Aircraft engine deactivation apparatus

• US 5,074,488 A
• Filed: 05/23/1990
• Issued: 12/24/1991
• Est. Priority Date: 05/23/1990
• Status: Expired due to Fees

• Current Assignee: Colling, Robert E.
• Original Assignee: Colling, Robert E.
• Inventors: Colling, Robert E.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US07/527,317
• Time in Patent Office: 580 Days
• Field of Search: 340/904, 340/942, 340/943, 340/945, 340/958, 340/426, 244/76 R, 244/1 R, 244/53 R, 244/121, 180/279, 440/1
• US Class Current: 244/1.00R
• CPC Class Codes: G08G 5/0078 for monitoring traffic from the aircraft radar or analogous systems specially adapted for traffic control G01S13/91
• CPC Class Codes: G08G 5/065 Navigation or guidance aids, e.g. for taxiing or rolling

Abstract

Aircraft engine deactivation apparatus for stopping an aircraft engine while the aircraft is on the ground. The apparatus is for safety purposes and is used to prevent a detected object from coming into contact with an engine driven propeller or a jet propulsion intake. A detector, preferably an infra-red radiation sensor, detects an object or person within a selected distance and within a seleced area about the engine. Upon detection, a mechanical engine deactivator, such as brake calipers engageable with the engine flywheel, or an electronic deactivator, such as an electronic switch operable to ground magnetos, shuts down the engine. A by-pass switch renders the system inoperable, when desired.

Claims

1. Safety apparatus for stopping an engine on a propeller driven aircraft comprising:

detector means mounted on the aircraft for detecting an object within a selected distance from the engine; and

engine deactivation means controlled by said detector means for stopping an engine upon detection of an object within said selected distance.

2. The apparatus as described in claim 1 further comprising a detector override switch for preventing engine deactivation by said detector means.

3. The apparatus as described in claim 1 wherein said detector means comprises at least one infra-red radiation detector for receiving infra-red radiation from an object.

4. The apparatus as described in claim 1 further comprising a radio wave transmitter and wherein said detector means comprises a radio wave receiver for receiving radio waves emitted from the transmitter and reflected by an object.

5. The apparatus as described in claim 1 further comprising an acoustic wave transmitter and wherein said detector means comprises an acoustic wave receiver for receiving acoustic waves reflected by the object.

6. The apparatus as described in claim 1 wherein the engine includes a flywheel and wherein said engine deactivation means comprises hydraulic brake calipers engageable with the flywheel upon actuation by said detector means to stop the engine.

7. The apparatus as described in claim 1 wherein said aircraft is provided with at least one magneto and wherein said engine deactivation means includes an electronic switch operable to ground said magneto upon activation by said detector means

8. Safety apparatus for stopping an engine on a propeller driven aircraft, said apparatus comprising:

at least one infra-red radiation detector mounted on the aircraft and directed to an area adjacent the propeller;

a solenoid actuated by said detector; and

brake means controlled by said solenoid to deactivate the engine upon the sensing of an object by said detector.

9. The apparatus as described in claim 8 further comprising an override switch operable to prevent actuation of said brake means by said detector.