Helicopter multi-engine controller redundancy power distribution circuit and control method

Abstract

The application belongs to the technical field of helicopter engine control system, and particularly relates to a helicopter multi-engine controller redundancy power distribution circuit and a control method, the circuit comprising a plurality of power supply bus bars and a plurality of power distribution modules, the plurality of power supply bus bars are connected with the input end of each power distribution module, the output end of each power distribution module is connected with a power contactor, an engine control switch is connected on each power contactor, the engine control switch controls each power contactor to be simultaneously linked, and the output end of each power contactor is connected with the engine controller, so that the phenomenon that a certain engine cannot be powered on due to single-point failure of a circuit breaker, a switch or a relay can be reduced, and the power distribution redundancy and reliability of the engine control system are improved.

Description

Technical Field

[0001] This invention belongs to the technical field of helicopter engine control systems, specifically relating to a redundant power distribution circuit and control method for a helicopter multi-engine controller. Background Technology

[0002] As the power source of a helicopter, engine failure is a catastrophic and extremely dangerous malfunction. Each engine is equipped with an engine controller, and each controller has at least two power supply redundancies. Currently, the power supply design of the engine control system mainly relies on a combination of components such as circuit breakers, switches, and relays. Single points of failure can easily arise in these components, reducing the redundancy of the engine controller's power distribution system and increasing the likelihood of power distribution system failures that could lead to engine malfunction.

[0003] To address the issue of single-point failures in the power distribution of engine controllers, a redundant and highly reliable power distribution circuit and method are needed for dual-engine and multi-engine helicopter engine controllers. This would reduce the occurrence of a single-point failure of a circuit breaker, switch, or relay causing an engine to fail to power on, thereby improving the redundancy and reliability of the engine control system. Summary of the Invention

[0004] The purpose of this invention is to solve the problem of single-point failure in the power distribution of engine controllers. This invention provides a redundant power distribution circuit and control method for helicopter multi-engine controllers, which can reduce the phenomenon of a certain engine failing to power on due to single-point failure of circuit breakers, switches or relays, and improve the redundancy and reliability of the engine control system.

[0005] The technical solution of the present invention:

[0006] A redundant power distribution circuit for a helicopter multi-engine controller includes multiple power supply busbars and multiple power distribution modules. Each power supply busbar is connected to the input terminal of each power distribution module. The output terminal of each power distribution module is connected to a power contactor. Each power contactor is connected to an engine control switch. Each engine control switch controls each power contactor to operate simultaneously. The output terminal of each power contactor is connected to the engine controller.

[0007] Furthermore, circuit breakers and isolation diodes are installed on the lines connecting the multiple power supply busbars to the input terminal of each power distribution module.

[0008] Furthermore, each power contactor has at least four output lines, with at least three output lines connected to the corresponding engine controller and at least one output line connected to other engine controllers.

[0009] Furthermore, each power contactor has an isolation diode on the line connecting it to other engine controllers.

[0010] Furthermore, a circuit breaker is installed on the line connecting each power contactor to the engine controller.

[0011] Furthermore, the engine control switch includes at least two sets of contacts, which are connected in parallel and then connected to the coil of the corresponding power contactor to control the power contactor's on / off state.

[0012] The control method for redundant power distribution circuits of helicopter multi-engine controllers includes linkage on-state control, linkage off-state control, non-linkage on-state control, and non-linkage off-state control.

[0013] Furthermore, the linkage connection status control is as follows: when the engine control switch is linked and connected, the power contactor is energized and connected, and the power supply of each power distribution module provides redundant power supply to the corresponding engine controller through the corresponding power contactor, isolation diode and circuit breaker; each power contactor has at least one output that supplies power to the other engine controllers through the isolation diode and circuit breaker.

[0014] Furthermore, the linkage disconnection state control is as follows: when the engine control switch is disconnected, the power contactor cannot be engaged, and the power supply on the power distribution module will not supply power to the corresponding engine controller.

[0015] further,

[0016] The non-interlocking on-state control is as follows: When the engine control switch is non-interlocking on, any engine control switch is turned on, and the power contactor connected to the turned-on engine control switch is energized. The power supply of the power distribution module connected to the turned-on power contactor provides redundant power supply to the corresponding engine controller through the corresponding power contactor, isolation diode and circuit breaker; at least one output of the turned-on power contactor supplies power to the other engine controllers through the isolation diode and circuit breaker.

[0017] The non-interlocking disconnection state control is as follows: when all engine control switches are disconnected in a non-interlocking state, the power contactor cannot be engaged, and the power supply on the power distribution module will not supply power to the corresponding engine controller.

[0018] The beneficial effects of this invention are:

[0019] This invention provides a redundant power distribution circuit and control method for a helicopter multi-engine controller. The system consists of: two or more power supply busbars, two layers of isolation diodes, two layers of circuit breakers, and switches that can be linked or independent.

