Aircraft equipment configuration identification interface

• US 5,997,360 A
• Filed: 05/22/1998
• Issued: 12/07/1999
• Est. Priority Date: 10/14/1997
• Status: Expired due to Term

• Current Assignee: Vibro-Meter, SA (Meggitt PLC)
• Original Assignee: Endevco Corporation (Illinois Tool Works Inc.)
• Inventors: Karolys, Alexis Gabriel, Gen-Kuong, Fernando Francisco
• Primary Examiner(s): Abrams, Neil
• Application Number:
  US09/083,598
• Time in Patent Office: 564 Days
• Field of Search: 439/489, 439/188, 439/680, 439/681, 439/955, 439/700
• US Class Current: 439/700
• CPC Class Codes: G01H 1/003 of rotating machines G01H1/10 takes precedence
• CPC Class Codes: G01M 15/12 by monitoring vibrations
• CPC Class Codes: H01R 13/6453 comprising pin-shaped elements, capable of being orientated in different angular positions around their own longitudinal axes, e.g. pins with hexagonal base
• CPC Class Codes: H01R 13/6616 with resistor
• CPC Class Codes: H01R 13/6683 with built-in sensor
• CPC Class Codes: H01R 31/065 with built-in electric apparatus
• CPC Class Codes: Y10S 439/955 including electronic identifier or coding means

Abstract

In accordance with the present invention, an aircraft instrumentation interface for use with at least one electrically conductive mechanical key disposed in an interface connector and has an orientation specific to a particular type of aircraft equipment configuration. The interface is provided with a key engagement member which is formed to electrically engage the mechanical key for sensing the angular orientation of the mechanical key. The interface is further provided with an aircraft equipment configuration sensor for identifying the aircraft equipment configuration type in response to sensed orientation of the mechanical key and for generating an electrical signal in response to the identification of the orientation of the mechanical key.

Claims

1. An aircraft instrumentation interface, used with at least one electrically conductive mechanical key disposed in an interface connector, the mechanical key having an orientation specific to a particular type of aircraft equipment configuration, the interface comprising:

a key engagement member formed to electrically engage the mechanical key for sensing the angular orientation of the mechanical key; and

an aircraft equipment configuration sensor for identifying the aircraft equipment configuration type in response to sensed orientation of the mechanical key and for generating an electrical signal in response to the identification of the orientation of the mechanical key.

2. The interface of claim 1 wherein the key engagement member comprises at least one electrical contact surface, the electrical contact surface defined by the orientation of the mechanical key when the key engagement member is engaged with the mechanical key, the aircraft equipment configuration sensor being in electrical communication with the electrical contact surface.

3. The interface of claim 2 wherein the key engagement member further comprises at least one electrically conductive pin.

4. The interface of claim 3 wherein the at least one electrically conductive pin comprises multiple pins.

5. The interface of claim 3 wherein the pin being deflectable with respect to the mechanical key when the mechanical key is engaged with the key engagement member for facilitating electrical engagement of the mechanical key with the pin.

6. The interface of claim 3 wherein each pin having a shaft portion and a tip portion with the electrical contact surface disposed thereat.

7. The interface of claim 6 wherein the shaft portion and the tip portion of each pin being flexibly connected to each other, deflection of the tip portion relative to the shaft portion facilitates electrical engagement of the mechanical key with the tip portion when the mechanical key is engaged with the key engagement member.

8. The interface of claim 7 wherein each pin further comprises a spring flexibly connecting the shaft portion and the tip portion to each other, deflection of the spring facilitates deflection of the tip portion relative to the shaft portion facilitates electrical engagement of the mechanical key with the tip portion when the mechanical key is engaged with the key engagement member.

9. The interface of claim 7 wherein the tip portion comprises a spring, deflection of the tip portion relative to the shaft portion facilitates electrical engagement of the mechanical key with the tip portion when the mechanical key is engaged with the key engagement member.

10. The interface of claim 2 wherein the aircraft equipment configuration sensor comprises identification circuitry in electrical communication with the electrical contact surface for identifying the position of the electrical contact surface and for generating an electrical signal in response to the identification of the position of the electrical contact surface.

