ashfordeOU

@ashfordeou source repo

671 skills
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Plate Buckling · ashfordeou bundle
Use when a wing or fuselage skin panel, spar web or flat panel must be margin-checked against elastic instability in a stdlib-only environment without FEA software. Calculate the elastic buckling of flat plates and skin panels under compression and shear: resolve the plate buckling coefficient k from the edge conditions and the panel aspect ratio (k = 4.0 for a simply supported long plate, 6.97 for a clamped long plate), compute the critical compression buckling stress sigma_cr = k*pi^2*E/(12*(1-nu^2))*(t/b)^2 and the shear buckling stress tau_cr with the shear buckling coefficient k_s, run the combined compression-shear interaction check, and size the effective width of stiffened skin. Units are SI. Trigger: plate buckling, panel buckling, buckling coefficient, shear buckling, skin panel, spar web, critical buckling stress, effective width.

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Truss Analysis · ashfordeou bundle
Use when a truss model must be solved by hand or in a stdlib-only environment without FEA software. Compute the response of a 2D pin-jointed truss with the direct stiffness method: build each element stiffness matrix from E, A, L and orientation, assemble the global stiffness matrix, apply support conditions, solve the nodal displacements by Gaussian elimination, then recover member axial forces and support reactions. Units are SI. Trigger: truss analysis, direct stiffness method, element stiffness matrix, global stiffness matrix, nodal displacements, member forces, reaction forces, Gaussian elimination, pin-jointed, support conditions.

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Mil Std 1553 · ashfordeou bundle
Use when the task is a MIL-STD-1553 command word, status word, data word, Manchester II encoding, bus controller or remote terminal behavior, or military avionics data bus design. Encode and decode MIL-STD-1553B avionics data bus words for the 1 Mbps command/response multiplex bus: build the 20-bit command word from the 5-bit remote terminal address, transmit/receive bit, 5-bit subaddress, and 5-bit word count with odd parity, split a received word back into its fields, classify the message format (BC-to-RT, RT-to-BC, RT-to-RT, broadcast, mode code), and lay out dual redundant bus A/B operation with bus controller and remote terminal message scheduling. Trigger: mil-std-1553, 1553, command-response, remote-terminal, bus controller, dual redundant, Manchester II, mode code, 1 Mbps.

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Ramjet Cycle · ashfordeou bundle
Use when you must analyze the ideal ramjet cycle: compute the flight stagnation temperature from the speed of sound and Mach number, the total temperature ratio across the combustor from the fuel air ratio and lower heating value, the specific thrust from the Mach number and total temperature ratio, the total thrust from the captured mass flow, and the specific impulse and thermal efficiency from the fuel flow. Produces the specific thrust, thrust, specific impulse, and thermal efficiency that gate the airbreathing hypersonic engine assessment. Trigger: ramjet, fuel air ratio, total temperature ratio, specific thrust, specific impulse.

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Ramjet Inlet · ashfordeou bundle
Use when you must analyze the supersonic ramjet inlet: compute the diffuser total pressure recovery at the flight Mach number from the isentropic limit or from the normal shock standing at the cowl lip, convert the freestream stagnation pressure into the diffuser exit total pressure, apply the Kantrowitz starting criterion to the contraction ratio to decide whether the inlet swallows the shock and starts, and report the starting limit Mach number and the maximum startable contraction ratio. Produces the pressure recovery, the exit total pressure, and the start verdict that gate the ramjet intake assessment. Trigger: kantrowitz, supersonic inlet, pressure recovery, diffuser, starting criterion, contraction ratio, normal shock.

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Calculix Linear · ashfordeou bundle
Use when running or checking linear static finite element analysis for aircraft structure with CalculiX (ccx): determine margin of safety from allowables versus FEA stresses, validate unit discipline before post-processing, and check von Mises stress results. The skill covers element-basis stress checks, margin computation, and unit conversion discipline so that allowables and computed stresses are compared in consistent units. Trigger: finite element, fea, calculix, ccx, stress analysis, margin of safety, von mises, unit discipline, static analysis.

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Cfd Validation · ashfordeou bundle
Use when you must validate a computational fluid dynamics result against authoritative reference data: select the validation case for the flow regime and application (NACA 0012 or NACA 4412 airfoil, ONERA M6 transonic wing, DLR-F6 transport wing-body, flat plate boundary layer), compute the relative error, RMS error and max local error, run a Richardson extrapolation grid convergence check, judge pass or fail against tolerance bands, and estimate validation uncertainty. Produces the validation verdict and a validation report skeleton. Trigger: cfd validation, validation case selection, richardson extrapolation, grid convergence, naca 0012 drag, onera m6, dlr f6, error metrics, validation uncertainty, validation report.

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Arinc664 Afdx · ashfordeou bundle
Use when sizing an AFDX network, writing a virtual link configuration table, or reviewing a network design against bandwidth, jitter, and latency budgets for certification. Size and validate ARINC 664 Part 7 Avionics Full-Duplex Switched Ethernet (AFDX) network configurations for civil avionics: compute virtual link bandwidth from the BAG and the maximum frame size, check that the virtual link set fits the 100 Mbps link, bound frame transmission time, verify jitter against the tolerance, estimate end-to-end latency through the switched network, and select the largest legal BAG that still delivers a required bandwidth. Trigger: AFDX, ARINC 664, virtual link, BAG, jitter, end system, avionics network, switched ethernet.

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Airworthiness · ashfordeou bundle
Use when scoping transport-category airworthiness certification: determine the certification basis (FAR-25 for FAA programs, CS-25 for EASA programs), decide whether a system needs the 25.1309 safety assessment from its failure-condition severity, select a means of compliance (analysis, test, inspection, similarity), and sequence a type-certification program from application to issue. The mapped scope is transport-category; other categories must be re-scoped. Trigger: FAR-25, CS-25, airworthiness certification, certification basis, means of compliance, type certification, 25.1309 safety assessment, transport category.

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Nozzle Design · ashfordeou bundle
Use when you must design a rocket engine nozzle from the chamber conditions: compute the exit Mach number for a target area ratio, the choked mass flow through the throat, the exit velocity and the exit static pressure, and the ideal thrust with the pressure term. Produces the nozzle area ratio, exit Mach number, mass flow, exit velocity, and thrust, plus the expansion verdict against the ambient pressure, all in consistent SI units (Pa, K, kg/s, m/s, N). Trigger: nozzle design, area ratio, exit mach, mass flow, ideal thrust, expansion ratio, choked throat.

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Rocket Sizing · ashfordeou bundle
Use when you must size launch-vehicle propulsion with the rocket equation: calculate delta-v from specific impulse and the initial and final masses, derive the mass ratio from a delta-v requirement, compute the propellant mass, and sum the delta-v across the stages of a multistage launch vehicle. Produces the stage delta-v, the mass ratio, and the propellant mass that gate the vehicle sizing. Applies to each stage of the launch vehicle in consistent SI units. Trigger: rocket equation, delta-v, mass ratio, propellant mass, staging, specific impulse.

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Star Tracker · ashfordeou bundle
Use when the task is star identification, boresight and field of view selection, lost in space versus tracking mode, cross-boresight versus roll pointing accuracy, or star tracker update rate. Determine star tracker attitude determination for spacecraft ADCS: identify measured star centroids against an onboard star catalog, compute the angular separation between each measured centroid and its catalog star, and return the best match inside the field of view. The logic normalizes unit vectors, finds the nearest catalog star within the field of view radius, returns the matched star id plus boresight error in arcseconds, and selects lost in space or tracking mode from a prior attitude. Trigger: star identification, star catalog, boresight, field of view, lost in space, tracking mode, angular separation, pointing accuracy, attitude determination.

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

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Miner Damage · ashfordeou bundle
Use when you must evaluate fatigue life with cumulative damage: sum the Palmgren-Miner damage fractions over the load spectrum, check the total against the life limit, and report the percentage of fatigue life consumed. Produces the cumulative damage fraction, the life limit verdict, and the life consumed percentage that gate the fatigue assessment. Trigger: fatigue, cumulative damage, palmgren-miner, load spectrum, fatigue life, damage tolerance.