[0020] This invention provides a redundant power distribution circuit and control method for helicopter multi-engine controllers. The power distribution circuit and control method of this invention avoid the reduced redundancy caused by single-point failures such as switches or relays in conventional power distribution. This method increases the redundancy design of the ESC power supply, employing a double-layer isolation diode design. The first layer of isolation diodes prevents helicopter busbar failure caused by a power supply failure, while the second layer of isolation diodes prevents overcurrent failures in other power distribution modules or lines caused by a failure in one power distribution module. Multiple sets of contacts for the engine control switches are used in parallel to prevent switch failure caused by the failure of one set of contacts. The engine control switches can be used in conjunction, which is generally the case during flight, improving the system's power distribution redundancy and reliability. On the ground, the conjunction can be canceled for independent use to check for functional problems with the engine control switches, improving system maintainability and fault isolation rate. Each power contactor supplies power to all engine controllers, preventing engine controller failure due to power failure caused by the failure of a single power contactor. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the power distribution circuit structure of the present invention. Detailed Implementation

[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0023] like Figure 1 As shown, a redundant power distribution circuit for a helicopter multi-engine controller includes multiple power supply busbars and multiple power distribution modules. Each power supply busbar is connected to the input terminal of each power distribution module. Each power distribution module's output terminal is connected to a power contactor. Each power contactor is connected to an engine control switch. Each engine control switch controls each power contactor to operate simultaneously. The output terminal of each power contactor is connected to the engine controller. Circuit breakers and isolation diodes are installed on the lines connecting the multiple power supply busbars to the input terminals of each power distribution module. Isolation diodes are installed on the lines connecting each power contactor to other engine controllers. A circuit breaker is installed on the line connecting each power contactor to the engine controller.

[0024] In embodiments of the present invention, each power contactor has at least four output lines, with at least three output lines connected to the corresponding engine controller and at least one output line connected to other engine controllers. The three output lines of the power contactor respectively distribute power to the triple-redundant power supply of the corresponding engine controller, and at least one output line distributes power to other engine controllers. This ensures that even in the most severe case where all three sets of contacts of the contactor fail simultaneously, the failure of a single power contactor can prevent a single engine controller from losing all power and failing.

[0025] In embodiments of the present invention, the engine control switch includes at least two sets of contacts. These at least two sets of contacts are connected in parallel and are both connected to the coils of corresponding power contactors to control the on / off state of the power contactors. The use of multiple sets of contacts in parallel with the engine control switch prevents the switch from malfunctioning due to the failure of a single set of contacts.

[0026] The power distribution circuit of this engine is a highly feasible power distribution system that reduces single-point failures, increases power distribution redundancy and power distribution layer protection. It can avoid engine controller failure caused by single-point failures and can provide timely and effective protection for the engine controller, ensuring that the helicopter power supply system will not be affected by a power supply failure of a certain power supply to the engine controller.

[0027] The key points of this invention are as follows:

[0028] 1. This invention increases the stability and reliability of the power supply by using two or more busbars connected to the power distribution module via isolation diodes. Figure 1 The preferred configuration is two busbars;

[0029] 2. The power distribution module of the present invention is powered by multiple busbars, and the power supply characteristics are stable, making the power supply of the engine controller system stable and reliable;

[0030] 3. This invention uses an engine control switch that can be linked. When linked, it ensures that the helicopter engine controller is powered on simultaneously and provides redundant power supply to ensure system reliability. When not linked, it facilitates ground maintenance and inspection work, confirms whether there is a failure of a certain engine switch, and improves maintainability and fault isolation rate.

[0031] 4. This invention uses multiple sets of contacts of the engine control switch connected in parallel to prevent the switch from failing due to a fault in one set of contacts;

[0032] 5. This invention provides power to multiple power sources for the corresponding engine controllers through multiple sets of contacts of a power contactor, and also provides power to one power source for the other engine controllers, ensuring that an engine controller will not fail due to lack of power if one power contactor fails.

[0033] 6. This invention provides secondary circuit breaker protection for each power supply of the engine controller, ensuring that a short circuit or overcurrent fault in one power supply of the engine controller will not cause the entire power distribution module to fail due to a short circuit or overcurrent, and can quickly and accurately isolate the faulty power supply channel.

[0034] 7. When the present invention supplies power to different engine controllers through a power contactor, it adds an isolation diode for dual power supply isolation to prevent some lines from malfunctioning due to overcurrent after cross-connection.

[0035] Multiple engine control switches are linked together via a mechanical structure to achieve synchronous on / off operation. After removing this mechanical structure, each switch becomes an independent switch, controlling the engagement of its corresponding power contactor. The switch control logic includes linked on / off state control, linked off / off state control, non-linked on / off state control, and non-linked off / off state control.

