Built-in passive fault detection circuitry for an aircraft's electrical/electronic systems

• US 4,414,539 A
• Filed: 12/22/1978
• Issued: 11/08/1983
• Est. Priority Date: 12/22/1978
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Armer, James P.
• Primary Examiner(s): Crosland, Donnie L.
• Application Number:
  US05/972,501
• Time in Patent Office: 1,782 Days
• Field of Search: 340/500, 340/501, 340/506, 340/507, 340/509, 340/510, 340/511, 340/521, 340/522, 340/524, 340/27 R, 340/52 F, 340/514, 340/537, 340/650, 340/651, 340/652, 340/653 , 340/657, 340/661
• US Class Current: 340/500
• CPC Class Codes: G01R 31/008 on air- or spacecraft, railway rolling stock or sea-going vessels
• CPC Class Codes: G07C 5/0816 Indicating performance data, e.g. occurrence of a malfunction
• CPC Class Codes: G08B 19/00 Alarms responsive to two or more different undesired or abnormal conditions, e.g. burglary and fire, abnormal temperature and abnormal rate of flow

Abstract

Built-in test equipment (BITE) of the electrical/electronic systems of an aircraft is provided in-part by passive fault detection circuitry that is integrated into the electrical/electronic systems for continuous, in flight monitoring of line replaceable units (LRUs), such as temperature and pressure sensors. Both steady and intermittent failures of the LRU components are detected, and the type and location of each failure are identified and stored in a memory for continuous display or for subsequent recall by ground maintenance crews. The primary feature of the disclosed circuitry is its ability to detect and distinguish between an open impedance fault of a critical LRU component and an open wiring fault in the interconnect wiring that is associated with each component and is needed to electrically communicate signals developed at remotely mounted sensor components with a centralized controller, usually located in the avionics bay. To enable such differentiation between these two most frequent kinds of faults, each system component that is to be monitored is provided with one or more shunts having predetermined impedance relationships with the associated component so that an open component failure, when detected through the interconnect wiring, appears as a measurably different electrical condition than an open failure of the interconnected wiring which leads to that component. The capability of distinguishing between open component and open wiring faults minimizes the frequency at which LRUs incorporating critical components are simply replaced, without remedying the malfunction.

Claims

1. In a built-in test apparatus for an aircraft'"'"'s electrical/electronic system that has a plurality of LRUs each incorporating a nonswitching electrical LRU component, each of such LRU components havine an impedance within a predetermined range of finite, non-zero impedance values, and wherein the plurality of LRUs are mounted at diverse locations throughout the aircraft, and the electrical/electronic system has a plurality of electrical terminal means disposed at a central equipment bay and LRU-to-terminal interconnect wiring extending between said terminal means and associated LRUs for communicating non-test electrical control signals between individual terminal means and the associated LRU component, wherein the improvement in the built-in test apparatus comprises:

a plurality of passive test shunts each of which is permanently connected across an associated one of said plurality of LRU components so as to be physically part of the corresponding LRU and thus removable and replaceable as a unit with the associated LRU component, said test shunts each having an impedance selected to lie between a predetermined minimum and a predetermined maximum, said predetermined minimum impedance being substantially equal to or greater than the lowest impedance value of said predetermined range of values of the associated LRU component, and said predetermined maximum impedance being substantially less than a predetermined open wire impedance of the associated interconnect wiring so that an application of an associated one of said non-test electrical control signals to such associated LRU component over the interconnect wiring causes a first predetermined electrical condition at the associated terminal means when such LRU component and associated shunt and associated interconnect wiring are in an unfailed state, and causes a second predetermined electrical condition when such LRU component is in a failed open state and the associated interconnect wiring is in an unfailed state, and causes a third predetermined electrical condition when the associated interconnect wiring is in a failed open state;

fault detector means for detecting and distinguishing between said first, second and third predetermined electrical conditions at each of said terminal means, said detector means having first, second and third discrete electrical states, respectively representing unfailed states of one of said components and of its associated shunt and interconnect wiring, a failed open state of one of said components, and a failed open state of the associated interconnect wiring; and

coupling means for coupling said plurality of terminal means to said fault detector means so as to detect said electrical conditions at each of said terminal means.

2. In the built-in test apparatus of claim 1, wherein said interconnect wiring associated with each said LRU includes at least one connector means for disconnecting and reconnecting said interconnect wiring to said LRU component and its associated test shunt.

