Helicopter blade crack indicator

• US 3,985,318 A
• Filed: 11/14/1975
• Issued: 10/12/1976
• Est. Priority Date: 11/14/1975
• Status: Expired due to Term

• Current Assignee: Tyco Laboratories, Inc. (Johnson Controls International plc)
• Original Assignee: Tyco Laboratories, Inc. (Johnson Controls International plc)
• Inventors: Mahoney, John J., Dominey, Sam C.
• Primary Examiner(s): Blix, Trygve M.
• Assistant Examiner(s): Barefoot, Galen L.
• Application Number:
  US05/631,833
• Time in Patent Office: 333 Days
• Field of Search: 244/17.11, 244/1 R, 244/17.13, 416/61, 416/226, 340/58, 340/416, 250/303, 250/497, 250/374, 250/360, 73/517 R, 73/146.4, 73/146.5, 116/70, 116/114 P
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/007 adapted for detection of blade cracks

Abstract

Method and apparatus for continuously detecting cracks in aircraft blades while in flight. A hollow blade is sealed with a pressure differential, either above or below atmospheric. A reduction in the pressure differential such as results from cracks, is detected by a pressure sensor having a member which moves between a high pressure differential position and a low pressure differential position. A radiation source, typically a beta source, is carried on the member and moves from a shielded position to an unshielded position when the pressure differential drops. A radiation detector is mounted on a fixed portion of the aircraft and detects radiation from the source when the member moves to the unshielded position. The detector output may be used to operate a go-no go indicator providing a warning signal when the pressure differential falls below a predetermined value, or to operate an analog indicator providing an output varying as a function of the pressure differential.

Claims

1. A system for indicating cracks in a hollow aircraft blade, wherein a pressure differential is maintained within the blade with respect to the ambient atmosphere, including in combination:

a pressure sensor adapted for mounting on the blade in communication with the interior of the blade,

said sensor including a member movable between a first position for a higher pressure differential and a second position for a lower pressure differential;

a radiation source mounted on said member;

a radiation shield positioned adjacent said member and having a radiation window, with said source disposed for radiation transmission through said window when said member is in said second position;

a radiation detector adapted for mounting on a non-rotating portion of the aircraft for receiving radiation from said source through said window; and

circuit means having the output of said detector as an input and providing an output varying as a function of the position of said member.

2. A system as defined in claim 1 wherein the pressure within the blade normally is above atmospheric pressure and said sensor functions to move said member from said first position to said second position when the pressure in the blade falls below a predetermined value.

3. A system as defined in claim 1 wherein the pressure within the blade normally is below atmospheric pressure and said sensor functions to move said member from said first position to said second position when the pressure in the blade rises above a predetermined value.

4. A system as defined in claim 1 wherein said shield comprises a cover for said member, formed of radiation absorbing material and having a thin wall section forming said window.

5. A system as defined in claim 4 wherein said cover has alternating opaque and transparent sections and said member has corresponding alternating sections of contrasting appearance,

with one of siad member sections disposed at said cover transparent sections when said member is in said first position, and with the other of said member sections disposed at said cover transparent sections when said member is in said second position.

6. A system as defined in claim 1 wherein said sensor includes manually actuable means for moving said member from said first position to said second position.

7. A system as defined in claim 1 wherein said circuit means includes:

an integrator having the detector pulse train as input and providing as output, a voltage level varying as a function of the pulse rate; and

a first comparitor having the integrator output as input and providing a warning signal as output when the integrator output exceeds a first predetermined value.

8. A system as defined in claim 7 wherein said circuit means includes a second comparitor having the integrator output as input and providing a safe signal as an output when the integrator output exceeds a second lower predetermined value.

9. A system as defined in claim 8 including an indicator unit operable between an first safe indicating condition and a second warning indicating condition, said indicator unit having said integrator output as inputs and providing said first condition when said second comparitor provides a safe signal and said first comparitor provides no signal, and providing said second condition when said second comparitor provides no signal and when said first comparitor provides a warning signal.

10. A system as defined in claim 7 including means responsive to a voltage for providing a visual indication and having the integrator output as input.

11. A system as defined in claim 1 wherein said circuit means includes:

an integrator having the detector pulse train as input and providing as output, a voltage level varying as a function of the pulse rate; and

means responsive to a voltage for providing a visual indication and having the integrator output as input.

12. A method of continuously indicating the condition of a hollow aircraft blade while in flight, including the steps of:

sealing the blade with a pressure differential therein with respect to the ambient atmosphere;

detecting a reduction in the pressure differential;

moving a radiation source on the blade between a shielded position for a higher pressure differential and an unshielded position for a lower pressure differential;

detecting radiation from the blade at a fixed location on the aircraft; and

providing a warning signal when the detected radiation increases.

13. A method as defined in claim 12 wherein the blade pressure is normally above atmospheric.

14. A method as defined in claim 12 wherein the blade pressure is normally below atmospheric.

15. A method as defined in claim 12 including providing the warning signal when the detected radiation exceeds a predetermined value.

16. A method as defined in claim 12 including providing the warning signal as an analog indication of the amount of detected radiation.