Productivity

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

ashfordeou Bundle

Use when the task is bode analysis, frequency response, gain crossover, phase crossover, gain margin, phase margin, or stability from the margins. Compute the Bode frequency response of an open loop transfer function for flight control design: evaluate the magnitude and phase at a frequency from the numerator and denominator coefficients at s = j*w, find the gain crossover and phase crossover frequencies, derive the gain margin in dB and the phase margin in degrees, and judge closed loop stability from the margins for the canonical type-1 plant K/(s(s+1)(s+2)). Produces the margins and the stability verdict that gate control law iteration. Trigger: bode plot, frequency response, gain margin, phase margin, gain crossover, phase crossover.

ashfordeou Bundle

Use when the task is an eigen-decomposition: spectral analysis, dominant eigenvalue, modal frequencies, covariance or stiffness matrix diagonalization, stability of a linear system, or verifying a pair with the residual A v minus lambda v, and numpy or other numerical libraries are unavailable. Compute eigenvalues and eigenvectors of square matrices with only the Python standard library: the power iteration returns the dominant eigenvalue-eigenvector pair of a general square matrix, deflation exposes the next pairs, and the Jacobi eigenvalue algorithm returns the full spectrum of a real symmetric matrix. Produces the eigenvalue-eigenvector pairs in descending order, unit-norm eigenvectors, and the residual that gates each pair. Trigger: eigenvalue, eigenvector, spectral decomposition, jacobi, power iteration, dominant eigenvalue, deflation, diagonalization, rayleigh quotient.

ashfordeou Bundle

Use when the task is attitude determination from two vector measurements such as a sun sensor and magnetometer pair, coarse attitude estimation for initial acquisition, or computing the attitude quaternion and rotation angle that gate the ADCS attitude reference before fine pointing. Determine the spacecraft attitude matrix from a pair of non-parallel vector observations with the TRIAD algorithm: normalize the measured body frame directions and the matching reference frame directions, build the orthonormal triads from the cross products, assemble the 3 by 3 attitude matrix from the triad outer products, and validate the estimate with the rotation angle, the orthogonality error, and the inter observation angle consistency. Trigger: triad algorithm, attitude determination, vector observation, reference vector, body frame, attitude matrix, coarse attitude, sun sensor, magnetometer.

ashfordeou Bundle

Use when the task is the payload versus range trade-off, max payload, max fuel, design range, ferry range, or reserve fuel sizing in conceptual aircraft design. Build the payload-range diagram for a conceptual transport aircraft: compute the range at the maximum payload point, the range at the maximum fuel point, the ferry range, and the payload available at the design range from operating empty weight, maximum payload, maximum takeoff weight, and fuel capacity using the Breguet range equation with a reserve fuel policy and fuel fraction. Produces the diagram corner points that gate the payload-range trade assessment. Trigger: payload-range diagram, max payload, ferry range, design range, payload range trade, reserve fuel.

ashfordeou Bundle

Use when the task is spin recovery, autorotation, spin modes, incipient spin, flat spin, or post-stall departure recovery. Analyze spin entry, developed spin modes, and recovery controls for a stalled aircraft: compute the post-stall autorotative band and stall penetration, estimate the spin descent rate and rotation rate from weight, wing area, and spin drag, classify the spin mode as steep or flat, and size the altitude lost and rotation stop time during spin-recovery. Trigger: spin recovery, autorotation, flat spin, incipient spin, spin entry, anti-spin controls, post-stall departure.

ashfordeou Bundle

Use when the task is boundary-layer thickness estimation, displacement or momentum thickness, skin-friction coefficient on a surface, Reynolds-number regime classification, or transition location on a smooth surface. Compute laminar and turbulent boundary-layer thicknesses for a smooth flat plate: estimate the 99-percent thickness, displacement thickness, and momentum thickness from the local Reynolds number with the Blasius and 1/7 power-law correlations, evaluate the local and average skin-friction coefficients, and classify the flow into laminar or turbulent regimes by the transition Reynolds number. Trigger: boundary layer, displacement thickness, momentum thickness, skin friction, transition, Reynolds number, Blasius.

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.

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.

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.

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.

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.

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.

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.

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.

mturac Skill

Evidence-first repo execution workflow for ecc. Use when the user wants a command run, a repo checked, a CI failure debugged, or a narrow fix pushed with exact proof of what was executed and verified.

mturac Skill

Convert local Hermes operator workflows into sanitized ecc skills and release-pack artifacts. Use when preparing a Hermes workflow for public ecc reuse without leaking private workspace state, credentials, or local-only paths.

mturac Skill

Suggests manual context compaction at logical intervals to preserve context through task phases rather than arbitrary auto-compaction.

mturac Skill

Operate notifications as one ecc-native workflow across GitHub, Linear, desktop alerts, hooks, and connected communication surfaces. Use when the real problem is alert routing, deduplication, escalation, or inbox collapse.

tuyv Bundle

Ship workflow: detect + merge base branch, run tests, review diff, bump VERSION, update CHANGELOG, commit, push, create PR. (gstack)

tuyv Bundle

This skill should be used when the user invokes /vet to manually surface the current session task and have Claude evaluate whether it is clear and complete.

tuyv Bundle

Use when the user asks to invoke, delegate to, or collaborate with Codex on any task. Also use PROACTIVELY when an independent, non-Claude perspective from Codex would add value — second opinions on code, plans, architecture, or design decisions.

tuyv Bundle

Comet Native workflow. Use when the user explicitly invokes /comet-native, asks to start or resume a Native change, or the entry routes to Native.

tuyv Bundle

This skill should be used when the user invokes /need-vet to enable work verification for the current task. Claude must verify completion and append the verified tag before the session can end.

tuyv Bundle

Comet Classic workflow entry. Use when the user explicitly invokes /comet-classic, asks to start or resume Classic, or resume-probe returns auto_resume for one unambiguously recoverable active Classic change.

ashfordeou Bundle

Use when the task is nacelle geometric sizing, inlet capture and highlight sizing, cowl thickness, wetted area, or nacelle drag bookkeeping for a high bypass turbofan. Size the engine nacelle geometry for a turbofan: derive the fan face area and diameter from the fan mass flow, density, Mach number and temperature; enlarge the fan face to the inlet highlight area with the lip area ratio; compute the free stream capture area and the A0/A1 capture area ratio at the flight Mach number; scale the nacelle length from the fan diameter with a length to diameter ratio; set the cowl maximum thickness from a thickness to chord ratio; estimate the cowl wetted area with a shape factor; and bookkeep the nacelle drag into friction, form and interference components. Trigger: nacelle sizing, inlet highlight, fan face area, capture area ratio, cowl thickness, wetted area, nacelle drag.

ashfordeou Bundle

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