ashfordeOU

@ashfordeou source repo

671 skills
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Mil Std 1797a · ashfordeou bundle
Use when the task is flying qualities assessment, handling qualities level classification, or MIL-STD-1797A compliance review. Assess the flying qualities of a piloted aircraft against MIL-STD-1797A level criteria: classify the flight phase category (A precision tracking, B gradual nonterminal, C terminal), select the aircraft class (I small light, II medium, III large heavy, IV high maneuverability), and grade each dynamic mode against the level tables: short period damping and frequency by category and class, phugoid minimum damping 0.04, dutch roll minimum damping 0.19, spiral minimum time to double 20 s, roll mode maximum time constant 1.0 s, roll performance. Produces a Level 1, 2, or 3 verdict per mode, the overall limiting level, and the Cooper-Harper band. Trigger: mil-std-1797a, flying qualities, handling qualities, short period, dutch roll, phugoid, spiral mode, roll mode, roll performance, flight phase category, aircraft class, cooper-harper band.

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Icing Flight Test · ashfordeou bundle
Use when you must categorize an icing encounter and plan the icing certification flight test campaign for a transport airplane against the FAR/CS 25 Appendix C icing envelopes: judge the continuous maximum and intermittent maximum regime membership from liquid water content, median volumetric diameter and total air temperature, rate the icing encounter severity for the flight test log, screen the natural icing search conditions against the freezing level and the forecast liquid water content, build the artificial ice shape test matrix with glaze, rime, mixed and runback shapes over the critical surfaces, and list the ice protection effectiveness test points to fly. Produces the envelope verdict, severity rating, search go/no-go and shape matrix verdict that gate the program. Trigger: icing flight test, natural icing, artificial ice shapes, appendix C envelope, liquid water content, median volumetric diameter, runback ice, supercooled large droplet, icing encounter severity.

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Vmc Determination · ashfordeou bundle
Use when you must predict and check the minimum control speed Vmc of a multi-engine airplane for the engine-inoperative flight test: identify the critical engine from the engine-out yawing moment geometry, build the asymmetric yawing moment from the operating-engine thrust at the failed engine lateral arm plus the windmilling drag contribution, solve the rudder authority limited speed, apply the rudder pedal force criterion with the boost factor against the 150 lbf pedal limit, and apply the stall protection guard on the reference stall speed. Produces the predicted Vmc in m/s and knots, the governing limit label, the asymmetric moment model, and the flight test go verdict. Trigger: minimum control speed, Vmc determination, critical engine, rudder pedal force, asymmetric yawing moment, engine inoperative flight test, 150 lbf pedal limit.

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Vmu Determination · ashfordeou bundle
Use when you must reduce the takeoff rotation runs of a transport airplane flight test to the minimum unstick speed Vmu in the spirit of the FAR/CS 25.107(b) method, summary-only: classify each measured rotation run against the certified tail-strike rotation limit, correct each liftoff speed from the test weight, altitude, temperature, and flap setting to the reference conditions, and take the minimum corrected speed of the limit-reaching runs as the Vmu verdict with the no-unstick and premature-unstick bracket checks. Produces the corrected run table, the Vmu in m/s and knots, the bracket consistency verdict, and the certification margins against the 1.08 Vmu liftoff constraint and the 1.10 Vs1 rotation floor that gate the V1/VR scheduling. Trigger: minimum unstick speed, vmu determination, rotation limit speed, unstick certification, tail strike rotation limit, takeoff rotation run.

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Particle Filter · ashfordeou bundle
Use when you must estimate the state of a nonlinear or non-Gaussian system with a bootstrap particle filter: draw an initial particle ensemble from a Gaussian prior, propagate the particles through a constant-velocity or random-walk motion model with additive Gaussian process noise, weight them with a Gaussian measurement likelihood, normalize the importance weights, track the effective sample size, and trigger systematic resampling when the effective sample size drops below half the particle count. Produces the per-step posterior mean and standard deviation, the effective sample size, the resampling flags, and the final ensemble for every measurement, which gate a nonlinear and multimodal tracking assessment. Trigger: particle filter, sequential Monte Carlo, SIR, bootstrap filter, resampling, effective sample size, importance weights, nonlinear estimation, non-Gaussian posterior, multimodal likelihood.

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Bearing Only Localization · ashfordeou bundle
Use when you must locate a stationary emitter from passive angle-of-arrival bearing lines measured at known observer positions. Build the linearized bearing equations sin(beta_i)*(x - xi) - cos(beta_i)*(y - yi) = 0 per observer, solve the Stansfield closed-form weighted least squares for the two-dimensional emitter fix with an equal-angle first pass and a distance-weighted second pass, and read the fix covariance error ellipse plus the per-bearing residual angles. Produces the emitter position fix, the 1-sigma error ellipse, the per-bearing residuals and the observer-geometry dilution verdict. Trigger: bearing-only-localization, angle-of-arrival-triangulation, stansfield-weighted-least-squares, bearing-line-intersection, emitter-fix-covariance, per-bearing-residual, observer-geometry-dilution.

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Eddy Current Inspection · ashfordeou bundle
Use when you must plan and execute an eddy current inspection (ET) of an aerospace part and turn probe impedance readings into defect findings: compute the standard depth of penetration from test frequency, electrical conductivity, and magnetic permeability; select the frequency that places a surface or subsurface flaw within the usable penetration band; convert percent IACS conductivity to siemens per meter; estimate the eddy current density ratio and the phase lag at the flaw depth; and interpret the impedance plane to separate lift-off, conductivity changes, and crack indications. Produces the depth of penetration, the selected test frequency, and the density and phase values that gate eddy current acceptance dispositions. Trigger: eddy current, eddy-current testing, depth of penetration, impedance plane, subsurface flaw, surface crack, lift-off, IACS conductivity, phase lag.

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Radiographic Inspection · ashfordeou bundle
Use when you must plan and evaluate a radiographic inspection (RT) for aerospace NDT: compute the geometric unsharpness from the focal spot size, the source-to-object distance, and the object-to-detector distance; size the image quality indicator (IQI) penetrameter and its percent sensitivity; apply the inverse-square law to X-ray or gamma-ray exposure time; check the film density against the 2.0 to 4.0 band; and classify indications such as porosity, cracks, inclusions, and slag. Produces the setup geometry, exposure settings, and the sensitivity and density verdicts that gate radiographic acceptance of welds and castings. Trigger: radiography, X-ray, gamma ray, IQI, penetrameter, geometric unsharpness, film density, porosity.

