Mechanically linked active sidesticks

• US 5,456,428 A
• Filed: 07/21/1993
• Issued: 10/10/1995
• Est. Priority Date: 07/21/1993
• Status: Expired due to Fees

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Hegg, Jeffrey W.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/095,870
• Time in Patent Office: 811 Days
• Field of Search: 244/194, 244/195, 244/197, 244/228, 244/229, 244/234, 244/235, 244/336, 244/17.13
• US Class Current: 244/229
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: B64C 13/10 comprising warning devices
• CPC Class Codes: B64C 13/12 Dual control apparatus
• CPC Class Codes: B64C 13/30 using cable, chain, or rod mechanisms
• CPC Class Codes: B64C 13/503 Fly-by-Wire
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: G05G 2009/04766 providing feel, e.g. indexing means, means to create counterforce
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Conventional column controls for aircraft flight control systems are replaced by active sidesticks which are connected to port and starboard aircraft mechanical, electrical or hydraulic systems by means of servo motors and cables. Movement of the active sidestick handles is detected and a signal generated to drive a servo motor in manner corresponding thereto, which in turn will drive cable assemblies which control aircraft flight control surfaces. Two sidesticks are provided, preferably with an electrical cross-cockpit interconnect to cause movement of one sidestick to result in a signal being transmitted to a second sidestick to cause the motor thereof to force the sidestick to track the movement of the first sidestick. In an alternative implementation, the sidesticks are employed in a fly-by-wire system with a conventional cable system as backup. The cable system is disengaged from the sidesticks by means of a disengage clutch whereupon failure of the fly-by-wire system, the clutch will engage the cable system and provide a mechanical backup to the fly-by-wire system in the event of failure thereof.

Claims

1. An active hand controller system comprising:

first and second active control handles each moveable along a pitch axis (x) and a roll axis (y), each of the first and second handles including;

sensor means for detecting movement of and force applied to the respective first and second active control handle along said pitch axis (x) and said roll axis (y) for generating a signal representative of said movement and force applied thereto;

control electronics means for receiving said signal from said sensor means and for generating a control signal in response thereto representative of the movement and force applied to the respective first and second active control handle, the control electronics means of the respective first and second control handles being coupled to one another; and

at least one servo motor connected to each of the pitch and roll axes of each of the first and second active control handles and to respective cable linkages connected to an aircraft flight control system, the servo motors being further connected to said control electronic means for moving said cable linkages in response to the control signal received from said control electronic means as a result of any one of the first and second active control handles being actuated by a user along at least one of said pitch axis (x) and said roll axis (y), the control signal being further communicated to the control electronics means of the first and second control handle unactuated by a user such that the servo motors of the unactuated first and second control handle cause movement of the unactuated control handle in concert with the control handle actuated by a user.

2. A system as in claim 1 further comprising electronic disconnect means for selectively electrically disconnecting one of said first and second active control handles from the other of said first and second active control handles for preventing signals generated by the corresponding sensor means of said one of said first and second active control handles as a result of movement thereof from being reflected in the control signal received by the corresponding control electronics of the other of said first and second active control handles.

3. A system as in claim 1 further comprising mechanical connection means for mechanically connecting the cable linkages of the respective first and second active control handles to ensure said cable linkages operate together as a single unit.

4. A system as in claim 3 further comprising mechanical and electrical disconnect means for selectively disconnecting said mechanical connection means and the control electronics means of the first and second active control handles, respectively, to allow each cable linkage to operate independently of the other.

5. A system as in claim 1 wherein the control electronics means of each of the first and second active control handles generates a further control signal in response to the signal received from the sensor means of the respective first and second control handle, the further control signal being transmitted to a fly-by-wire flight control system for control thereof.