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Contact Analysis · ashfordeou bundle
Use when the task is FEA contact, penalty or Lagrange methods, contact stiffness, penetration, friction, stick-slip, master-slave contact, node-to-surface, or tied interfaces in bolted joints and bearing contacts. Compute finite element contact analysis quantities for aircraft structure: determine normal contact forces with the penalty method from contact stiffness and penetration, estimate penalty stiffness from the contacting element properties, check Lagrange multiplier enforcement of zero penetration, apply Coulomb friction to categorize stick or slip, and run penetration control until penetration is under tolerance. The skill covers master-slave and node-to-surface gaps, tie constraints, and bolted joint and bearing contacts. Trigger: contact analysis, fea contact, penalty method, lagrange multiplier, contact stiffness, penetration, coulomb friction, stick-slip, master-slave, node-to-surface, tie constraint, bolted joint, bearing contact.

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Cfd Convergence · ashfordeou bundle
Use when you must judge whether a computational fluid dynamics run has converged: check that residuals drop below tolerance and stay monotone, confirm the Courant number respects the scheme stability limit, and compare mesh refinement levels for answer stability. Produces the residual verdict, the CFL check, and the mesh convergence flag that decide whether results can be trusted. Trigger: cfd convergence, residual convergence, courant number, mesh refinement, solver stability.

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Software Testing · ashfordeou bundle
Use when a task asks how many test cases a boolean condition requires, how to derive tests from high-level and low-level requirements, which coverage objectives apply per software level (level A requires mc-dc, B decision coverage, C statement coverage, D and E none), or how to measure and document structural coverage against the DO-178C Table A-7 objectives. Generate requirements-based-testing test cases for DO-178C airborne software and count the test cases each structural-coverage metric demands: statement coverage needs 1 case per statement, decision coverage 2 cases per decision, and mc-dc needs n+1 cases for a compound boolean condition with n independent terms. Trigger: requirements-based-testing, mc-dc test-case-count, structural-coverage measurement, coverage-objectives per level, test case generation.

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Hardware Planning · ashfordeou bundle
Use when you must plan DO-254 design assurance for airborne electronic hardware: classify an item as simple or complex AEH, scope the plan for hardware aspects of certification (PHAC) and the hardware design assurance data, and plan requirements capture, verification, and configuration management for the item. Complex AEH (programmable logic, processors, or designs whose correct behavior cannot be fully established from top-level data alone) follows the full design assurance process; simple AEH uses a reduced but still planned process. Trigger: DO-254 hardware planning, airborne electronic hardware, PHAC, simple vs complex hardware, hardware design assurance, programmable logic.

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Runs Test · ashfordeou bundle
Use when you must run the Wald-Wolfowitz runs test: determining whether the ordering of a two-sign sequence (plus and minus signs, or 1/0 flags recoded as plus and minus) is random by counting the runs of identical signs, computing the expected number of runs and its variance under the randomness null from the two sign counts, forming the standard normal z statistic, and returning the randomness verdict against the two-sided 95 percent normal critical value. Produces the run count, expected runs, variance, standard deviation, z statistic, and the REJECT or FAIL_TO_REJECT randomness verdict. Trigger: runs-test, wald-wolfowitz runs, sequence randomness test, runs count statistic, run length pattern, nonparametric randomness, two sign sequence.

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Mpd Thruster · ashfordeou bundle
Use when you must compute the steady operating point of a magnetoplasmadynamic (self-field electromagnetic) MPD thruster for electric propulsion: electromagnetic thrust from the discharge current squared via the self-field thrust law T = (mu0/(4 pi)) J^2 ln(r_a/r_c) at the anode-to-cathode radius ratio, exhaust velocity and specific impulse from the propellant mass flow, jet kinetic power, and the reference-only thrust-to-power band verdict for the steady-state self-field MPD class. Produces the single-point MPD summary with thrust, exhaust velocity, specific impulse, jet power, thrust-to-power and the class operating-band verdict in one call, bands reported never enforced. Trigger: mpd thruster, magnetoplasmadynamic thruster, self-field electromagnetic arc, discharge current squared thrust law, anode to cathode radius ratio, MPD jet power, thrust-to-power band verdict.

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Rocket Staging · ashfordeou bundle
Use when you must analyze multi-stage rocket staging for a launch vehicle: compute the ideal delta-v per stage from the rocket equation, allocate the stage mass ratios and the payload fraction across the stages, derive the structural index from the inert and the propellant masses, and optimize the stage count for a target total delta-v. Produces the per-stage delta-v, the stage mass ratio, the stage payload fraction, the structural index, the optimal stage split, and the minimum stage count, in SI units. Applies the equal-stage optimum split for identical stages. Trigger: rocket staging, stage mass ratio, payload fraction, structural index, stage count, delta-v.

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Buckling Analysis · ashfordeou bundle
Use when a column, strut, spar cap, landing-gear leg or actuator rod must be sized or margin-checked against elastic instability in a stdlib-only environment without FEA software. Calculate the Euler critical buckling load of slender compression members: apply Pcr = pi^2*E*I/(K*L)^2 for pinned-pinned, fixed-fixed, fixed-pinned and cantilever end conditions, resolve the effective length factor K from the support type, compute the slenderness ratio from the radius of gyration, and run the buckling stress check against the yield-based transition slenderness. Units are SI. Trigger: euler buckling, critical buckling load, slenderness ratio, effective length factor, column buckling, buckling stress, end conditions, radius of gyration, cantilever.

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Pressure Bulkhead · ashfordeou bundle
Use when you must size a fuselage pressure-bulkhead dome: compute the membrane stresses of a spherical cap, a hemisphere, or a 2:1 ellipsoid closing a pressurized cylindrical barrel with membrane theory, including the apex and equator meridional and circumferential stresses of an ellipsoidal dome, the dome margin against ultimate strength under the FAR 25.303 1.5 factor of safety, the spherical-cap rise, and the unbalanced meridional-resultant junction ring load at the dome-barrel interface with the ring area required. Produces the dome stresses, the margin, and the junction ring area that gate the bulkhead design. Trigger: pressure bulkhead, ellipsoidal bulkhead, spherical cap dome, dome margin, junction ring, dome to barrel ring, pressurized fuselage dome, 2:1 ellipsoid.

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Real Time Scheduling · ashfordeou bundle
Use when you must decide the offline schedulability of a periodic hard-real-time task set: compute the processor utilization of (C, T) tasks with implicit deadlines, apply the Liu-Layland utilization bound for rate-monotonic fixed-priority scheduling, run the exact iterative response-time analysis task by task, and test earliest-deadline-first feasibility with the full-utilization condition. Produces the utilization, the RM bound verdict, the exact response times with an RM feasibility verdict, the EDF feasibility verdict, and an overall scheduling verdict for avionics process and partition task sets. Trigger: rate monotonic scheduling, response time analysis, liu layland bound, earliest deadline first, cpu utilization, fixed priority scheduling, schedulability, worst case execution time.

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Orbit Dynamics · ashfordeou bundle
Use when analyzing spacecraft orbital mechanics with two-body and J2-perturbed motion: compute velocities with the vis-viva equation, size Hohmann transfer delta-v and transfer time between coplanar circular orbits, and sanity-check LEO-to-GEO transfer budgets (about 3.9 km/s total delta-v). Flags nodal-regression drift from J2 that exceeds an allowed rate for orbit maintenance planning. Uses Earth gravitational parameter 3.986004418e14 m^3/s^2. Trigger: orbit, orbital mechanics, hohmann transfer, delta-v, vis-viva, orbital elements, j2 perturbation, propagation, transfer time.

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Hall Thruster · ashfordeou bundle
Use when the task is Hall effect thruster (HET) design, sizing, or performance analysis for electric propulsion: thrust from beam current, mass flow and exhaust velocity, specific impulse, thrust-to-power ratio, the total efficiency decomposition (mass, voltage, current and divergence utilization), anode vs total efficiency, discharge power, xenon vs krypton propellant comparison, and propellant mass for a delta-v mission from the rocket equation. Produces the HET performance summary with thrust, mass flow, efficiency terms and a 5 kW class sizing. Trigger: hall thruster, electric propulsion, specific impulse, thrust-to-power, beam current, discharge power, xenon, krypton, propellant mass, delta-v.