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Shearography Inspection · ashfordeou bundle
Use when you must plan and interpret a laser shearography NDT inspection on an aerospace composite or bonded part: compute the phase sensitivity of the shearography setup from the laser wavelength and the shear distance, select the shear distance for the minimum defect size of interest, size the vacuum, thermal, or vibration load step for the part stiffness, build the scan plan covering the part with the required overlap, convert a measured phase anomaly from the fringe map into a strain gradient estimate, and disposition the anomaly against the maximum allowable disbond or delamination size. Produces the setup parameters, the scan plan, the anomaly strain estimate, and the disposition verdict that gate the inspection under an approved NDT procedure. Trigger: laser shearography, shearography inspection, phase map, shear distance, strain gradient, vacuum load step, fringe anomaly, disbond detection, composite panel inspection, minimum detectable strain.

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Polytropic Efficiency · ashfordeou bundle
Use when you must convert between the isentropic and the polytropic efficiency of a compressor or a turbine for performance sizing: recover the polytropic efficiency from the isentropic efficiency at the overall pressure ratio and the reverse, resolve either from inlet and exit total states, restate the stage-count-independent polytropic efficiency at the per-stage pressure ratio, and run the reheat-factor log-sum cross-check of per-stage ratios against the overall ratio. Produces the converted efficiency pair, the state-resolved efficiency and the stage-consistency verdict in air-standard gamma 1.4 closed forms. Trigger: polytropic efficiency, isentropic efficiency, stage-count-independent efficiency, per-stage pressure ratio, reheat-factor cross-check, efficiency conversion, compressor sizing, turbine sizing.

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Turbine Blade Cooling · ashfordeou bundle
Use when you must analyze the cooling flow required to protect a gas turbine blade row: compute the cooling effectiveness from the hot gas total temperature, the allowable blade metal temperature and the coolant supply temperature, convert it into the required coolant-to-gas mass flow fraction with a simplified energy balance, check the fraction against the practical bleed limit, and estimate the achievable metal temperature when film cooling lifts the effectiveness. Produces the effectiveness, coolant fraction, bleed-limit verdict, metal temperature and margin that gate hot section cooling design in the FAR-33 engine context. Trigger: turbine blade cooling, cooling effectiveness, coolant flow fraction, film cooling, allowable metal temperature, coolant supply temperature, bleed limit, hot section cooling.

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Gravity Gradient Stabilization · ashfordeou bundle
Use when you must design or analyze passive gravity-gradient stabilization: check the inertia-ratio stability criterion I_y > I_x > I_z with y along the orbit normal for a nadir-pointing spacecraft, compute the pitch libration frequency and period from the mean motion and the inertia spread, estimate the gravity-gradient restoring torque at a pitch offset, and size a gravity boom tip mass for a target libration stiffness. Produces the stability verdict, the libration period, the restoring torque and the boom sizing that gate the passive attitude design of a nadir-pointing spacecraft. Trigger: gravity-gradient stabilization, inertia-ratio criterion, pitch libration frequency and period, gravity boom sizing, nadir-pointing spacecraft, passive attitude stabilization.

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Ground Track Repeat · ashfordeou bundle
Use when you must compute a repeating ground track for a circular Earth orbit: determine the semimajor axis and mean motion from the altitude, evaluate the J2 nodal regression rate, derive the nodal period, count the integer revolutions per sidereal day, and find the repeat cycle in whole days after which the ground track retraces itself. Produces the semimajor axis, mean motion, nodal regression rate, nodal period, revolutions per day, and repeat cycle that gate repeat-ground-track orbit selection for remote sensing and constellation design. Trigger: repeat ground track, ground track repeat, nodal period, revolutions per day, sidereal day, integer revolutions, nodal regression, j2.

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Continuous Turbulence Gust Loads · ashfordeou bundle
Use when you must compute the continuous turbulence gust design loads of an airplane by the power spectral density gust method: build the von Karman or Dryden power spectral density of the vertical gust velocity from the scale of turbulence and the turbulence intensity, form the rigid-aircraft gust response transfer function, multiply into the response power spectral density, integrate to the rms load response and scale to the design limit load factor of the continuous turbulence design criterion, and report the equivalent discrete gust velocity the discrete-gust envelope analysis takes as its input. Produces turbulence PSD and response PSD ordinates, the rms load factor, the design gust loads and the discrete-gust equivalent in SI units. Trigger: continuous turbulence gust loads, von Karman spectrum, Dryden spectrum, gust response transfer function, turbulence PSD, power spectral density gust method, rms load response, continuous turbulence design.

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Inertia Estimation · ashfordeou bundle
Use when you must estimate mass properties for vehicle design: compute moments of inertia from masses and radii of gyration, move inertia between axes with the parallel axis theorem, and check the gyration radius against the component dimension. Produces the inertia estimates, the parallel axis transfers, and the gyration sanity verdict that feed the loads analysis. Trigger: mass properties, moment of inertia, radius of gyration, parallel axis theorem, inertia estimation.

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Multidisciplinary Optimization · ashfordeou bundle
Use when you must set up a multidisciplinary optimization (MDO) loop for an aircraft or spacecraft: define the design variables, the objective function, and the constraints, identify the coupled disciplines (aerodynamics, structures, propulsion, trajectory), choose a monolithic or distributed architecture, and run the analysis loop that iterates the coupling variables to convergence with a fixed-point scheme and a sensitivity check. Produces the converged coupled state, the constraint feasibility verdict, and the optimum design point that ties the sizing, mass-properties, cost-estimation, and structures-integration leaves together. Trigger: multidisciplinary optimization, mdo, aero-structural coupling, fixed point iteration, design variables, objective function, constraints, coupling, disciplines, design space.

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Avionics Bay Cooling Sizing · ashfordeou bundle
Use when you must size the cooling airflow for the avionics and equipment bay: rolling up the bay heat load from the LRU heat dissipations, sizing the bay cooling mass flow from the allowable cooling air temperature rise so the bay exhaust temperature stays at or below the LRU inlet air temperature limit, converting the mass flow to the volumetric flow and to cubic feet per minute, and checking each LRU case temperature against its case limit from the dissipated power and the case to air conductance. Produces the bay heat load, the required cooling mass flow and CFM, the exhaust temperature, the per LRU case temperature verdicts and the bay cooling PASS or FAIL verdict that gate the bay ventilation layout. Trigger: avionics bay cooling sizing, equipment bay cooling airflow, LRU heat dissipation, LRU case temperature check, cooling air temperature rise, case to air conductance.

