Simple Variable Mass 6DOF (Euler Angles)

Implement Euler angle representation of six-degrees-of-freedom equations of motion of simple variable mass

Libraries:
Aerospace Blockset / Equations of Motion / 6DOF

Description

The Simple Variable Mass 6DOF (Euler Angles) block considers the rotation of a body-fixed coordinate frame (X_b, Y_b, Z_b) about a flat Earth reference frame (X_e, Y_e, Z_e).

For a description of the coordinate system and the translational dynamics, see the description for the Simple Variable Mass 6DOF (Euler Angles) block. For more information on the body-fixed coordinate frame, see Algorithms.

Limitations

The block assumes that the applied forces are acting at the center of gravity of the body.

Ports

Input

expand all

F_xyz — Applied forces
three-element vector

Applied forces, specified as a three-element vector.

Data Types: double

M_xyz(N-m) — Applied moments
three-element vector

Applied moments, specified as a three-element vector.

Data Types: double

dm/dt (kg/s) — Rate 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

V_re — Relative velocity
three-element vector

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

Dependencies

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

Data Types: double

Output

expand all

V_e — Velocity in flat Earth reference frame
three-element vector

Velocity in the flat Earth reference frame, returned as a three-element vector.

Data Types: double

X_e — Position in flat Earth reference frame
three-element vector

Position in the flat Earth reference frame, returned as a three-element vector.

Data Types: double

φ θ ψ (rad) — Euler rotation angles
three-element vector

Euler rotation angles [roll, pitch, yaw], returned as three-element vector, in radians.

Data Types: double

DCM_be — Coordinate transformation
3-by-3 matrix

Coordinate transformation from flat Earth axes to body-fixed axes, returned as a 3-by-3 matrix.

Data Types: double

V_b — Velocity in body-fixed frame
three-element vector

Velocity in body-fixed frame, returned as a three-element vector.

Data Types: double

ω_b (rad/s) — Angular rates in body-fixed axes
three-element vector

Angular rates in body-fixed axes, returned as a three-element vector, in radians per second.

Data Types: double

dω_b/dt — Angular accelerations
three-element vector

Angular accelerations in body-fixed axes, returned as a three-element vector, in radians per second squared.

Data Types: double

A_bb — Accelerations in body-fixed axes
three-element vector

Accelerations in body-fixed axes with respect to body frame, returned as a three-element vector.

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.

Data Types: double

A_be — Accelerations with respect to inertial frame
three-element vector

Accelerations in body-fixed axes with respect to inertial frame (flat Earth), returned as a three-element vector. You typically connect this signal to the accelerometer.

Dependencies

This port appears only when the Include inertial acceleration check box is selected.

Data Types: double

Parameters

expand all

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.	6DOF (Euler Angles) 6DOF (Quaternion) 6DOF Wind (Wind Angles) 6DOF Wind (Quaternion) 6DOF ECEF (Quaternion)
`Simple Variable`	Mass and inertia vary linearly as a function of mass rate.	Simple Variable Mass 6DOF (Euler Angles) Simple Variable Mass 6DOF (Quaternion) Simple Variable Mass 6DOF Wind (Wind Angles) Simple Variable Mass 6DOF Wind (Quaternion) Simple Variable Mass 6DOF ECEF (Quaternion)
`Custom Variable`	Mass and inertia variations are customizable.	Custom Variable Mass 6DOF (Euler Angles) Custom Variable Mass 6DOF (Quaternion) Custom Variable Mass 6DOF Wind (Wind Angles) Custom Variable Mass 6DOF Wind (Quaternion) Custom Variable Mass 6DOF ECEF (Quaternion)

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

Programmatic Use

Block Parameter: mtype

Type: character vector

Values: Fixed | Simple Variable | Custom Variable

Default: Simple Variable

Representation — Equations of motion representation
`Euler Angles` (default) | `Quaternion`

Equations of motion representation, specified according to the following table.

Representation	Description
`Euler Angles`	Use Euler angles within equations of motion.
`Quaternion`	Use quaternions within equations of motion.

The Euler Angles selection conforms to the equations of motion in Algorithms.

Programmatic Use

Block Parameter: rep

Type: character vector

Values: Euler Angles | Quaternion

Default: 'Euler Angles'

Initial position in inertial axes [Xe,Ye,Ze] — Position in inertial axes
`[0 0 0]` (default) | three-element vector

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

Programmatic Use

Block Parameter: xme_0

Type: character vector

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

Default: '[0 0 0]'

Initial velocity in body axes [U,v,w] — Velocity in body axes
`[0 0 0]` (default) | three-element vector

Initial velocity in body axes, specified as a three-element vector, in the body-fixed coordinate frame.