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Injector Design · ashfordeou bundle
Use when you must design the rocket engine injection elements and their atomization basis: orifice discharge flow from discharge coefficient and pressure drop, injection velocity, the momentum flux ratio of impinging unlike-doublet elements, the fuel and oxidizer orifice counts for a chamber mass flow at a given mixture ratio, and the per-element flow balance. Produces per-orifice mass flow, injection velocity, momentum flux ratio, fuel and oxidizer orifice counts, and per-element mass flow for the element layout. Trigger: unlike doublet, impinging jet, atomization, injector pressure drop, momentum flux ratio, orifice count, discharge coefficient, injection velocity, mixture ratio.

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Free Turbine · ashfordeou bundle
Use when the task is free-turbine sizing, power-turbine matching, turboprop shaft power, or turboshaft cycle estimates. Size and match a free-turbine turboprop or turboshaft power section: compute the power-turbine exit temperature and shaft power from the gas generator exhaust state (mass flow, inlet temperature, expansion ratio, polytropic efficiency), convert to torque at the power-turbine speed, blade speed from the mean diameter, reduction gearbox ratio to the propeller or rotor, specific fuel consumption, and the flow function that the turbine nozzle must swallow for spool compatibility. Produces the free-turbine matching assessment dict that gates the power section selection. Trigger: free turbine, power turbine, turboprop, turboshaft, gas generator, shaft power, spool matching.

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Calculix Nonlinear · ashfordeou bundle
Use when you must understand or verify a nonlinear finite element static analysis in the CalculiX (ccx) style: solve the equilibrium of a structure whose stiffness depends on its own state, apply Newton-Raphson iteration with load stepping, check convergence against a residual tolerance, and report the convergence verdict. The scalar model is a bar with state-dependent axial stiffness k(u) = k0 * (1 + alpha * u); the solver iterates u_{n+1} = u_n - r(u_n) / kt(u_n) with residual r(u) = k(u)*u - F and tangent stiffness kt = k0 * (1 + 2*alpha*u). Produces the converged displacement, the iteration count, the final residual norm, and the converged or not-converged verdict. Trigger: calculix, ccx, nonlinear fem, newton-raphson, load stepping, convergence tolerance, residual, tangent stiffness, geometric nonlinearity, material nonlinearity.

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Crippling Analysis · ashfordeou bundle
Use when you must compute the local crippling and inter-rivet allowables of a formed compression stiffener (angle, channel, Z, hat stringer, bulb angle): compute the element crippling stress F_cc = min(F_cy, C*sqrt(F_cy*E)*(t/b)**0.75) with the shape constants C = 0.31 for one-edge-free flanges and C = 0.55 for webs between corners, average the element crippling loads over the section area, compute the inter-rivet buckling stress of the attached flat from the rivet pitch, and run the Johnson-Euler interaction that anchors the stiffener column curve on the local crippling stress. Produces the crippling allowable, the inter-rivet allowable, the column interaction allowable, the compression allowable and the margin against the applied stress that gate the local stiffener compression check. Trigger: stringer crippling, local crippling stress, inter-rivet buckling, shape constant method, formed compression shapes.

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Lug Joint Analysis · ashfordeou bundle
Use when you must analyze a metallic pin-loaded lug fitting under an axial load: compute the hole bearing stress, the net section tension stress across the lug width, the tearout shear stress on the two planes from the hole tangent to the round outer contour, the per-mode margins against the material tension, shear and bearing allowables, the governing failure mode and the pass/fail verdict, the limiting allowable capacity, and the governing-mode map over the edge distance ratio for a round-end lug with w = 2e. Produces the applied stresses, per-mode margins, governing mode and margin, pass/fail, capacity, and the short-lug tension, intermediate tearout and long-lug bearing e/D sweep. Trigger: lug joint analysis, pin-loaded lug, lug bearing stress, lug tearout shear, lug net section tension, lug edge distance ratio, round-end lug.

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Restrained Warping · ashfordeou bundle
Use when you must compute the restrained (non-uniform) torsion response of a thin-walled open I-beam section: the warping constant Cw = I_y*h^2/4 of the doubly symmetric I-section, the sectorial coordinate at the flange tip, the decay parameter k = sqrt(G*J/(E*Cw)) of the non-uniform torsion equation E*Cw*theta'''' - G*J*theta'' = 0, the hyperbolic closed-form twist and twist rate, the bimoment B = -E*Cw*theta'' and the warping normal stress sigma_w = B*omega/Cw at the flange tip for a built-in cantilever under a tip torque and a fork-supported beam under a midspan torque, and the shear-torque versus warping-torque split. Produces the section constants, the twist and twist-rate profiles, the bimoment with its root or midspan peak, the flange-tip warping stress and the torque-partition table that gate restrained-torsion checks of open-section spars and stiffeners. Trigger: restrained warping, non-uniform torsion, warping constant, bimoment, torsional flexure, warping normal stress.

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Torsion Shear Flow · ashfordeou bundle
Use when you must compute the torsion shear flow of a closed or open structural section: the polar second moment J for solid and tube shafts, the Saint-Venant torsion constant for thin open rectangles and built-up open sections, the Bredt-Batho closed-section shear flow q = T/(2 A_m), the closed-section twist rate, the shear stress and torsional stress margin, and the multi-cell shear-flow distribution of a two-cell section under an applied torque. Produces the shear flow, twist rate, shear stress and margin that gate torsion checks of fuselage, wing-box and shaft sections. Trigger: torsion shear flow, Bredt-Batho, Saint-Venant torsion, angle of twist, closed-section shear flow, multi-cell section, torsional stress margin, shaft torque, fuselage torsion.

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Tail Sizing · ashfordeou bundle
Use when you must size the empennage with tail volume coefficients: compute the horizontal and vertical tail volume coefficients from the tail areas, the tail arms, and the wing reference area, solve for the required tail area for a target volume coefficient, and judge the result against the typical transport ranges. Covers V_h = S_h * L_h / (S_w * cbar) and V_v = S_v * L_v / (S_w * b), with the tail arm measured from the wing aerodynamic center to the tail quarter chord. Trigger: tail volume coefficient, tail sizing, horizontal tail, vertical tail, empennage, tail arm, stabilizer sizing.

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Tire Sizing · ashfordeou bundle
Use when you must size the tires for an aircraft landing gear at the conceptual level: split the static load per tire from the takeoff weight, the gear load share, and the tire count, compute the tire diameter and width with the power law fit, select the number of tires from the load capacity per tire, set the inflation pressure, and compute the footprint contact area and the rolling radius. Produces the tire dimensions, the required tire count, and the footprint that gate the landing gear configuration. Trigger: tire sizing, tire diameter, tire width, static load per tire, number of tires, inflation pressure, footprint, rolling radius.

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Ws Tw Trade · ashfordeou bundle
Use when you must size the aircraft by matching wing loading and thrust to weight: compute the takeoff distance constraint, climb gradient constraint, and cruise constraint curves, and find the binding constraint that sets the minimum thrust to weight at a given wing loading. Produces the wing loading constraint envelope and the required thrust to weight for the sizing matching chart that gate the conceptual sizing trade. Trigger: wing loading, thrust to weight, matching chart, sizing, takeoff distance, climb gradient, binding constraint.

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Fanno Flow · ashfordeou bundle
Use when you must solve the Fanno flow of a steady adiabatic constant-area duct with wall friction: evaluate the fanno-line integral fL*/D that chokes the duct from a Mach number, compute the friction-duct-choking length from the inlet Mach, recover the downstream Mach number for a given friction parameter fL/D on the subsonic or the supersonic branch, find the friction required to choke a duct of given length, and report the total-pressure loss ratio p0/p0* and the static pressure, temperature and density ratios to the sonic state along the duct. Produces the fL*/D values, choke lengths, downstream Mach numbers, friction to choke and the loss ratios that gate duct sizing and gas-dynamics coursework. Trigger: fanno flow, fanno line, friction duct, choking length, adiabatic duct friction, fL*/D.