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Component Weight Estimation · ashfordeou bundle
Use when you must predict the airframe structural group weights at the class-II level from geometry and design loading: evaluate the statistical wing-group-weight regression on the planform area, aspect ratio, sweep, thickness ratio and design load factor, the horizontal-tail-group-weight and vertical-tail-group-weight regressions on the tail planforms, and the fuselage-group-weight regression on the wetted area, fineness ratio and design gross weight, with the limit load factor scaled to ultimate by the 1.5 safety factor and the pressurization penalty added when a pressurized volume and differential are supplied. Produces the four group masses in kg, the airframe group total, and the group fractions of MTOW that feed the weight statement. Trigger: component weight estimation, group weight equation, wing group weight, fuselage group weight, horizontal tail weight, vertical tail weight, statistical weight prediction, class ii weight buildup.

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Windtunnel Data Reduction · ashfordeou bundle
Use when the task is experimental wind tunnel data reduction, tare or blockage correction, wall interference, dynamic pressure correction, coefficient reduction, or uncertainty from repeated runs. Correct wind tunnel balance and pressure measurements into standard aerodynamic coefficients: subtract support tare and tareshift, apply solid and wake blockage corrections, correct wall interference and streamline curvature, apply Reynolds number and Mach corrections, estimate repeat-run uncertainty of the measured coefficients, and reduce raw runs to lift, drag, and pitching moment coefficients plus pressure distributions referenced to planform area and reference length, with a full correction ledger. Trigger: windtunnel data reduction, tare correction, blockage correction, wall interference, reynolds correction, aerodynamic coefficients, pressure distribution, uncertainty estimation, balance data, experimental aerodynamics.

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Performance Computation · ashfordeou bundle
Use when the task is FMS performance computation, ECON speed selection, cost index, fuel versus time trade, step-climb logic, or top of descent for a flight management system. Compute flight management system performance values: derive the cost index from time and fuel costs, select the ECON cruise Mach that minimizes total fuel and time cost, quantify the fuel-for-time trade between candidate cruise speeds, evaluate step-climb benefit between flight levels, and compute the VNAV top of descent with wind-corrected descent distance for the vertical profile. Produces the ECON Mach and true airspeed, the fuel and time per leg, the step-climb verdict, and the top-of-descent distance from cruise altitude to the arrival constraint. Trigger: cost index, econ cruise speed, fuel time trade, step climb, top of descent, vnav, fms performance.

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Poisson Confidence Interval · ashfordeou bundle
Use when you must compute a confidence interval for a Poisson rate from a count over an exposure: estimate the rate lambda_hat = k / T, form the exact Garwood interval from in-leaf chi-square quantiles with lower bound chi2(2k, alpha/2)/(2T) and upper bound chi2(2k+2, 1-alpha/2)/(2T), and report the normal approximation as the large-count cross-check. Produces the rate estimate, the exact lower and upper bounds per exposure unit, the approximation bounds, and the containment verdict that gates defect-rate and rare-event claims. Trigger: poisson rate confidence interval, defect count per flight cycle, garwood exact bound, count rate interval, rare event rate claim.

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Balanced Field Length · ashfordeou bundle
Use when you must compute the balanced field length and V1 decision speed of a multi-engine transport: derate the total thrust to the remaining engines, derive the constant ground accelerations and the braking deceleration, trace the accelerate-stop distance (roll on all engines to V1, react, brake to a stop) and the accelerate-go distance (roll to V1, continue on the remaining engines to lift-off, rotate, and climb over the 35-ft obstacle on the engine-out climb gradient), solve the quadratic balance for the V1 where the two distances are equal, and read the balanced field length. Produces the engine-out thrust, the accelerations, the accelerate-stop and accelerate-go distance curves, the balanced V1, and the balanced field length that gate the runway-length and engine-out certification assessment. Trigger: balanced field length, V1 decision speed, accelerate-stop distance, accelerate-go distance, engine-out field length, balanced V1.

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Envelope Expansion · ashfordeou bundle
Use when you must plan flight test envelope expansion: compute the corner speed (maneuvering speed VA) from the stall speed and the limit load factor, classify airspeeds into the flight test speed categories, and size the expansion steps against the load factor envelope. Produces the corner speed, the airspeed classification per test point, the per-step speed increment, and the load factor limit verdict that gate the expansion program. Trigger: envelope expansion, corner speed, airspeed classification, load factor, flight test, expansion step, maneuver envelope.

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Vmcg Determination · ashfordeou bundle
Use when you must reduce the engine-failure ground roll demonstration runs of a transport airplane flight test to the ground minimum control speed Vmcg in the spirit of the FAR/CS 25.149 ground leg method, summary-only: build the asymmetric yawing moment from the failed engine thrust at its lateral arm, apply the nosewheel steering authority below the steering cutout speed, solve the steering-free rudder authority limited and 150 lbf pedal force limited ground speeds with the boost factor, classify runs into the steering-held, departed, at-limit and with-margin classes, and take the minimum corrected at-limit speed as the Vmcg verdict with bracket checks. Produces the corrected run table, the Vmcg in m/s and knots, the bracket verdict, the stall guard check against 1.05 Vs1, and the V1 gate verdict with the required V1 speed. Trigger: ground minimum control speed, vmcg determination, nosewheel steering authority, steering cutout speed, engine failure ground roll run.

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Vmcl Determination · ashfordeou bundle
Use when you must reduce the landing-configuration approach-cut demonstration runs of a multi-engine transport airplane flight test to the approach and landing minimum control speeds VMCL and VMCL-2 in the spirit of the FAR/CS 25.149(f)/(g) method, summary-only: build the asymmetric yawing moment of the critical-engine cut over the operating engine set, solve the rudder authority limited and 150 lbf pedal force limited airspeeds with go-around thrust, classify each run by the bank-5-degree and 20-degree-heading-change control criteria, correct the demonstrated speeds to the most favorable weight and reference landing flap, and add the VMCL-2 second-cut leg for three-plus-engine airplanes with the go-around thrust change. Produces the predicted and demonstrated VMCL in m/s and knots, the run-classed verdict with bracket checks, the stall guard check, and the margin against the operating approach speed set. Trigger: VMCL, VMCL-2, landing minimum control speed, go-around thrust.

