Simple Variable Mass 3DOF (Wind Axes)

Implement three-degrees-of-freedom equations of motion of simple variable mass with respect to wind axes

• Library:

• Aerospace Blockset / Equations of Motion / 3DOF

• 

Description

The Simple Variable Mass 3DOF (Wind Axes) block implements three-degrees-of-freedom equations of motion of simple variable mass with respect to wind axes. The block considers the rotation in the vertical plane of a wind-fixed coordinate frame about a flat Earth reference frame. For more information about the rotation and equations of motion, see Algorithms.

Ports

Input

Fx — Applied force along x-axis

scalar

Applied force along the body x-axis, specified as a scalar, in the units selected in Units.

Data Types: double

Fz — Applied force along z-axis

scalar

Applied force along the body z-axis, specified as a scalar.

Data Types: double

M — Applied pitch moment

scalar

Applied pitch moment, specified as a scalar.

Data Types: double

dm/dt — Rates of change of mass

scalar

One or more rates of change of mass (positive if accreted, negative if ablated), specified as a scalar.

Data Types: double

g — Gravity

scalar

Gravity, specified as a scalar.

Dependencies

To enable this port, set Gravity source to External.

Data Types: double

Vre — Relative velocities

two-element vector

Sum of one or more relative velocities at which mass is accreted to or ablated from the body in body-fixed axes, specified as a two-element vector.

Dependencies

To enable this port, select Include mass flow relative velocity.

Data Types: double

Output

γ — Flight path angle

scalar

Flight path angle, within ±pi, returned as a scalar, in radians.

Data Types: double

ωy (rad/s) — Pitch angular rate

scalar

Pitch angular rate, specified as a scalar, in radians per second.

Data Types: double

dωy/dt — Pitch angular acceleration

scalar

Pitch angular acceleration, returned as a scalar, in radians per second squared.

Data Types: double

XeZe — Location of body

two-element vector

Location of the body in the flat Earth reference frame, (Xe, Ze), returned as a two-element vector.

Data Types: double

Vw — Velocity in wind-fixed frame

two-element vector

Velocity of the body resolved into the wind-fixed coordinate frame, (V, 0), returned as a two-element vector.

Data Types: double

AxbAzb — Acceleration of body

two-element vector

Acceleration of the body with respect to the body-fixed coordinate frame, (Ax, Az), returned as a two-element vector.

Data Types: double

α — Angle of attack

scalar

Angle of attack, returned as a scalar, in radians.

Data Types: double

Fuel — Fuel tank status

scalar

Fuel tank status, returned as:

• 1 — Tank is full.

• 0 — Tank is neither full nor empty.

• -1 — Tank is empty.

Dependencies

To enable this port, set Mass type to Simple Variable.

Data Types: double

AxeAze — Acceleration of body

two-element vector

Accelerations of the body with respect to the inertial (flat Earth) coordinate frame, returned as a two-element vector. You typically connect this signal to the accelerometer.

Dependencies

To enable this port, select the Include inertial acceleration check box.

Data Types: double

Parameters

Main

Units — Input and output units

Metric (MKS) (default) | English (Velocity in ft/s) | English (Velocity in kts)

Input and output units, specified as Metric (MKS), English (Velocity in ft/s), or English (Velocity in kts).

Units	Forces	Moment	Acceleration	Velocity	Position	Mass	Inertia
Metric (MKS)	Newton	Newton-meter	Meters per second squared	Meters per second	Meters	Kilogram	Kilogram meter squared
English (Velocity in ft/s)	Pound	Foot-pound	Feet per second squared	Feet per second	Feet	Slug	Slug foot squared
English (Velocity in kts)	Pound	Foot-pound	Feet per second squared	Knots	Feet	Slug	Slug foot squared

Programmatic Use

Block Parameter: units

Type: character vector

Values: Metric (MKS) | English (Velocity in ft/s) | English (Velocity in kts)

Default: Metric (MKS)

Mass type — Mass type

Simple Variable (default) | Fixed | Custom Variable

Mass type, specified according to the following table.