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Shock Tube · ashfordeou bundle
Use when you must determine the four-region state of a shock-tube run from the driver-to-driven diaphragm pressure ratio and driver sound-speed ratio: recover the incident-shock Mach number by deterministic bisection of the implicit diaphragm-match equation, then the post-shock pressure, temperature and density ratios with the region-2 absolute state, the contact-surface velocity shared by shocked driven gas and expanded driver gas with the region-2 and region-3 flow Mach numbers, the driver expansion wave ratios with the region-3 absolute state, and the fan head and tail wave speeds. Produces the incident-shock Mach number, the four-region state table and the contact checks that gate shock-tube facility design, driver-gas selection and gas-dynamics coursework. Trigger: shock tube, shock-tube run, diaphragm pressure ratio, contact surface, driver gas, driven gas, incident shock, driver sound-speed ratio, post-shock state, fan head wave, fan tail wave, four-region state table.

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Tool Qualification · ashfordeou bundle
Use when assessing software tool qualification per DO-330 and DO-178C: determine the tool qualification level (TQL-1 through TQL-5) from the applicable tool criteria, check that a qualification level meets the required rigor, select the governing criterion when several apply, and validate that tool operational requirements (TOR) and qualification artifacts are complete. DO-330 tool criteria 1-5 map to TQL-1..TQL-5 with lower numbers meaning stricter rigor; all logic is deterministic, offline stdlib. Trigger: tool qualification, DO-330, TQL, tool criteria, qualification level, tool operational requirements, TOR, tool credit, verification tool.

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Ode Solvers · ashfordeou bundle
Use when a task asks for an ODE solver, differential-equation time marching, an initial-value problem, a decay or response trajectory, or an error-versus-exact comparison. Solve first-order ordinary differential equations numerically with explicit Euler, Heun's method (RK2), and classical RK4: step the initial-value problem forward from y(t0), tabulate the solution, compare it against a closed-form reference, and check step-size convergence of the global error. Produces the solution table, the chosen method, and the max absolute error. Trigger: ode solver, initial value problem, explicit euler, runge kutta, heun method, step size convergence.

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Turbofan Cycle · ashfordeou bundle
Use when you must compute turbofan cycle parameters: calculate the bypass ratio from the fan and core mass flow, the propulsive efficiency from flight and jet velocity, the net thrust from total mass flow and the velocity change, and the specific thrust from net thrust per unit mass flow. Produces the bypass ratio, propulsive efficiency, net thrust, and specific thrust that gate the engine cycle assessment. Trigger: turbofan, bypass ratio, propulsive efficiency, specific thrust, fan mass flow, jet velocity.

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Goodman Diagram · ashfordeou bundle
Use when a fluctuating load case must be checked against a mean-stress fatigue limit or a Haigh diagram / fatigue diagram comparison is needed for a structure. Determine the allowable stress amplitude for infinite life under mean stress: compute the modified Goodman, Gerber, and Soderberg allowable amplitudes from the endurance limit, ultimate strength, and yield strength, plot the Haigh diagram with the design point, and give the infinite-life verdict when the applied amplitude exceeds the allowable. Trigger: goodman, gerber, soderberg, haigh diagram, fatigue diagram, mean stress, endurance limit, allowable amplitude, infinite life, stress ratio.

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Beam Frame Analysis · ashfordeou bundle
Use when you must solve a two-dimensional rigid-jointed frame with the Euler Bernoulli beam element: build the local beam element stiffness from the axial and bending contributions, rotate it into the global frame with the member orientation, assemble the global stiffness matrix, apply the fixed support conditions, solve for the nodal displacements and rotations with a compact elimination solver, and recover the support reactions and the member end actions. Produces the nodal displacement and rotation vector, the support reactions, the member end bending moments and shears, and equilibrium checks for a hand-calc or stdlib-only frame analysis. Units are SI. Trigger: beam frame analysis, rigid jointed frame, Euler Bernoulli beam element, rotation degree of freedom, bending moment recovery, portal frame.

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Shrink Fit Analysis · ashfordeou bundle
Use when you must compute the shrink-fit contact pressure and stresses of a two-cylinder radial-interference assembly: convert the total radial interference into the interface contact pressure from the Lame thick-cylinder radial compliance of both members, recover the bore radial and hoop stresses at the critical bore of each member, form the von-Mises yield margin of each bore against its yield strength, and close with the governing member and the maximum allowable radial interference before that bore yields. Produces the interference-fit contact pressure, the bore radial and hoop stresses of both members, the von-Mises yield margins of both bores, the governing member and the allowable radial interference that gate the shrink-fit design check. Trigger: shrink fit, press fit, interference fit, contact pressure, radial interference, Lame solution, thick cylinder, bore hoop stress, yield margin.

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Creep Rupture · ashfordeou bundle
Use when you must assess the elevated-temperature creep and stress rupture behavior of an aerospace metallic part: compute the steady-state creep strain rate with the Norton power law eps_dot = A * sigma^n * exp(-Q/(R*T)) from the stress and the temperature, estimate the rupture life in hours with the Larson-Miller parameter from the stress-LMP master curve, apply the Monkman-Grant relation between the minimum creep rate and the rupture life, accumulate the creep strain over the service time, and check the time to 1 percent creep strain and the rupture life against the required design life with the margin verdict. Produces the creep rate, the rupture life, the accumulated creep strain, and the governing margin for the hot-section component. Trigger: creep-rupture, norton-creep-law, steady-state-creep-rate, larson-miller-parameter, monkman-grant, rupture-life, stress-rupture, accumulated-creep-strain, time-to-one-percent-creep, elevated-temperature.

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Xfoil Analysis · ashfordeou bundle
Use when running XFOIL-style airfoil analysis for a given section: plan viscous and inviscid polar runs, validate lift and drag coefficient points against physical plausibility bands, and check NACA 0012 results at Reynolds number 6 million against the classic wind-tunnel anchor (lift coefficient about 0.82 at 10 degrees, zero-lift drag about 0.0079). Distinguishes inviscid runs (drag meaningless) from viscous runs and flags high-drag cases needing transition or mesh-density checks. Trigger: xfoil, airfoil, polar, lift coefficient, drag coefficient, naca, viscous analysis, reynolds number, transition.

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Drag Polar · ashfordeou bundle
Use when you must compute the parabolic drag-polar of a wing from the zero-lift-drag coefficient cd0, the Oswald span-efficiency, and the aspect-ratio: calculate the induced-drag factor k with k = 1 / (pi * e * AR), the drag coefficient at a given lift coefficient, the lift-to-drag ratio at a point, and the maximum lift-to-drag ratio with its optimal lift coefficient. Also fit a parabolic drag-polar to two measured lift and drag points to recover cd0 and k. Produces the fitted polar coefficients and the peak performance values that gate the wing aerodynamic efficiency assessment. Trigger: drag-polar, parabolic, Oswald span-efficiency, induced-drag factor, aspect-ratio, cd0, lift-to-drag, max L/D, polar fit.

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Arinc429 Protocol · ashfordeou bundle
Use when checking a bus monitor decode, writing a test stimulus for an LRU interface, or explaining the one-transmitter up-to-20-receivers twisted shielded pair topology. Encode and decode ARINC 429 digital information transfer words for avionics data buses: build the 32-bit word from the octal label, SDI, 19-bit data field, SSM, and odd parity bit, split a received word back into its fields, and convert BNR and BCD parameters to and from engineering units at the word rate of 12.5 or 100 kbps. Trigger: ARINC 429, data word, octal label, SDI, SSM, parity, BNR, BCD, 100 kbps, 12.5 kbps, avionics data bus.

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Lightning Protection · ashfordeou bundle
Use when you must evaluate DO-160 lightning protection for airborne equipment: select the section 22 induced transient susceptibility test level and waveform set, and check the section 23 direct effects pass criteria. Verdict logic classifies whether test results pass with no physical damage, no upset, and no latch-up; level and waveform checks validate inputs before the verdict is issued. Selection and verdict logic only; no standard tables reproduced. Trigger: lightning, DO-160, waveform, test level, transient susceptibility.

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Requirements Capture · ashfordeou bundle
Use when you must capture and review DO-254 hardware requirements for a complex airborne electronic hardware item: check each requirement for vague terms, missing identifiers, and missing trace links, classify derived requirements from allocated ones, and score capture readiness before the requirements review. Produces the requirement issue list, the derived-versus-allocated classification, and the readiness verdict the design phase consumes. Trigger: hardware requirements, requirements capture, derived requirements, traceability, do-254, requirement characteristics.