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Flight Test Safety · ashfordeou bundle
Use when the task concerns flight test safety: risk assessment, flight envelope limits, emergency procedures, safety pilot duties, go/no-go criteria, risk mitigation. Assess the flight test safety package: score the hazards on the severity by likelihood risk matrix, check that every test point stays inside the flight envelope limits, confirm the emergency procedures cover the required conditions, verify the safety pilot duties are assigned, run the go/no-go criteria gate, and list the mitigation gaps. Trigger: flight test safety, risk assessment, safety pilot duties, emergency procedures, go/no-go criteria, flight envelope limits.

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Impact Time Control Guidance · ashfordeou bundle
Use when you must compute the impact-time-control-guidance command for a salvo or simultaneous-impact engagement: the proportional-navigation baseline acceleration from the closing speed and the line of sight rate, the PNG time-to-go estimate on the collision course, the impact-time error between the commanded remaining time to go and the natural PNG time, and the time-to-go-error-feedback bias that lengthens or shortens the intercept path so the group arrives at the commanded impact time. Produces the total lateral acceleration command with its PN baseline, bias term, time-to-go estimate and impact-time error. Trigger: impact time control, salvo attack, simultaneous impact, commanded impact time, time to go error feedback, ITCG.

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Ins Gnss Integrated Filter · ashfordeou bundle
Use when you must fuse INS and GNSS in a loosely coupled error-state integration filter: assemble the 5-state psi-angle error model of the horizontal INS drift from the specific forces, discretize it into the state transition matrix, predict the position, velocity and heading error states and their covariance between GNSS fixes, and apply the GNSS position measurement update that drives the estimated error state toward the innovation through the Kalman gain. Produces the error-state matrix, the state transition matrix, the innovation and gain of each fix, the corrected error trajectory, and the gated integrated navigation solution of a level-flight profile. Trigger: ins-gnss-integrated-filter, error-state-filter, loosely-coupled-integration, gnss-position-update, ins-drift-correction, psi-angle-model, state-transition-matrix, horizontal-specific-force.

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Cusum Ewma Monitoring · ashfordeou bundle
Use when you must monitor a production process for small sustained mean shifts: compute the tabular CUSUM path (upper S+ and lower S- statistics from standardized deviations with slack k and decision interval h) and the first signal sample, run the EWMA recursion with per-sample time-varying sigma limits (lambda weighting, L-sigma UCL/LCL) and its first signal sample, and combine both charts into one monitoring verdict that catches small shifts a single-point check misses. Produces the CUSUM and EWMA statistics paths, first-signal indices, per-sample EWMA control limits and the combined verdict. Trigger: cusum-ewma-monitoring, cusum-control-chart, ewma-control-chart, cumulative-sum-monitoring, small-shift-detection, sequential-process-monitoring.

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Axial Compressor Stage · ashfordeou bundle
Use when you must analyze a single axial compressor stage: compute the specific work, the flow coefficient, the work coefficient, the degree of reaction, and the stage pressure ratio 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 compressor stage assessment in the FAR-33 engine design context. Trigger: axial compressor, velocity triangle, degree of reaction, flow coefficient, work coefficient, blade speed, stage pressure ratio, rotor, stator.

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Multi Stage Compressor · ashfordeou bundle
Use when you must design or match a multi-stage axial compressor for a gas turbine: compute the overall pressure ratio as the product of the stage pressure ratios, size the stage count required to reach the target pressure ratio from a design stage pressure ratio, account for the reheat factor that inflates the actual work split, size the annulus area from the mass flow, the axial velocity, and the density, distribute the stage work with equal or rising schemes, and correct the rotor speed to the reference temperature for off-design matching. Produces the stage count, overall pressure ratio, reheat factor, annulus area, and work distribution in SI units that gate the FAR-33 compressor architecture review. Trigger: multi-stage compressor, stage matching, overall pressure ratio, stage count, reheat factor, annulus area, work distribution.

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Entry Descent Landing · ashfordeou bundle
Use when the task is entry corridor, ballistic coefficient, deceleration loads, convective heating, or parachute descent sizing for an entry vehicle. Size the atmospheric entry, descent, and landing phase of a spacecraft mission: check the entry corridor against the flight path angle, compute the ballistic coefficient beta = m / (Cd * A), estimate the peak deceleration g-load of a steep ballistic entry, apply the Sutton-Graves convective heating correlation q_dot = k * sqrt(rho) * V^3 for the stagnation point heat rate and integrate the heat load, and size the parachute descent with the terminal velocity v = sqrt(2 * W / (rho * Cd * S)). Produce the corridor verdict, peak g-load, heat rate and heat load, and terminal velocity for Earth or Mars conditions. Trigger: entry corridor, flight path angle, ballistic coefficient, sutton-graves, convective heating, heat load, deceleration g-load, parachute terminal velocity, mars entry, reentry heating.

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Synodic Launch Window · ashfordeou bundle
Use when you must determine the interplanetary launch-window timing between two planets: compute the synodic period of the launch opportunity recurrence for near-circular coplanar orbits, the heliocentric departure phase angle required for a Hohmann window, the recurrence epochs, and the phase progression between windows. Produces the synodic period, the departure phase angle, the window epochs, and the phase check that gate interplanetary mission window planning. Trigger: synodic period, launch window recurrence, departure phase angle, hohmann window, heliocentric transfer, interplanetary window, opportunity recurrence, synodic-launch-window, earth to mars.

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Bi Elliptic Transfer · ashfordeou bundle
Use when you must analyze the bi-elliptic three-impulse transfer between two coplanar circular orbits and compare it against the Hohmann transfer: compute the three burn delta-v values (the perigee raise to the intermediate apogee radius, the intermediate-apogee burn that raises the perigee to the target radius, and the target circularization), the total bi-elliptic delta-v, the Hohmann delta-v for the same orbit pair as the comparison baseline, the delta-v saving of the cheaper strategy, and the chosen transfer verdict. Produces the three impulse magnitudes, the two transfer totals, the saving, and the strategy verdict that gate an orbit-transfer design choice at large radius ratios. Trigger: bi-elliptic-transfer, three-impulse-transfer, intermediate-apogee, delta-v-saving, orbit-transfer-comparison, bi-elliptic-crossover.

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Three Body Libration · ashfordeou bundle
Use when you must analyze the circular restricted three-body problem (CR3BP) for a spacecraft near two massive primaries: compute the mass ratio from the primary masses, locate the collinear points L1, L2, L3 by solving the rotating-frame force balance with a bracketed Newton iteration, place the triangular points L4 and L5 from the closed-form equilateral construction, convert dimensionless coordinates into physical distances from each primary, and evaluate the Jacobi constant for a planar state. Produces the five libration point locations, the physical distances, and the Jacobi constant that gate a three-body mission assessment. Trigger: three-body-libration, cr3bp, libration-points, lagrange-points-l1-l2, jacobi-constant, earth-moon-l1.

