Report
Currently I’ve been working on one gadget that belong to the Electronic flight instrument systems (EFIS) which is the primary flight display.
This PFD will display the attitude and system control commands. Additionally it will be distributed in the following way.
First, the attitude indicator will be displayed in the centre, this specifies the pitch, roll and stall angle of the aircraft. Second, at the left hand side the airspeed. This speed is measured in knots which are taken above mean sea level. Third at the right hand side the attitude indicator shown as numbers and next to it, the vertical attitude indicator which indicates how many feet per minute the aircraft is ascending. This V indicator illustrates in one or two unit number. For instance if is indicating number two (2) that means 2000 feet pre minute or 2 X 103 .
There are some parts in the PFD that are going to be omitted, because some of the inputs are taken from other gadgets. For example:
SPD: this allows the automatic pilot to take control of the velocity and other matters.
CMD: indicates that the automatic pilot is on.
Approach Reference: Displays the selected ILS identifier or frequency approach course and ILS DME distance.
Glideslope and localizer Scales: appears when the previews frequency is in tune. At low altitudes and with the autopilot or flight director engage.
Moreover, the package will have the functions or classes in order to enable these facilities if the other gadgets exist.
PROBLEMS FOUND
Although the attitude indicator interacts with keyboard input, there are some constrains that need to be put into account. For instance: 1. If the user (pilot) input ascending command and the velocity of the plane is 0 or less than the velocity required (differ depending on the airplane aerodynamic) the indicator must not increase. 2. If the plane has the necessary velocity to be able to flight and the pilot applies more or less 10 to 20 degrees the indicator will have to follow an equation in order to know how many feet per hour the rate is increasing, the rate of the pitch scale and some other variable that will be discussed later in this paper.

POSSIBLE ANSWERS TO SOLVE THE PREVIEWS PROBLEMS

1. Make a function that check before the input is action to check the velocity of the airplane. Additionally create a local data base to check the model of the airplane and the min of airspeed needed in order the airplane to flight and weather condition (Fluid Dynamics).

2. The following diagram and equation will try to explain the possible answer of the second problem.

Body X

0
Earth X (direction) α Wf

U uf Earth Z(direction)

This equation annulets the winds force applies only in rigid bodies :

Xf = -MU d(θ - α)/dt * sin(θ - α ); // applied force in axis X
Zf = MU d(θ - α)/dt * cos(θ - α ); // applied force in axis Z

M= Mass by the rotation motion. On the application so far is seen like this: