VTOL altitude hold system with automatic ground effect compensation

• US 4,603,388 A
• Filed: 02/16/1983
• Issued: 07/29/1986
• Est. Priority Date: 02/16/1983
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Sperry Corporation
• Inventors: Griffith, Carl D., Skutecki, Edmund R.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US06/466,816
• Time in Patent Office: 1,259 Days
• Field of Search: 364/427, 364/428, 364/433, 364/434, 364/424, 364/571, 244/17.13, 244/223, 244/180-182, 318/584, 73/178 R, 73/178 H, 73/178 T, 340/967, 340/970
• US Class Current: 701/4
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa
• CPC Class Codes: G05D 1/0669 specially adapted for vertical take-off

Abstract

During a transition of a VTOL aircraft such as a helicopter, from one altitude held without its ground effect zone to another to be held within its ground effect zone, or vice versa, a collective stick position synchronizer which can memorize the proper trim condition at the previous altitude in conjunction with the stick force sensor out-of-detent logic and a low vertical speed sensor, together constituting a ground effect zone detector, is used to drive the collective stick trim actuator in a direction which relieves any force being exerted by the pilot in order to maintain the new commanded altitude.

Claims

1. In an automatic altitude hold control system for an aircraft subject to ground effect, said control system including a manual controller for controlling the lift of the aircraft, a parallel servoactuator including a trim actuator and a controller force feel spring for coupling to said manual controller, an out-of-detent and in-detent spring deflection condition sensor for providing a signal indicative of a displacement of said manual controller, a controller position sensor for providing a signal corresponding to a position of said manual controller, and a servo amplifier responsive to altitude error for normally positioning said manual controller for reducing said altitude error to zero, apparatus responsive to a transition of said aircraft from an altitude outside an aircraft ground effect zone to an altitude within the aircraft ground effect zone and vice versa for automatically compensating said system for the resulting change in lift of the aircraft by driving said trim actuator in a direction which relieves any force being exerted by a human pilot in order to maintain the new commanded altitude, said apparatus comprising

(a) a collective position synchronizer responsive to said controller position sensor, for supplying a signal corresponding to the controller position at a previously held altitude,

(b) means for sensing the presence and absence of ground effect on said aircraft, and

(c) means responsive to said ground effect sensor means for supplying said synchronizer signal corresponding to the controller position to said servo amplifier for driving said trim actuator to compensate said system.

2. A ground effect compensation apparatus as set forth in claim 1 wherein said controller position synchronizer comprises

(a) switch means having one condition for causing said synchronizer to follow-up on said controller position sensor and another condition for clamping said synchronizer, and

first logic means responsive to said spring deflection sensor for operating said switch means.

3. A ground effect compensation apparatus as set forth in claim 2 wherein said ground effect sensor means comprises

(a) second logic means responsive to the vertical speed of the aircraft relative to a predetermined low vertical speed value and the condition of said spring deflection sensor.

4. A ground effect compensation apparatus as set forth in claim 3 wherein said second logic means provides a first condition signal upon said vertical speed exceeding said predetermined low value and said spring deflection sensor is in its out-of-detent condition, said apparatus further comprising

(a) switch means coupled with said servo amplifier and responsive to said first condition signal of said second logic means for disabling its control of said trim actuator whereby said controller position synchronizer signal has no effect on said trim actuator.

5. A ground effect compensation apparatus as set forth in claim 4 wherein said second logic means provides a second condition signal upon said vertical speed being less than said predetermined low value and said spring deflection sensor is in its out-of-detent condition, and wherein said servo amplifier switch means is responsive to said second condition signal of said second logic means for enabling its control of said trim actuator, whereby said controller position synchronizer signal controls said trim actuator.

6. A ground effect compensation apparatus as set forth in claim 5 wherein said first logic means is responsive to said spring deflection sensor in its out-of-detent condition for placing said controller position synchronizer in its clamping condition of operation whereby said controller position synchronizer signal is supplied to said servo amplifier.

7. A ground effect compensation apparatus as set forth in claim 5 further comprising

(a) switch means responsive to said spring deflection sensor in its out-of-detent condition for disengaging said altitude error from the input of said servo amplifier.

8. A ground effect compensation apparatus as set forth in claim 3 wherein said ground effect sensor means further comprises

(a) means for sensing the magnitude of actual aircraft vertical speed and supplying a signal in accordance with an absolute value thereof,

(b) means for providing a fixed bias signal corresponding to a predetermined low vertical speed, and

(c) means for comparing said absolute value vertical speed signal and said bias signal and supplying an output representative of a first logical condition when said absolute value vertical speed signal exceeds said bias signal and of a second logical condition when said absolute value vertical speed signal is less than said bias signal.

9. A ground effect compensation apparatus as set forth in claim 8 wherein said second logic means comprises

(a) logic gate means responsive to the output of said comparator means and to the condition of said spring deflection sensor.

10. A ground effect compensation apparatus as set forth in claim 9 wherein said gate means comprises

(a) an AND gate responsive to said comparator output and said spring deflection sensor and for supplying a first output when said comparator output is of said first logical condition and said spring deflection sensor is in its out-of-detent condition and for supplying a second output when said comparator output is of said logical condition, said first and second outputs corresponding to first and second logical conditions.