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Communication Link Budget · ashfordeou bundle
Use when you must build or check a spacecraft communications link budget: compute the free space path loss from distance and frequency, derive EIRP from transmit power and antenna gain, estimate received power and carrier to noise density ratio, and verify the link margin against the required energy per bit to noise ratio at the data rate. Produces path loss, EIRP, received power, C/N0, Eb/N0, and the margin verdict that closes the link. Trigger: link budget, path loss, eirp, carrier to noise density, eb n0, link margin, data rate, spacecraft communications.

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Spacecraft Battery Sizing · ashfordeou bundle
Use when you must size the spacecraft battery energy storage for an Earth-orbiting power subsystem: compute the eclipse energy from the eclipse load and the eclipse duration, convert it into the required nameplate capacity with the depth of discharge limit and the discharge efficiency, convert to ampere hours at the bus voltage, lay out the series and parallel Li-ion cell counts for the regulated bus, check the discharge C-rate against the cell limit, and estimate the pack mass from the pack specific energy. Produces the eclipse energy, required capacity, cell layout, installed capacity and mass estimate that gate the spacecraft power sizing. Trigger: spacecraft battery sizing, eclipse energy, depth of discharge, orbit battery capacity, series parallel cell layout, bus voltage cell count, LEO power storage.

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Laminate Progressive Failure · ashfordeou bundle
Use when you must compute the progressive failure of a composite laminate past first-ply failure by the ply-discount method: degrade the stiffness of the failed ply at each ply event, reassemble the in-plane laminate stiffness, reapply the load resultant and march to the last-ply-failure ultimate load. Produces the sequential-ply-failure event loads with the matrix and fiber modes, the degraded laminate stiffness after each event, the first-ply-failure load from the per-ply Tsai-Wu index at unity, the ultimate laminate load and the post-FPF reserve factor of the post-fpf-load-redistribution analysis. Trigger: laminate progressive failure, ply discount method, last ply failure, ultimate laminate load, degraded laminate stiffness, sequential ply failure, progressive failure analysis.

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Emergency Exit Configuration · ashfordeou bundle
Use when you must configure passenger emergency exits against the discrete exit-type rules: look up each exit type's minimum rectangular opening and per-exit seating credit from the constant table, verify that the exits on each side of the fuselage alone cover the passenger capacity, check the capacity-band minimum exit counts and minimum types, apply the two-C-or-larger rule when a type-a, type-b or type-c exit is installed, check the 60-foot adjacent-exit spacing rule on the same side with the implied maximum seat distance to an exit, and compute the aggregate evacuation demand ratio. Produces the per-side capacity sums, the adequacy verdict with the failing-rule list, the required per-side exit set, and the demand ratio that gate the exit configuration. Trigger: emergency-exit-configuration, exit-type-requirements, exit-count-check, exit-placement-rule, per-side-exit-capacity, evacuation-demand-ratio.

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Environmental Control Sizing · ashfordeou bundle
Use when you must size the environmental control system of a transport aircraft: compute the cabin ventilation fresh air flow from the occupant count and per-occupant rate, roll up the cabin heat load from occupants, solar, equipment and skin with a design margin, derive the pack cooling airflow from the heat load and the supply air temperature rise, take the pack airflow as the governing maximum of fresh and cooling flow, and build the cabin pressurization schedule that holds the design cabin pressure altitude until the design differential pressure binds, then clamps at constant differential as the cabin altitude rises. Produces fresh air flow, cabin heat load, pack airflow, cabin differential at cruise and cabin altitude under both regimes. Trigger: environmental control system sizing, ECS, cabin ventilation, fresh air flow, pack cooling airflow, cabin heat load, pressurization schedule, cabin pressure altitude, differential pressure limit.

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Singular Value Decomposition · ashfordeou bundle
Use when you must compute the singular value decomposition of a general real rectangular matrix into its singular value factors: the economy U diag(s) Vh form with orthonormal factors from deterministic one-sided Jacobi rotations, singular values in descending order, the 2-norm condition number, the numerical rank at a relative tolerance and the Moore-Penrose inverse. Pure Python standard library, offline. Produces the SVD factors, the condition assessment and the pseudoinverse that control-allocation leaves consume. Trigger: singular value decomposition, SVD, one-sided Jacobi, singular values, condition number, numerical rank, Moore-Penrose inverse, matrix factorization, rectangular matrix.

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Aileron Reversal · ashfordeou bundle
Use when you must assess the aileron control reversal of a wing from its torsional stiffness: compute the reversal dynamic pressure q_rev = k_t / (C_l_alpha * eta * S * c * e) from the torsional stiffness about the elastic axis, the lift curve slope, the aileron effectiveness factor, the wing area, the mean chord, and the elastic axis to aerodynamic center offset, convert it into the reversal true airspeed with V_rev = sqrt(2 q_rev / rho) at the flight density, evaluate the aileron effectiveness fraction 1 - q / q_rev at the flight dynamic pressure, and check whether the dive speed limit exceeds the reversal speed for the control reversal verdict. Produces the reversal dynamic pressure, the reversal speed, the effectiveness fraction, and the reversed verdict that gate the aeroelastic control assessment. Trigger: aileron reversal, control reversal, reversal speed, torsional stiffness, elastic axis, aileron effectiveness, reversal dynamic pressure.

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Flight Loads Survey · ashfordeou bundle
Use when you must build a flight test loads survey: calibrate strain gauge load stations against applied ground loads, compute the calibration factor and the measured load at each station, and reduce the load factor versus speed survey points (symmetric and rolling maneuvers) to lift coefficient and load factor for comparison with the predicted loads envelope. Produces the strain calibration factor, per-point measured loads, the survey load factor and lift coefficient, and the maneuver point feasibility verdict that gate the loads survey program. Trigger: loads survey, strain gauge calibration, strain gauge, maneuver point, load factor versus speed, wing bending.

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Alpha Beta Filter · ashfordeou bundle
Use when you must design and run an alpha-beta tracking filter for a constant-velocity target in SI units: predict the target position and velocity at the next sample time, form the residual from a noisy position measurement, apply the alpha and beta gain update to track position and velocity, and select the steady-state alpha and beta gains from the smoothing factor and the target maneuverability index. Produces the predicted and updated position and velocity, the residual sequence, and the tracking error metrics that gate a target tracking assessment. Trigger: alpha beta filter, tracking filter, constant velocity target, steady state gains, smoothing factor, maneuverability index, position tracking, velocity tracking.

