwich panel, honeycomb core, foam core, face wrinkling, core shear, face stress, sandwich deflection.

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Landing Ground Loads · ashfordeou bundle
Use when you must compute the ground loads on an aircraft structure for the certification landing and ground-handling conditions: the static nose and main gear reactions from the weight and CG position over the wheelbase, the level-landing reactions at a limit vertical inertia load factor, the braked-roll deceleration and brake force from the main gear friction, the tail-down-condition reaction with the nose gear unloaded, and the one-wheel-load reaction from the lateral CG offset over the track. Produces gear reactions, the braking deceleration and the critical per-station condition that gates a landing loads check. Trigger: landing-ground-loads, ground-reactions, level-landing, tail-down-condition, one-wheel-load, braked-roll.

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Mmpsd Allowables · ashfordeou bundle
Use when computing statistically based metallic material design allowables per MMPDS: determine A-basis and B-basis values from coupon test data, run the one-sided normal tolerance k-factor approximation, and validate that derived allowables sit below the sample mean. The skill applies minimum sample counts, confidence/content conventions, and sanity checks on design values, following the statistical approach of MMPDS and its MIL-HDBK-5 heritage. Trigger: allowables, a-basis, b-basis, k-factor, metallic materials, sample statistics, design values, mil-hdbk-5, test specimens.

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Surrogate Modeling · ashfordeou bundle
Use when you must build and validate an approximation model of an expensive aerospace analysis from sampled design data: assemble the full quadratic basis, fit a ridge-regularized quadratic response surface, fit a Gaussian radial basis function interpolant, predict the response at new design points, run a leave-one-out cross validation on both models, and recommend the surrogate with the lower estimated prediction error. Produces the fitted coefficients or weights, the cross-validation and in-sample quality metrics (rmse, max absolute error, r2), and the model recommendation that gates replacing the expensive analysis inside a multidisciplinary optimization loop. Trigger: surrogate model, metamodel, response surface, radial basis function, kriging alternative, leave one out cross validation, approximation model, prediction error.

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Fuselage Sizing · ashfordeou bundle
Use when you must size a transport fuselage from the payload: compute the cabin length from the seat count and the seat pitch, compute the cabin width and the fuselage diameter from the seats-abreast layout and the aisle width, judge the overall fuselage length to diameter ratio against the typical transport band, and check the underfloor cargo volume against the required baggage volume. Produces the cabin length, fuselage diameter, and cross-section layout that feed the conceptual sizing loop, with the sanity band and cargo verdicts. Trigger: fuselage sizing, cabin length, fuselage diameter, seats abreast, seat pitch, cabin width, aisle width, cargo volume.

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Airfoil Selection · ashfordeou bundle
Use when you must select an airfoil section for a wing design: score candidate airfoils by lift-to-drag ratio at the design condition, filter them by minimum thickness, and choose the best qualified section from classic airfoil data. Produces the candidate scoring, the thickness filter verdict, and the selected airfoil identifier that feeds the wing layout. Trigger: airfoil selection, wing design, lift to drag ratio, thickness, naca airfoils, section selection.

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Vortex Lattice Method · ashfordeou bundle
Use when you must compute the spanwise loading of a straight trapezoidal wing with the vortex lattice method: build the horseshoe vortex panel lattice at the quarter chord, assemble the influence coefficient matrix at the three-quarter chord control points, solve the linear system for the panel circulations, and derive the spanwise lift distribution, the downwash angles, and the induced drag. Produces the circulation solution, the per-panel lift, and the lift and induced drag coefficients that gate wing aerodynamic efficiency estimates. Trigger: vortex lattice method, horseshoe vortex, panel lattice, influence coefficients, spanwise lift distribution, downwash angle, induced drag, Trefftz plane.

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Parasite Drag · ashfordeou bundle
Use when the task is drag buildup, zero-lift drag estimation, the wetted-area method, skin-friction coefficients, form factor, interference factor, or equivalent skin-friction coefficient in a preliminary drag assessment. Estimate the parasite (zero-lift) drag of a fixed-wing aircraft with the component buildup method: compute the flat-plate skin-friction coefficient from the Reynolds number for laminar and turbulent flow, apply the form factor and interference factor to each component, convert the wetted area into a drag coefficient, and sum the wing, fuselage, nacelle, and tail contributions into the total parasite drag. Also back out the equivalent skin-friction coefficient from the total wetted area and the total drag. Trigger: parasite drag, zero-lift drag, skin friction, wetted area, form factor, interference factor, drag buildup, Reynolds number.

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Arinc429 Bus Loading · ashfordeou bundle
Use when you must budget the ARINC 429 bus loading: sum the per-label transmission rates in labels per second into the total word rate, price each transmitted word at 36 bit-times (32 data bits plus the 4-bit gap) for the bus load in bits per second, compute the percent utilization of the 100 kbps or 12.5 kbps link, flag schedules that exceed the word-per-second capacity (about 2778 words per second at 100 kbps), and report the headroom against the common 80 percent design guideline. Produces the total word rate, bus load, percent utilization, capacity verdict, and design headroom that gate the ARINC 429 label rate table. Trigger: arinc 429 bus loading, label rate budget, percent bus utilization, word rate capacity, transmit schedule headroom, 100 kbps link.

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Electrostatic Discharge · ashfordeou bundle
Use when planning or auditing ESD qualification of LRUs and cabin equipment that personnel handle during normal operation or maintenance. Determine DO-160 Section 25 electrostatic discharge (ESD) test parameters for airborne equipment: select the single equipment category and 15 kV air discharge test level, compute the stored energy and discharge waveform currents (peak, 30 ns, 60 ns) from the 150 pF and 330 ohm generator model, check the 10 positive and 10 negative discharges per test point, and judge test point applicability from personnel accessibility with connector pins excluded. Verdict logic classifies pass criteria; input validation and summary formulas only, no standard tables reproduced. Trigger: electrostatic discharge, ESD testing, air discharge, discharge waveform, test point.

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Dme Arc Leg · ashfordeou bundle
Use when you must compute the geometry of a constant-DME arc leg: the arc length between two radials at a published DME radius, a point on the arc at a given radial, the bank angle that holds the arc at a true airspeed, the turn radius implied by a bank angle, the chord between two arc fixes, and the signed radial intercept for joining or leaving the arc. Produces the arc length, arc points, holding bank angle, chord and intercept angle that gate a DME-arc procedure path check around a VOR/DME station. Trigger: dme arc leg, vor dme arc, arc length between radials, dme radius, arc bank angle, radial intercept, arc chord.

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Skill Evaluation · ashfordeou bundle
Use when you must evaluate a delivered skill against SEP-2640-style conformance and quality criteria: run conformance checks on the package (frontmatter, description with trigger, license, standards references), judge whether the skill's contract test exercises the core logic, score deterministic quality criteria (offline, no network, stdlib only), compute coverage ratio of tested versus total behavior, and issue an acceptance verdict (accept, rework, or reject). SEP-2640 stays an emerging spec and an adapter over the agentskills.io content format, so evaluation reuses the same conformance shape as skill delivery. Trigger: skill evaluation, SEP-2640, conformance check, acceptance verdict, quality score, coverage ratio, skill review.

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Root Locus Design · ashfordeou bundle
Use when you must design a feedback loop with the classical root locus method: compute the closed loop pole locations as the forward-path gain K varies, find the gain that places the dominant poles at a target damping ratio zeta, and judge closed loop stability from the characteristic equation 1 + K*G(s) = 0. Applies to the canonical type-1 plant G(s) = 1/(s(s + a)) used in flight control analysis. Produces the pole pair, the gain for the requested zeta, and the stability verdict that feeds control law iteration. Trigger: root locus, closed loop poles, damping ratio, gain selection, characteristic equation, pole locations, zeta, stability.

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Pursuit Guidance · ashfordeou bundle
Use when you must compute pursuit guidance commands for a planar intercept: derive the line of sight angle, the pure pursuit heading that points the interceptor velocity at the target, the wrapped guidance error between the current heading and the aim heading, the lead angle for a lead pursuit collision course, and the capture condition from the interceptor to target speed ratio. Produces the pursuit aim heading, guidance error, lead angle, capture feasibility, intercept time, and the proportional navigation acceleration command for comparison that gate a pursuit guidance assessment. Trigger: pursuit guidance, pure pursuit, lead pursuit, lead angle, guidance error, heading error, capture condition, collision course, intercept time, terminal homing.

