Built-in passive fault detection circuitry for an aircraft's electrical/electronic systems
First Claim
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.
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Accused Products
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.
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Citations
9 Claims
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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:
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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. - View Dependent Claims (2, 3, 4, 5, 6)
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7. An aircraft electrical/electronic system having a built-in test apparatus, comprising in combination:
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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. - View Dependent Claims (8, 9)
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Specification