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Impact Angle Control Guidance · ashfordeou bundle
Use when you must compute the impact-angle-control-guidance command for a planar intercept against a stationary target with a commanded terminal flight path angle: the collision-course nulling baseline from the crossrange offset, the crossrange velocity and the time to go, the terminal crossrange velocity that realizes the commanded impact angle, the impact-angle error between the commanded terminal flight path angle and the current flight path angle, and the impact-angle-error-feedback bias that reshapes the intercept path so the interceptor meets the target at the commanded impact angle. Produces the total lateral acceleration command with its nulling baseline, bias term, time-to-go estimate and impact-angle error. Trigger: impact angle control, terminal impact angle, commanded impact angle, impact angle error feedback, terminal flight path angle constraint, angle-constrained intercept, impact angle guidance, ryoo cho tahk.

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Loop Transfer Recovery · ashfordeou bundle
Use when you must run loop-transfer-recovery on the LQG loop of the two-state plant family: inflate the filter process noise weight q on the driven input channel through Qw(q) = Qw0 + q^2 B B^T, re-solve the filter Riccati equation for the error covariance and the estimator gain at every q, and compare the recovered output loop transfer function with the full-state target loop on a log-spaced frequency grid until the grid-max mismatch M(q) falls at or below the recovery tolerance. Produces the full-state target loop samples, the mismatch-versus-q recovery trace, the recovery gain q* first meeting the tolerance, the recovered filter covariance and estimator gain, and the recovery verdict that gate the loop-shaped LQG design. Trigger: loop-transfer-recovery, LTR, full-state-loop-recovery, lqg-loop-shaping, recovery-gain-tuning, target-feedback-loop.

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Counterfeit Prevention · ashfordeou bundle
Use when you must plan counterfeit parts prevention for an aerospace procurement: score the counterfeit risk from the sourcing and verification controls in place, decide whether reporting is required, and confirm the procurement control set is complete per AS9100 practice. Produces the risk level, the reporting trigger, and the control completeness verdict that gate procurement release. Trigger: counterfeit prevention, counterfeit parts, procurement control, as9100, supply chain, incoming inspection.

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Internal Quality Audit · ashfordeou bundle
Use when you must plan and score an internal quality audit program under an AS9100-style quality management system: compute the audit due date from the last audit date, the base interval and the process risk category, check auditor independence and competence for the assigned audit scope, size the record sample from the lot size and confidence level, and categorize an audit finding by impact severity, containment need and systemic spread. Produces the audit schedule, the auditor assignment verdict, the sample size, the finding classification, and the closure verdict that gate an internal audit program. Trigger: internal-quality-audit, audit-schedule, auditor-independence, audit-sample-size, finding-classification, closure-verification.

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Nonconformance Control · ashfordeou bundle
Use when dispositioning nonconforming parts, running an MRB decision, or checking disposition record completeness for identification, segregation, disposition, disposition authority, and customer notification. Determine and record the disposition of nonconforming aerospace product per AS9100 control of nonconforming output: identify and segregate the part, choose between rework, repair, scrap, use-as-is (derogation), and return to supplier, route repair and use-as-is dispositions through the material review board (MRB), and re-verify reworked characteristics before release. Trigger: nonconforming product, material review board, mrb, disposition, rework, repair, scrap, use as is, segregation, re-verification.

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Hydrazine Monopropellant Thruster · ashfordeou bundle
Use when you must size and assess a hydrazine monopropellant thruster for spacecraft reaction control: compute the catalytic decomposition products and net decomposition heat release of hydrazine at a documented ammonia dissociation fraction, the adiabatic decomposition temperature from the hydrazine decomposition energy balance, and the frozen composition isentropic nozzle expansion of the decomposed gas mixture to the vacuum exhaust velocity, the vacuum specific impulse and the propellant mass flow at the required thrust, with the advisory catalyst-bed temperature band check. Produces the decomposed mixture composition, decomposition temperature, mixture gas constant, isentropic exponent, exhaust velocity, vacuum specific impulse, propellant mass flow and the catalyst-bed band verdict that size a monopropellant RCS thruster. Trigger: hydrazine-monopropellant-thruster, catalytic-decomposition, ammonia-dissociation-fraction, monopropellant-rcs, decomposition-temperature.

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Launch Window Analysis · ashfordeou bundle
Use when you must determine launch windows and launch geometry for orbital missions: compute the launch azimuth for a target inclination from cos(inc) = cos(lat) * sin(az), the daily launch window when the target orbit plane passes through the launch site (window center and half-width from the plane-crossing geometry), sun-synchronous LTAN to RAAN conversion, the plane change delta-v penalty for out-of-plane launches, window duration from the orbit plane regression rate versus Earth rotation, and pass elevation and lighting checks. Produces the azimuth, window open/close times, RAAN, delta-v penalty, and constraint verdicts for the launch. Trigger: launch window, launch azimuth, inclination, sun-synchronous, ltan, raan, plane change, delta-v, orbital plane, direct injection, ksc.

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Mission Delta V Budget · ashfordeou bundle
Use when you must build the spacecraft mission delta-v budget: sum the launch insertion, orbit transfer, plane change, station keeping, and deorbit contributions, apply a margin allocation, and convert the budget into propellant mass with the Tsiolkovsky rocket equation from the dry mass and the specific impulse. Produces the nominal and margined delta-v totals, the required propellant and wet masses, and the budget verdict that closes the propulsion sizing. Trigger: mission delta-v budget, delta-v summation, propellant mass, tsiolkovsky, specific impulse, dry mass, station keeping, deorbit.

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Orbital Perturbations · ashfordeou bundle
Use when you must quantify the J2 secular perturbations of a circular Earth orbit: compute the RAAN drift rate and the argument-of-perigee drift from the mean motion, semimajor axis, and inclination, derive the nodal period change against the Keplerian period, and scale the perturbation magnitude with altitude from LEO to GEO. Produces drift rates in radians per second and degrees per day, the critical inclination, and the oblateness acceleration ratio. Trigger: orbital-perturbations, j2-nodal-regression, raan-drift, argument-of-perigee-drift, secular-drift, nodal-precession, nodal period change, perigee drift.

