Aircraft controls simulator

• US 4,713,007 A
• Filed: 10/11/1985
• Issued: 12/15/1987
• Est. Priority Date: 10/11/1985
• Status: Expired due to Fees

• Current Assignee: Eugene P. Alban
• Original Assignee: Eugene P. Alban
• Inventors: Alban, Eugene P.
• Primary Examiner(s): Picard, Leo P.
• Application Number:
  US06/786,871
• Time in Patent Office: 795 Days
• Field of Search: 434/20, 434/30, 434/43, 434/44, 434/45, 273/DIG. 28, 244/233, 244/228
• US Class Current: 463/37
• CPC Class Codes: G06F 3/0334 Foot operated pointing devices
• CPC Class Codes: G09B 9/28 Simulation of stick forces or the like

Abstract

An aircraft controls simulator, for use with a computer programmed for aircraft flight simulation, having a yoke, a throttle control and a rudder control. A cabinet has a shaft extending therefrom attached to a simulated yoke control. The shaft operates an elevator potentiometer responsive to horizontal movement of the shaft and an aileron control responsive to rotation of the shaft. A throttle knob connected to a second shaft operates a throttle potentiometer. A foot operated potentiometer produces rudder control signals. A cable connects the potentiometers to the computer which utilizes the potentiometer positions to operate the flight simulation program.

Claims

1. A simulated aircraft control system for providing input signals to computer flight simulation programs to thereby produce graphic flight simulation displays on a personal computer screen comprising:

a chassis having a first bracket disposed vertically and attached thereto;

a first electrical potentiometer having a control shaft and attached to said chassis

a simulated aircraft yoke control having a yoke shaft projecting therefrom, said shaft supported in a horizontal position by said first bracket, and rotatable and movable horizontally with respect to said first bracket by said yoke control;

a second electrical potentiometer having a control shaft, said control shaft directly connected to said yoke shaft, said second potentiometer having a second bracket disposed horizontally and attached thereto, said second bracket and said second potentiometer movable horizontally by said yoke shaft, said second bracket including means for preventing said second bracket from rotating when said yoke control and yoke shaft are rotated thereby causing rotation of said yoke shaft to operate said second potentiometer; and

first coupling means for coupling said second bracket to said control shaft of said first potentiometer for rotating same when said second bracket is moved horizontally.

2. The system as defined in claim 1 which further comprises:

a third bracket disposed vertically and attached to said chassis;

a simulated aircraft throttle knob having a throttle shaft projecting therefrom, said throttle shaft supported by said third bracket in a horizontal position and movable horizontally by said knob;

a third electrical potentiometer having a control shaft and attached to said chassis; and

second coupling means for coupling said throttle shaft to said control shaft of said third electrical potentiometer for rotating same when said throttle shaft is moved horizontally by said knob.

3. The system as defined in claim 2 which further comprises:

a second chassis disposed adjacent said first chassis;

a fourth electrical potentiometer having a control shaft and attached to said second chassis;

a pair of foot pedals attached and rotatable with respect to said second chassis;

third coupling means for coupling said foot pedals to said fourth potentiometer control shaft for rotation thereof; and

an electrical cable connected to said first, second, third and fourth potentiometers for connecting same to an electrical plug, said plug adapted to connect to a computer for permitting control of a flight simulation computer program.

4. The system as defined in claim 2 which further comprises:

a fourth electrical potentiometer attached to said chassis and having a rotatable control shaft; and

a rudder control knob attached to said fourth potentiometer control shaft for rotation of said fourth potentiometer for simulation of an aircraft rudder control.

5. The system as defined in claim 2 in which said second coupling means includes:

a horizontal lever arm attached to said third potentiometer control shaft for rotating same;

a vertically oriented fork attached to said throttle shaft, said lever arm being captivated by said fork to cause horizontal motion of said throttle shaft to rotate said third potentiometer control shaft.