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Root Finding · ashfordeou bundle
Use when a task asks for a root finder, zero finding, nonlinear equation solving, compressible flow Mach number solution, or implicit performance equation inversion in aerospace analysis. Determine the root of a nonlinear scalar equation f(x) = 0 numerically with the bisection method, Newton-Raphson, the secant method, or fixed-point iteration: bracket the root or supply an initial guess, apply the iteration, and produce the root to a specified tolerance under function tolerance, step tolerance, and max iteration convergence criteria. Produces the root, the method, and the iteration count. Trigger: root-finding, bisection, newton-raphson, secant-method, fixed-point iteration, mach number root, nonlinear equation, zero finding.

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Dual Cycle · ashfordeou bundle
Use when you must compute the operating point of a reciprocating high-speed compression-ignition aircraft powerplant: the air-standard dual-cycle thermal efficiency from the compression ratio, the specific-heat ratio, the pressure ratio of the constant-volume heat-addition phase and the cutoff ratio of the constant-pressure phase, the isentropic compression temperature ratio and state temperatures, the four-stroke indicated and brake power from the indicated mean effective pressure, displacement, crankshaft speed and mechanical efficiency, and the brake specific fuel consumption on Jet-A. Produces the single-point summary dict with the dual-cycle efficiency, heat additions, mean effective pressure, BSFC in both units, thermal efficiencies, volumetric fuel flow and the reference-only compression-ignition band verdict, reported and never enforced. Trigger: dual-cycle, air-standard-dual-cycle, sabathe-cycle, limited-pressure-cycle, mixed-heat-addition, pressure-ratio-of-heat-addition.

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Cold Gas Thruster · ashfordeou bundle
Use when you must size and assess a cold gas thruster for spacecraft reaction control: compute the choked mass flow through the nozzle throat from the plenum pressure and temperature, the thrust from the mass flow and specific impulse, the tank gas mass from the plenum volume and pressure, the isothermal blowdown time constant and pressure history, the operating time to the minimum usable pressure, and the total impulse available over the blowdown. Produces the throat area, mass flow, thrust, tank gas mass, time constant, pressure at a query time, operating time, and total impulse that gate a cold gas RCS sizing. Trigger: cold gas thruster, nitrogen RCS, choked mass flow, plenum blowdown, total impulse, reaction control thruster sizing, isothermal blowdown time constant.

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Beam Column Analysis · ashfordeou bundle
Use when you must margin-check a compression member that also carries bending: compute the Euler load P_E, the moment amplification factor delta that grows the moment as the axial load nears the Euler load, the amplified moment, the secant-formula peak compressive stress of an eccentrically loaded column, and the axial-plus-bending interaction ratio with its margin of safety and pass verdict. Produces P_E, the amplification factor, the amplified moment, the peak combined stress, the interaction ratio, the margin and the verdict for the combined-loading check. SI units, stdlib. Trigger: combined axial compression and bending, moment amplification factor, euler load, secant formula, load eccentricity, margin of safety.

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Curved Beam Analysis · ashfordeou bundle
Use when you must stress-check a curved member with the Winkler curved-beam correction: compute the neutral-axis radius from the closed form A / integral(dA / rho) for a rectangular radial or circular tube section, take the neutral-axis-eccentricity, resolve the Winkler inner and outer fiber stresses, add the axial stress P / A, compare the inner fiber to the straight Euler-Bernoulli reading for the curved-beam amplification, and return the stress-to-allowable ratio with the pass or fail verdict. Produces the neutral-axis radius, neutral-axis-eccentricity, inner and outer fiber stresses, curved-beam amplification over the straight-beam value, and verdict against the allowable. Trigger: winkler curved beam, curved frame segment, torque link arc, clevis arc, curved member stress.

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Ramberg Osgood · ashfordeou bundle
Use when you must build the elastic-plastic stress-strain response of a metallic material with the Ramberg-Osgood three-parameter model: compute the total strain at a given stress with strain = stress/E + 0.002*(stress/sigma_0.2)^n, invert the implicit equation by bisection for the stress at a required total strain, and derive the plastic strain, secant modulus, and tangent modulus along the curve. Produces the stress-strain curve points and stiffness values used in metallic structural analysis beyond the yield point. Trigger: ramberg-osgood, stress-strain-curve, plastic-strain, secant-modulus, tangent-modulus, offset-yield-strength, strain-hardening, elastic-plastic.

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Canard Sizing · ashfordeou bundle
Use when you must size the canard of a canard-configured aircraft: compute the required canard area for a target canard volume coefficient from the canard arm and the wing reference geometry, derive the trim lift share carried by the forward canard from the longitudinal geometry, resolve the canard and wing lift coefficients at the trim condition, and run the stall precedence check that the canard reaches maximum lift before the wing so the nose drops instead of pitching up. Produces the canard area, trim lift share, trim lift coefficients, and the stall precedence verdict. Trigger: canard sizing, canard volume coefficient, canard area, forward wing, stall precedence, canard configuration, trim lift share.

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Engine Sizing · ashfordeou bundle
Use when you must size the propulsion system for the transport aircraft: compute the sea level static thrust from the design thrust to weight ratio and the takeoff gross weight, lapse the thrust to the cruise and top of climb altitude through the ISA density ratio, apply the installed thrust loss for the takeoff thrust, check the thrust margin against the cruise drag, estimate the engine weight from the engine thrust to weight ratio, and split the total thrust across the number of engines. Produces the sea level static thrust, the altitude thrust, the takeoff thrust, the top of climb margin, the fuel flow from the specific fuel consumption, and the thrust per engine that gate the engine selection in the conceptual sizing loop. Trigger: engine sizing, thrust lapse, sea level static thrust, takeoff thrust, top of climb, engine weight, specific fuel consumption.

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V Tail Sizing · ashfordeou bundle
Use when you must size a V-tail empennage from the equivalent horizontal and vertical tail volume requirements: convert each target volume coefficient into its equivalent area, resolve the two areas onto one canted surface pair under the planform-area projection convention, split the total area equally between the two panels, derive the panel span and chord from the surface aspect ratio, size the ruddervator control area as a fraction of the total, and verify the effective volume round trip at the dihedral angle. Produces the equivalent areas, total V-tail area, dihedral angle, per-surface area, span and chord, ruddervator area, and met verdicts. Trigger: v tail sizing, butterfly tail, vee tail, ruddervator, tail dihedral, projected tail area.

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Cfd Mesh Generation · ashfordeou bundle
Use when the task is CFD mesh generation, grid type selection, prism layer setup, near-wall resolution, domain sizing, or cell quality checking for a solver run. Generate a CFD mesh for an aerospace flow case: choose between structured, unstructured, and hybrid grids, size the near-wall first cell height from a y plus target and skin friction coefficient, build boundary-layer prism layers with a growth ratio, flag cell quality with skewness, orthogonality, and aspect ratio checks, size the far-field domain, and plan refinement levels. Produces the grid type recommendation, first cell height, prism layer count, quality verdict, cell count estimate, and refinement plan. Trigger: mesh generation, grid types, prism layers, first cell height, skewness, orthogonality, aspect ratio, domain size, mesh refinement.

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Normal Shock · ashfordeou bundle
Use when you must compute normal shock relations for compressible flow: find the downstream Mach number, static pressure, density, and temperature ratios across the shock, and the stagnation pressure loss from the upstream Mach number. Produces the five shock ratios that gate inlet and high-speed aerodynamic analysis of a supersonic flow. Trigger: normal shock, oblique shock, mach number, compressible flow, pressure ratio, stagnation pressure, supersonic inlet, shock relations.

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Special Conditions · ashfordeou bundle
Use when you must determine whether a novel or unusual transport-category design feature needs a special condition under FAR 25.17 or CS-25.17 instead of being covered by the existing airworthiness standards: classify the feature from its novelty, existing coverage, and safety significance, then draft the special condition scope with the affected subject, the issue addressed, and the proposed means of compliance (analysis, test, simulation). Produces the special-condition verdict and the scoped content for the certification program. Trigger: special condition, novel design feature, fly-by-wire, envelope protection, unusual technology, new technology, means of compliance, FAR 25.17, CS 25.17.