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Orbit Determination · ashfordeou bundle
Use when you must determine an initial orbit from three inertial position vectors: run the Gibbs method to recover the velocity at the central observation, apply the Herrick-Gibbs finite-difference method when the vectors are closely spaced, and convert the state to classical orbital elements with the vis-viva energy consistency check. Produces the central velocity, the classical elements (a, e, i, RAAN, argp, nu), the chosen method verdict and the orbit-fit verdict. Trigger: orbit-determination, gibbs-method, herrick-gibbs, three position vectors, initial orbit determination, rv-to-elements, orbital elements, angular separation.

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Delta Fai · ashfordeou bundle
Use when you must classify a change and determine the AS9102 delta first article inspection (delta FAI) scope: classify part number, material, process, tooling, drawing revision, location, or supplier changes as full new FAI, delta FAI, or no FAI, then scope the affected forms 1, 2, and 3 and the affected characteristics for the delta. Determine whether a full new FAI is required or a delta FAI suffices, and produce the change classification, the delta scope forms, and the affected characteristic list. Trigger: delta fai, change classification, full new fai, delta first article, material change, process change, tooling change, drawing revision.

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Leak Testing · ashfordeou bundle
Use when you must plan and evaluate a leak test on a fuel tank, accumulator, valve, or sealed enclosure: compute the leak rate in scc per second from pressure decay or vacuum decay measurement, size the test time a gauge resolution needs to catch a target leak, convert a measured helium leak to the air equivalent and back, recommend the leak test method from required sensitivity and access, and disposition the part against the maximum allowable leak rate. Produces the leak rate, the method recommendation, and the accept, reject, or review verdict. Trigger: leak testing, pressure decay, vacuum decay, helium mass spectrometer, sniffer test, bubble test, leak rate, scc per second, helium to air conversion, gauge resolution, maximum allowable leak.

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Thermography · ashfordeou bundle
Use when you must plan or interpret an infrared thermography (IRT) inspection on an aerospace part: decide between active and passive thermography, choose pulsed or flash thermography versus lock-in thermography, compute the surface temperature rise of a semi-infinite solid under a heating pulse, estimate the time of maximum thermal contrast and the observation window for a disbond, delamination, void, or corrosion at depth, evaluate thermal contrast against the noise floor, and size the inspection parameters of heating pulse energy, acquisition rate, and observation time window. Compares thermography with ultrasonic, radiographic, and eddy current methods and produces the inspection plan and contrast results that gate the acceptance disposition under an approved NDT procedure. Trigger: thermography, infrared thermography, flash thermography, pulsed thermography, lock-in thermography, thermal contrast, disbond, delamination, void, corrosion, composite panel.

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Propellant Selection · ashfordeou bundle
Use when you must select and screen rocket propellants for a mission: classify propellant families (cryogenic, storable, hypergolic, solid, hybrid), compare specific impulse and density impulse, compute the mixture bulk density and the O/F ratio optimum, derive the required propellant mass fraction from a delta-v budget with the rocket equation, and judge storability and handling for the mission. Produces the propellant family classification, the density-impulse ranking, the O/F verdict, the mass fraction, and the suitability verdict, in SI units (s, kg/m^3, m/s). Trigger: propellant selection, specific impulse, density impulse, mixture ratio, O/F ratio, hypergolic, cryogenic, storable, solid propellant, storability.

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Bypass Ratio Trade · ashfordeou bundle
Use when you must size the bypass ratio design trade for a turbofan: compute the thrust split between the fan and core streams, the specific thrust, and the thrust-specific fuel consumption across candidate bypass ratios, and weigh them against the fan pressure ratio trend. Produces the per-stream mass flows and thrust shares, the TSFC versus bypass ratio trend, and the fan pressure ratio verdict that feed the engine trade study. Trigger: bypass ratio, bpr, specific thrust, tsfc, fan pressure ratio, turbofan trade.

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Mixed Flow Exhaust · ashfordeou bundle
Use when you must compute the two-stream turbofan design point with a mixing exhaust: traverse the fan and core streams to the mixer entry, close the constant-area mixer by the energy and momentum balance over the two streams' total states to the mixed total temperature and pressure with the mixing loss, expand the mixed stream through the common convergent nozzle, and report the net thrust and TSFC of the mixed-flow configuration against the separate-exhaust baseline. Produces the mixed total state, the mixer pressure loss ratio, the common-nozzle exit velocity, net thrust and TSFC, and the mixed-vs-separate comparison that gate the exhaust-configuration decision. Trigger: mixed-flow exhaust, turbofan mixing exhaust, constant-area mixer, common nozzle, mixing loss, exhaust mixer, low bypass ratio mixed turbofan.

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Control Moment Gyro · ashfordeou bundle
Use when you must size and analyze a control moment gyro (CMG) cluster for agile spacecraft attitude control: compute the torque from the rotor momentum and the gimbal rate with the CMG torque law, derive the gimbal rates for a commanded torque with the pseudoinverse steering law and its null-space term, judge the torque amplification of the gimbal against a wheel actuator at equal momentum, evaluate the singularity measure and verdict of the gimbal state, and size the cluster momentum envelope of the pyramid array for the slew with the gimbal rate saturation flag. Produces the gimbal rates, the achieved torque, the envelope coverage verdict, and the singularity verdict that gate CMG selection. Trigger: control moment gyro, CMG cluster, gimbal rate, gimbal axis, steering law, singularity measure, gimbal lock, momentum envelope, pyramid cluster, torque amplification.

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Gyro Allan Variance · ashfordeou bundle
Use when you must characterize gyroscope noise for ADCS sensor selection: compute the overlapping Allan deviation AD(tau) over a correlation-time grid from a rate sample time series with cumulative sums, fit the log-log noise slope, categorize the noise process from the slope band (white noise or angle random walk at about -1/2, rate random walk at about +1/2, quantization at about -1, bias instability as a flat floor), and extract the angle random walk coefficient in deg/sqrt(h). Produces the Allan deviation curve, the noise classification, the fitted slope and the ARW coefficient that gate gyro selection. Trigger: gyro Allan deviation, allan deviation, angle random walk, rate random walk, bias instability, gyro noise model, noise slope, gyroscope rate noise, ARW coefficient, deg per root hour.

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Systems Engineering · ashfordeou bundle
Use when scoping or gating European space systems engineering per ECSS-E-ST-10C: determine the lifecycle phase (0 through F), map each phase to its review gate (MDR, PRR, SRR, PDR, CDR, QR, AR, FRR, CRR, ER), and validate that a phase is ready to exit when its required review records are complete. The phase-gate sequence drives program planning and procurement milestones for space systems, from mission analysis through disposal. Trigger: ecss, e-st-10c, lifecycle phases, phase gate, mdr, prr, srr, pdr, cdr, qr, ar, frr, space systems engineering.

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Doppler Shift · ashfordeou bundle
Use when you must compute the doppler frequency shift on a spacecraft link: derive the line-of-sight range rate from the circular-orbit altitude and the ground elevation angle, convert it to the received frequency and offset on an s-band downlink carrier, and estimate the worst-case doppler near the horizon and the doppler-rate at acquisition for receiver acquisition design. Produces the range rate, received frequency, delta-f offset, maximum doppler, slant range and doppler rate that gate communication link acquisition. Trigger: doppler shift, received frequency offset, acquisition frequency offset, worst-case doppler, doppler rate, line-of-sight range rate, s-band downlink, leo overflight, spacecraft ground link.

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Cmh17 Allowables · ashfordeou bundle
Use when the task is composite allowables, basis values, coupon pooling, or laminate knockdown factors for polymer matrix composites. Compute composite material design allowables per the CMH-17 method: determine A-basis and B-basis values from coupon test data using the one-sided normal tolerance k-factor approximation, pool coupon batches across environments to enlarge the effective data set, and apply knockdown factors for environmental conditioning, barely visible impact damage, and open hole features to derive laminate-level allowables from lamina allowables. Produce the lamina and laminate allowable table with basis designation and the confidence and content statement, and validate the counts against the minimums. Trigger: composite allowables, cmh-17, a-basis, b-basis, tolerance k-factors, coupon pooling, laminate allowables, knockdown factors, environmental conditioning, open hole.

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Composite Repair · ashfordeou bundle
Use when you must size a bonded scarf repair for a damaged composite laminate: compute the scarf length from the parent thickness and the scarf angle, the average adhesive shear stress carried by the scarf joint at the parent laminate stress, the required scarf angle for an adhesive shear allowable, and the external patch thickness that restores the parent stiffness. Produces the scarf length, adhesive shear stress, required scarf angle, and stiffness-matched patch thickness that gate a composite repair design. Trigger: composite-repair, scarf-repair, scarf-length, adhesive-shear-stress, stiffness-matched-patch, scarf angle, adhesive shear allowable, bonded repair, patch thickness.