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Plane Change Maneuver · ashfordeou bundle
Use when you must compute the delta-v of an orbital plane change maneuver and compare the pure inclination change against the combined burn that merges the plane change with an orbit transfer: evaluate the circular-orbit speed at the maneuver radius with sqrt(mu/r), the pure plane change delta-v 2 v sin(di/2), the speed on the elliptic transfer orbit at the maneuver point with the vis-viva equation, and the combined-burn delta-v from the law of cosines when the plane change rides the circularization burn at apogee. Produces the orbit speeds, the pure and combined delta-v values, and the maneuver-selection verdict that gate the orbit maneuver plan. Trigger: plane-change-maneuver, inclination-change-delta-v, combined-burn, orbital-plane-change, apsidal-plane-change, 2-v-sin-half-inclination, inclination-change, orbital-maneuver-plan.

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Honeycomb Core Micromechanics · ashfordeou bundle
Use when you must predict the equivalent mechanical properties of a hexagonal honeycomb core from the cell geometry and the foil material: compute the relative density of the hexagonal cell with double-thickness vertical walls, the core density from the foil density, the stabilized out-of-plane compressive modulus E3 from the foil modulus, the out-of-plane shear moduli G13 and G23 from the foil shear modulus, and the in-plane cell-wall-bending moduli E1, E2 and G12 by the Gibson and Ashby hexagonal-cell closed forms. Produces the equivalent core properties the sandwich panel workflow collects as given inputs; the foil shear modulus derives from the foil modulus and Poisson ratio of the isotropic foil. Cell geometry and foil properties are inputs; no core property tables are reproduced. Trigger: honeycomb core micromechanics, hexagonal honeycomb cell, gibson ashby closed forms, equivalent core properties, out of plane shear modulus, stabilized compressive modulus, relative density.

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Markov Analysis · ashfordeou bundle
Use when you must run a quantitative Markov analysis for an aircraft system safety model per ARP4761A: compute continuous time Markov chain state probabilities from the transition rate matrix, evaluate two-state failure and repair availability with steady state limits, derive the non-repairable failure probability and the mean time to failure, sum series failure rates, and estimate redundant configuration reliability with k-out-of-n combinations. Produces the state probability vector, the availability, and the MTTF that gate the quantitative safety case for the failed state. Trigger: Markov analysis, Markov chain, state probability, transition rate, failure rate, repair rate, availability, MTTF, absorbing state, k-out-of-n.

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Aircraft Oxygen System Sizing · ashfordeou bundle
Use when you must size the aircraft supplemental oxygen system: computing passenger continuous-flow chemical generator demand and unit count, crew diluter-demand gaseous oxygen requirement, converting standard-litre demand volumes to oxygen mass at standard conditions, and sizing crew gaseous oxygen bottle volume from the ideal gas law at the service pressure and storage temperature. Produces the passenger and crew oxygen demands, the generator count, the crew bottle volume and the stored oxygen mass that gate the oxygen system architecture. Trigger: supplemental oxygen sizing, oxygen generator count, oxygen demand mass, oxygen bottle volume, breathing oxygen, diluter-demand, chemical generator, gaseous oxygen.

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Fuel System Weight Estimation · ashfordeou bundle
Use when you must predict the fuel system group weight at the class-II level for the weight statement: evaluate the statistical fuel system weight regression of the transport integral-tank fuel system on the total fuel weight and the tank arrangement, the fixed 80 lb count allowance per tank and engine unit plus the 15 lb volume term scaling with the square root of the tank count and the cube root of the fuel quantity at the published fuel specific weight, and sum the terms into the fuel system group mass. Produces the fuel system group mass in kg for the tanks, sealing, pumps, plumbing and distribution hardware, and its fraction of the total fuel weight for the weight statement and the mass budget rollup. Trigger: fuel system weight estimation, fuel system group weight, fuel system weight regression, class ii fuel system weight buildup, tank group weight estimation.

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Flutter Speed Prediction · ashfordeou bundle
Use when the task is classical wing flutter of the two-DOF typical section, the V-g method, damping crossing, frequency coalescence, or flutter clearance. Compute the classical flutter speed of a two-degree-of-freedom bending-torsion wing section: build the typical section with plunge and pitch about the elastic axis, apply Theodorsen unsteady aerodynamics with the complex lift-deficiency function C(k), run the V-g method across the reduced frequency range, locate the flutter speed where the artificial structural damping g crosses zero, check frequency coalescence near the flutter boundary, and assess the flutter margin against the design dive speed in the FAR 25.629 clearance context. Produces the flutter speed, flutter frequency, reduced frequency, coalescence verdict, and a clearance margin assessment. Trigger: flutter speed, v-g method, bending-torsion flutter, frequency coalescence, typical section, flutter margin, far 25.629.

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Sears Function Gust Lift · ashfordeou bundle
Use when you must compute the frequency-domain gust response of a rigid thin airfoil to a convected sinusoidal vertical gust: evaluate the complex sears-function S(k) from the Bessel series with the Theodorsen lift-deficiency function, the gust gain and the phase lag of the gust load, and the unsteady gust-load amplitude against the quasi-steady 2*pi*rho*V*b*w_g reference, with the |S| = 1 quasi-steady limit at zero reduced frequency, the monotone gain roll-off, and the reduced frequency where the gust load falls to half the quasi-steady value. Produces the complex sears function, gain and phase tables versus reduced frequency, and the unsteady gust-load amplitudes that gate sinusoidal-gust load estimates and unsteady thin-airfoil coursework. Trigger: sears function, sinusoidal gust, gust transfer function, unsteady gust load, gust reduced frequency sweep.

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Rough Wall Skin Friction · ashfordeou bundle
Use when you must estimate the turbulent skin-friction on a rough flat plate: it computes the smooth-wall turbulent baseline Cf from the local Reynolds number, the friction velocity and the sand-roughness reynolds number k+; classifies the k-plus-regime as smooth, transitional or fully rough; evaluates the Schlichting fully-rough-cf correlation for the fetch; and selects the operative coefficient without iteration, the direct fully-rough value or a log-linear blend. Produces the regime class, k+ value, smooth baseline, rough or blended coefficient, operative coefficient with treatment note, and the trip-criterion verdict for roughness and trip-strip sizing on aerodynamic surfaces. Trigger: rough-wall-skin-friction, sand-roughness-height, equivalent-sand-roughness, roughness-reynolds-number, k-plus-regime, fully-rough-cf, trip-criterion, trip-strip-sizing.

