A system and method for acquiring the operating current of an aircraft DC generator

Abstract

This invention proposes a system and method for acquiring the operating current of an aircraft DC generator. The system acquires the DC generator's switch and starter switch status from the control panel via an electrical display box and transmits this data to a busbar power controller. The busbar power controller automatically controls the connection or disconnection of the DC generator's generating and starting circuits within the intelligent power distribution cabinet based on these statuses. It also determines whether the current collected by the current sensor is the DC generator's generating current or the starting current based on the current status. The internal software of the busbar power controller assigns values ​​to the generating and starting currents according to pre-set logic and algorithms, and sends these values ​​to the electrical display box for storage. The data is then sent to the avionics display to provide the pilot with crucial electromechanical system parameters. This invention can reduce the number of current sensors and related acquisition circuits used to acquire the DC generator's operating current by half, effectively simplifying the parameter acquisition circuitry, reducing costs, and lightening the system weight.

Description

Technical Field

[0001] This invention belongs to the field of power supply technology for aircraft electromechanical systems, and relates to the acquisition and monitoring of parameters of aircraft DC power generation and starting systems, especially the acquisition method and algorithm for the operating current of aircraft DC generators. Background Technology

[0002] An aircraft DC generator can convert electrical energy from an external power source into mechanical energy to start the aircraft engine. After the engine starts, it can convert the mechanical energy back into electrical energy to power all the aircraft's electrical equipment.

[0003] A certain type of large amphibious aircraft uses DC generators as its main DC power source and engine starter motors, with as many as nine DC generators. Conventional power parameter acquisition technology is used to collect the generator current and starting current separately, requiring as many as 18 imported high-precision current sensors and their acquisition circuits. This results in a high-cost, heavy, and complex interconnected power parameter acquisition system. Therefore, reducing the number of imported high-precision current sensors and their acquisition circuits can effectively reduce aircraft costs and simplify the parameter acquisition system circuitry, which is of great value. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing technologies and improve the functionality and performance of power parameter acquisition systems. This invention proposes an aircraft DC generator operating current acquisition system and algorithm for acquiring and calculating the generator current during power supply and the starting current during engine start-up. By placing a current sensor on the parameter acquisition circuit in a shared section of the starting and power supply circuits, and in conjunction with software logic and algorithms, only one current sensor can be used to simultaneously measure the starting current and power supply current. The method includes the placement of the current sensor on the circuit, the acquisition and judgment of the DC generator's power generation and starting states by the busbar power controller, and specific software logic and algorithms for assigning values ​​to the DC generator's power generation current and starting current based on the generator's power generation or starting state.

[0005] The technical solution adopted by this invention to solve its technical problem is:

[0006] To achieve the above objectives, according to a first aspect of the present invention, an aircraft DC generator operating current acquisition system is provided, characterized in that it includes a DC generator 100, a starter box 200, an intelligent power distribution cabinet 300, a DC generator control box 400, a control panel 500, an avionics display 600, and an electrical display and control box 700.

[0007] The intelligent power distribution cabinet 300 is used to control the DC generator to start the engine and supply power to the whole machine according to certain logic, including a central bus bar 301, a bus bar power controller 302, a current sensor 303, a first contactor 304, and a second contactor 305;

[0008] The DC generator 100 is used during the start-up phase when the starter motor is used to start the engine; and after the engine is started, when the DC generator is used to generate DC power, it is connected to the central busbar 301 in the intelligent power distribution cabinet 300 via the power supply circuit 101.

[0009] The starter box 200 is used to provide starting power to the DC generator and is connected to the DC generator 100 through the starting circuit 201.

[0010] The power supply circuit 101 and the starting circuit 201 share a common section 110;

[0011] The DC generator control box 400 is used to control the excitation to ensure the normal operation of the DC generator, and at the same time to control the contactor's engagement and disengagement to control the on / off of the power supply circuit. The DC generator control box 400 is connected to the busbar power controller 302 and also to the second contactor 305.

[0012] The control panel 500 is used to operate the DC generator switch, starter switch and ground power switch, and communicates with the electrical display and control box to send the generator switch, starter switch and ground power switch signals to the electrical display and control box. The control panel 500 is connected to the electrical display and control box 700 and the intelligent power distribution cabinet 300 through circuits respectively.

[0013] The avionics display 600 is used to display key parameters of the DC generator system and is connected to the intelligent power distribution cabinet 300 via a circuit.

