Simple Variable Mass 3DOF (Body Axes)

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

Libraries:
Aerospace Blockset / Equations of Motion / 3DOF

Description

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

Ports

Input

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

Data Types: double

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

Data Types: double

Applied pitching moment, specified as a scalar.

Data Types: double

Rate of change of mass (positive if accreted, negative if ablated), specified as a scalar.

Data Types: double

Gravity, specified as a scalar.

Dependencies

To enable this port, set Gravity source to External.

Data Types: double

Relative velocity 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

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Pitch attitude, within ±pi, returned as a scalar, in radians.

Data Types: double

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

Data Types: double

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

Data Types: double

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

Data Types: double

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

Data Types: double

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

Data Types: double

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

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

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Main

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

UnitsForcesMomentAccelerationVelocityPositionMassInertia
Metric (MKS) NewtonNewton-meterMeters per second squaredMeters per secondMetersKilogramKilogram meter squared
English (Velocity in ft/s) PoundFoot-poundFeet per second squaredFeet per secondFeetSlugSlug foot squared
English (Velocity in kts) PoundFoot-poundFeet per second squaredKnotsFeetSlugSlug 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)

Body or wind axes, specified as Wind or Body

Programmatic Use

 Block Parameter: axes Type: character vector Values: Wind | Body Default: Body

Mass type, specified according to the following table.

Mass TypeDescriptionDefault For
Fixed

Mass is constant throughout the simulation.

Simple Variable

Mass and inertia vary linearly as a function of mass rate.

Custom Variable

Mass and inertia variations are customizable.

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

Programmatic Use

 Block Parameter: v_ini Type: character vector Values: '100' | scalar Default: '100'

Initial pitch attitude of the body, (θ0), specified as a scalar.

Programmatic Use

 Block Parameter: theta_ini Type: character vector Values: '0' | scalar Default: '0'

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

Programmatic Use

 Block Parameter: q_ini Type: character vector Values: '0' | scalar Default: '0'

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 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 of the rigid body, specified as a scalar.

Programmatic Use

 Block Parameter: mass Type: character vector Values: '1.0' | scalar Default: '1.0'

Mass of body when fuel tank is empty, specified as a scalar.

Programmatic Use

 Block Parameter: mass_e Type: character vector Values: '0.5' | scalar Default: '0.5'

Mass of body when fuel tank is full, specified as a scalar.

Programmatic Use

 Block Parameter: mass_f Type: character vector Values: '3.0' | scalar Default: '3.0'

Body inertia when the fuel tank is full, specified as a double scalar.

Programmatic Use

 Block Parameter: Iyy_e Type: character vector Values: '0.5' | scalar Default: '0.5'

Full inertia of the body, specified as a scalar.

Programmatic Use

 Block Parameter: Iyy_f Type: character vector Values: '3.0' | scalar Default: '3.0'

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, 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'

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'

Select this check box to limit the input mass flow rate when one of these is true:

• Fuel tank is full and input mass flow rate is positive.

• Fuel tank is empty and input mass flow rate is negative.

When the input mass flow rate might cause the mass to exceed its limits, the block uses a zero mass flow rate value in the equations of motion. For more information, see Algorithms.

If you do not want to limit the input mass flow rate, clear this check box.

Dependencies

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

Programmatic Use

 Block Parameter: mdot_flag Type: character vector Values: 'off' | 'on' Default: 'on'

Data Types: double

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 AxeAze 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.

• The number of names must match the number of states, as shown for each item, or be empty. Set all or none of the block states.

• To assign names to single-variable states, enter unique names between quotes, for example, 'q' or "q".

• To assign names to two-variable states, enter a comma-separated list surrounded by braces, for example, {'Xe','Ze'}.

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

• 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 of character vectors, or string.

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

Programmatic Use

 Block Parameter: vel_statename Type: character vector Values: '' | comma-separated list surrounded by braces Default: ''

Pitch attitude state name, specified as a character vector or string.

Programmatic Use

 Block Parameter: theta_statename Type: character vector | string Values: '' Default: ''

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: ''

Pitch angular rate state name, specified as a character vector or string.

Programmatic Use

 Block Parameter: q_statename Type: character vector | string Values: '' | scalar Default: ''

Mass state name, specified as a character vector or string.

Programmatic Use

 Block Parameter: mass_statename Type: character vector | string Values: '' | scalar Default: ''

Algorithms

It considers the rotation in the vertical plane of a body-fixed coordinate frame about a flat Earth reference frame.

The equations of motion are

$\begin{array}{l}{A}_{xb}=\stackrel{˙}{u}={A}_{xe}-qw\\ {A}_{zb}=\stackrel{˙}{w}={A}_{ze}+qu\\ {A}_{xe}=\frac{\left({F}_{x}-\stackrel{˙}{m}{u}_{re}\right)}{m}-g\mathrm{sin}\theta \\ {A}_{ze}=\frac{\left({F}_{z}-\stackrel{˙}{m}{w}_{re}\right)}{m}+g\mathrm{cos}\theta \\ {\stackrel{˙}{X}}_{e}=u\mathrm{cos}\theta +w\mathrm{sin}\theta \\ {\stackrel{˙}{Z}}_{e}=-u\mathrm{sin}\theta +w\mathrm{cos}\theta \\ \stackrel{˙}{q}=\frac{{M}_{y}-{\stackrel{˙}{I}}_{yy}q}{{I}_{yy}}\\ \stackrel{˙}{\theta }=q\\ {\stackrel{˙}{I}}_{yy}=\frac{{I}_{yy_full}-{I}_{yy_empty}}{{m}_{full}-{m}_{empty}}\stackrel{˙}{m}\\ {I}_{yy}={I}_{yy_empty}+\left({I}_{yy_full-}{I}_{yy_empty}\right)\frac{m-{m}_{empty}}{{m}_{full}-{m}_{empty}}\end{array}$

where the applied forces are assumed to act at the center of gravity of the body. Input variables are Fx, Fz, My, $\stackrel{˙}{m}$. ure, wre, and g are optional input variables. Mass m is limited to between mempty and mfull. Whenever mass is saturated at empty or full, for consistency, limit $\stackrel{˙}{m}$ within the equations of motion.

Version History

Introduced in R2006a

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