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Engineering casebook

Case 02 / Flight dynamics

Aircraft trim and linearization

Find a steady-flight operating point, derive a local linear model and compare its response with the nonlinear aircraft simulation.

MATLAB trim solution · matched linear / nonlinear responses
Flight dynamicsControl systemsMATLAB/Simulink
The engineering question

What does a steady flight condition look like, and how accurately does a linear model describe nearby motion?

I solved for steady, level flight in a nonlinear aircraft model, calculated numerical state and input Jacobians, and compared linear and nonlinear responses to identical elevator and aileron pulses. Small and larger inputs show how the approximation changes as the aircraft moves away from the trim condition.

Inside the method

Method and workflow

  1. 01

    Choose a flight condition

    Set 120 m/s and 3,000 m altitude, with body velocities and attitude consistent with level flight.

  2. 02

    Solve the equilibrium

    Search elevator, throttle and pitch until the longitudinal acceleration and pitch-acceleration residuals approach zero.

  3. 03

    Build A and B

    Use central finite differences about the same equilibrium. Separate longitudinal and lateral modes.

  4. 04

    Check the approximation

    Apply matched control pulses and compare nonlinear and linear motion, including where the local approximation starts to diverge.

Equilibrium → local model

Trim first. Then perturb.

Download A, B & trim ↗
Airspeed120 m/s
Altitude3,000 m
Pitch / angle of attack0.925°
Elevator0.234°
Throttle32.87%
Longitudinal modes
-4-3-2-10Real (s⁻¹)Imaginary (s⁻¹)-202-2.8153 + 1.3079i-2.8153 − 1.3079i-0.0187 + 0.0927i-0.0187 − 0.0927i

Calculated about this trim point. The pole locations describe the local model.

Lateral-directional modes
-4-3-2-10Real (s⁻¹)Imaginary (s⁻¹)-202-0.2702 + 1.9149i-0.2702 − 1.9149i-0.0826 + 0.0000i-3.5218 + 0.0000i

Calculated about this trim point. The pole locations describe the local model.

Dynamics residual norm: 1.09e-11 for the trim equations. This is a numerical equilibrium check, not a measure of real-aircraft model accuracy.

Explore the result

Same run. Every view.

Loading the numerical recording…
Project figures / 3 selected figures

Related flight-control analysis

01 / 03
Flight-control analysis / 01
Flight-control analysis / 01
Flight-control analysis / 01

Pitch-feedback and pitch-hold analysis from a separate aircraft-control model. The trim comparison uses the nonlinear model described above.

Open full-size image ↗
Technical notes

Model assumptions and scope

  • The analysis uses a representative aircraft parameter set. The displayed geometry illustrates the recorded motion.
  • The angle-of-attack-rate contribution is held at zero in both models.
  • The comparison uses open-loop control pulses around a single trimmed operating point.
Potential extensions

Repeat the comparison over a speed/altitude grid, then build and verify gain-scheduled control loops.

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