Programmatic Use

Block Parameter: Vm_0

Type: character vector

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

Default: '[0 0 0]'

Initial Euler orientation [roll, pitch, yaw] — Initial Euler orientation
`[0 0 0]` (default) | three-element vector

Initial Euler orientation angles [roll, pitch, yaw], specified as a three-element vector, in radians. Euler rotation angles are those between the body and north-east-down (NED) coordinate systems.

Programmatic Use

Block Parameter: eul_0

Type: character vector

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

Default: '[0 0 0]'

Initial body rotation rates [p,q,r] — Initial body rotation
`[0 0 0]` (default) | three-element vector

Initial body-fixed angular rates with respect to the NED frame, specified as a three-element vector, in radians per second.

Programmatic Use

Block Parameter: pm_0

Type: character vector

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

Default: '[0 0 0]'

Initial mass — Initial mass
`1.0` (default) | scalar

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

Programmatic Use

Block Parameter: mass_0

Type: character vector

Values: '1.0' | double 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: double scalar

Default: '0.5'

Full mass — Full mass of body
`2.0` (default) | scalar

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

Programmatic Use

Block Parameter: mass_f

Type: character vector

Values: double scalar

Default: '2.0'

Empty inertia matrix — Empty inertia matrix
`eye(3)` (default) | 3-by-3 matrix

Inertia tensor matrix for the empty inertia of the body, specified as 3-by-3 matrix.

Programmatic Use

Block Parameter: inertia_e

Type: character vector

Values: 'eye(3)' | 3-by-3 matrix

Default: 'eye(3)'

Full inertia matrix — Full inertia of body
`2*eye(3)` (default) | 3-by-3 matrix

Inertia tensor matrix for the full inertia of the body, specified as 3-by-3 matrix.

Programmatic Use

Block Parameter: inertia_f

Type: character vector

Values: '2*eye(3)' | 3-by-3 matrix

Default: '2*eye(3)'

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 port.

Dependencies

To enable the A_{b ff} 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.

Position: e.g., {'Xe', 'Ye', '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: xme_statename

Type: character vector

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

Default: ''

Velocity: e.g., {'U', 'v', 'w'} — Velocity state name
`''` (default) | comma-separated list surrounded by braces

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

Programmatic Use

Block Parameter: Vm_statename

Type: character vector

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

Default: ''

Euler rotation angles: e.g., {'phi', 'theta', 'psi'} — Euler rotation state name
`''` (default) | comma-separated list surrounded by braces

Euler rotation angle state names, specified as a comma-separated list surrounded by braces.

Programmatic Use

Block Parameter: eul_statename

Type: character vector

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

Default: ''

Body rotation rates: e.g., {'p', 'q', 'r'} — Body rotation state names
`''` (default) | comma-separated list surrounded by braces

Body rotation rate state names, specified comma-separated list surrounded by braces.

Programmatic Use

Block Parameter: pm_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: '' | character vector

Default: ''

Algorithms

The origin of the body-fixed coordinate frame is the center of gravity of the body, and the body is assumed to be rigid, an assumption that eliminates the need to consider the forces acting between individual elements of mass. The flat Earth reference frame is considered inertial, an excellent approximation that allows the forces due to the Earth's motion relative to the fixed stars to be neglected.

Graphic of Flat Earth reference frame

The translational motion of the body-fixed coordinate frame is given below, where the applied forces [F_x F_yF_z]^Tare in the body-fixed frame. Vre_b is the relative velocity in the body axes at which the mass flow ( $\dot{m}$ ) is ejected or added to the body in body axes.

$\begin{array}{l} {\bar{F}}_{b} = [\begin{array}{l} F_{x} \\ F_{y} \\ F_{z} \end{array}] = m ({\dot{\bar{V}}}_{b} + \bar{ω} \times {\bar{V}}_{b}) - \dot{m} \bar{V} r e_{b} \\ A_{b e} = \frac{{\bar{F}}_{b} + \dot{m} {\bar{V}}_{r e}}{m} \\ A_{b b} = [\begin{matrix} {\dot{u}}_{b} \\ {\dot{v}}_{b} \\ {\dot{ω}}_{b} \end{matrix}] = \frac{{\bar{F}}_{b} + \dot{m} {\bar{V}}_{r e}}{m} - \bar{ω} \times {\bar{V}}_{b} \\ {\bar{V}}_{b} = [\begin{array}{l} u_{b} \\ v_{b} \\ w_{b} \end{array}], \bar{ω} = [\begin{array}{l} p \\ q \\ r \end{array}] \end{array}$

The rotational dynamics of the body-fixed frame are given below, where the applied moments are [L M N]^T, and the inertia tensor I is with respect to the origin O.