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Failure Criteria · ashfordeou bundle
Use when you must evaluate a composite lamina against strength failure criteria: compute the Tsai-Wu, Tsai-Hill, and max-stress failure indices from the in-plane stresses and the ply allowables, and return the failure verdict. Produces each criterion index, the governing criterion, and the pass or fail verdict for the ply stress state. Trigger: lamina failure, tsai wu, tsai hill, max stress, failure index, composite ply strength, in plane stress.

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Strain Life Fatigue · ashfordeou bundle
Use when you must determine the strain-life (low-cycle fatigue) endurance of an aerospace structure: Coffin-Manson total strain amplitude from reversals to failure, reversals to failure from a fully reversed strain amplitude, the transition life where elastic and plastic amplitudes cross, low-cycle versus high-cycle regime categorization, the Neuber local-strain rule that converts a nominal elastic stress at a notch into local elastic-plastic strain through the cyclic Ramberg-Osgood curve, and the strain-life verdict for a load point. Produces reversals and cycles to failure, local notch strain, and the regime string. Trigger: strain-life-fatigue, coffin-manson, low-cycle-fatigue, reversals-to-failure, transition-life, neuber-local-strain, ramberg-osgood, elastic-plastic-strain, notched-lug.

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Hertzian Contact Stress · ashfordeou bundle
Use when you must compute the Hertzian contact stress between curved elastic bodies pressed together: determine the contact patch radius or half-width for sphere pairs, sphere-on-flat, ball-in-socket, cylinder pairs, cylinder-in-bore, roller-in-race or crossed cylinders from the load, the equivalent radius of curvature and the equivalent elastic modulus with 1/E* = (1-nu1^2)/E1 + (1-nu2^2)/E2; compute the maximum contact pressure p0 = 3P/(2 pi a^2) (circular) and p0 = 2P/(pi b L) (strip); report the subsurface shear and von Mises maxima with depth and magnitude; and run the yield-limit load check with p0_yield = 3.3 sigma_y (point) and 1.6 sigma_y (line). Produces patch size, peak pressure, subsurface stress location and magnitude, and yield-limit load and margin in SI units. Trigger: hertzian contact stress, hertz contact patch, contact pressure ellipse, subsurface shear stress, equivalent elastic modulus, equivalent radius of curvature, maximum contact pressure, contact yield limit.

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Fuel Tank Sizing · ashfordeou bundle
Use when you must size the fuel tanks for the aircraft: convert the fuel mass to the fuel volume with the fuel density, add the ullage allowance to get the required tank volume, and check it against the available volume in the wing and fuselage tanks. Produces the usable fuel volume, the required tank volume with ullage, and the fits verdict that gate the fuel system sizing. Trigger: fuel tank sizing, ullage, fuel volume, usable fuel, tank capacity.

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Propeller Sizing · ashfordeou bundle
Use when you must size the propeller geometry and set its operating point at the conceptual design point: derive the propeller diameter from the blade-tip constraint and the ground clearance, select the blade count and the blade chord from the solidity and the activity factor, compute the disk loading of the selected disk, and locate the operating point with the advance ratio from the forward motion, the revolutions per second, and the propeller diameter. Produces the propeller diameter, blade count, chord, solidity, activity factor, disk loading, and advance ratio that feed the propeller installation and the matching leaves. Trigger: propeller sizing, propeller diameter, blade count, solidity, activity factor, disk loading, advance ratio, ground clearance, blade-tip constraint.

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Delta Wing Vortex Lift · ashfordeou bundle
Use when you must estimate the vortex lift of a sharp-edged delta wing: apply the Polhamus leading-edge suction analogy to split the total lift into the attached potential term Kp sin(alpha) cos^2(alpha) and the leading-edge-separation vortex term Kv cos(alpha) sin^2(alpha), with the slender-wing potential slope Kp = pi AR / 2 and the vortex factor Kv growing linearly from 3.14 at AR 0 to about 3.45 at AR 4. Produces the total lift coefficient, the potential and vortex lift split, the vortex fraction, the drag due to lift CL tan(alpha), and the angle where vortex lift overtakes potential lift. Valid for sharp leading edges, subsonic flow, aspect ratio about 0.5 to 2.0, alpha up to about 25 degrees. Trigger: Polhamus suction analogy, leading edge suction, vortex lift, slender delta wing, nonlinear lift.

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Hypersonic Flow · ashfordeou bundle
Use when you must estimate aerodynamic forces on a body in hypersonic flow with modified Newtonian impact theory: stagnation pressure behind the normal shock (Rayleigh pitot relation), the finite-Mach stagnation pressure coefficient, local pressure by the Newtonian sine-squared law, the hypersonic vacuum limit on shadowed surfaces, and integrals over a sphere, cone and flat plate giving sphere drag, cone axial force, and flat plate lift, drag and lift-to-drag ratio. Produces the stagnation Cp and body force coefficients. Trigger: hypersonic flow, modified Newtonian theory, Newtonian impact pressure, stagnation pressure coefficient, blunt body drag, sphere drag coefficient, cone axial force, hypersonic vacuum limit.

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Winglet Design · ashfordeou bundle
Use when you must size a winglet as a wingtip device for induced-drag reduction on a fixed-wing aircraft: compute the effective span extension and the effective aspect ratio from the winglet height fraction and the cant angle, estimate the improved span efficiency, the induced-drag factor and the induced-drag coefficient at a reference lift coefficient, the percent drag reduction, and the root bending moment penalty at the wing root, then size the winglet height by bisection to hit a target drag reduction. Produces the winglet height, the effective aspect ratio, the drag reduction and the bending penalty that gate the wingtip device trade. Trigger: winglet design, wingtip device, induced drag reduction, effective aspect ratio, span efficiency, cant angle, winglet height, root bending moment penalty.

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Configuration Management · ashfordeou bundle
Use when you must determine the DO-254 configuration management action for a hardware change: classify the change class, decide whether a formal engineering change order (ECR/ECO) with reverification applies, and produce the hardware configuration index (HCI) entry against the current baseline. A change to form, fit, or function, any safety effect, or complex hardware is class 1 with baseline update, reverification, and independent review; otherwise class 2 uses documented but lighter review. Trigger: do 254 hardware configuration, change class, engineering change order, ecr, eco, configuration baseline, hardware configuration index, hci.

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Gdandt Basics · ashfordeou bundle
Use when the task is GD&T fundamentals: feature control frames, datum reference frames, form tolerances such as flatness, straightness, circularity, and cylindricity, orientation tolerances such as perpendicularity, parallelism, and angularity, position tolerance, profile, runout, or material condition and bonus tolerance on drawings. Interpret geometric dimensioning and tolerancing callouts per ASME Y14.5: parse a feature control frame into its symbol, tolerance, and datum references, identify the tolerance zone type and whether the callout is a form, orientation, position, profile, or runout tolerance, apply the material condition modifiers MMC, LMC, and RFS, and compute the bonus tolerance and the total tolerance when the feature departs from its maximum material condition size. Produce the callout summary with zone, category, modifier meaning, and any bonus. Trigger: feature control frame, GD&T, MMC, LMC, RFS, bonus tolerance, datum reference frame, flatness, perpendicularity, position tolerance.

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Part107 Sora · ashfordeou bundle
Use when assessing the operational risk of a small UAS (drone) operation: check FAA Part 107 applicability (weight under 55 lb, visual line of sight, daylight, below 400 ft AGL, airspace class, remote pilot certificate), classify the operation under EASA SORA into open, specific or certified from kinetic energy and population density, compute the ground risk class (GRC), the air risk class (ARC) from airspace type, apply SORA robustness levels and containment, evaluate BVLOS waiver considerations, and produce an operational safety case summary. Trigger: part 107 applicability, part107 sora, sora operational category, ground risk class, air risk class, arc, grc, robustness level, containment, bvlos waiver, drone risk assessment, uas risk, remote pilot certificate, 400 ft agl, visual line of sight.

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Control Allocation · ashfordeou bundle
Use when you must allocate a commanded roll, pitch, yaw moment vector across redundant aerodynamic and propulsive effectors: assemble the control effectiveness matrix, solve the pseudoinverse allocation or the weighted least squares problem, enforce the position limits with the redistributed pseudoinverse, distribute the moment between the aerodynamic and thrust vectoring groups with the daisy chain scheme, and report the achieved moment, allocation error and saturated effectors. Produces the effector command vector and the saturation verdict for output distribution. Trigger: control allocation, control effectiveness matrix, pseudoinverse allocation, weighted least squares, daisy chain, redistributed pseudoinverse, actuator limits, saturated effectors, redundant effectors.

