Precision Pilot Model

Represent precision pilot model

  • Library:
  • Aerospace Blockset / Pilot Models

  • Precision Pilot Model block

Description

The Precision Pilot Model block represents the pilot model described in Mathematical Models of Human Pilot Behavior [1]. This pilot model is a single input, single output (SISO) model that represents some aspects of human behavior when controlling aircraft. When modeling human pilot models, use this block for more accuracy than that provided by the Tustin Pilot Model and Crossover Pilot Model blocks.

This block has non-linear behavior. If you want to linearize the block (for example, with one of the linmod functions), you might need to change the Pade approximation order. The Precision Pilot Model block implementation incorporates the Transport Delay block with the Pade order (for linearization) parameter set to 2 by default. To change this value, use the set_param function, for example:

set_param(gcb,'pade','3')

This block is an extension of the Crossover Pilot Model block. It implements the equation described in Algorithms.

Ports

Input

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Signal command that the pilot model controls, specified as a scalar.

Data Types: double

Signal that the pilot model controls, specified as a scalar.

Data Types: double

Output

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Aircraft command, returned as a scalar.

Data Types: double

Parameters

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Aircraft dynamics control. The equalizer form changes according to these values. For more information, see [2]. To help you decide, this table lists the options and associated dynamics.

Option (Controlled Element Transfer Function)Transfer Function of Controlled Element (Yc)Transfer Function of Pilot (Yp)
Proportional

Kc

Lag-lead, TI >> TL
Rate or velocity

Kcs

1
Acceleration

Kcs2

Lead-lag, TL >> TI
Second order

Kcωn2s2+2ζωns+ωn2

Lead-lag if ωm << 2/τ.

Lag-lead if ωm >> 2/τ.

This table defines the variables used in the list of control options.

VariableDescription
K c Aircraft gain.
T I Lag constant.
T L Lead constant.
ζDamping ratio for the aircraft.
ω n Natural frequency of the aircraft.

Programmatic Use

Block Parameter: sw_popup
Type: character vector
Values: 'Proportion' | 'Rate or velocity' | 'Acceleration' | 'Second order'
Default: 'Proportion'

Pilot gain, specified as a double scalar.

Programmatic Use

Block Parameter: Kp
Type: character vector
Values: double scalar
Default: '1'

Total pilot time delay, specified as a double scalar, in seconds. This value typically ranges from 0.1 s to 0.2 s.

Programmatic Use

Block Parameter: time_delay
Type: character vector
Values: double scalar
Default: '0.1'

Equalizer lead constant, specified as a double scalar.

Dependencies

To enable this parameter, set Type of control to Proportional, Acceleration, or Second order.

Programmatic Use

Block Parameter: TL
Type: character vector
Values: double scalar
Default: '1'

Equalizer lag constant, specified as a double scalar.

Dependencies

To enable this parameter, set Type of control to Proportional, Acceleration, or Second order.

Programmatic Use

Block Parameter: TI
Type: character vector
Values: double scalar
Default: '5'

Neuromuscular system lag constant, specified as a double scalar.

Programmatic Use

Block Parameter: TN1
Type: character vector
Values: double scalar
Default: 0.1

Undamped natural frequency of the neuromuscular system, specified as a double scalar, in rad/s.

Programmatic Use

Block Parameter: nat_freq
Type: character vector
Values: double scalar
Default: 20

Damping neuromuscular system, specified as a double scalar.

Programmatic Use

Block Parameter: damp
Type: character vector
Values: double scalar
Default: 0.7

Controlled element undamped natural frequency, specified as a double scalar, in rad/s.

Dependencies

To enable this parameter, set Type of control to Second order.

Programmatic Use

Block Parameter: omega_m
Type: character vector
Values: double scalar
Default: 15

Algorithms

When calculating the model, this block also takes into account the neuromuscular dynamics of the pilot. This block implements the following equation:

Yp=Kpeτs(TLs+1TIs+1))[1(TN1s+1)(s2ωN2+2ζNωNs+1)],

where:

VariableDescription
K p Pilot gain.
τ Pilot delay time.
T L Time lead constant for the equalizer term.
T I Time lag constant.
T N1 Time constant for the neuromuscular system.
ω N Undamped frequency for the neuromuscular system.
ζ N Damping ratio for the neuromuscular system.

A sample value for the natural frequency and the damping ratio of a human is 20 rad/s and 0.7, respectively. The term containing the lead-lag term is the equalizer form. This form changes depending on the characteristics of the controlled system. A consistent behavior of the model can occur at different frequency ranges other than the crossover frequency.

References

[1] McRuer, D. T., Krendel, E., Mathematical Models of Human Pilot Behavior . Advisory Group on Aerospace Research and Development AGARDograph 188, Jan. 1974.

[2] McRuer, D. T., Graham, D., Krendel, E., and Reisener, W., Human Pilot Dynamics in Compensatory Systems . Air Force Flight Dynamics Lab. AFFDL-65-15. 1965.

Extended Capabilities

C/C++ Code Generation
Generate C and C++ code using Simulink® Coder™.

Introduced in R2012b