Mass Type	Description	Default For
Fixed	Mass is constant throughout the simulation.	3DOF (Body Axes) 3DOF (Wind Axes)
Simple Variable	Mass and inertia vary linearly as a function of mass rate.	Simple Variable Mass 3DOF (Body Axes) Simple Variable Mass 3DOF (Wind Axes)
Custom Variable	Mass and inertia variations are customizable.	Custom Variable Mass 3DOF (Body Axes) Custom Variable Mass 3DOF (Wind Axes)

The Simple Variable selection conforms to the equations of motion described in Algorithms.

Programmatic Use

Block Parameter: mtype

Type: character vector

Values: Fixed | Simple Variable | Custom Variable

Default: 'Simple Variable'

Initial airspeed — Initial speed

100 (default) | scalar

Initial speed of the body, (V₀), specified as a scalar.

Programmatic Use

Block Parameter: V_ini

Type: character vector

Values: '100' | scalar

Default: '100'

Initial incidence — Initial angle

0 (default) | scalar

Initial angle between the velocity vector and the body, (α₀), specified as a scalar.

Programmatic Use

Block Parameter: alpha_ini

Type: character vector

Values: '0' | scalar

Default: '0'

Initial flight path angle — Initial flight path angle

0 (default) | scalar

Initial flight path angle of the body, (γ₀), specified as a scalar.

Programmatic Use

Block Parameter: gamma_ini

Type: character vector

Values: '0' | scalar

Default: '0'

Initial body rotation rate — Initial pitch rotation rate

0 (default) | scalar

Initial pitch rotation rate, (q₀), specified as a scalar.

Programmatic Use

Block Parameter: q_ini

Type: character vector

Values: '0' | scalar

Default: '0'

Initial position (x,z) — Initial location

[0 0] (default) | two-element vector

Initial location of the body in the flat Earth reference frame, specified as a two-element vector.

Programmatic Use

Block Parameter: pos_ini

Type: character vector

Values: '[0 0]' | two-element vector

Default: '[0 0]'

Initial mass — Initial mass

1.0 (default) | scalar

Initial mass of the rigid body, specified as a scalar.

Programmatic Use

Block Parameter: mass

Type: character vector

Values: '1.0' | scalar

Default: '1.0'

Empty mass — Empty mass

0.5 (default) | scalar

Empty mass of the body, specified as a double scalar.

Programmatic Use

Block Parameter: mass_e

Type: character vector

Values: '0.5' | scalar

Default: '0.5'

Full mass — Full mass of body

3.0 (default) | scalar

Full mass of the body, specified as a scalar.

Programmatic Use

Block Parameter: mass_f

Type: character vector

Values: '3.0' | scalar

Default: '3.0'

Empty inertia body axes — Empty inertia of body

0.5 (default) | scalar

Empty inertia of the body, specified as a double scalar.

Dependencies

To enable this parameter, set Mass type to Simple Variable.

Programmatic Use

Block Parameter: Iyy_e

Type: character vector

Values: '1.0' | scalar

Default: '1.0'

Full inertia body axes — Full inertia body axes

3.0 (default) | scalar

Full inertia of the body, specified as a scalar.

Dependencies

To enable this parameter, set Mass type to Simple Variable.

Programmatic Use

Block Parameter: Iyy_f

Type: character vector

Values: '3.0' | scalar

Default: '3.0'

Gravity Source — Gravity source

Internal (default) | External

Gravity source, specified as:

External	Variable gravity input to block
Internal	Constant gravity specified in mask

Programmatic Use

Block Parameter: g_in

Type: character vector

Values: 'Internal' | 'External'

Default: 'Internal'

Acceleration due to gravity — Gravity source

9.81 (default) | scalar

Acceleration due to gravity, specified as a double scalar and used if internal gravity source is selected. If gravity is to be neglected in the simulation, this value can be set to 0.

Dependencies

• To enable this parameter, set Gravity Source to Internal.

Programmatic Use

Block Parameter: g

Type: character vector

Values: '9.81' | scalar

Default: '9.81'

Include mass flow relative velocity — Mass flow relative velocity port

off (default) | on

Select this check box to add a mass flow relative velocity port. This is the relative velocity at which the mass is accreted or ablated.

Programmatic Use

Block Parameter: vre_flag

Type: character vector

Values: off | on

Default: 'off'

Include inertial acceleration — Include inertial acceleration port

off (default) | on

Select this check box to add an inertial acceleration in flat Earth frame output port. You typically connect this signal to the accelerometer.

