Vertical control system for rotary wing aircraft

• US 5,428,543 A
• Filed: 07/06/1994
• Issued: 06/27/1995
• Est. Priority Date: 08/28/1991
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Stiles, Lorren, Post, Joseph A., Gold, Phillip J.
• Primary Examiner(s): Teska, Kevin J.
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US08/271,221
• Time in Patent Office: 356 Days
• Field of Search: 244/17.13, 244/223, 244/177, 244/236, 244/234, 364/433, 364/434, 364/424, 364/424.01, 235/150.26
• US Class Current: 701/5
• CPC Class Codes: G05D 1/0669 specially adapted for vertical take-off

Abstract

A vertical control system for a rotary winged aircraft receives inputs from a displacement collective stick and a sidearm controller. The system provides a set point for the vertical rate of change of the helicopter as a function of a vertical lift command signal from the sidearm controller. The set point is used as a reference for an altitude rate of change feedback path, and an integrated value of the set point is used for an altitude feedback path. The set point is also input to a feedforward control path having an inverse vehicle model to provide a command signal indicative of the command for aircraft collective pitch necessary to achieve the desired set point. Signals from all three paths (i.e., the altitude rate of change feedback path, the altitude feedback path, and the feedforward path) are summed to provide a signal to backdrive the displacement collective which controls main rotor collective pitch.

Claims

1. A vertical control system for a rotary winged aircraft which receives signals indicative of aircraft vertical acceleration, aircraft vertical rate, and aircraft altitude from various sensors on the aircraft, for controlling the collective pitch of main rotor blades of the aircraft, comprising:

a four axis sidearm controller which provides a first signal indicative of desired lift;

a collective stick;

means for sensing the position of said collective stick, and for providing a position signal indicative thereof;

means for driving said collective stick in response to said position signal and changing values of said first signal;

means responsive to said first signal for providing a desired aircraft vertical rate of change command signal; and

means responsive to said desired aircraft vertical rate of change command signal, for computing an altitude rate error signal which is the difference between the rate of change indicated by said desired aircraft vertical rate of change command signal and the actual aircraft vertical rate of change, for integrating said desired aircraft vertical rate of change command signal to provide a desired altitude command signal, for calculating an altitude error signal which is the difference between the altitude indicated by said desired altitude command signal and the actual aircraft altitude, for computing a feedforward command signal in response to said desired aircraft vertical rate of change signal, and for summing said altitude rate error signal with said altitude error signal and said feedforward command signal to provide a rotor command signal indicative of the collective pitch necessary to drive the actual aircraft altitude rate of change toward the rate indicated by said desired aircraft vertical rate of change signal.

2. The system of claim 1 further comprising:

means for summing said position signal and said rotor command signal to provide a collective pitch command signal.

3. The system of claim 1, further comprising:

means for limiting the time rate of change of said rotor command signal, for limiting the magnitude of said rotor command signal, and for providing a limited rotor command signal indicative thereof; and

means for summing said position signal and said limited rotor command signal to provide a collective pitch command signal.

4. A flight control system for a helicopter having:

sensors which provide signals indicative of the helicopter'"'"'s actual altitude and actual altitude rate of change, a sidearm controller which provides a vertical lift command signal indicative of the desired lift along the vertical axis, and a collective stick which provides a collective command signal indicative of desired collective pitch;

the flight control system controls vertical lift of the helicopter by providing to the helicopter'"'"'s main rotor a set point signal indicative of the desired collective pitch of the helicopter'"'"'s main rotor blades, the flight control system comprising;

means for providing, for each value of the vertical lift command signal presented thereto, a vertical rate of change command signal indicative of a corresponding desired value for the helicopter'"'"'s vertical rate of change;

means for integrating said vertical rate of change command signal to provide a desired altitude command signal;

first means of computing a first difference value between the value of said desired altitude command signal and the value of said helicopter'"'"'s actual altitude signal, and for providing an altitude error signal indicative of said first difference value;

second means for computing a second difference value between the value of said vertical rate of change command signal and the value of said helicopter'"'"'s actual altitude rate of change signal, and for providing an altitude rate of change error signal indicative of said second difference value;

inverse model means for providing for each value of said vertical rate of change command signal, a feedforward collective set point signal indicative of the collective pitch required for the helicopter to aerodynamically respond along its vertical axis at a rate set by the value of said vertical rate of change command signal;

means for summing said altitude error signal, said altitude rate of change error signal, and said feedforward collective set point signal, and for providing as a summation thereof a modifying collective pitch command signal;

means for summing said collective command signal with said modifying collective pitch command signal to provide, as the sum thereof, said desired collective pitch set point signal; and

output means for providing said desired collective pitch set point signal value to the helicopter'"'"'s main rotor, such that by commanding the collective pitch of helicopter'"'"'s main rotor blades in response to said desired collective pitch set point signal, the helicopter will aerodynamically respond along its vertical axis in a manner to cause the values of said altitude error signal and said altitude rate error signal to approach zero.

