Flight control laws for vertical flight path

1. A flight control system for vertical flight path control of an aircraft having a sensor, the system comprising:

a flight control computer having an algorithm, the algorithm having a stable decoupled model having a decoupled lateral equation of aircraft motion and a decoupled longitudinal equation of aircraft motion; and

a feedback command loop operably associated with the stable decoupled model, the feedback command loop having:

a vertical flight path angle control law configured to receive data from the sensor and a vertical command from a controller;

an altitude control law configured to receive data from the sensor; and

a vertical speed control law configured to receive data from the sensor and configured to send a command to the actuator;

a switch in communication with both the vertical flight path angle control law and the altitude control law, the switch being configured to send data to the vertical speed control law;

wherein the vertical flight path angle control law, the altitude control law, and the vertical speed control law utilize the lateral equation of aircraft motion and the longitudinal equation of aircraft motion; and

wherein the vertical speed control law is operably associated with the altitude control law when an aircraft altitude hold device is activated.

2. The flight control system of claim 1 , wherein the controller is selected from the group consisting of a cockpit vertical controller, a vertical beep switch, and a vertical controller force trim release switch.

3. The flight control system of claim 1 , wherein in the absence of the vertical command from the controller, the feedback command loop will automatically engage altitude hold when an absolute value of either vertical speed of the aircraft or the vertical flight path angle fall below a design threshold.

4. The flight control system of claim 1 , wherein the feedback command loop uses a vertical controller force to determine when the controller is out of a no force detent position.

5. The flight control system of claim 4 , wherein the feedback command loop calculates a vertical controller displacement when the controller is out of detent.

6. The flight control system of claim 1 , further comprising:

wherein the aircraft sensor is selected from the group consisting of an internal navigation system, an air data computer, and a radar altimeter.

7. The flight control system of claim 1 , further comprising:

a main rotor collective pitch actuator operably associated with the feedback command loop.

8. The flight control system of claim 1 , wherein the feedback command loop further comprises:

a speed hysteresis control loop for preventing rapid switching between a low speed control law and a high speed control law when operating in a transition zone;

wherein during acceleration of the aircraft, the feedback command loop switches to a high speed vertical flight path control envelope when passing an upper limit of the transition zone; and

wherein during deceleration of the aircraft, the feedback command loop switches to a low speed vertical flight path control envelope when passing a lower limit of the transition zone.

9. The flight control system of claim 1 , wherein the vertical flight path angle control law is computed with the following equation:

γ

=

tan

-

1

⁡

(

V

z

V

x

)

;

wherein γ is the vertical flight path angle, V z is the vertical speed, and V x is the forward groundspeed relative to the aircraft.

10. The flight control system of claim 1 , further comprising:

a pitch attitude control loop for predicting the change in vertical speed caused by a pitch attitude change, the pitch attitude control loop being computed with the following equation:

V zΔθ =V x ·tan Δθ;

wherein V zΔθ is the pitch vertical speed change and Δθ is the change in pitch attitude, and V x is the forward groundspeed relative to the aircraft.

11. The flight control system of claim 10 , wherein Δθ is calculated using a washout filter.

12. The flight control system of claim 1 , wherein the vertical flight path angle control law utilizes the following equation to compute the vertical speed needed to hold a reference vertical flight path angle:

V z REF =V x ·tan γ REF

wherein V z REF is a reference vertical speed and γ REF is the reference vertical flight path angle.

13. The flight control system of claim 1 , further comprising:

a logic switch;

wherein the logic switch is adapted to allow the feedback command loop to back drive a vertical controller trim actuator.

14. The flight control system of claim 1 , wherein a command from the feedback command loop is added to a vertical controller position for operating a vertical control surface actuator.

15. A method for vertical flight path control of an aircraft, comprising:

providing a flight control computer having an algorithm, the algorithm being configured to decouple a model having a lateral equation of aircraft motion and a longitudinal equation of aircraft motion;

stabilizing the aircraft by individually analyzing the lateral equation of motion and the longitudinal equation of motion; and

controlling the vertical flight path of the aircraft with a feedback command loop associated with the algorithm, the feedback command loop, having:

a vertical flight path angle control law configured to receive data from the sensor and a vertical command from a controller;

an altitude control law configured to receive data from the sensor; and

a vertical speed control law configured to receive data from the sensor and configured to send a command to the actuator;

communicating both the vertical flight path angle control law and the altitude control law with a switch, the switch being configured to send data to the vertical speed control law;

wherein the vertical flight path angle control law, the altitude control law, and the vertical speed control law utilize the lateral equation of aircraft motion and the longitudinal equation of aircraft motion; and

wherein the vertical speed control law is operably associated with the altitude control law when an aircraft altitude hold device is activated.

16. The method of claim 15 , further comprising:

calculating the vertical flight path angle control law with the following equation:

γ

=

tan

-

1

⁡

(

V

z

V

x

)

;

wherein γ is the vertical flight path angle, V z is the vertical speed with up positive, and V x is the forward groundspeed relative to the aircraft.

17. The method of claim 15 , further comprising:

predicting the change in vertical speed caused by a pitch attitude change with a pitch attitude control loop with the following equation:

V zΔθ =V x ·tan Δθ;

wherein V zΔθ is the pitch vertical speed change and Δθ is the change in pitch attitude, and V x is the forward groundspeed relative to the aircraft.