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H Infinity Control · ashfordeou bundle
Use when you must run the h-infinity mixed-sensitivity norm analysis of a feedback loop: given the plant transfer function, a candidate controller, the sensitivity weight and the control-effort weight, verify the closed loop is stable and compute the h-infinity norms of the weighted sensitivity functions by gamma iteration over the imaginary-axis frequency response, locating the worst-case peak magnitude of each channel. Produces the weighted-sensitivity norm, the weighted control-sensitivity norm, the achieved gamma of the mixed-sensitivity weighting as the larger of the two norms, and the bound verdict when both weighted norms stay below one so the s-over-ks sensitivity bounds hold at every frequency. Trigger: h infinity norm, gamma iteration, mixed sensitivity weighting, s ks weighted bounds, sensitivity weight, control weight, worst case peak gain, weighted loop analysis.

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Pid Control Design · ashfordeou bundle
Use when the task is PID tuning, proportional integral derivative terms, anti-windup, integrator clamping, pole placement, or gain and phase margin checks. Design PID controller gains for aerospace flight and GNC control loops: compute the controller output from the proportional, integral, and derivative error terms, tune the gains from the plant model with Ziegler-Nichols using the ultimate gain and ultimate period, or place closed loop poles directly for a first or second order plant, add integrator anti-windup clamping, and check the gain margin and phase margin of the loop. Trigger: pid, proportional, integral, derivative, ziegler-nichols, ultimate gain, ultimate period, anti-windup, integrator clamp, pole placement, phase margin, gain margin.

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Lqg Design · ashfordeou bundle
Use when you must design a linear-quadratic-Gaussian output-feedback compensator for a two-state system whose state is not fully measurable: solve the regulator algebraic Riccati equation for the symmetric stabilizing P and the gain K from the quadratic cost weights, solve the filter (Kalman) algebraic Riccati equation for the error covariance S and the estimator gain L from the process and measurement noise covariances, assemble the dynamic output-feedback compensator state-space realization, and verify the separation principle that the closed-loop eigenvalues are the union of the regulator and estimator poles. Produces the two Riccati solutions with their gains, the compensator matrices and transfer function, and the separation verdict. Trigger: lqg, linear-quadratic-gaussian, output-feedback-compensator, separation-principle, regulator-riccati, filter-riccati-gain, compensator-transfer-function.

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Lqr Design · ashfordeou bundle
Use when you must design an LQR state-feedback gain matrix for a scalar-input two-state system such as spacecraft attitude control: solve the algebraic Riccati equation for the cost weights, compute the gain matrix, verify closed-loop stability of the regulated system, and assess the Q over R weighting trade. Produces the Riccati solution, the gain vector, and the stability verdict that feed the control-law design. Trigger: lqr, linear quadratic regulator, riccati equation, gain matrix, state feedback, closed loop stability, control effort, spacecraft attitude control.

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Ballooning · ashfordeou bundle
Use when you must balloon the characteristics of an engineering drawing for an AS9102 first article inspection: assign sequential balloon numbers to every characteristic, map each verification method label to the AS9102 method code (measuring, attribute, functional, visual, analytical), classify each characteristic as key, critical, or standard, and reconcile the balloon count against the form 3 line items and the D-list accountability matrix. Produce the numbered characteristic list, the method code column, and the accountability verdict that feed the FAI characteristic accountability form. Trigger: ballooning, characteristic numbering, balloon number, D-list, accountability matrix, verification method code, drawing characteristics.

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Thrust Vector Control · ashfordeou bundle
Use when you must size or analyze a rocket thrust vector control (TVC) system: compute the side force from the engine thrust and the nozzle deflection angle, the control torque about the vehicle center of gravity from the side force and the moment arm, and the axial thrust loss from the deflection cosine, and size the actuator authority the gimbal actuators must deliver. Covers the TVC mechanisms: gimbaled engine or nozzle, flex-seal nozzle, jet vanes, and liquid injection, and contrasts thrust vector control with aerodynamic control surfaces for launch vehicles and upper stages. Produces the deflection angle, side force, control torque, axial thrust loss, and actuator sizing in consistent SI units. Trigger: thrust vector control, tvc, gimbal deflection, nozzle deflection, side force, control torque, axial thrust loss, actuator authority, jet vanes, flex-seal nozzle.

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Turbofan Off Design · ashfordeou bundle
Use when you must evaluate turbofan performance away from the design point: correct the inlet mass flow and the spool speed to standard-day conditions, scale the sea-level net thrust to altitude with the density ratio and the ram drag penalty, apply the SFC altitude and throttle behavior, sanity-check the throttle setting, and judge the fan and core component matching. Produces corrected mass flow, corrected speed, altitude net thrust, cruise SFC factor, and the matching verdict that gate the off-design operating assessment in the FAR-33 engine context. Trigger: off-design, corrected mass flow, corrected speed, component matching, altitude thrust, cruise SFC, throttle setting, ram drag.

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Magnetorquer Control · ashfordeou bundle
Use when the task is magnetorquer control, dipole moment calculation, B-dot detumbling, cross-product torque steering, detumbling rate damping, or torque authority limits. Compute the magnetic dipole moment for spacecraft magnetic attitude control with magnetorquers: solve torque = m x B for the required dipole from a torque demand and the local magnetic field vector, apply the B-dot detumbling law to damp body rates, check the achievable torque against the magnetorquer torque authority limit, warn when the torque demand lies along the field, and size the torque rod coils. Produces the dipole moment vector, the B-dot control dipole, the achievable torque magnitude, the underdetermined-axis warning, the coil sizing, and the orbit-averaged torque authority. Trigger: magnetorquer, dipole moment, B-dot, detumbling, torque authority, cross-product, magnetic field, coil sizing.

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Software Engineering · ashfordeou bundle
Use when scoping European space software work per the ECSS series: classify space software criticality (A-D) from failure consequence, size the assurance and verification rigor for the category, gate lifecycle phases (requirements through acceptance) on their review records, and scope heritage-reuse evidence. ECSS-E-ST-40C governs software engineering, Q-ST-80C software product assurance, and the series is the European space procurement baseline. Trigger: ECSS, space software, E-ST-40C, software criticality, product assurance, Q-ST-80C, heritage software, space software lifecycle, software verification.

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Thermal Design · ashfordeou bundle
Use when you must size the thermal control subsystem for a spacecraft: compute the radiator area from the Stefan-Boltzmann balance, solve the equilibrium radiator temperature for a heat load, and check the thermal margin against the dissipation budget. Produces the radiator sizing, the equilibrium temperature, and the margin verdict that gate the thermal design. Trigger: thermal design, radiator sizing, thermal balance, heat load, spacecraft thermal control.

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Bird Strike · ashfordeou bundle
Use when the task is bird strike impact analysis and certification of transport aeroplane structure per FAR 25.631 and CS-25: estimate the impact kinetic energy of a 4 pound or 8 pound bird at cruise velocity with impact_energy, convert the bird mass to kilograms with bird_mass_kg, compute the specific energy with specific_energy, and rate the strike against the component damage threshold with damage_severity_ratio, penetration_verdict, and residual_strength_fraction for the residual strength after impact. Covers leading edge, windshield, radome, and engine inlet damage modes, energy absorption, soft-body impact behavior, and test versus analysis compliance. Trigger: bird strike, birdstrike, bird-strike, soft body impact, soft-body-impact, impact energy, impact-energy, leading edge, leading-edge, 4 pound bird, 8 pound bird, FAR 25.631, windshield, radome, engine inlet.

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Elliptical Hertz Contact · ashfordeou bundle
Use when you must compute the general Hertz elliptical contact patch between two elastic bodies with unequal principal radii pressed together: form the per-plane curvature sums A and B from the signed principal curvatures (convex positive, concave negative, flat infinite), solve the hertz-elliptic-integrals eccentricity from the unequal curvature ratio, then the contact-ellipse major and minor semi-axes a and b, the peak pressure p0 = 3P/(2 pi a b), the approach, the patch area and the yield-limit margin for the elliptical patch. Produces the elliptical contact solution with semi-axes, peak pressure, approach and yield verdicts. Trigger: elliptical contact, unequal principal radii, ball in groove, conforming raceway, crossed unequal cylinders, contact ellipse eccentricity.

