Custom Variable Mass 6DOF (Euler Angles)

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

Library

Equations of Motion/6DOF

Description

The Custom 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). 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.

The translational motion of the body-fixed coordinate frame is given below, where the applied forces [F_x F_y F_z]^T are 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-fixed axes.

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

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.

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

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.

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

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

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

For more information on aerospace coordinate systems, see About Aerospace Coordinate Systems.

Parameters

Main

Units

Specifies the input and output units:

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

Mass Type

Select the type of mass to use:

`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 Custom Variable selection conforms to the previously described equations of motion.

Representation

Select the representation to use:

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

The Euler Angles selection conforms to the previously described equations of motion.

Initial position in inertial axes

The three-element vector for the initial location of the body in the flat Earth reference frame.

Initial velocity in body axes

The three-element vector for the initial velocity in the body-fixed coordinate frame.

Initial Euler rotation

The three-element vector for the initial Euler rotation angles [roll, pitch, yaw], in radians.

Initial body rotation rates

The three-element vector for the initial body-fixed angular rates, in radians per second.

Include mass flow relative velocity

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.

Include inertial acceleration

Select this check box to enable an additional output port for the accelerations in body-fixed axes with respect to the inertial frame. You typically connect this signal to the accelerometer.

State Attributes

Assign 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-delimited list surrounded by braces, for example, {'a', 'b', 'c'}. Each name must be unique.
If a parameter is empty (' '), no name assignment occurs.
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'}

Specify position state names.

Default value is ''.

Velocity: e.g., {'U', 'v', 'w'}

Specify velocity state names.

Default value is ''.

Euler rotation angles: e.g., {'phi', 'theta', 'psi'}

Specify Euler rotation angles state names. This parameter appears if the Representation parameter is set to Euler Angles.

Default value is ''.

Body rotation rates: e.g., {'p', 'q', 'r'}

Specify body rotation rate state names.

Default value is ''.

Inputs and Outputs

Input	Dimension Type	Description
First	Vector	Contains the three applied forces.
Second	Vector	Contains the three applied moments.
Third (Optional)	Vector	Contains one or more rates of change of mass (positive if accreted, negative if ablated).
Fourth	Scalar	Contains the mass.
Fifth	3-by-3 matrix	Contains the rate of change of inertia tensor matrix.
Sixth	3-by-3 matrix	Contains the inertia tensor matrix.
Seventh (Optional)	Three-element vector	Contains one or more relative velocities at which the mass is accreted to or ablated from the body in body-fixed axes.

Output	Dimension Type	Description
First	Three-element vector	Contains the velocity in the flat Earth reference frame.
Second	Three-element vector	Contains the position in the flat Earth reference frame.
Third	Three-element vector	Contains the Euler rotation angles [roll, pitch, yaw], within ±pi, in radians.
Fourth	3–by-3 matrix	Contains the coordinate transformation from flat Earth axes to body-fixed axes.
Fifth	Three-element vector	Contains the velocity in the body-fixed frame.
Sixth	Three-element vector	Contains the angular rates in body-fixed axes, in radians per second.
Seventh	Three-element vector	Contains the angular accelerations in body-fixed axes, in radians per second squared.
Eight	Three-element vector	Contains the accelerations in body-fixed axes with respect to body frame.
Ninth (Optional)	Three-element vector	Contains the accelerations in body-fixed axes with respect to inertial frame (flat Earth). You typically connect this signal to the accelerometer.

Assumptions and Limitations

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

Reference

Stevens, Brian, and Frank Lewis, Aircraft Control and Simulation, Second Edition, John Wiley & Sons, 2003.

Zipfel, Peter H., Modeling and Simulation of Aerospace Vehicle Dynamics. Second Edition, AIAA Education Series, 2007.

Documentation

Custom Variable Mass 6DOF (Euler Angles)

Library

Description

Parameters

Main

State Attributes

Inputs and Outputs

Assumptions and Limitations

Reference

See Also

Extended Capabilities

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

Introduced in R2006a

Aerospace Blockset Documentation

Support

Documentation

Custom Variable Mass 6DOF (Euler Angles)

Library

Description

Parameters

Main

State Attributes

Inputs and Outputs

Assumptions and Limitations

Reference

See Also

Extended Capabilities

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

Introduced in R2006a

Aerospace Blockset Documentation

Support

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