3. In a built-in test apparatus of claim 1, wherein said fault detector means comprises a common detection circuit that is common to said plurality of LRU components and associated test shunts and interconnect wiring, and wherein said means for coupling comprises:

a plurality of normalization circuit means, a different one of which is associated with each separate said LRU component, each said normalization circuit means having an input coupled to the terminal means of the associated LRU component and an output at which a normalized fault indicating electrical condition is produced in response to an unnormalized electrical condition at such terminal means; and

multiplexing means for sequentially and cyclically coupling said outputs of said plurality of normalization circuit means to said common detection circuit so as to sequentially monitor said electrical conditions at each of said terminal means.

4. In the built-in test apparatus of claim 3, wherein the improvement further comprises electrical condition storage means for individually storing a detected fault condition represented by either of said second or third electrical states of said detector means for each of said LRU components and associated interconnect wiring, and further comprising demultiplexing means for operating in synchronization with said multiplexing means and for sequentially and cyclically coupling said detection circuit to said electrical storage means so as to receive and store each occurrence of said second electrical state or third electrical state of said detector means for each said LRU component and its associated interconnect wiring.

5. In the built-in test apparatus of claim 1, wherein at least one of said LRU components comprises an impedance element having a variable impedance value that varies in a continuous manner within said predetermined range in response to an independently varying environmental condition on the aircraft.

6. In the built-in test apparatus of claim 1, wherein at least certain said interconnect wiring includes at least one connector of the pin and socket type, whereby such connector when fatigued by repeated use is prone to intermittent open faults.

7. An aircraft electrical/electronic system having a built-in test apparatus, comprising in combination:

a plurality of nonswitching electrical LRU components mounted at diverse locations throughout the aircraft, each of said LRU components having a non-zero impedance lying within a predetermined range of finite impedance values;

a plurality of electrical terminal means disposed at a central equipment bay;

LRU component-to-terminal interconnect wiring extending between said terminal means and associated ones of the LRU components of communicating non-test electrical control signals between individual terminal means and the associated LRU component;

a plurality of passive test shunts each of which is permanently connected across a separate, associated one of said plurality of LRU components, said test shunts each having an impedance selected to lie between a predetermined minimum and a predetermined maximum, said predetermined minimum impedance being substantially equal to or greater than the lowest impedance value of said predetermined range of values of the associated LRU component, and said predetermined maximum impedance being substantially less than a predetermined open wire impedance of the associated interconnect wiring so that an application of an associated one of said non-test electrical control signals to such associated LRU component over the interconnect wiring causes a first predetermined electrical condition at the associated terminal means when such LRU component and associated shunt and associated interconnect wiring are in an unfailed state, and causes a second predetermined electrical condition when such LRU component is in a failed open state and the associated interconnect wiring is in an unfailed state, and causes a third predetermined electrical condition when the associated interconnect wiring is in a failed open state;

common fault detector means for detecting failed open states of each of said components and of the associated interconnect wiring, said detector means having first, second and third discrete electrical states, respectively representing an unfailed state of one of said components and of its associated shunt and interconnect wiring, a failed open state of such one of said components, and a failed open state of the associated interconnect wiring; and

means for sequentially coupling said terminal means to said common fault detector means so as to successively monitor the electrical conditions at each of said terminal means, said means for sequentially coupling including a plurality of normalization circuit means, a different one of which is associated with each separate said LRU component, each said normalization circuit means having an input coupled to the terminal means of the associated LRU component and an output at which a normalized fault indicating electrical condition is produced in response to the electrical condition at such terminal means, said common fault detector means assuming said first state in response to the presence of said first, predetermined electrical condition at one of said terminal means, and assuming said second state in response to the occurrence of the second predetermined electrical condition at one of said terminal means, and assuming said third state in response to the occurrence of the third predetermined electrical condition at one of said terminal means.

8. In the built-in test apparatus of claim 7, wherein the improvement further comprises electrical condition storage means for individually storing a detected fault condition represented by either of said second or third electrical states of said detector means for each of said LRU components and associated interconnect wiring, and further comprising demultiplexing means for operating in synchronization with said multiplexing means and for sequentially and cyclically coupling said detection circuit to said electrical storage means so as to receive and store each occurrence of said second electrical state or third electrical state of said detector means for each said LRU component and its associated interconnect wiring.

9. In the built-in test apparatus of claim 7, wherein at least one of said LRU components comprises an impedance element having a variable impedance value that varies in a continuous manner within said predetermined range in response to an independently varying environmental condition on the aircraft.