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Metallic Fastener Joints · ashfordeou bundle
Use when you must analyze a metallic multi-fastener joint: split the applied load into the per-fastener share of a symmetric bolt or rivet pattern, check the fastener shear in single or double shear, the sheet bearing P/(D*t), net-section tension across the row and shear-out at the edge distance, and resolve an eccentric bolt group by the polar moment method for a load applied off the pattern centroid. Produces the per-fastener loads, the shear, bearing, net-section and shear-out stresses, the group torque with the per-bolt direct and secondary resultants, the max-loaded fastener, and the margin of safety of each mode against MMPDS-style allowables stated as module parameters, under MoS = allowable/(factor*applied) - 1 with the 1.5 ultimate factor. Trigger: metallic fastener joints, bolt group analysis, eccentric bolt group, fastener shear margin, single lap splice.

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Statically Indeterminate · ashfordeou bundle
Use when you must find the elastic end moments and support reactions of statically indeterminate beams and continuous beams: compute the fixed-end moments (uniform w*L^2/12 and central P*L/8 hogging at both fixed ends; w*L^2/8 and 3*P*L/16 hogging at the fixed end of a propped cantilever), solve the interior support moments with the three-moment (Clapeyron) equation, apply the moment distribution (Hardy-Cross) method with distribution factors and the 1/2 carry-over, and the slope-deflection and consistent deformation (force) methods with flexibility coefficients for propped cantilevers and frames. Produces the fixed-end moments, interior support moments, member end moments, joint rotations, support reactions and the equilibrium and method-agreement checks in a stdlib-only elastic redundancy analysis. Trigger: moment distribution, three-moment equation, slope deflection, fixed-end moment, consistent deformation, statically indeterminate beam, continuous beam support moment.

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Fracture Toughness · ashfordeou bundle
Use when you must apply the plane-strain fracture toughness K_IC of an aerospace material: compute the applied stress intensity K = Y * sigma * sqrt(pi * a) for a crack of size a under remote stress sigma with geometry factor Y, check the failure criterion K >= K_IC, size the critical crack at which fast fracture starts, and judge whether a test specimen meets the ASTM E399 plane-strain validity requirement that thickness and crack size both exceed 2.5 * (K_IC / sigma_ys)^2. Connects fracture toughness data to damage tolerance analysis and MMPDS material allowables. Trigger: fracture-toughness, kic, stress-intensity-factor, critical-crack-size, plane-strain, fast-fracture, damage-tolerance, mmpds.

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Material Selection · ashfordeou bundle
Use when you must select a structural material for an aerospace component: compare candidate materials across the aluminum, titanium, steel, and composite families, compute Ashby-style selection indices (E/rho for tension stiffness, E^(1/2)/rho for beam bending, E^(1/3)/rho for panel bending, sigma/rho for strength-limited tension), and rank candidates by stiffness-to-weight and strength-to-weight. Covers design drivers: temperature limits, corrosion and galvanic coupling, cost and availability, fatigue, and damage tolerance. Produces a ranked candidate list and the index-based justification for the selection, with representative property values flagged for verification against MMPDS. Trigger: material selection, selection indices, stiffness-to-weight, strength-to-weight, specific stiffness, specific strength, aluminum, titanium, steel, composites.

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Weight Estimation · ashfordeou bundle
Use when performing class-I or class-II vehicle weight estimation: compute moments and center of gravity from component weights and arms, check the CG against the forward and aft envelope limits, and validate empty-weight fractions against typical band ranges per aircraft category. The skill supports weight and balance calculations in the FAR-25 / CS-25 certification context. Trigger: weight estimation, weight and balance, center of gravity, cg envelope, mass, weight fraction, moment, class-i, class-ii.

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Cfd Turbulence Modeling · ashfordeou bundle
Use when you must estimate the wall-normal first cell height for a CFD mesh: compute the y plus value from the friction velocity and kinematic viscosity, derive the friction velocity from the wall shear stress or the skin friction coefficient, and recommend the turbulence model and wall treatment for the boundary layer. Produces the y plus value, the friction velocity, and the turbulence model recommendation that size the near-wall mesh. Trigger: turbulence model, y plus, friction velocity, boundary layer, wall treatment, cfd.

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High Lift Systems · ashfordeou bundle
Use when the task is high-lift device selection, flap clmax estimation, slat contribution, wing CLmax, or stall speed with flaps. Estimate high-lift system performance for conceptual design: compute the section clmax increment for trailing-edge flaps (plain, split, slotted, Fowler) and leading-edge devices (slat, Krueger), scale the increment with deflection, flap chord ratio, and flapped span fraction, combine flap and slat increments by superposition, apply the three-dimensional and sweep reduction to get wing CLmax, and derive the resulting stall speed. Produces the wing maximum lift coefficient, stall speed, drag increment, and pitching moment increment that size the flap schedule and drive field performance estimates. Trigger: high-lift, flap, slat, Fowler, Krueger, clmax, stall speed, lift increment.

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Radio Frequency Emissions · ashfordeou bundle
Use when you must plan and check the DO-160 section 21 radio frequency emission test of airborne equipment: convert the measured conducted emission amplitude from volts to dBuV and the radiated emission field to dBuV/m at the antenna, classify the equipment installation category, apply the CE102 conducted emission limit curve and the RE102 radiated emission limit curve for the category, compute the emission margin at each frequency, find the worst case frequency, and judge the equipment pass or fail for the EMC qualification. Produces the emission margin, the worst case frequency, and the pass or fail verdict that gate the DO-160 EMC qualification. Trigger: radio frequency emissions, DO-160 section 21, conducted emissions, radiated emissions, CE102, RE102, emission limit, emission margin, dBuV, dBuV/m, EMC qualification.

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Aperiodic Server Scheduling · ashfordeou bundle
Use when you must give the aperiodic or event-driven jobs of an avionics flight software task set a bounded service under fixed-priority scheduling: reduce the event streams to their load utilization, size the polling-server, deferrable-server or sporadic-server capacity and period from that load with a burst margin, fold the server budget into the fixed-priority response-time analysis as a periodic task at its priority slot, and place it at the highest slot where every periodic task keeps its implicit deadline and the budget completes within its period. Produces the sized server budget, the insertion index with the augmented response times and total utilization, the worst-case aperiodic response bounds with the capacity-loss wait and replenishment arithmetic, and the no-feasible-slot verdict. Trigger: aperiodic server, sporadic server, deferrable server, polling server, server budget, event driven jobs, aperiodic response time.

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Cyclic Executive Scheduling · ashfordeou bundle
Use when you must design and verify the offline repeating frame table of a time-triggered cyclic executive for a periodic avionics flight software task set with implicit deadlines: compute the hyperperiod as the least common multiple of the task periods, choose an admissible frame length that divides every task period and is at least every task execution time C_i, lay each frame-boundary release into the frame that starts at its release time over the hyperperiod, and confirm every per-frame execution total stays within the frame length. Produces the hyperperiod, the admissible and capacity-feasible frame lengths, the constructive cyclic frame table with per-frame loads and per-frame slack, and a FITS or no-admissible-frame verdict with the reject reason. Trigger: cyclic executive scheduling, cyclic frame table, hyperperiod, frame length selection, frame fit feasibility, time triggered frame schedule, frame boundary release.

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Virtual Deadline Scheduling · ashfordeou bundle
Use when you must decide the offline schedulability of an avionics flight software task set under the dual-criticality execution-time model scheduled by edf-vd virtual-deadline scheduling: each task carries the C_LO and C_HI execution-time estimates with C_HI at least C_LO and the implicit-deadline period T, sum the per-mode demand contributions of the LO and HI tasks, derive the common virtual-deadline factor x for the HI tasks, and check the lo-criticality-mode and the hi-criticality-mode demand conditions after the criticality mode change. Produces the per-mode demand sums, the virtual-deadline factor x, the per-HI-task virtual deadlines x*T, the lo-criticality-mode feasible verdict, the hi-criticality-mode feasible verdict, and the whole-set edf-vd feasible verdict. Trigger: edf vd scheduling, virtual deadline scheduling, virtual deadline factor, dual criticality mode change, lo criticality mode demand, hi criticality mode demand.

