Crack detecting means for rotor blades of rotary wing aircrafts

• US 4,026,660 A
• Filed: 04/13/1976
• Issued: 05/31/1977
• Est. Priority Date: 04/15/1975
• Status: Expired due to Term

• Current Assignee: Kawasaki Jukogyo Kabushiki Kaisha (Kawasaki Heavy Industries Limited)
• Original Assignee: Kawasaki Jukogyo Kabushiki Kaisha (Kawasaki Heavy Industries Limited)
• Inventors: Ueda, Kazuo, Kanayama, Kazunori, Arima, Takao
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/676,496
• Time in Patent Office: 413 Days
• Field of Search: 416/61, 416/226, 340/248 E, 340/248 F
• US Class Current: 416/61
• CPC Class Codes: B64C 27/007 adapted for detection of blade cracks

Abstract

Rotary wing aircrafts include one or more rotors having a plurality of rotary blades. Each of the rotor blades has crack sensor in the form of an induction coil or conductive wire. The crack sensor is connected with a further induction coil to form a circuit of which inductance is changed when a crack is produced in the associated rotor blade. On a stationary part such as a stationary swash plate of the rotorcraft, there is provided a stationary induction coil which is brought into cyclical and electromagnetical co-operation with the further induction coil on the rotor as the rotor rotates. The stationary induction coil is connected with a load resistor and an oscillator in such a way that cracks in the rotor blades can be detected in the form of a voltage change at the load resistor.

Claims

1. In rotary wing aircrafts including a stationary part and at least one rotor assembly having plurality of rotor blades, means for detecting cracks in the rotor blades, said detecting means comprising crack sensing means associated with each rotor blade so as to provide a change in an electrical property when a crack is produced in the rotor blade, first induction means provided on the rotor at least one for each rotor blade and connected with said crack sensing means to form circuit means of which impedance is changed in accordance with the change in the electrical property in the crack sensing means, second induction means provided on said stationary part of the rotary wing aircraft and adapted to cooperate with said first induction means, means for applying alternating power to one of the first and the second induction means to produce an output signal at the second induction means, means for discriminating the output signal of the second induction means to determine whether there is a crack in the rotor blade.

2. The crack detecting means in accordance with claim 1 in which said discriminating means comprises comparison circuit means for comparing the output signal corresponding to one of the rotor blades with that corresponding to another rotor blade.

3. The crack detecting means in accordance with claim 1 in which said crack sensing means includes induction coil means of which inductance is changed when a crack is produced in the associated rotor blade.

4. The crack detecting means in accordance with claim 1 in which said crack sensing means includes electrically conductive wire means which is attached to each rotor blade and adapted to be broken when a crack is produced in the associated rotor blade.

5. The crack detecting means in accordance with claim 1 which further includes counting means for producing an output signal when a predetermined number of crack signal is received.

7. The crack detecting means in accordance with claim 1 which includes only one second induction means which is adapted to co-operate with all of the first induction means.

8. The crack detecting means in accordance with claim 1 which includes a plurality of second induction means, one for each first induction means, said second induction means being so arranged with respect to the first induction means that each second induction means co-operates to only associated one of the first induction means, so as to exclude any influence from the other first induction means.

9. The crack detecting means in accordance with claim 1 which includes a plurality of second induction means, one for each first induction means, gate means being provided for each of the second induction means so as to allow output signals which have been produced under influence of the associated first induction means only, but block any signals which have been produced under influence of the other first induction means.

6. In tandem rotor type rotary wing aircrafts including a stationary part and two rotor assemblies each having a plurality of rotor blades, means for detecting cracks in the rotor blades, said detecting means comprising crack sensing means associated with each rotor blade so as to provide a change in an electrical property when a crack is produced in the rotor blade, first induction means provided on the rotor at least one for each rotor blade and connected with said crack sensing means to form circuit means of which impedance is changed in accordance with the change in the electrical property in the crack sensing means, second induction means provided on said stationary part of the rotary wing aircraft and adapted to co-operate with said first induction means, means for applying alternating power to one of the first and the second induction means to produce an output signal at the second induction means, comparison circuit means for comparing the output signals corresponding to the rotor blades in one of the rotor assemblies with those corresponding to the rotor blades in the other rotor assembly to determine whether there is a crack in any of the rotor blades.