Documentation |
Calculate forces used by sixth-order point mass in coordinated flight
The 6th Order Point Mass Forces (Coordinated Flight) block calculates the applied forces for a single point mass or multiple point masses.
The applied forces [F_{x} F_{y} F_{h}]^{T }are in a system is defined by x-axis in the direction of vehicle velocity relative to air, z-axis is upwards and y-axis completes the right-handed frame and are functions of lift (L), drag (D), thrust (T), weight (W), flight path angle (γ), angle of attack (α), and bank angle (μ).
$$\begin{array}{l}{F}_{x}=T\mathrm{cos}\alpha -D-W\mathrm{sin}\gamma \\ F\gamma =(L+T\mathrm{sin}\alpha )\mathrm{sin}\mu \\ {F}_{z}=(L+T\mathrm{sin}\alpha )\mathrm{cos}\mu -W\mathrm{cos}\gamma \end{array}$$
Input | Dimension Type | Description |
---|---|---|
First | Contains the lift in units of force. | |
Second | Contains the drag in units of force. | |
Third | Contains the weight in units of force. | |
Fourth | Contains the thrust in units of force. | |
Fifth | Contains the flight path angle in radians. | |
Sixth | Contains the bank angle in radians. | |
Seventh | Contains the angle of attack in radians. |
Output | Dimension Type | Description |
---|---|---|
First | Contains the force in x-axis in units of force. | |
Second | Contains the force in y-axis in units of force. | |
Third | Contains the force in z-axis in units of force. |
The block assumes that there is fully coordinated flight, i.e., there is no side force (wind axes) and sideslip is always zero.
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.