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Ads B Surveillance · ashfordeou bundle
Use when you must assess an ADS-B Out installation and ADS-B In reception geometry against the DO-260B-style performance categories: map the navigation integrity category (NIC) to its containment radius, map the navigation accuracy category for position (NACp) to its 95-percent accuracy bound, map the source integrity level (SIL) to its per-flight-hour probability bound, select the NIC and NACp category whose bound covers a required containment or accuracy value, and compute the 1090 MHz extended squitter radio line-of-sight range between two altitudes. Produces the containment radius, accuracy bound, integrity probability, chosen categories, and coverage range that gate an ADS-B surveillance assessment. Trigger: ads-b-out, ads-b-in, extended-squitter, nic, nacp, sil, containment-radius, ads-b-range.

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Fir Filter Design · ashfordeou bundle
Use when you must design a linear-phase finite-impulse-response lowpass filter with the windowed-sinc method: build the ideal lowpass impulse response from the cutoff frequency and the sample rate, apply a selected window (rectangular, Hann, Hamming, or Blackman), normalize the coefficient vector to unity DC gain, evaluate the magnitude response in dB at any frequency as the real cosine sum of the symmetric tap set, return the group delay of the taps, and filter a sampled signal by direct convolution. Produces the coefficient vector, the magnitude response checks (passband gain, -6 dB point at the cutoff, stopband attenuation), the group delay, and the filtered signal that gate a digital filter design task. Trigger: fir-filter-design, windowed-sinc, fir lowpass, finite impulse response, hamming window, filter taps, cutoff frequency, linear phase, magnitude response dB, group delay.

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Fisher Exact Test · ashfordeou bundle
Use when you must test a 2x2 contingency table with small expected counts: run the exact Fisher test under the fixed-margin null, compute the hypergeometric probability of the observed table, enumerate every table with the same margins, sum the one-tailed and two-tailed exact p-values, compute the odds ratio with the Haldane-Anscombe zero-cell correction, and return the small-expected-count verdict that recommends the exact test over the large-sample approximation. Produces p_obs, p_one_tail, p_two_tail, direction, odds ratio and the verdict. Trigger: fisher exact test, 2x2 contingency table, hypergeometric tail probability, small expected count, two by two table, odds ratio, exact independence test.

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Matrix Operations · ashfordeou bundle
Use when the task is a direct-method dense matrix problem: a linear system solve, a determinant evaluation, a matrix inverse, a singular-matrix check, or a residual verification of a solution, and numpy or other numerical libraries are unavailable. Compute and verify dense square-matrix operations with only the Python standard library: solve the linear system Ax=b by Gaussian elimination with partial pivoting, compute the determinant, invert the matrix, and detect singularity. Produces the solution vector, the determinant value, the inverse matrix, and a singularity verdict with the residual check that gates the solve. Trigger: gaussian elimination, partial pivoting, linear system solve, Ax equals b, determinant, matrix inverse, singular matrix, pivot.

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Isa Atmosphere · ashfordeou bundle
Use when you must apply the international standard atmosphere in aerospace calculations: read temperature, pressure, and density at altitude from the ISA model, from sea level through the tropopause and lower stratosphere. Produces the atmospheric state values at the requested altitude for performance and flight mechanics work. Trigger: standard atmosphere, isa, atmospheric density, temperature lapse, pressure altitude, troposphere.

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V Speeds · ashfordeou bundle
Use when you must compute the v-speeds set for a flight test: derive the vref reference landing speed as 1.3 times the vs0 stalling speed in landing configuration, the v2 takeoff safety speed as 1.2 times the vs1 stalling speed in takeoff configuration, and the vr rotation speed as 1.1 times vs1, then validate the speed ordering and check the vno normal operating limit and the vne never exceed speed. Produces the vref, v2, and vr speeds, a validated v-speeds dict, and the vne guard verdict with the margin in m/s that gate the flight test speed assessment. Trigger: vref, v2, vr, vs0, vs1, vno, vne.

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L1 Adaptive Control · ashfordeou bundle
Use when you must design and simulate an l1-adaptive-control law for a first-order plant with an unknown coefficient: run the state-predictor from the design model, drive the projection-based-adaptation-law with the prediction error, pass the adaptive signal through the low-pass filter omega_c/(s + omega_c) and form the control as the feedforward minus the filtered estimate. Produces the tracking-error and prediction-error time histories, the sigma_hat and filtered-signal histories, the projection engagement, the convergence verdict and the certified transient-bound check that gate an L1 adaptive control assessment. Trigger: l1-adaptive-control, state-predictor, low-pass-filtered-adaptation, projection-based-adaptation-law, guaranteed-transient-response.

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Midcourse Guidance · ashfordeou bundle
Use when a task asks how to reach an intermediate condition before final intercept, how much speed remains to be gained, or when to hand off to terminal guidance. Shape the midcourse flight of an interceptor or guided vehicle between launch and terminal handover: steer through a planned waypoint with a turn-rate-limited heading law, compute the velocity-to-be-gained speed deficit along the desired course, evaluate the zero-effort-miss of the closing geometry, size the handover condition that passes control to terminal guidance such as proportional navigation, and shape ascent trajectories with gravity-compensated commands. Trigger: midcourse guidance, waypoint steering, trajectory shaping, velocity-to-be-gained, zero-effort-miss, handover condition, turn-rate limit, gravity-compensated ascent.

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Fod Control · ashfordeou bundle
Use when you must audit a foreign object debris (FOD) prevention program for aerospace production: classify the FOD zone from the part criticality and debris exposure, compute the FOD risk score, derive the FOD sweep interval and the tool-control and housekeeping controls for the zone, reconcile the issued tool count against the returned tools, and score the program against the required control set for the audit verdict with findings. Produces the zone class, the risk score, the sweep interval, the tool-count reconciliation result, the control completeness, and the fod-pass or fod-fail verdict that gates the FOD prevention assessment. Trigger: FOD prevention, foreign object debris, FOD zone classification, FOD risk score, FOD sweep interval, tool count reconciliation, FOD audit.

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Gridded Ion Thruster · ashfordeou bundle
Use when you must size or analyze a gridded ion thruster (Kaufman type) for electrostatic propulsion: ion exhaust velocity and specific impulse from the net beam voltage, Child-Langmuir space-charge limit and perveance margin of the accelerator grid, beam current from extraction area and grid transparency, thrust from beam current and from power with total efficiency, and propellant mass for a delta-v mission. Produces the gridded thruster performance summary with thrust, specific impulse, perveance check, power budget and propellant mass, plus the gridded versus hall comparison at equal power. Trigger: gridded ion thruster, Kaufman thruster, electrostatic propulsion, accelerator grid, perveance, beam extraction, net voltage, ion optics, specific impulse.

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Thrust Chamber Cooling · ashfordeou bundle
Use when you must estimate the regenerative cooling of a liquid rocket thrust chamber: the throat area and propellant mass flow anchor of the operating point, the Bartz hot gas convective coefficient at the throat, the coolant side convective coefficient from the channel flow with the Dittus-Boelter correlation, the series wall resistance network giving the heat flux and the hot and cold wall temperatures, the coolant mass flux required to hold a copper wall temperature limit, and the film cooling handoff verdict when plain regenerative flow cannot hold the limit. Produces the heat flux, hot and cold wall temperatures, the plain regenerative shortfall and the required coolant mass flux. Trigger: regenerative cooling, thrust chamber cooling, Bartz heat transfer, throat heat flux, coolant channel sizing, copper wall limit, film cooling, rocket chamber wall, throat wall temperature.

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Pointing Error Budget · ashfordeou bundle
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 allocated contributor budget, and the dominant error source, the assembly layer from sensor metrology to payload pointing. Trigger: rss pointing error, 3 sigma requirement, error budget allocation, control deadband, jitter budget, dominant error source.

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Software Verification · ashfordeou bundle
Use when you must plan the ECSS-E-ST-40C verification of spacecraft flight software: select the verification method (test, analysis, inspection, review) for each requirement category (functional, performance, interface, resource, safety, data), determine the verification depth and independence required by the software criticality, and list the verification records each method must produce. Produces the per-requirement method map, the criticality depth verdict, and the record list that closes the verification plan. Trigger: ecss verification, software test method, verification depth, verification records, requirement category, criticality, flight software, analysis inspection review.

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Laminate Stiffness · ashfordeou bundle
Use when you must compute the stiffness of a composite laminate with classical lamination theory: build the ply stiffness from the material constants, rotate it to the ply angle, and assemble the A matrix for a symmetric laminate. Produces the ply stiffness, the rotated stiffness with coupling terms, and the laminate A matrix used in strength and stability analyses. Trigger: composite laminate, classical lamination theory, ply stiffness, laminate a matrix, symmetric laminate, composites.