6. The system as defined in claim 1 which further comprises:

first biasing means coupled to said first bracket and said second potentiometer for centering said first potentiometer in a preselected neutral position and for simulating aircraft elevator control forces on said yoke control; and

second biasing means coupled to said second bracket and said yoke shaft for centering said second potentiometer in a preselected neutral position and for simulating aircraft aileron control forces on said yoke control.

7. The system as defined in claim 6 in which:

said first biasing means is a compression spring disposed between said first bracket and said second potentiometer; and

said second biasing means is a torsion spring disposed between said yoke shaft and said second bracket.

8. The system as defined in claim 1 in which said first coupling means includes:

a first horizontal lever arm attached to said first potentiometer control shaft for rotating same; and

said second bracket having a vertical slot therein, said slot adapted to engage said first lever arm whereby horizontal movement of said second bracket causes rotation of said first potentiometer control shaft.

9. In a system ahving a computer programmed to provide an operator with graphical display simulation of aircraft flight in which variable output voltages represent movement of aircraft ailerons, elevators, rudder and throttle, apparatus for providing the operator with simulated aircraft controls therefor comprising:

(a) a chassis having a front panel;

(b) means for simulating an aircraft yoke control, said means including

(i) a first shaft projecting from said panel,

(ii) a yoke attached to said first shaft for moving said first shaft horizontally to a simulate control of elevators and rotating said first shaft to simulate control of ailerons;

(iii) a first potentiometer having a control element operatively coupled to said first shaft and to a source of voltage, said first potentiometer adapted to cause its said control element to rotate when said first shaft is rotated thereby producing an aileron control voltage to said computer,

(iv) a second potentiometer having a control element operatively coupled to said first shaft and to a source of voltage, said second potentiometer adapted to cause its said control element to rotate when said first shaft is moved horizontally thereby producing an elevator control voltage to said computer,

(c) means for simulating a throttle control, said means including

(i) a second shaft projecting from said panel,

(ii) a knob attached to said second shaft for moving said shaft horizontally,

(iii) a third potentiometer having a control element operatively coupled to said second shaft and to a source of voltage, said third potentiometer adapted to cause its said control element to rotate when said second shaft is moved horizontally, thereby producing a throttle control voltage to said computer,

(d) means for simulating a rudder control, said means including

(i) a fourth potentiometer mounted to said panel and coupled to a source of voltage, said fourth potentiometer having a control element,

(ii) a rudder knob coupled to said fourth potentiometer control element for rotation by an operator to thereby produce a rudder control voltage to said computer; and

(e) a multiconductor electrical cable connected to said first, second, third and fourth potentiometers at a first end thereof and an electrical connector connected to the other end thereof for connecting to said computer, said cable for providing said voltages to said potentiometers and for communicating said aileron, elevator, throttle and rudder control voltages to said computer.

10. In a personal computer programmed to simulate flight of an aircraft, an input device for manual operation by a user to simulate aileron and elevator control of the aircraft comprising:

a chassis;

an aircraft type control yoke having a horizontally disposed yoke shaft, said yoke shaft attached to said chassis so as to be movable horizontally fore and aft with respect to said chassis and rotatable clockwise and counterclockwise;

an aileron potentiometer having a first body portion and a first rotatable wiper portion, said aileron potentiometer operatively coupled to said yoke shaft and having an input electrically connected to a voltage source and a first variable voltage output controlled by rotation of said first wiper by said yoke shaft, said aileron potentiometer moving fore and aft when said yoke shaft is moved fore and aft;

means attached to said chassis and coupled to said aileron potentiometer to prevent said first body portion thereof from rotating when said yoke shaft is rotated thereby causing rotation of said first wiper;

an elevator potentiometer having a second body portion and a second rotatable wiper, said second body portion attached to said chassis, said elevator potentiometer having an input electrically connected to said voltage source and a second variable voltage output controlled by rotation of said second wiper;

coupling means attached to said yoke shaft and to said elevator potentiometer for rotating said second wiper when said yoke shaft moves horizontally fore and aft; and

electrical connection means for coupling said first and second variable voltage outputs to said computer.