11. The interface of claim 1 wherein the identification circuitry comprises a microprocessor formed to receive the electrical signal from the aircraft equipment configuration sensor for correlating the electrical signal to aircraft equipment configuration specific test sequence data.

12. The interface of claim 1 wherein the interface comprises a connector.

13. The interface of claim 12 wherein the interface comprises a female connector.

14. The interface of claim 1 wherein the mechanical key further having a geometry specific to a particular type of aircraft equipment configuration, wherein the key engagement member comprises at least one electrical contact surface, the electrical contact surface defined by the geometry of the mechanical key when the key engagement member is engaged with the mechanical key, the aircraft equipment configuration sensor being in electrical communication with the electrical contact surface.

15. The interface of claim 14 wherein the aircraft equipment configuration sensor comprises identification circuitry in electrical communication with the electrical contact surface for identifying the position of the electrical contact surface and for generating an electrical signal in response to the identification of the position of the electrical contact surface.

16. An aircraft instrumentation interface, used with at least one electrically conductive mechanical key disposed in an interface connector, the mechanical key having a geometry specific to a particular type of aircraft equipment configuration, the interface comprising:

a key engagement member formed to electrically engage the mechanical key for sensing the geometry of the mechanical key; and

an aircraft equipment configuration sensor for identifying the aircraft equipment configuration type in response to sensed geometry of the mechanical key and for generating an electrical signal in response to the identification of the geometry of the mechanical key.

17. The interface of claim 16 wherein the key engagement member comprises at least one electrical contact surface, the electrical contact surface defined by the geometry of the mechanical key when the key engagement member is engaged with the mechanical key, the aircraft equipment configuration sensor being in electrical communication with the electrical contact surface.

18. The interface of claim 17 wherein the key engagement member further comprises at least one electrically conductive pin.

19. The interface of claim 18 wherein the aircraft equipment configuration sensor comprises identification circuitry in electrical communication with the electrical contact surface for identifying the position of the electrical contact surface and for generating an electrical signal in response to the identification of the position of the electrical contact surface.

20. A method of identifying the type of aircraft equipment configuration connected to an instrumentation interface connector having an electrically conductive mechanical key, the mechanical key having an orientation specific to a particular type of aircraft equipment configuration, the method comprising the steps of:

(a) providing a key engagement member formed to electrically engage the mechanical key; and

(b) sensing the orientation of the mechanical key by electrically engaging the mechanical key with the key engagement member.

21. The method of claim 20 wherein the key engagement member comprises at least one electrical contact surface defined by the orientation of the mechanical key when the key engagement member is engaged with the mechanical key, wherein step (b) the orientation of the mechanical key is sensed by identifying of the position of the electrical contact surface.

22. The method of claim 21 further comprising the step of:

(c) generating an electrical signal representative of the sensed orientation of the mechanical key corresponding to a particular type of aircraft equipment configuration.

23. The method of claim 22 further comprising the step of:

(d) correlating the electrical signal to aircraft equipment configuration specific test sequence data.

24. The method of claim 20 wherein the mechanical key further having a geometry specific to a particular type of aircraft equipment configuration, wherein the key engagement member comprises at least one electrical contact surface defined by the geometry of the mechanical key when the key engagement member is engaged with the mechanical key.

25. A method of identifying the type of aircraft equipment configuration connected to an instrumentation interface connector having an electrically conductive mechanical key, the mechanical key having a geometry specific to a particular type of aircraft equipment configuration, the method comprising the steps of:

(a) providing a key engagement member formed to electrically engage the mechanical key; and

(b) sensing the geometry of the mechanical key by electrically engaging the mechanical key with the key engagement member.

26. The method of claim 25 wherein the key engagement member comprises at least one electrical contact surface defined by the geometry of the mechanical key when the key engagement member is engaged with the mechanical key, wherein step (b) the geometry of the mechanical key is sensed by identifying of the position of the electrical contact surface.

27. The method of claim 26 further comprising the step of:

(c) generating an electrical signal representative of the sensed geometry of the mechanical key corresponding to a particular type of aircraft equipment configuration.

28. The method of claim 27 further comprising the step of:

(d) correlating the electrical signal to aircraft equipment configuration specific test sequence data.