Dependencies

To enable the A_xeA_ze port, select this parameter.

Programmatic Use

Block Parameter: abi_flag

Type: character vector

Values: 'off' | 'on'

Default: 'off'

State Attributes

Assign a unique name to each state. You can use state names instead of block paths during linearization.

• To assign a name to a single state, enter a unique name between quotes, for example, 'velocity'.

• To assign names to multiple states, enter a comma-separated list surrounded by braces, for example, {'a', 'b', 'c'}. Each name must be unique.

• If a parameter is empty (' '), no name is assigned.

• The state names apply only to the selected block with the name parameter.

• The number of states must divide evenly among the number of state names.

• You can specify fewer names than states, but you cannot specify more names than states.

  For example, you can specify two names in a system with four states. The first name applies to the first two states and the second name to the last two states.

• To assign state names with a variable in the MATLAB^® workspace, enter the variable without quotes. A variable can be a character vector, cell array, or structure.

Velocity: e.g., 'V' — Velocity state name

'' (default) | character vector

Velocity state name, specified as a character vector.

Programmatic Use

Block Parameter: V_statename

Type: character vector

Values: '' | scalar

Default: ''

Incidence angle e.g., 'alpha' — Incidence angle state name

'' (default) | scalar

Incidence angle state name, specified as a scalar.

Programmatic Use

Block Parameter: alpha_statename

Type: character vector

Values: '' | scalar

Default: ''

Flight path angle: e.g., 'gamma' — Flight path angle state name

'' (default) | character vector

Flight path angle state name, specified as a character vector.

Programmatic Use

Block Parameter: gamma_statename

Type: character vector

Values: '' | scalar

Default: ''

Body rotation rate: e.g., 'q' — Body rotation state name

'' (default) | scalar

Body rotation rate state names, specified as a character vector.

Programmatic Use

Block Parameter: q_statename

Type: character vector

Values: '' | scalar

Default: ''

Position: e.g., {'Xe', 'Ze'} — Position state name

'' (default) | comma-separated list surrounded by braces

Position state names, specified as a comma-separated list surrounded by braces.

Programmatic Use

Block Parameter: pos_statename

Type: character vector

Values: '' | comma-separated list surrounded by braces

Default: ''

Mass: e.g., 'mass' — Mass state name

'' (default) | character vector

Mass state name, specified as a character vector.

Programmatic Use

Block Parameter: mass_statename

Type: character vector

Values: '' | scalar

Default: ''

Algorithms

The block considers the rotation in the vertical plane of a wind-fixed coordinate frame about a flat Earth reference frame.

The equations of motion are

$$\begin{array}{l}\dot{V}=\frac{F_{x_{wind}}}{m}-\frac{\dot{m}Vr{e}_{x_{wind}}}{m}-g\sin \gamma \\ A_{be}=\left[\begin{array}{c}{A}_{xe}\\ A_{ze}\end{array}\right]=DC{M}_{wb}\left[\frac{F_w-\dot{m}{V}_{re}}{m}-g\right]\\ A_{bb}=\left[\begin{array}{c}{A}_{xb}\\ A_{zb}\end{array}\right]=DC{M}_{wb}\left[\frac{F_w-\dot{m}{V}_{re}}{m}-g-{\omega }_w\times {\overline{V}}_w\right]\\ \dot{\alpha }=\frac{F_{z_{wind}}}{mV}+q+\frac{g}{V}\cos \gamma -\frac{\dot{m}Vr{e}_{z_{wind}}}{mV}\\ \dot{q}=\dot{\theta }=\frac{M_{y_{body}}-{\dot{I}}_{yy}q}{I_{yy}}\\ \dot{\gamma }=q-\dot{\alpha }\\ {\dot{I}}_{yy}=\frac{I_{yyfull}-I_{yyempty}}{m_{full}-m_{empty}}\dot{m}\end{array}$$

where the applied forces are assumed to act at the center of gravity of the body. Vre_w is the relative velocity in the wind axes at which the mass flow ($$\dot{m}$$) is ejected or added to the wind axes.

References

[1] Stevens, Brian, and Frank Lewis. Aircraft Control and Simulation. Hoboken, NJ: John Wiley & Sons, 1992.

Extended Capabilities

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