Structural Spar Test Loading Frame
Rigid steel reaction frame with precision cantilever clamp holding a 1.2 m aircraft Z-spar.
Aerospace & Aeronautical Engineering / Wing Spar Unsymmetrical Bending
FREE TO EXPLORELABORATORY 35 · AEROSPACE & AERONAUTICAL ENGINEERING
Unsymmetrical Bending and Principal Axes of Aircraft Wing Spars
Measure strain-gauge bending stresses and lateral deflections u in asymmetric Z-section aircraft wing spars to verify unsymmetrical beam theory and principal axes of inertia. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
LATERAL DEFLECTION U—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with P_y = 3.0 kN.
Adjust P_y, then execute aerospace trial.
Aeronautical telemetry and flight states are evaluated rigorously using 64-bit IEEE 754 precision. Residuals reflect ordinary least-squares regression across successive observations. Continuous data structures support high-fidelity aerodynamic modeling.
Aeronautical assumptions and boundary condition limits
Assumes linear elastic Bernoulli-Euler beam behavior without localized flange shear lag. Linear regression of lateral deflection against vertical load yields a compliance slope of 1.8500 mm/kN with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Aircraft Aluminum Alloy Z-Section Spar (7075-T6)
Extruded thin-walled Z-profile (h = 100 mm, b = 50 mm, t = 3.0 mm) with known section properties.
Precision Hydraulic Loading Actuator & Load Cell
Applies purely vertical downward load P_y at the tip without lateral friction.
2-Axis Optical Linear Dial Gauges (LVDT)
Measures vertical deflection v and lateral deflection u with 0.001 mm resolution.
Multi-Channel Electrical Resistance Strain Gauge Rake
Measures longitudinal strains epsilon_z across upper and lower flanges to verify the neutral axis angle.
Digital Structural DAQ Workstation
Logs load-deflection channels and computes principal moments of inertia (I_u, I_v).
FOLLOW THE METHOD
A reason behind every step.
Measure strain-gauge bending stresses and lateral deflections u in asymmetric Z-section aircraft wing spars to verify unsymmetrical beam theory and principal axes of inertia. Standardized parameter settings: 1.0, 2.0, 3.0, 4.0, 5.0, 6.0 kN.
01
Spar Clamp Rigid Mounting
Mount the Z-section spar into the heavy reaction wall, ensuring 100% fixed-end boundary conditions at the root clamp.
02
Sensor Alignment and Zero Balancing
Align vertical and horizontal LVDTs at the tip loading point (z = L = 1200 mm) and zero all strain gauge channels.
03
Vertical Load Application
Apply initial vertical calibration load P_y = 1.0 kN, recording vertical deflection v and coupled lateral deflection u.
04
Systematic Load Stepping
Increase vertical load through P_y = 2.0, 3.0, 4.0, 5.0, and 6.0 kN, allowing 30 seconds at each step for structural stabilization.
05
Neutral Axis Angle Calculation
Calculate the inclination angle of the neutral axis alpha_na = arctan[(I_xx / I_xy) * (M_y / M_x) - 1] from strain gauge readings.
06
Lateral Compliance Linear Regression
Plot lateral deflection u versus vertical load P_y, perform linear regression to determine compliance m = 1.8500 mm/kN, and verify I_xy.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Wing Spar Unsymmetrical Bending mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
u = \frac{I_{xy} L^3}{3 E (I_{xx} I_{yy} - I_{xy}^2)} \cdot P_y \implies u = m \cdot P_y + b
| # | Vertical Bending Load P_y (kN) | Lateral Deflection u (mm) | Applied Vertical Bending Load P_y (kN) | Lateral Cross-Coupled Deflection u (mm) | Remove |
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