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Windtunnel Wall Corrections · ashfordeou bundle
Use when you must apply closed-wall wind tunnel corrections to measured lift and drag coefficients: compute solid blockage from model volume over the test-section volume scale with K1 = 0.52, wake blockage from the uncorrected drag coefficient, total blockage, buoyancy drag increment from the streamwise pressure gradient, lift interference and streamline curvature alpha increment, sigma factor from span over section height, and first-order corrected lift and drag coefficients with corrected q and velocity. Produces corrected coefficients, alpha, q and V for free-air comparison. Trigger: wall corrections, solid blockage, wake blockage, wind tunnel boundary interference, lift interference, buoyancy drag, test section constraint, corrected drag coefficient.

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Aeronautical Data Sources · ashfordeou bundle
Use when you must assess an aeronautical engineering data source before relying on it as the engineering reference in a calculation or report: classify the authoritative data type (atmospheric model, aerodynamic database, materials properties, standard part library, regulatory data), check the publisher, edition, and review status, and score source credibility from regulatory, industry, vendor, or community origin. Produces a source registry entry, an approved or review-required verdict, and a credibility score, then format the citation line with publisher, edition, and access date for the engineering report. Trigger: data source, credibility, revision status, publisher, edition, access date, citation line, source registry.

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Finite Difference Derivatives · ashfordeou bundle
Use when you must compute numerical derivatives of a function or of tabulated data with finite difference formulas: choose between the forward, backward, and central difference stencils, size the step h, compute the second derivative with the centered three point stencil, and differentiate evenly spaced tabulated data with one sided differences at the boundaries. Produces the first and second derivative estimates and the tabulated derivative values that gate the differentiation step. Trigger: finite difference, central difference, forward difference, backward difference, step size, truncation error, second derivative, tabulated data.

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Rank Based Hypothesis Testing · ashfordeou bundle
Use when you must compare two samples without relying on the normality assumption: run the Wilcoxon rank-sum test (Mann-Whitney U) on two independent samples, the Wilcoxon signed-rank test and the sign test on paired measurements, using average ranks for ties, exact rank sums, the normal approximation z with the 0.5 continuity correction toward zero, the two-sided p-value from the standard normal CDF, and the reject or accept verdict at a chosen alpha. Produces the test statistic, z, p-value and verdict that remain valid when the normality assumption of the parametric sibling fails. Trigger: wilcoxon rank sum test, mann-whitney u test, wilcoxon signed rank test, sign test, nonparametric paired comparison, two sample rank test, continuity correction, distribution-free location test.

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Dynamic Stability · ashfordeou bundle
Use when you must evaluate the dynamic stability of an aircraft: compute the longitudinal stability derivatives (pitch stiffness M_alpha, pitch damping M_q, vertical force Z_alpha), estimate the short period and phugoid natural frequency and damping ratio from those derivatives, classify the lateral-directional modes (Dutch roll, roll subsidence, spiral) from the eigenvalues, and check each dynamic stability criterion: the short period damping band, the minimum Dutch roll damping, the spiral time to double, the roll subsidence limit, and the non-divergent phugoid. Produces the mode metrics and the adequate or inadequate verdicts that gate the dynamic stability assessment. Trigger: dynamic stability, short period, phugoid, stability derivatives, classify modes, damping ratio, natural frequency, eigenvalues, time to double, roll subsidence.

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Load Factor Envelope · ashfordeou bundle
Use when you must build the flight test load factor envelope (V-n diagram): compute the stall speed boundary from the wing loading and the maximum lift coefficient, derive the corner point speed at the positive limit load factor, compute the discrete gust line increment in the FAR 25.341 form, and judge the envelope against the placard speed and the transport positive and negative limit load factors. Produces the stall speed boundary, the corner point speed, the gust load factor increment, and the envelope verdict that gate the flight test program. Trigger: V-n diagram, load factor envelope, gust line, corner point, placard speed.

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Glide Flight Test · ashfordeou bundle
Use when you must run a glide flight test at idle thrust to measure the sink rate and the lift to drag ratio of an airplane: derive the sink rate from the altitude loss and the segment time, compute the lift to drag ratio from the true airspeed and the sink rate, correct the results for the weight change, the air density, and the residual idle thrust, and locate the best glide speed. Produces the measured and corrected sink rate in m/s, the lift to drag ratio, and the best glide speed that gate the glide test assessment. Trigger: glide test, sink rate, idle thrust, lift to drag, best glide speed, flight test.

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Flight Test Planning · ashfordeou bundle
Use when you must plan a flight test program: order the test points with the build-up approach so risk increases step by step and every prerequisite is flown before the dependent point, check that the instrumentation covers the required sensors, and confirm the test matrix covers every test objective. Produces the risk-ordered flight sequence with missing prerequisites flagged, the missing instrumentation list with the completeness verdict, the uncovered objectives with the matrix verdict, and the go/no-go gate verdict that releases or blocks the flight. Trigger: build-up approach, test matrix, flight test planning, instrumentation completeness, go/no-go gate, prerequisites.

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Gnss Pseudorange Positioning · ashfordeou bundle
Use when you must compute a GNSS receiver position fix from pseudorange measurements: given satellite positions in ECEF and their pseudoranges (geometric range plus receiver clock bias), solve the four-unknown navigation equations for x, y, z and clock bias with an iterated least-squares adjustment and 4x4 normal equation solves. Produces the converged ECEF position, clock bias, post-fit residuals with RMS, and post-fit position error from the geometry matrix. Requires at least four satellites; treats the Earth as spherical for geodetic conversion only. Trigger: pseudorange positioning, GNSS position fix, receiver clock bias, iterated least squares fix, ECEF position solution, satellite pseudorange residual, snapshot navigation solution.

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Ionospheric Delay Correction · ashfordeou bundle
Use when you must correct the L1 pseudorange for the broadcast ionospheric delay: apply the klobuchar-broadcast-model to the user position and the satellite line of sight, compute the geomagnetic latitude of the ionospheric pierce point from the earth-centred angle and the azimuth, evaluate the amplitude and period quartic polynomials in the broadcast alpha and beta coefficients at that geomagnetic latitude, form the vertical delay from the 5 ns base and the day-curve shape about the 14:00 local-time peak, and map the vertical delay to the slant delay with the elevation obliquity factor. Produces the pierce-point geomagnetic latitude, the amplitude and period coefficients, the vertical delay in seconds and the slant ionospheric delay in seconds and metres that gate the L1 pseudorange correction before positioning. Trigger: klobuchar broadcast model, ionospheric delay correction, slant delay correction, pierce point geometry, broadcast alpha and beta coefficients.

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671 published skills · page 7 of 7