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Interpolation · ashfordeou bundle
Use when you must estimate a value between the tabulated points of an aerospace data table: interpolate linearly between two adjacent data points, perform piecewise linear interpolation over a whole table, build a natural cubic spline through the data points and evaluate it at an intermediate abscissa, extend beyond the table ends with the boundary behavior, and validate that the table is sorted and well formed before the lookup. Produces the interpolated value, the spline coefficients, and the bracketing segment that gate the table lookup step. Trigger: linear interpolation, cubic spline, piecewise linear, table lookup, spline coefficients.

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Skill Delivery · ashfordeou bundle
Use when packaging or delivering domain skills over MCP per SEP-2640: check that a skill package carries a conformant SKILL.md (kebab-case name, description), build the skill URI (skill:// namespace and path), and verify the MCP server exposes the delivery model (resources/read and directory listing behind the directoryRead capability). SEP-2640 serves skills as resources and stays an adapter over the agentskills.io content format, an emerging spec not yet stable. Trigger: SEP-2640, skills over MCP, skill delivery, skill URI, MCP resources, directory read, skill packaging, agentskills.io.

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Gain Scheduling · ashfordeou bundle
Use when you must design and schedule controller gains against dynamic-pressure across nonlinear flight envelope, interpolate gain schedule breakpoint table across Mach-number operating points, and select the scheduling variable (dynamic-pressure, Mach number, angle of attack, or altitude). Choose nearest, linear, or spline interpolation, apply scheduling-variable rate limiting, and distinguish gain scheduling from gain updating. Verify stability between operating points and handle anti-windup interaction when scheduling autopilot and flight control gains across the envelope. Produces the interpolated gain at the current operating point and the rate-limited scheduling variable value. Trigger: gain scheduling, gain-scheduling, scheduling variable, dynamic pressure, Mach number, angle of attack, altitude, breakpoint table, schedule table, interpolation, rate limiting, gain updating, anti-windup, flight envelope.

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Observer Design · ashfordeou bundle
Use when you must design a full-order Luenberger state observer for a linear time-invariant system whose states are not all directly measurable: build the observability matrix and check observability, compute the estimator gain matrix by pole placement with the Ackermann formula so the observer error dynamics eigenvalues sit at the desired locations, verify the error dynamics are Hurwitz stable with the characteristic polynomial, confirm the separation principle so observer poles and controller poles combine by union in the closed loop, and size the convergence with the settling time. Produces the observer gain, the error dynamics matrix and characteristic polynomial, the stability verdict, and the separation check that gate an output feedback design. Trigger: observer design, luenberger, estimator gain, pole placement, separation principle, error dynamics, observability, ackermann, settling time, output feedback.

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Smith Predictor · ashfordeou bundle
Use when you must compensate the dead time of a feedback loop with the smith-predictor structure: given a first-order-plus-dead-time plant model and given PI controller gains, run the delay-free plant model on the controller output, hold the model output in the delay line by the dead time, and subtract the delayed model output from the measured plant output to form the predictor feedback signal, so the primary controller closes on a delay-free compensated error. Produces the compensated error signal of the primary loop, the closed-loop step responses of the predictor-compensated loop, which re-emits the delay-free design response after the dead time, and of the same loop without compensation, and the step-response metrics of both loops: overshoot, settling time to the 2 percent band and final deviation. Trigger: smith predictor, dead time compensation, time delay compensation, transport delay, delay free model prediction, predictor feedback signal.

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Attitude Dynamics · ashfordeou bundle
Use when the task is spacecraft attitude dynamics, rotational kinematics, or momentum management for ADCS dynamics analysis and simulation. Model spacecraft attitude dynamics with the Euler rotational equations of motion: propagate quaternion kinematics from angular velocity, integrate the inertia tensor and applied torques into angular rates, and compute angular momentum, torque-free nutation, gravity-gradient torque, and momentum wheel effects. The stdlib logic is deterministic and offline: quaternion rate and Euler integration steps, body-cone nutation rates, gravity-gradient torque at a given orbital radius, and wheel angular momentum from spin rate. Trigger: quaternion, angular velocity, inertia tensor, nutation, gravity gradient, momentum wheel, euler equations.

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Quality · ashfordeou bundle
Use when scoping or preparing AS9100 aerospace quality management work: map an audit focus area to the aerospace clauses (operational risk, configuration management, product safety, counterfeit prevention, external providers, special processes), assemble the minimum audit evidence for each clause, and determine when a corrective action record closes a nonconformance. AS9100 is ISO 9001:2015 plus aerospace-specific requirements, so audits demonstrate the QMS against both. Trigger: AS9100 audit, quality management system, QMS, aerospace clause, audit evidence, counterfeit prevention, corrective action, nonconformance, special processes.

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Solid Rocket Motor · ashfordeou bundle
Use when the task is solid rocket motor design, grain sizing, or ballistics estimation. Size and analyze solid propellant rocket motors from first ballistics: compute the Vieille burn rate from the pressure exponent, solve the chamber pressure equilibrium between propellant burn rate and choked throat discharge, evaluate grain geometry with web thickness and burn area, and derive mass flow, thrust, and total impulse from the characteristic velocity c*. Uses typical AP/HTPB composite propellant parameters and judges the burn neutrality, regressivity, or progressivity of the grain. Produce the motor ballistics summary with the equilibrium chamber pressure, burn time, thrust, and impulse. Trigger: solid rocket motor, grain geometry, burn rate, chamber pressure, total impulse, characteristic velocity, web thickness.

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Turboprop Cycle · ashfordeou bundle
Use when you must analyze the turboprop powerplant cycle and propeller performance: compute the propeller (Froude) efficiency from the flight velocity and the slipstream velocity, the thrust delivered from the shaft power at the flight speed, the static thrust from the shaft power and the propeller disk area at zero speed, the equivalent shaft power that credits the residual jet thrust, the advance ratio and the power and thrust coefficients at the propeller speed, the specific fuel consumption based on shaft power, and the overall efficiency from the thermal, propeller, and mechanical efficiencies. Produces the turboprop performance dict that gates the powerplant assessment. Trigger: turboprop cycle, propeller efficiency, static thrust, equivalent shaft power, advance ratio, power coefficient, thrust coefficient, slipstream velocity.

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Fire Protection Sizing · ashfordeou bundle
Use when you must size the aircraft fire protection extinguishing agent: fix the protected zone (Class C cargo compartment or powerplant fire zone), take zone free volume and agent concentration by volume, compute total-flooding agent mass and closure check from agent vapor specific volume at discharge temperature, roll up installed agent from bottle and shot count, and set discharge nozzle count from zone coverage. Produces the required agent mass per shot, the installed agent mass, the closure fraction, the nozzle count, and a coverage verdict that gate the layout (FAR 25.851, 25.855, 25.1191 context). Trigger: extinguishing agent mass, total flooding agent, class C cargo compartment, powerplant fire zone, agent bottle sizing, discharge nozzle count.

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Ram Air Turbine Sizing · ashfordeou bundle
Use when you must size the ram air turbine: computing the RAT rotor swept area from the required emergency power at a fixed emergency airspeed with the wind-power relation P = 0.5 rho V^3 A Cp at a fixed design power coefficient, deriving the rotor disk diameter and checking the round-trip available power at that condition. Produces the required swept area, the disk diameter, the available power and margin at that condition, and a fit verdict against the stowage diameter limit for the emergency power extraction installation. Trigger: ram air turbine sizing, rat disk diameter, ram air turbine rotor, rat swept area, emergency power extraction, wind power rotor sizing, emergency descent airspeed, required emergency power.

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Window Aperture Sizing · ashfordeou bundle
Use when you must size a pressurized-cabin passenger window aperture as a flat circular pane: compute the design pressure differential from the ISA pressures at the cabin and flight altitudes with the certification pressure factor applied, compute the clamped-circular-plate bending stress at the pane edge, invert the relation for the required window-pane-thickness, check the pane-margin against the material allowable, and roll up the pane weight over the window count. Produces the design differential, the pane stress, the required thickness, the margin and the weight that gate the window aperture layout. Trigger: window aperture sizing, window pane thickness, pressure differential stress, clamped circular plate, pane margin check, cabin pressure load.