$\begin{array}{l} {\bar{M}}_{B} = [\begin{array}{l} L \\ M \\ N \end{array}] = I \dot{\bar{ω}} + \bar{ω} \times (I \bar{ω}) + \dot{I} \bar{ω} \\ I = [\begin{array}{l} I_{x x} & - I_{x y} & - I_{x z} \\ - I_{y x} & I_{y y} & - I_{y z} \\ - I_{z x} & - I_{z y} & I_{z z} \end{array}] \end{array}$

The inertia tensor is determined using a table lookup which linearly interpolates between I_full and I_empty based on mass (m). While the rate of change of the inertia tensor is estimated by the following equation.

$\dot{I} = \frac{I_{f u l l} - I_{e m p t y}}{m_{f u l l} - m_{e m p t y}} \dot{m}$

The relationship between the body-fixed angular velocity vector, [p q r]^T, and the rate of change of the Euler angles, [ $\dot{ϕ} \dot{θ} \dot{ψ}$ ]^T, can be determined by resolving the Euler rates into the body-fixed coordinate frame.

$[\begin{array}{l} p \\ q \\ r \end{array}] = [\begin{array}{l} \dot{ϕ} \\ 0 \\ 0 \end{array}] + [\begin{array}{l} 1 & 0 & 0 \\ 0 & \cos ϕ & \sin ϕ \\ 0 & - \sin ϕ & \cos ϕ \end{array}] [\begin{array}{l} 0 \\ \dot{θ} \\ 0 \end{array}] + [\begin{array}{l} 1 & 0 & 0 \\ 0 & \cos ϕ & \sin ϕ \\ 0 & - \sin ϕ & \cos ϕ \end{array}] [\begin{array}{l} \cos θ & 0 & - \sin θ \\ 0 & 1 & 0 \\ \sin θ & 0 & \cos θ \end{array}] [\begin{array}{l} 0 \\ 0 \\ \dot{ψ} \end{array}] \equiv J^{- 1} [\begin{array}{l} \dot{ϕ} \\ \dot{θ} \\ \dot{ψ} \end{array}]$

Inverting J then gives the required relationship to determine the Euler rate vector.

$[\begin{array}{l} \dot{ϕ} \\ \dot{θ} \\ \dot{ψ} \end{array}] = J [\begin{array}{l} p \\ q \\ r \end{array}] = [\begin{array}{l} 1 & (\sin ϕ \tan θ) & (\cos ϕ \tan θ) \\ 0 & \cos ϕ & - \sin ϕ \\ 0 & \frac{\sin ϕ}{\cos θ} & \frac{\cos ϕ}{\cos θ} \end{array}] [\begin{array}{l} p \\ q \\ r \end{array}]$

References

[1] Stevens, Brian, and Frank Lewis. Aircraft Control and Simulation. 2nd ed. Hoboken, NJ: John Wiley & Sons, 2003.

[2] Zipfel, Peter H. Modeling and Simulation of Aerospace Vehicle Dynamics. 2nd ed. Reston, VA: AIAA Education Series, 2007.

Extended Capabilities

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

Version History

Introduced in R2006a

Simple Variable Mass 6DOF (Euler Angles)

Description

Limitations

Ports

Input

Fxyz — Applied forces three-element vector

Mxyz(N-m) — Applied moments three-element vector

dm/dt (kg/s) — Rate of change of mass scalar

Vre — Relative velocity three-element vector

Dependencies

Output

Ve — Velocity in flat Earth reference frame three-element vector

Xe — Position in flat Earth reference frame three-element vector

φ θ ψ (rad) — Euler rotation angles three-element vector

DCMbe — Coordinate transformation 3-by-3 matrix

Vb — Velocity in body-fixed frame three-element vector

ωb (rad/s) — Angular rates in body-fixed axes three-element vector

dωb/dt — Angular accelerations three-element vector

Abb — Accelerations in body-fixed axes three-element vector

Fuel — Fuel tank status scalar

Abe — Accelerations with respect to inertial frame three-element vector

Dependencies

Parameters

Main

Units — Input and output units Metric (MKS) (default) | English (Velocity in ft/s) | English (Velocity in kts)

Programmatic Use

Mass Type — Mass type Simple Variable (default) | Fixed | Custom Variable

Programmatic Use

Representation — Equations of motion representation Euler Angles (default) | Quaternion

Programmatic Use

Initial position in inertial axes [Xe,Ye,Ze] — Position in inertial axes [0 0 0] (default) | three-element vector