[0036] The linkage connection status control is as follows: When the engine control switch is activated, the power contactor engages, and the power supply of each power distribution module provides redundant power to the corresponding engine controller through the corresponding power contactor, isolation diode, and circuit breaker. Each power contactor has at least one output that supplies power to the remaining engine controllers through the isolation diode and circuit breaker. In addition to supplying redundant power to the corresponding engine controller, each power contactor also supplies power to the remaining engine controllers through at least one output, preventing the corresponding engine controller from losing all redundant power and failing due to a failure of a power contactor. When the engine controller's operating power comes from two power contactors, isolation diodes are used for power isolation to prevent a failure of one power supply from affecting the normal operation of the other. The second-level circuit breaker at the front end of the engine controller power supply can protect each redundant power supply line, preventing the entire power distribution module from failing due to a failure of one redundant power supply line.

[0037] The interlock disconnection control is as follows: when the engine control switch is disconnected, the power contactor cannot engage, and the power supply on the power distribution module will not supply power to the corresponding engine controller. The engine controller will not operate without power.

[0038] The non-interlocking on / off state control works as follows: When the engine control switch is non-interlocking on, activating any engine control switch will cause the power contactor connected to that activated switch to engage. The power supply from the distribution module connected to that activated power contactor provides redundant power to the corresponding engine controller through the corresponding power contactor, isolation diode, and circuit breaker. At least one output from this activated power contactor supplies power to the remaining engine controllers through the isolation diode and circuit breaker. Activating a non-interlocking engine control switch only activates the corresponding power contactor, which can then supply power to all engine controllers. This allows for checking whether the switch function is malfunctioning and whether the redundant power supply circuit for the remaining engine controllers is faulty, improving system maintainability.

[0039] The non-interlocking disconnection state control is as follows: When all engine control switches are disconnected in a non-interlocking state, the power contactor cannot engage, and the power supply on the power distribution module will not supply power to the corresponding engine controller. The engine controller will not operate without power.

[0040] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A redundant power distribution circuit for a helicopter multi-engine controller, characterized in that: It includes multiple power supply busbars and multiple power distribution modules. Each power supply busbar is connected to the input terminal of each power distribution module. The output terminal of each power distribution module is connected to a power contactor. Each power contactor is connected to an engine control switch. Each engine control switch controls each power contactor to operate simultaneously. The output terminal of each power contactor is connected to an engine controller. Circuit breakers and isolation diodes are installed on the lines connecting the multiple power supply busbars to the input terminals of each power distribution module. Each power contactor has at least four output lines. At least three output lines of each power contactor are connected to the corresponding engine controller, and at least one output line is connected to other engine controllers.

2. The redundant power distribution circuit for a helicopter multi-engine controller according to claim 1, characterized in that: Each power contactor has an isolation diode on the line connecting it to other engine controllers.

3. The redundant power distribution circuit for a helicopter multi-engine controller according to claim 1, characterized in that: A circuit breaker is installed on the line connecting each power contactor to the engine controller.

4. The redundant power distribution circuit for a helicopter multi-engine controller according to claim 1, characterized in that: The engine control switch includes at least two sets of contacts, which are connected in parallel and then connected to the coil of the corresponding power contactor to control the power contactor's on / off state.

5. The control method for the redundant power distribution circuit of the helicopter multi-engine controller according to any one of claims 1-4, characterized in that: This includes linkage on-state control, linkage off-state control, non-linkage on-state control, and non-linkage off-state control.

6. The control method for the redundant power distribution circuit of the helicopter multi-engine controller according to claim 5, characterized in that: The linkage connection status control is as follows: when the engine control switch is linked and connected, the power contactor is energized and connected. The power supply of each power distribution module provides redundant power supply to the corresponding engine controller through the corresponding power contactor, isolation diode and circuit breaker; each power contactor has at least one output that supplies power to the other engine controllers through the isolation diode and circuit breaker.

7. The control method for the redundant power distribution circuit of the helicopter multi-engine controller according to claim 5, characterized in that: The linkage disconnection state control is as follows: when the engine control switch is disconnected, the power contactor cannot be engaged, and the power supply on the power distribution module will not supply power to the corresponding engine controller.

8. The control method for the redundant power distribution circuit of the helicopter multi-engine controller according to claim 5, characterized in that: The non-interlocking on-state control is as follows: When the engine control switch is non-interlocking on, any engine control switch is turned on, and the power contactor connected to the turned-on engine control switch is energized. The power supply of the power distribution module connected to the turned-on power contactor provides redundant power supply to the corresponding engine controller through the corresponding power contactor, isolation diode, and circuit breaker. At least one output of the turned-on power contactor supplies power to the other engine controllers through the isolation diode and circuit breaker. The non-interlocking disconnection state control is as follows: when all engine control switches are disconnected in a non-interlocking state, the power contactor cannot be engaged, and the power supply on the power distribution module will not supply power to the corresponding engine controller.

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