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Crack Growth · ashfordeou bundle
Use when you must calculate fatigue crack growth for damage-tolerant structure: estimate the mode I stress intensity factor at a crack, apply the Paris law crack growth rate, and project the cycles to grow the crack from the initial detectable size to the critical size. Produces the stress intensity factor, the Paris da/dN rate, the crack extension per cycle, and the cycles-to-critical estimate that feed residual strength and inspection interval assessments. Trigger: crack growth, stress intensity, paris law, damage tolerance, fatigue crack, da/dn.

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Inelastic Column Buckling · ashfordeou bundle
Use when you must compute the inelastic column strength of a solid round, tube or extruded compression member in the intermediate slenderness band: the effective slenderness lambda = K*L/r of the member, the euler-johnson-tangent transition lambda_t = sqrt(2*pi^2*E/F_cy) where the yield-anchored Johnson parabola meets the Euler arm at F_cy/2, the johnson-parabola stress F_col = F_cy*(1 - F_cy*lambda^2/(4*pi^2*E)) below the transition and the Euler arm stress above it, the column capacity P_col = F_col*A and the margin of safety against the applied axial load, with the johnson or euler regime verdict. Produces the inelastic column allowable stress and load, the stubby-column-allowable and the pass-fail margin that gate compression checks of 7075-T6 and 2024-T3 actuator rods, tube members and extruded struts. Trigger: inelastic column buckling, Johnson parabola, column strength curve, intermediate slenderness, stubby column allowable.

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Plastic Collapse Analysis · ashfordeou bundle
Use when you must find the plastic collapse (limit) load of a beam or a simple frame: compute the fully plastic moment Mp = sigma_y*Zp from the plastic section modulus Zp (rectangle b*h^2/4, circle d^3/6, I-beam with the plastic neutral axis in the web), the shape factor nu = Zp/Z, and the plastic hinge mechanisms of statically indeterminate beams and rectangular frames, applying the kinematic (virtual work) and static (equilibrium plus yield) theorems to give the plastic collapse load, the collapse load factor against the applied load and the ultimate margin in the 1.5 ultimate-factor context of FAR 25.303. Produces the plastic section moduli and shape factors, fully plastic moments, plastic collapse loads with hinge mechanisms, and the load factor and ultimate margin verdicts that gate metallic beam and frame strength checks. Trigger: plastic collapse, plastic hinge, collapse mechanism, fully plastic moment, shape factor.

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Shock Response Spectrum · ashfordeou bundle
Use when you must compute the shock response spectrum (SRS) of a transient base acceleration pulse for shock qualification of equipment: single-degree-of-freedom oscillator peak response over a frequency grid at fixed damping, RK4 integration of the oscillator equation x_ddot + 2*zeta*wn*x_dot + wn^2*x = -a_base(t), half-sine pulse A*sin(pi*t/T) and decaying-sine pulse A*sin(2*pi*fd*t)*exp(-t/tau) support, peak pseudo acceleration wn^2 times peak relative displacement, the SRS curve as frequency to peak response in m/s2 and in g, and the maximum response with its amplifying frequency. Produces the SRS curve points, the peak response, and the frequency of the maximum that gate shock qualification assessment of equipment. Trigger: shock response spectrum, SRS, transient shock response, half sine pulse, base acceleration, pseudo acceleration, oscillator peak response, shock qualification, amplified frequency.

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Tow Estimation · ashfordeou bundle
Use when you must estimate the takeoff gross weight in conceptual aircraft sizing: apply the fuel-fraction method to payload and class-based empty and fuel fractions, iterate the estimate to convergence, and check the weight breakdown balances. Produces the takeoff gross weight estimate, the convergence verdict, and the breakdown check that gate the sizing iteration. Trigger: takeoff gross weight, conceptual sizing, fuel fraction, empty weight fraction, sizing iteration.

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Design Of Experiments · ashfordeou bundle
Use when you must plan a design of experiments (DOE) for an aircraft or spacecraft conceptual design study and analyze the runs: build the coded design matrix with a full factorial, a fractional factorial two-level half-fraction with its defining relation and alias structure, a seeded latin hypercube sample, or a central composite design around the baseline point, then compute the per-factor main effects, the two-factor interaction effects, and the factor screening ranking. Produces the coded design matrix with its run count and the ranked main effects and interaction effects that gate which planform, loading, or configuration factors to carry into multidisciplinary optimization. Trigger: design of experiments, DOE, factorial design, fractional factorial, latin hypercube, central composite, main effects, interaction effects, factor screening, design space exploration.

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Airfoil Optimization · ashfordeou bundle
Use when you must optimize an airfoil shape for an aerodynamic objective: set up design variables with NACA or PARSEC parameterization, evaluate objectives such as lift to drag ratio, maximum lift coefficient, and drag bucket width, enforce geometric constraints on thickness and camber, and run trade studies with sensitivity analysis. Produces the parameter sweep, the constraint verdict, the sensitivity ranking, and the recommended design point that feeds section selection and polar analysis. Trigger: airfoil shape optimization, design space, trade study, drag bucket, parsec, sensitivity analysis, geometric constraints.

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Lift Curve Slope · ashfordeou bundle
Use when you must estimate the lift curve slope of a wing from section data: compute the thin-airfoil section slope a0 = 2*pi per radian, correct it for finite aspect ratio with the lifting-line formula a = a0 / (1 + a0 / (pi * e * AR)), apply the simple sweep theory cosine correction, apply the Prandtl-Glauert Mach correction a / sqrt(1 - M^2) with a documented M < 0.7 limit, and predict lift coefficient from angle of attack with C_L = a * (alpha - alpha_zero), including an optional stall guard. Produces the corrected wing slope and lift coefficient for a given angle of attack that feed wing sizing and performance estimates. Trigger: lift curve slope, thin-airfoil theory, finite wing correction, aspect ratio, sweep correction, Prandtl-Glauert, lift coefficient.

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Ground Effect · ashfordeou bundle
Use when you must estimate the ground effect on a wing operating near the ground: compute the induced drag reduction factor and the induced drag ratio from the height to span ratio, apply the image vortex correction to the downwash and the effective aspect ratio, and estimate the lift increase and lift curve slope change in ground effect for takeoff and landing analysis. Produces the ground effect factor, the corrected induced drag, and the lift curve slope that feed low altitude performance estimates. Trigger: ground effect, induced drag reduction, image vortex, height to span ratio, ground cushion, takeoff lift.

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Rhumb Line Leg · ashfordeou bundle
Use when you must compute the rhumb-line leg geometry between waypoints: derive the constant Mercator course and rhumb-line distance that connect two fixes, the along-parallel leg length at a fixed latitude, and the rhumb-versus-great-circle distance delta that gates long-range FMS leg and airway geometry checks. Produces the constant course in degrees, the rhumb distance in metres, the parallel leg length, and the comparison delta in metres and percent. Trigger: rhumb line leg, constant course leg, mercator course, parallel leg length, rhumb versus great circle, long range leg, fms leg geometry, waypoint leg distance.

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Mixed Criticality Scheduling · ashfordeou bundle
Use when you must decide the offline schedulability of an avionics flight software task set under the dual-criticality execution-time model: each task carries the C_LO and C_HI execution-time estimates with C_HI at least C_LO, run the lo-criticality-mode fixed-point response-time iteration over the C_LO estimates for every task, then run the hi-criticality-mode amc-rtb fixed point after the criticality-mode change, with higher-priority LO tasks charged at C_LO and higher-priority HI tasks charged at C_HI in the interference sum. Produces the per-task lo-mode response times and the LO-mode feasible verdict, the hi-mode response times of the HI tasks under the AMC-rtb bound with the HI-mode feasible verdict, the overall mixed-criticality feasible verdict, and the divergence verdict when an iterate crosses a deadline. Trigger: mixed criticality scheduling, amc rtb analysis, dual criticality execution time, lo mode feasibility, hi mode response time, criticality mode change.

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Hypothesis Testing · ashfordeou bundle
Use when you must run significance tests on aerospace engineering data: the one-sample and two-sample Student t tests (pooled and Welch), the paired t test, the two-variance F test, the chi-square test of independence, and the one-way ANOVA F test, computing each statistic, its degrees of freedom, and its p-value from the incomplete beta and gamma functions and returning the reject-null or fail-to-reject verdict at a stated significance level. Produces the statistic, df, p-value, and verdict that gate the data-comparison conclusion for test versus baseline, batch versus batch, or configuration A versus B. Trigger: hypothesis testing, student t test, welch test, paired t test, ANOVA, F test for variances, chi-square test of independence, p-value, reject null hypothesis.