Programmatic Use

Initial velocity in body axes [U,v,w] — Velocity in body axes [0 0 0] (default) | three-element vector

Programmatic Use

Initial Euler orientation [roll, pitch, yaw] — Initial Euler orientation [0 0 0] (default) | three-element vector

Programmatic Use

Initial body rotation rates [p,q,r] — Initial body rotation [0 0 0] (default) | three-element vector

Programmatic Use

Initial mass — Initial mass 1.0 (default) | scalar

Programmatic Use

Empty mass — Empty mass 0.5 (default) | scalar

Programmatic Use

Full mass — Full mass of body 2.0 (default) | scalar

Programmatic Use

Empty inertia matrix — Empty inertia matrix eye(3) (default) | 3-by-3 matrix

Programmatic Use

Full inertia matrix — Full inertia of body 2*eye(3) (default) | 3-by-3 matrix

Programmatic Use

Include mass flow relative velocity — Mass flow relative velocity port off (default) | on

Programmatic Use

Include inertial acceleration — Include inertial acceleration port off (default) | on

Dependencies

Programmatic Use

State Attributes

Position: e.g., {'Xe', 'Ye', 'Ze'} — Position state name '' (default) | comma-separated list surrounded by braces

Programmatic Use

Velocity: e.g., {'U', 'v', 'w'} — Velocity state name '' (default) | comma-separated list surrounded by braces

Programmatic Use

Euler rotation angles: e.g., {'phi', 'theta', 'psi'} — Euler rotation state name '' (default) | comma-separated list surrounded by braces

Programmatic Use

Body rotation rates: e.g., {'p', 'q', 'r'} — Body rotation state names '' (default) | comma-separated list surrounded by braces

Programmatic Use

Mass: e.g., 'mass' — Mass state name '' (default) | character vector

Programmatic Use

Algorithms

References

Extended Capabilities

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

Version History

See Also

F_xyz — Applied forces
three-element vector

M_xyz(N-m) — Applied moments
three-element vector

dm/dt (kg/s) — Rate of change of mass
scalar

V_re — Relative velocity
three-element vector

V_e — Velocity in flat Earth reference frame
three-element vector

X_e — Position in flat Earth reference frame
three-element vector

φ θ ψ (rad) — Euler rotation angles
three-element vector

DCM_be — Coordinate transformation
3-by-3 matrix

V_b — Velocity in body-fixed frame
three-element vector

ω_b (rad/s) — Angular rates in body-fixed axes
three-element vector

dω_b/dt — Angular accelerations
three-element vector

A_bb — Accelerations in body-fixed axes
three-element vector

Fuel — Fuel tank status
scalar

A_be — Accelerations with respect to inertial frame
three-element vector

Units — Input and output units
`Metric (MKS)` (default) | `English (Velocity in ft/s)` | `English (Velocity in kts)`

Mass Type — Mass type
`Simple Variable` (default) | `Fixed` | `Custom Variable`

Representation — Equations of motion representation
`Euler Angles` (default) | `Quaternion`

Initial position in inertial axes [Xe,Ye,Ze] — Position in inertial axes
`[0 0 0]` (default) | three-element vector

Initial velocity in body axes [U,v,w] — Velocity in body axes
`[0 0 0]` (default) | three-element vector

Initial Euler orientation [roll, pitch, yaw] — Initial Euler orientation
`[0 0 0]` (default) | three-element vector

Initial body rotation rates [p,q,r] — Initial body rotation
`[0 0 0]` (default) | three-element vector

Initial mass — Initial mass
`1.0` (default) | scalar

Empty mass — Empty mass
`0.5` (default) | scalar

Full mass — Full mass of body
`2.0` (default) | scalar

Empty inertia matrix — Empty inertia matrix
`eye(3)` (default) | 3-by-3 matrix

Full inertia matrix — Full inertia of body
`2*eye(3)` (default) | 3-by-3 matrix

Include mass flow relative velocity — Mass flow relative velocity port
`off` (default) | `on`

Include inertial acceleration — Include inertial acceleration port
`off` (default) | `on`

Position: e.g., {'Xe', 'Ye', 'Ze'} — Position state name
`''` (default) | comma-separated list surrounded by braces

Velocity: e.g., {'U', 'v', 'w'} — Velocity state name
`''` (default) | comma-separated list surrounded by braces

Euler rotation angles: e.g., {'phi', 'theta', 'psi'} — Euler rotation state name
`''` (default) | comma-separated list surrounded by braces

Body rotation rates: e.g., {'p', 'q', 'r'} — Body rotation state names
`''` (default) | comma-separated list surrounded by braces

Mass: e.g., 'mass' — Mass state name
`''` (default) | character vector

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