CONTROL SYSTEM WITH MULTIPLE FUNCTION CAPABILITY

• US 3,578,267 A
• Filed: 11/21/1968
• Issued: 05/11/1971
• Est. Priority Date: 11/21/1968
• Status: Expired due to Term

• Current Assignee: GEC Astronics Corporation
• Original Assignee: Kazmarek Edward
• Inventors: KAZMAREK EDWARD
• Application Number:
  US04/777,798
• Time in Patent Office: 901 Days
• US Class Current: 244/197
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa
• CPC Class Codes: Y10T 74/20 Control lever and linkage systems
• CPC Class Codes: Y10T 74/20582 Levers

Abstract

A first force-transmitting mechanism is adapted to move relative to a stationary frame responsive to a servoactuator. An element to be controlled is coupled to the first mechanism such that it moves with the first mechanism relative to the frame. A second force-transmitting mechanism is adapted to move relative to the frame in response to a manual input device. Mechanical coupling between the first and second mechanisms enables operation in one of two modes. In one mode, the mechanisms are coupled to move in a mutually independent manner relative to the frame within predetermined limits beyond which they move together. In addition to its normal function, the servoactuator operates responsive to a transducer that senses the displacement between the first and second mechanisms and returns the first mechanism to a null position relative to the second mechanism. In the other mode, the mechanisms are coupled to move together relative to the frame without appreciable play.

Claims

1. A control system comprising:

a stationary frame;

a servoactuator;

a first force transmitting mechanism adapted to move relative to the frame in response to the servoactuator;

a manual input device;

a seconD force transmitting mechanism adapted to move relative to the frame in response to the manual input device;

mechanical coupling means between the first and second mechanisms capable of assuming either a first state or a second state, the mechanisms being coupled in the first state in move independently relative to the frame and being coupled in the second state to move together relative to the frame;

means for sensing the displacement between the first and second mechanisms from a null position, the servoactuator operating responsive to the displacement sensed by the sensing means to return the first mechanism to the null position relative to the second mechanism; and

an element to be controlled connected to the first mechanism such that the element is controlled as the first mechanism moves relative to the frame.

2. The control system of claim 1, in which the mechanisms are coupled to move independently relative to the frame in the first state within predetermined limits beyond which they move together relative to the frame.

3. The control system of claim 1, in which the servoactuator operates responsive to a source of electrical signals representing a command input as well as the means for sensing the displacement between the first and second mechanisms.

4. The control system of claim 1, in which the servoactuator operates responsive to the output of a summing junction, the means for sensing the displacement between the first and second mechanisms from a null position produces a signal applied to one input of the summing junction, and an electrical signal representing a command input is applied to another input of the summing junction.

5. The control system of claim 1, in which the servoactuator drives a shaft, the first mechanism is fixed to the shaft, the second mechanism is rotatably supported with respect to the shaft, the coupling means between the first and second mechanisms comprises a hole in one of the mechanisms and a pin that is connected to the other mechanism without appreciable play in the direction of rotation of the shaft, and the pin is movable within the hole transverse to the direction of rotation of the shaft to assume either the first or second state, the pin being adapted to fit in the hole with substantial play in the first state and to fit snugly in the hole without appreciable play in the second state.

6. The control system of claim 5, in which the axis of the pin is parallel to the axis of the shaft, the pin has a base with a larger diameter than its extremity that adjoins the one mechanism, the hole is a cylindrical bore with a diameter slightly larger than the base of the pin and alignable therewith, and the pin is axially moveable.

7. The control system of claim 6, in which the pin has a tapered portion connecting the base and the extremity and the portion of the hole facing the other mechanism is flared to match the angle of the tapered portion of the pin.

8. The control system of claim 5, in which the axis of the pin is parallel to the axis of the shaft, the pin extends from the other mechanism into the hole of the one mechanism, the pin is connected to the other mechanism without appreciable play in the direction of rotation of the shaft, the pin is movable in a radial direction from the shaft, and the hole is dimensioned so the pin fits in a wide portion of the hole with substantial play when the pin assumes the first state and the pin fits snugly in a narrow portion of the hole without appreciable play when the pin assumes the second state.

9. The control system of claim 5, in which the axis of the pin is radially perpendicular to the axis of the shaft, the pin is axially movable, the pin has an extremity with a smaller diameter than its base, the one mechanism has a portion extending transverse to the pin, the hole is located in the transverse portion of the one mechanism so it is axially alignable with the pin, the portion of the hole facing the pin has a diameter slightly larger than the base of tHe pin, and the portion of the hole facing away from the pin has a diameter slightly larger than the extremity of the pin, the extremity of the pin lying within the larger portion of the hole in the first state and lying within the smaller portion of the hole in the second state.