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Supercritical Airfoil · ashfordeou bundle
Use when you must analyze or design a supercritical airfoil for high-speed flight: compute the drag-divergence Mach number from the Korn thickness-lift rule, estimate the terminating shock strength of the upper-surface supersonic pocket, quantify the wave-drag penalty above drag divergence, and size the maximum thickness ratio or cruise lift coefficient that the flat upper surface permits. Produces the drag-divergence Mach, the shock-strength reduction, the wave-drag penalty, and the aft-loading pitching moment that feed high-speed wing design. Trigger: supercritical airfoil, drag divergence Mach, aft loading, flat upper surface, wave drag, shock strength.

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Wing Planform Design · ashfordeou bundle
Use when you must derive the wing-planform-design reference geometry and the spanwise loading of a straight-tapered wing from the span, the area, and the taper-ratio: compute the root-chord and the tip-chord, the mean-geometric-chord, the mean-aerodynamic-chord with its mac-span-station, and convert the leading-edge-sweep into the quarter-chord-sweep. Compute the spanwise-load-distribution with the schrenk-approximation to obtain the local-lift-coefficient at any station, and size the washout-angle so the root reaches stall before the tip, giving the stall-sequencing for a benign stall. Produces the reference chords, the sweep line, and the loading check that feed the lift-curve-slope and vortex-lattice-method leaves. Trigger: wing planform design, taper ratio, mean aerodynamic chord, MAC span station, quarter chord sweep, Schrenk approximation, spanwise load distribution, washout angle.

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Radio Frequency Susceptibility · ashfordeou bundle
Use when you must plan and execute a DO-160 section 20 radio frequency susceptibility (RF immunity) test on airborne equipment: compute the radiated field strength from amplifier power, antenna gain, and distance; size the amplifier power budget for a required field level including cable loss and calibration margin; convert between V/m and dBuV/m, A and dBuA, and W and dBm; estimate the AM-modulated peak field and average power; and check conducted immunity margins against CS114 category current limits. Produces the field strength, the amplifier power budget, and the pass-fail margins that gate RF immunity test planning. Trigger: radio frequency susceptibility, RS103, CS114, radiated immunity, conducted immunity, field strength, RF test, amplifier power.

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Previously Developed Software · ashfordeou bundle
Use when you must scope the reuse credit of previously developed software in a DO-178C project: classify a reused item from its origin standard, its modification state and whether its assurance level meets the target level into unchanged direct credit, modified PDS with delta qualification over the changed scope plus affected interfaces, or level upgrade needing additional verification at the higher level, compute the delta objective coverage ratio and verdict against the required objective set, and bound the regression of modified items from the changed code fraction and touched interfaces. Produces the reuse classification, the credit path, the delta objective gap and verdict, and the bounded regression scope that frame the reuse argument. Trigger: previously developed software, PDS reuse, reuse credit, delta objective coverage, modified software scope, regression scope, direct credit, level upgrade.

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Lateral Navigation · ashfordeou bundle
Use when you must compute the lateral navigation (LNAV) guidance quantities of a flight management system between and along the flight plan legs: derive the great-circle track angle and distance from the current position to the next waypoint, determine the cross-track error to the active leg with its sign, compute the track angle error and the intercept heading that recaptures the desired track at a fixed intercept angle, size the turn anticipation distance before the fly-by waypoint from the speed and bank angle, and judge the along-track distance remaining on the leg. Produces the leg track and distance, the cross-track error, the intercept heading, and the fly-by versus fly-over transition point that gate FMS lateral guidance. Trigger: lateral navigation, lnav, cross-track error, track angle error, great-circle track, turn anticipation, fly-by waypoint, fly-over waypoint, intercept heading, fms lateral guidance.

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Complex Number Algebra · ashfordeou bundle
Use when you must compute complex-number algebra with the Python standard library: form a complex value from rectangular or polar coordinates, add, subtract, multiply and divide complex values, take the conjugate, modulus and argument, raise a complex value to an integer power by De Moivre's formula, generate the n-th roots of unity, and convert between rectangular, polar and Euler exponential forms, verifying identities such as z times its conjugate equals the squared modulus and e to the i pi plus 1 equals 0. Produces the algebra result set that gates phasor, impedance, frequency-response and AC circuit work that needs an explicit complex toolkit. Trigger: complex-number-algebra, complex-arithmetic, polar-form, euler-formula, de-moivre, roots-of-unity, phasor-math, rectangular-form, complex-conjugate.

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Descriptive Statistics · ashfordeou bundle
Use when you must summarize a sample of engineering measurements with descriptive statistics: compute the arithmetic mean, median, data range, sample and population variance and standard deviation, the quartiles and interquartile range by linear interpolation, the five-number summary, the coefficient of variation, and flag outliers with the 1.5-IQR rule. Produces the location, spread, and outlier report that gates a first look at any measured data set; pure Python stdlib, deterministic, no distribution fitting or hypothesis testing. Trigger: descriptive-statistics, summary-statistics, five-number-summary, interquartile-range, coefficient-of-variation, sample-variance, quartiles, outlier flagging.

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Fast Fourier Transform · ashfordeou bundle
Use when you must compute the frequency content of a sampled signal with the discrete Fourier transform or the radix-2 fast Fourier transform: apply the DFT definition for small N, use the Cooley-Tukey decomposition when N is a power of two, extract the magnitude and phase spectrum, and recover the time series with the inverse FFT. Produces the complex spectrum, the magnitude, phase, and power spectra, and the reconstructed signal with Parseval energy checks that gate spectral analysis of sampled time series. Trigger: fast fourier transform, discrete fourier transform, cooley tukey, radix 2, magnitude spectrum, phase spectrum, inverse fft, frequency bin, parseval.

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Power Spectral Density · ashfordeou bundle
Use when you must estimate the power spectral density of a stochastic signal: Welch averaged periodogram estimation with a Hann window, overlapping segments (default 50 percent), and one-sided density scaling in units squared per hertz. Produces the PSD array and its frequency axis, the equivalent noise bandwidth, the integrated total power, and a peak summary for random-vibration and noise surveys of measured acceleration or response time histories. Trigger: power spectral density, welch periodogram, hann window, segment averaged, equivalent noise bandwidth, random vibration survey, g squared per hertz, spectral density estimation.

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Airspeed Conversion · ashfordeou bundle
Use when you must convert airspeeds through the compressibility-corrected air-data chain: calibrated airspeed from impact pressure, calibrated airspeed from true airspeed at altitude, true airspeed from calibrated airspeed at altitude through the compressible inversion on the local static pressure, equivalent airspeed from true airspeed and the density ratio, Mach number from calibrated or true airspeed, and impact pressure from Mach number or calibrated airspeed. Produces the full calibrated, equivalent, true and Mach set plus the impact pressure that gates air-data reduction and performance work. Trigger: calibrated airspeed, equivalent airspeed, true airspeed, mach-airspeed, impact pressure, airspeed-indicator compressibility correction, air-data chain, knots calibrated.

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Turn Performance · ashfordeou bundle
Use when you must compute sustained turn performance for a fixed-wing aircraft: derive the load factor from the bank angle or the bank angle from the load factor, compute the turn rate and turn radius at a given airspeed, and check whether the available thrust sustains the turn against the increased drag. Produces the load factor, bank angle, turn rate, turn radius, and the sustained verdict that gate the maneuvering performance assessment. Trigger: turn rate, turn radius, bank angle, load factor, sustained turn, level turn, maneuvering performance.

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Impact Point Prediction · ashfordeou bundle
Use when a task asks where a round will land, how long the ballistic flight lasts, or how launch speed and flight path angle errors displace the impact point. Compute the ballistic impact point prediction for a projectile from launch position, launch speed, and flight path angle: determine the flat earth vacuum range with the range equation, the time of flight, the impact coordinates from the launch point and heading, and the sensitivity of the landing point to initial condition errors. Trigger: impact point prediction, ballistic trajectory, range equation, time of flight, flight path angle, launch speed, impact coordinates, flat earth.

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Proportional Navigation · ashfordeou bundle
Use when you must compute the proportional navigation guidance command for a planar intercept in SI units: determine the closing velocity from the relative position and velocity vectors, compute the line of sight rate, and calculate the commanded acceleration perpendicular to the line of sight from the navigation constant. Produces range, closing velocity, LOS rate, and the acceleration command that gate an intercept guidance assessment. Trigger: proportional navigation, line of sight rate, closing velocity, navigation constant, intercept guidance, pursuit guidance, terminal guidance, engagement geometry.