5. The flight control system of claim 4, wherein:

said means for providing includes a first order lag filter which is responsive to each value of the vertical lift command signal; and

said inverse model means includes a first order lead filter responsive to each of said desired values of vertical rate of change signal.

6. The flight control system of claim 4, further comprising:

means for magnitude and rate limiting said modifying collective pitch command signal values to provide a limited signal indicative thereof; and

means for moving the collective stick in response to the value of said limited signal such that the collective stick position commands the collective pitch of the main rotor blades.

7. The flight control system of claim 4, further comprising means for fading in and out said command modifying signal to/from said second means for summing, such that the collective pitch of the helicopter'"'"'s main rotor blades is controlled exclusively in response to values of the collective command signal when said command modifying signal is faded out, and when faded in said command modifying signal is a bias to the collective command signal.

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

means for tracking the collective command signal value by providing a signal value which is equal to the value of the collective command signal when a first discrete signal is true, and for storing the collective command signal value when said first discrete signal is false;

means for magnitude and rate limiting said modifying collective pitch command signal values to provide a limited signal indicative thereof;

synchronizing means, for storing each value of said limited signal when said first discrete signal is false, for providing a synchronizer output signal equal to zero when said first signal is false, and for providing said synchronizer output signal at a value which is equal to the present value of said limited signal and the stored value of limited signal; and

motive means for moving the collective stick in response to the value of said synchronizer output signal such that the collective stick position commands the collective pitch of the main rotor blades.

9. The flight control system of claim 8, wherein said inverse model means includes a lead filter of at least first order which provides said feedforward collective set point signal value.

10. A helicopter flight control system which receives signals indicative of:

the helicopter'"'"'s actual altitude and actual altitude rate of change, a vertical lift command signal indicative of desired vertical lift along the helicopter'"'"'s vertical axis, and a collective command signal indicative of main rotor collective pitch;

the flight control system controls vertical lift of the helicopter by providing to the helicopter'"'"'s main rotor a set point signal indicative of the desired collective pitch of the helicopter'"'"'s main rotor blades, the flight control system comprising;

means for providing, for each value of said vertical lift command signal presented thereto, a corresponding desired vertical rate of change command signal;

means for integrating said desired vertical rate of change command signal to provide a desired altitude command signal;

first means, for computing a first difference value between the value of said desired altitude command signal and the value of said helicopter'"'"'s actual altitude signal, and for providing an altitude error signal indicative of said first difference value;

second means for computing a second difference value between the value of said desired vertical rate of change command signal and the value of said helicopter'"'"'s actual altitude rate of change signal, and for providing an altitude rate of change error signal indicative of said second difference value;

inverse model means for providing for each value of said desired vertical rate of change command signal, a feedforward collective set point signal indicative of the collective pitch required for the helicopter to aerodynamically respond along its vertical axis in a manner set by the value of said desired vertical rate of change command signal;

means for summing said altitude error signal, said altitude rate of change error signal, and said feedforward collective set point signal, and for providing as a summation thereof a modifying collective pitch command signal;

means for summing said collective command signal with said modifying collective pitch command signal to provide as the sum thereof said desired collective pitch set point signal; and

output means, for presenting said desired collective pitch set point signal to the helicopter'"'"'s main rotor to set the collective pitch of helicopter'"'"'s main rotor blades in response to the value of said desired collective pitch set point signal so the helicopter aerodynamically responds along its vertical axis in a manner to cause the values of said altitude error signal and said altitude rate error signal to approach zero.

11. The flight control system of claim 10, wherein:

said means for providing includes a first order lag filter which is responsive to each value of the vertical lift command signal; and

said inverse model means includes a first order lead filter responsive to each of said desired values of vertical rate of change signal.

12. The flight control system of claim 11, further comprising means for fading in and out said command modifying signal to/from said second means for summing, such that the collective pitch of the helicopter'"'"'s main rotor blades is controlled exclusively in response to values of the collective command signal when said command modifying signal is faded out, and when faded in said command modifying signal is a bias to the collective command signal.

13. The flight control system of claim 12, further comprising:

means for tracking the collective command signal value by providing a signal value which is equal to the value of the collective command signal when a first discrete signal is true, and for storing the collective command signal value when said first discrete signal is false; and

means for magnitude and rate limiting said modifying collective pitch command signal values to provide a limited signal indicative thereof;

synchronizing means for storing each value of said limited signal when said first discrete signal is false, for providing a synchronizer output signal equal to zero when said first signal is false, and for providing said synchronizer output signal at a value which is equal to the present value of said limited signal and the stored value of limited signal; and

motive means for moving the collective stick in response to the value of said synchronizer output signal such that the collective stick position commands the collective pitch of the main rotor blades.

14. The flight control system of claim 13, wherein

said inverse model means includes a lead filter of at least first order which provides said feedforward collective set point signal value;

and

said means for providing includes a lag filter which provides said desired vertical rate of change signal value.