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Quaternion Algebra · ashfordeou bundle
Use when you must compute single-step quaternion algebra with the Python standard library: form the Hamilton quaternion product, take the conjugate, norm, and inverse, normalize to a unit quaternion, rotate a 3-vector by a quaternion with the stated conjugate rotation convention, build a quaternion from an axis and angle or from yaw-pitch-roll angles with the ZYX convention, convert between quaternion and direction cosine matrix, and interpolate between two unit quaternions with spherical linear interpolation. Produces the product quaternion, the rotated vector, the converted angles or matrix, and the slerp result at the requested parameter. Trigger: quaternion product, quaternion multiply, rotate vector by quaternion, euler to quaternion, quaternion to euler, direction cosine matrix, slerp, quaternion conjugate, unit quaternion, axis angle to quaternion.

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Unit Conversion · ashfordeou bundle
Use when you must convert aerospace quantities between SI and imperial or aviation units: length (m, ft, NM), speed (m/s, kt, ft/s, Mach), temperature (K, C, F, R), pressure (Pa, hPa, psi, inHg), density (kg/m3, slug/ft3), mass (kg, lb, slug), and force (N, lbf). Converts with a deterministic factor table, handles offset temperature scales, computes Mach from true airspeed and speed of sound, and relates pressure altitude to geometric altitude. Trigger: unit conversion, convert units, knots, mach number, temperature conversion, pressure altitude, SI imperial.

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Wind Effects · ashfordeou bundle
Use when you must resolve the wind triangle for a fixed-wing aircraft: decompose the wind into the headwind, tailwind, and crosswind components along the track, combine the true airspeed with the wind components to find the groundspeed, derive the wind correction angle needed to hold the track against the crosswind, and convert a leg distance into the enroute time at the resulting groundspeed. Produces the wind components, the groundspeed, the wind correction angle, and the enroute time that gate the wind effects assessment. Trigger: headwind, crosswind, wind correction angle, crab angle, groundspeed, enroute time, wind triangle.

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Backstepping Control · ashfordeou bundle
Use when you must design and simulate the backstepping control law for a second-order strict-feedback plant x1_dot = x2 + f1(x1), x2_dot = u + f2(x1, x2) tracking a reference: choose the virtual control that stabilizes the first error variable z1 = x1 - x1d, propagate the inner-state mismatch z2 = x2 - alpha1 as the second error variable, differentiate the virtual control analytically along the plant, and assemble the final control from the recursion so the composite Lyapunov function V2 = (z1^2 + z2^2)/2 decays at the design rates set by c1 and c2. Produces the error-variable and virtual-control histories, the analytic virtual-control derivative, the closed-loop command, the quadratic-Lyapunov decay audit, and the tracking-error history that gate a backstepping control assessment. Trigger: backstepping-control, integrator-backstepping, strict-feedback, virtual-control, control-lyapunov-function, recursive-control-design, backstepping-control-law, error-variable-recursion.

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H Infinity Synthesis · ashfordeou bundle
Use when you must synthesize the state-space h-infinity controller of the generalized plant with the dgkf two-Riccati method: given the state matrices and the performance and control channels, iterate the gamma level while the x-infinity and y-infinity algebraic Riccati equations admit stabilizing positive-semidefinite solutions and the spectral-radius coupling stays below gamma squared, then form the central h-infinity controller state matrices from the state-feedback gain and the observer gain. Produces the infimum feasible gamma level from the bisection, the two stabilizing Riccati solutions with the coupling check, the central controller state matrices at the working suboptimal level, and the closed-loop stability check with the disturbance-to-output peak below that level. Trigger: h infinity synthesis, dgkf two riccati, gamma level iteration, spectral radius coupling, central h infinity controller, x infinity y infinity riccati, state feedback gain, observer gain.

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Sliding Mode Control · ashfordeou bundle
Use when you must design a sliding-mode-control law for a second-order plant with matched uncertainty: choose the sliding surface from the tracking error and its derivative, compute the equivalent control that holds the surface on the nominal model, add the switching term sized above the uncertainty bound inside the boundary layer to enforce the reachability condition, and suppress chattering with the saturation thickness. Produces the surface and equivalent-control histories, the sliding-condition audit of the reachability inequality at every sample, the finite-time reach of the boundary layer, the boundary-layer command with the chattering-suppression check, and the tracking-error history that gate a sliding-mode control assessment. Trigger: sliding-mode-control, sliding-surface-design, equivalent-control, constant-plus-proportional-reaching-law, switching-term, chattering-suppression, matched-uncertainty, variable-structure-control, boundary-layer-command.

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State Space Analysis · ashfordeou bundle
Use when you must analyze a linear time-invariant system in state space: form the controllability and observability matrices, decide controllability and observability from their ranks, compute the 2x2 eigenvalue stability verdict, build the state transition matrix by the Cayley-Hamilton method, and produce the controller or observer canonical forms. Applies to flight control and GNC state-space models written as x_dot = A x + B u with output y = C x. Produces the controllability and observability verdicts, the stability verdict, the transition matrix at a time t, and the canonical form realizations that feed control law design. Trigger: state space, controllability, observability, state transition matrix, eigenvalues, stability, canonical form, linear system, A matrix, B matrix, C matrix.

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Navigation Frames · ashfordeou bundle
Use when you must convert navigation coordinate frames for an aircraft or spacecraft: transform geodetic latitude, longitude, and altitude on the WGS-84 ellipsoid into ECEF position, build the ECEF to NED rotation matrix at a reference point, resolve velocity into north, east, and down components, and compute the Earth rotation angle from a Julian date for inertial to Earth-fixed frames. Produces ECEF coordinates in meters, the NED rotation matrix, NED velocity, and GMST rotation angle in radians. Trigger: navigation frames, ecef, ned, geodetic, wgs 84, earth rotation, coordinate conversion.

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Turbine Stage · ashfordeou bundle
Use when you must analyze a single axial turbine stage: compute the specific work output, the stage loading, the flow coefficient, the degree of reaction, the total-to-total efficiency, and the blade row losses from the blade speed, the axial velocity, the absolute flow angles, and the relative flow angles. Produces the velocity-triangle performance parameters in SI units that gate the turbine stage design review in the FAR-33 engine context. Trigger: axial turbine stage, stage loading, degree of reaction, flow coefficient, blade row loss, total-to-total efficiency, specific work output, turbine rotor, turbine stator.

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Turbofan Design Point · ashfordeou bundle
Use when you must compute the two-stream turbofan design point at flight Mach and altitude: traverse the fan-stream-station-states and the core stream of the separate-exhaust-cycle down the 0-2-13-2.5-3-4-4.5-5-9/19 station chain from the overall pressure ratio, the turbine-inlet temperature, the bypass ratio and the fan pressure ratio with the component efficiencies; close the two-spool-work-balance of the high-pressure compressor on the HP turbine and of the fan plus booster on the LP turbine; and report the burner fuel-air ratio, the per-stream nozzle exit velocities with the choked pressure terms, and the net thrust and TSFC of the separate-exhaust turbofan. Produces the station total states, the spool works, the jet velocities, the net thrust and the TSFC, in SI units, that gate the engine design-point assessment. Trigger: turbofan design point, two-spool engine cycle, fan stream station states, separate exhaust cycle, overall pressure ratio, fuel-air ratio, net thrust and tsfc.

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Reaction Wheel Control · ashfordeou bundle
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 torque and dipole. Trigger: reaction wheel control, wheel torque command, wheel momentum saturation, momentum desaturation, desaturation horizon, wheel momentum excess, unloads wheel cluster, local magnetic field, magnetorquer dipole, torque demand along the field, warn when the demand lies along the field, find the desaturation dipole for the target momentum, quaternion error feedback, desaturation torque, spacecraft pointing.

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Delamination Growth · ashfordeou bundle
Use when you must assess delamination growth in a composite laminate by fracture mechanics: compute the mode I strain energy release rate of a DCB double cantilever beam specimen and the mode II rate of an ENF end-notched flexure specimen from load, crack length and coupon geometry, blend mixed-mode rates with the Benzeggagh-Kenane criterion, and compare the total rate against the critical rate for the onset and growth verdict. Produces G_I, G_II, the mixed-mode ratio, critical rate G_c, onset margin and growth verdict gating the delamination tolerance assessment. Trigger: delamination growth, strain energy release rate, double cantilever beam, end notched flexure, mixed mode fracture, benzeggagh kenane criterion, mode I, mode II.

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671 published skills · page 3 of 7