Flight control system

• US 5,908,177 A
• Filed: 05/30/1996
• Issued: 06/01/1999
• Est. Priority Date: 07/12/1995
• Status: Expired due to Term

• Current Assignee: Yasunari Tanaka
• Original Assignee: Yasunari Tanaka
• Inventors: Tanaka, Yasunari
• Primary Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/652,697
• Time in Patent Office: 1,097 Days
• Field of Search: 244/75 R, 244/87, 244/90 R, 244/221, 244/223, 244/227, 244/228, 244/232, 244/236
• US Class Current: 244/223
• CPC Class Codes: B64C 13/507 with artificial feel

Abstract

Herein disclosed is a flight control system comprising a control member, a control surface controllable to assume different angle positions within a control angle range, a transmission linkage provided between the control member and the control surface to transmit the control force from the control member to the control surface, and a power assist actuator associated with the control member and the transmission linkage to control the control surface. The flight control system further comprises a force sensor provided between a pivot portion of the control member and a support portion of the aircraft to detect a reaction force exerted thereon by the control member and the transmission linkage, and assist force regulating means for regulating the assist force from the power assist actuator to be proportional to the control force from the control member in response to the output signal of the force sensor, thereby making it possible to give an operational feeling corresponding to the detected reaction force to the pilot without providing an artificial feeling apparatus in spite of the fact that the control surface is controlled by the power assist actuator and the human power under the normal condition.

Claims

1. A flight control system for controlling a flight of an aircraft, comprising:

a control member having an input portion, a pivot portion and a control force output portion, said input portion of said control force output portion pivotally move around said pivot portion;

a control surface pivotally mounted at its hinge portion on said aircraft and controllable to assume different angle positions within a control angle range, said control surface being controlled by the control force outputted from said control member;

a transmission linkage provided between said control force output portion of said control member and said control surface to transmit said control force from said control member to said control surface;

a power assist actuator associated with said control member and said transmission linkage to control said control surface with an assist force, said power assist actuator being constituted by a motor connected to the hinge portion of the control surface to output an assist torque in response to the reaction force detected by said force sensor;

a force sensor provided between said pivot portion of said control member and said aircraft to detect a reaction force exerted thereon by said control member and said transmission linkage, said force sensor producing an output signal representative of said reaction force; and

force regulating means for regulating the assist force outputted from said power assist actuator as to be proportional to the control force from said control member in response to said output signal outputted from said force sensor;

wherein the assist torque from the motor is regulated to be less than the operation torque applied to said hinge portion of said control surface from said control member when said predetermined maximum value of said reaction force is detected by said force sensor.

2. A flight control system as set forth in claim 1, in which said force sensor is constituted by a link member pivotally connected at one end with said pivot portion of said control member and at the other end with said aircraft, and a strain gauge attached on said link member to detect a force exerted on the link member by said control member and said transmission linkage.

3. A flight control system as set forth in claim 1, in which said transmission linkage is constituted by a first pulley rotatably supported by said aircraft, a connecting link pivotally connected at one end to said operation force output portion of said control member and at the other end with the peripheral portion of said first pulley, an endless member encircling said first pulley, a second pulley connected with said hinge portion of said control surface and driven by said first pulley through said endless member when said control member is manually operated.

4. A flight control system as set forth in claim 1, which further comprises a surface angle sensor for detecting the angle position of said control surface and outputting an output signal, and in which said force regulating means regulates said assist force outputted from said power assist actuator on the basis of the output signal of said surface angle sensor.

5. A flight control system for controlling a flight of an aircraft, comprising:

a control member having an input portion, a pivot portion and a control force output portion, said input portion of said control force output portion pivotally move around said pivot portion;

a control surface pivotally mounted at its hinge portion on said aircraft and controllable to assume different angle positions within a control angle range, said control surface being controlled by the control force outputted from said control member;

a transmission linkage provided between said control force output portion of said control member and said control surface to transmit said control force from said control member to said control surface;

a power assist actuator associated with said control member and said transmission linkage to control said control surface with an assist force, comprising a motor connected to the hinge portion of the control surface to output an assist torque in response to the reaction force detected by said force sensor;

a force sensor provided between said pivot portion of said control member and said aircraft to detect a reaction force exerted thereon by said control member and said transmission linkage, said force sensor producing an output signal representative of said reaction force;

force regulating means for regulating the assist force outputted from said power assist actuator as to be proportional to the control force from said control member in response to said output signal outputted from said force sensor;

and a motor angle sensor for detecting the angle position of said motor and outputting an output signal, and in which said force regulating means regulates said assist force outputted from said power assist actuator on the basis of the output signal of said motor angle sensor.