2-Cell Aircraft Wing Box Test Specimen
Aviation-grade aluminum 2024-T3 wing box (L = 1500 mm, chord = 400 mm, depth = 80 mm) with front, center, and rear webs.
Aerospace & Aeronautical Engineering / Multi-Cell Wing Box Torsion
FREE TO EXPLORELABORATORY 37 · AEROSPACE & AERONAUTICAL ENGINEERING
Torsion and Shear Flow Distribution in Multi-Cell Wing Boxes
Measure shear flow q_1, q_2 in a 2-cell thin-walled aircraft wing box using Bredt-Batho theory and determine torsional stiffness constant J. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
TWIST RATE X 10^3—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with T = 1.5 kN-m.
Adjust T, 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
Bredt-Batho theory assumes constant shear flow along each segment without localized rivet hole stress concentrations. Linear regression of the rate of twist against applied torque yields a compliance slope of 1.1765 mrad/(kN-m^2) corresponding to GJ = 850.0 kN-m^2 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Closed-Loop Torsional Actuator Rig
Applies pure torque T up to 5.0 kN-m via opposing hydraulic cylinders and torque disk.
Twin Rotary Inclinometer Stations
Measures relative cross-sectional rotation theta_1 and theta_2 at two spanwise stations to calculate dtheta/dz.
48-Channel Rosette Strain Gauge Network
Measures shear strains gamma_xy on cell outer skins and interior web to evaluate shear flow q = G*t*gamma.
Laser Alignment Beam Interferometer
Monitors vertical and lateral displacements to ensure zero spurious bending during pure torsion testing.
Structural Analysis Workstation
Solves multi-cell Bredt-Batho compatibility matrix equations and computes torsional stiffness J.
FOLLOW THE METHOD
A reason behind every step.
Measure shear flow q_1, q_2 in a 2-cell thin-walled aircraft wing box using Bredt-Batho theory and determine torsional stiffness constant J. Standardized parameter settings: 0.6, 1.0, 1.5, 2.0, 2.5, 3.0 kN-m.
01
Wing Box Cantilever Root Clamping
Rigidly clamp the root bulkhead into the heavy reaction frame, ensuring zero rotational compliance at z = 0.
02
Torque Disk Calibration
Mount the tip torque loading disk, aligning hydraulic actuators to generate pure couple torque without net shear.
03
Initial Torque Loading
Apply initial torque T = 0.6 kN-m, recording skin shear strains and spanwise rotation angles.
04
Systematic Torque Stepping
Step the torque through T = 1.0, 1.5, 2.0, 2.5, and 3.0 kN-m, allowing 30 seconds at each plateau for strain stabilization.
05
Twist Rate and Shear Flow Extraction
Compute rate of twist dtheta/dz = (theta_tip - theta_mid) / Delta z and extract shear flows q_1 and q_2 from skin rosette strains.
06
Torsional Compliance Linear Regression
Plot (dtheta/dz) x 10^3 versus T, perform linear regression to determine slope 10^3 / (GJ), and compute experimental torsional constant J.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Multi-Cell Wing Box Torsion mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
\left(\frac{d\theta}{dz}\right) \times 10^3 = \left(\frac{10^3}{G J}\right) \cdot T \implies \left(\frac{d\theta}{dz}\right) \times 10^3 = m \cdot T + b
| # | Applied Torsional Torque T (kN-m) | Twist Rate x 10^3 (mrad/m) | Applied Torsional Torque T (kN-m) | Torsional Twist Rate (dtheta/dz) x 10^3 (mrad/m) | Remove |
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