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Dilution Of Precision · ashfordeou bundle
Use when you must evaluate GNSS positioning accuracy from satellite geometry: build the geometry matrix H from satellite line-of-sight unit vectors, form the normal matrix H^T H, invert it, and read the dilution of precision values (GDOP, PDOP, HDOP, VDOP, TDOP) off the diagonal. Applies to GPS/GNSS receiver analysis, elevation mask studies, and satellite subset selection. Produces the DOP values, the 1-sigma position error from a user equivalent range error, the elevation mask filter, and the k-satellite subset with the lowest PDOP. Trigger: dilution of precision, gdop, pdop, hdop, vdop, tdop, satellite geometry, elevation mask, uere, gps, gnss, satellite selection.

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Dymos Trajectory · ashfordeou bundle
Use when setting up and assessing pseudospectral trajectory optimization with Dymos: plan optimal-control problems as phases with collocation nodes, check that phase setup includes initial-state and final bounds plus an objective, and verify convergence, state continuity across segments, and total delta-v against expected budgets for ascent or orbit-transfer trajectories. Flags under-resolved phases (fewer than 5 nodes), unconverged runs, and discontinuities at segment boundaries. Trigger: trajectory optimization, optimal control, dymos, pseudospectral, phase, convergence, collocation, launch ascent, bounds.

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Document Control · ashfordeou bundle
Use when you must control aerospace manufacturing documents: maintain the master list of controlled documents, check that a document is approved before issue, confirm that the shop floor copy is at the current revision, and disposition obsolete revisions by removing them from active use while retaining them in the register as history. Produces the register validity verdict, the use verdict for a copy, and the obsolete disposition that gate document control. Trigger: document control, master list, controlled document, current revision, obsolete revision, revision control, approval before issue, doc number.

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Supplier Control · ashfordeou bundle
Use when you must control externally provided processes, products, and services: classify the supplier risk from part criticality and quality and delivery history, derive the required controls (on-site audit, monitoring frequency, delegated verification, flow-down), and check the supplier record for evaluation, approved supplier list, monitoring, re-evaluation, and flow-down completeness before approving the supplier. Produces the risk class, the control set, and the approval verdict that gate purchase release. Trigger: supplier evaluation, approved supplier list, flow down, external provider, supplier monitoring.

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Fai Revalidation · ashfordeou bundle
Use when you must schedule a first article inspection (FAI) revalidation per AS9102 practice: compute the revalidation due date from the last FAI date and the revalidation interval, check whether a process, tooling, drawing revision, location, or supplier change triggers a revalidation, and scope the characteristics to re-verify. Produces the revalidation status, the next revalidation date, and the re-verification scope that gate FAI currency. Trigger: fai revalidation, revalidation due date, last fai date, annual interval, revalidation frequency, change driven revalidation, revalidation scope.

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Computed Tomography · ashfordeou bundle
Use when you must plan and interpret a volumetric X-ray computed tomography (CT) inspection of an aerospace part: compute the geometric magnification and the voxel size from the source, object and detector geometry, check the spatial resolution against the smallest flaw to detect, size the cone beam projection count for the scan, estimate the scan time and the required tube energy for the part material and thickness, convert the measured linear attenuation into CT numbers and classify the material, and measure the porosity volume fraction with the equivalent spherical void diameter from a segmented region of interest. Produces the voxel size, resolution verdict, projection count, scan settings and porosity measurement that gate the CT inspection plan for castings, weldments and additive parts. Trigger: computed tomography, CT scan, voxel size, cone beam, CT number, volumetric inspection, porosity volume fraction, magnification, projection count, additive part porosity.

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Combustor Design · ashfordeou bundle
Use when the task is combustor sizing, burner fuel-air ratio, flame temperature, or heat release for a gas turbine engine. Compute the gas turbine combustor design point: the stoichiometric fuel-air-ratio from the fuel carbon and hydrogen mass fractions, the operating fuel-air-ratio from the fuel and air flows, the equivalence ratio, the combustion efficiency, the heat release from the fuel flow and lower heating value, and the temperature rise across the combustor with the adiabatic flame temperature estimate from a constant-specific-heat energy balance. Produces the fuel flow, heat release, combustor exit temperature, and flame temperature that gate the combustor design assessment. Trigger: combustor design, fuel air ratio, adiabatic flame temperature, combustion efficiency, heat release.

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Nozzle Area Ratio Selection · ashfordeou bundle
Use when you must select the rocket nozzle expansion ratio for a design altitude: solve the inverse isentropic problem for the matched-expansion-ratio whose ideal exit static pressure equals the ambient pressure at the design altitude, using the supersonic-branch area-Mach root and the monotone expansion solve by bisection, and evaluate the sea-level, vacuum and design-altitude delivered isp at the chosen ratio from the ideal rocket relations with the choked mass flow. Produces the design-altitude-expansion-ratio, the matched exit Mach and exit static pressure, the delivered isp triple at the chosen ratio, and the attached-flow-guard decision that the exit static pressure stays above K_SEP times the operating ambient. Trigger: nozzle-area-ratio-selection, design-altitude-expansion-ratio, matched-expansion-ratio, expansion-ratio-selection, attached-flow-guard.

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Radiation Debris · ashfordeou bundle
Use when you must assess the space radiation and orbital debris environment for a spacecraft mission design: estimate the trapped radiation belt (van Allen) dose rate as a function of altitude and inclination with a simplified AE-8/AP-8 style flux band model, add the solar particle event fluence, compute the single-event upset rate with the RPP model from the upset cross-section and LET spectrum, size aluminum shielding against total ionizing dose with exponential attenuation, and estimate the debris collision probability from the flux, cross-section, and mission life. Produces the dose, SEU rate, and debris risk verdicts for the orbit. Trigger: radiation environment, trapped belts, total ionizing dose, single-event effects, seu rate, solar particle events, orbital debris, collision probability.

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Power Thermal Budget · ashfordeou bundle
Use when sizing spacecraft electrical power and thermal budgets per ECSS practice: estimate battery capacity from eclipse power draw, depth of discharge, and efficiency; size the solar array from daylight-only generation; and check power margins against spacecraft bus requirements. The skill covers orbit-period eclipse fractions, battery sizing, solar array sizing, and margin checks for power budgets. Trigger: power budget, thermal budget, eps, eclipse, battery sizing, solar array, spacecraft, orbit period, power margin.

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Composite Bolted Joints · ashfordeou bundle
Use when you must analyze a bolted joint in a composite laminate under bearing and bypass loading: compute the bolt bearing stress from the applied load, bolt diameter, and laminate thickness, the net-tension stress across the net section, the shear-out stress at the edge distance, and the joint margin against each allowable. Produces the applied stresses, the governing failure mode, the pass or fail verdict, and the margins for the fastener row with the bypass load share. Trigger: bolted joint, bearing stress, bypass loading, net-tension, shear-out, bolt diameter, edge distance, fastener, joint margin, composite laminate joint.

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Laminate Plate Buckling · ashfordeou bundle
Use when you must compute the elastic buckling load of an orthotropic or laminated flat plate: evaluate the energy-method critical load N_x_cr(m, n) per unit width for integer half-wave counts m and n from the classical lamination theory bending stiffnesses D11, D22, D12 and D66, minimize over the mode counts, and return the critical load, the governing buckling mode and the stability margin against the applied in-plane compression load. Produces the critical load, the buckling mode and the margin that gate composite panel stability checks. Trigger: laminate-plate-buckling, laminate-buckling, orthotropic-plate-buckling, d-matrix, buckling-mode-minimization, composite-panel-stability, compression-buckling.

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Residual Strength · ashfordeou bundle
Use when you must compute the residual strength of a cracked structure for a damage tolerance assessment: derive the residual strength from fracture toughness and crack length, find the critical crack length at which the applied stress reaches Kc, and evaluate the margin of the residual strength against the limit load. Produces the residual strength, the critical crack length, and the limit-load margin verdict that size inspection intervals and repair decisions. Trigger: residual strength, critical crack, fracture toughness, limit load, stress intensity, damage tolerance.

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671 published skills · page 5 of 7