10. An aircraft control system comprising:

an aircraft frame;

a first source of command signals for controlling the aircraft in one mode;

a second source of command signals for controlling the aircraft in another mode;

a servoactuator;

means for alternatively connecting the first and second sources to the servoactuator;

a first member supported to move relative to the frame responsive to the servoactuator;

an aircraft control surface coupled to the first member such that the control surface is controlled as the first member moves relative to the frame;

a pilot operated input device;

a second member supported to move relative to the frame responsive to the pilot operated input device;

means for coupling the first and second members to move together relative to the frame without appreciable play when the first source is connected to the servoactuator; and

means for disengaging the coupling means to permit independent movement of the first and second members relative to the frame within predetermined limits when the second source is connected to the servoactuator, the members moving together after the predetermined limits are reached.

11. The control system of claim 10, in which the displacement between the first and second members from a null position is sensed and the first member moves responsive to the sensed displacement as well as the first source so the first member follows the pilot operated input device when the coupling means are disengaged.

12. A control system comprising:

a stationary frame;

a first input device that produces an indication of a command;

a first member supported to move relative to the frame;

a device to be controlled coupled to the first member such that the device is controlled as the first member moves relative to the frame;

a second input device that produces an indication of a command;

a second member supported to move relative to the frame responsive to the second input device, the second member being movable independently of the first member;

means for indicating the displacement between the first and second members from a null position;

means for combining the indications of the first input device and the displacement indicating means; and

means responsive to the combining means for moving the first member in a sense to reduce the difference between the indications.

13. The control system of claim 12, in which means are provided for coupling the first and second members to move together relative to the frame without appreciable play and means are provided for disengaging the coupling means to permit independent movement of the first and second members relative to the frame.

14. A control system comprising:

a stationary frame;

a first input source;

a first force transmitting member;

means for connecting the first input source to the first force transmitting member to move the first force transmitting member relative to the frame responsive to the first input source;

a device to be controlled connected to the first force transmitting member such that the device is controlled as the first force transmitting member moves relative to the frame;

a second input source;

a second force transmitting member;

means for connecting the second input source to the second force transmitting member to move the second member relative to the frame responsive to the second input source;

a mechanical coupling device between the first and second force transmitting members that is capable of assuming either a first state or a second state, the members being coupled in the first state to move independently relative to the frame within predetermined limits and being coupled in the second state to move together relative to the frame; and

means for disengaging the connecting means between the first input source and the first member when the relative movement between the first and second members reaches the predetermined limit.

15. The control system of claim 14, in which the connecting means between the first input source and the first member is a clutch.

16. The control system of claim 14, in which the coupling device couples the first and second members in the first state so they move together beyond the predetermined limits.

17. The control system of claim 16, in which the displacement between the first and second members from a null position is sensed and the first input source represents the sensed displacement so as to return the first member to the null position relative to the second member.

18. The control system of claim 14, in which the coupling changes from the first state to the second state when the relative movement between the first and second members reaches the predetermined limit.

19. A yaw axis control system for an aircraft comprising:

a stability augmentation system for generating an electrical signal to control the course of the aircraft;

a servoactuator;

a first force transmitting mechanism supported to move relative to the frame of the aircraft in response to the servoactuator;

a pilot operated input device;

a second force transmitting mechanism supported to move relative to the frame of the aircraft in response to the pilot operated input device;

mechanical coupling means between the first and second mechanisms capable of assuming either a first state or a second state, the mechanisms being coupled in the first state to move independently relative to the frame and being coupled in the second state to move together relative to the frame;

an automatic maneuver system for generating electrical signals to control the course of the aircraft during landing;

means for connecting the stability augmentation system to the input of the servoactuator while the coupling means is in the first state; and

means for connecting the automatic maneuver system to the input of the servoactuator while the coupling means is in the second state.

20. The control system of claim 19, in which a transducer produces a signal representing the displacement between the first and second mechanisms from a null position and transducer is also connected to the input of the servoactuator so the servoactuator operates responsive to the combination of the transducer signal and the stability augmentation system signal to reduce the combination.

21. The control system of claim 20, in which the mechanisms are coupled to move independently relative to the frame in the first state within predetermined limits beyond which they move together relative to the frame.

22. The control system of claim 19, in which the mechanisms are coupled to move independently relative to the frame in the first state within predetermined limits beyond which they move together relative to the frame.