[0014] The electrical display and control box 700 is used to collect the switch status on the control panel and send it to the intelligent power distribution cabinet. At the same time, it records the key parameters of the DC generator system transmitted by the intelligent power distribution cabinet and is connected to the intelligent power distribution cabinet 300 through a circuit.

[0015] The busbar power controller 302 is installed inside the intelligent power distribution cabinet 300 to facilitate the collection of the status and parameters of each contactor, protector and sensor in the cabinet;

[0016] The current sensor 303 is installed on the common section 110. In conjunction with the software logic and algorithm inside the busbar power controller 302, the starting current and the power supply current can be measured simultaneously using only one current sensor.

[0017] The central busbar 301 is electrically connected to the DC generator 100 via the second contactor 305; the second contactor 305 cannot be installed on the common section 110; the busbar power controller 302 is connected to the second contactor 305 and controls the engagement and disengagement of the second contactor 305;

[0018] The DC generator 100 is electrically connected to the starter box 200 through the first contactor 304; the first contactor 304 cannot be installed on the common section 110; the busbar power controller 302 is connected to the first contactor 304 and controls the engagement and disengagement of the first contactor 304.

[0019] In one possible embodiment, the current sensor 303 has a measurement range of -900A to 400A and an acquisition accuracy of not less than 1%FS.

[0020] In one possible embodiment, the communication protocol between the intelligent power distribution cabinet 300 and the electrical display and control box 700 is CAN communication, with a transmission rate of not less than 10Hz.

[0021] In one possible embodiment, the communication protocol between the intelligent power distribution cabinet 300 and the avionics display 600 is 429 communication with a transmission rate of 1-2Hz.

[0022] According to a second aspect of the present invention, a method for acquiring the operating current of an aircraft DC generator is provided, employing the aforementioned aircraft DC generator operating current acquisition system, characterized in that it specifically includes the following steps:

[0023] S1: The electrical display and control box 700 collects the status of the DC generator switch, starter switch and ground power switch on the control panel 500 and sends them to the busbar power controller 302 in the intelligent power distribution cabinet 300 via bus;

[0024] S2: The busbar power controller 302 controls the first contactor 304 on the power supply circuit 101 between the DC generator 100 and the central busbar 301 to engage or disengage according to the switch position on the control panel 500, and controls the second contactor 305 on the starting circuit 201 between the DC generator 100 and the starting box 200 to engage or disengage.

[0025] S3: The starting current and power supply current signals of the DC generator 100 are collected by the current sensor 303 of the intelligent power distribution cabinet 300, and the collected current signals are sent to the busbar power controller 302.

[0026] S4: The busbar power controller 302 calculates the starting current and supply current of the DC generator 100 according to the relevant logic, calculation formula and the starting or supplying state of the DC generator in the internal software, and sends the calculated supply current and starting current of the DC generator 100 to the avionics display 600 so that the pilot can grasp the key parameters of the aircraft DC generator system.

[0027] S5: The busbar power controller 302 sends the calculated starting current value and supply current value of the DC generator 100 to the electrical display and control box 700 for storage, so that maintenance personnel can view and refer to it for analysis when performing maintenance or troubleshooting.

[0028] In one possible embodiment, in step S2:

[0029] When the DC generator switch on the control panel 500 is in the off position, the ground power switch is in the on position, and the start switch is in the on position, the busbar power controller 302 in the intelligent power distribution cabinet 300 controls the first contactor 304 to engage and the DC generator control box 400 controls the second contactor 305 to release, so that the DC generator 100 and the starter box 200 are connected through the starter circuit 201, and the power supply circuit 101 between the DC generator 100 and the central busbar 301 is disconnected, so that the DC generator 100 is in the starting state and the engine is started.

[0030] When the DC generator switch on the control panel 500 is in the ON position, the ground power switch is in the on-machine position, and the start switch is in the OFF position, the busbar power controller 302 in the intelligent power distribution cabinet 300 controls the first contactor 304 to release and controls the second contactor 305 to engage through the DC generator control box 400, thereby disconnecting the start circuit 201 between the DC generator 100 and the starter box 200, and connecting the DC generator 100 and the central busbar 301 through the power supply circuit 101, the DC generator 100 is in the power generation state, realizing the DC generator supplying power to the central busbar.

[0031] In one possible embodiment, in step S4, the internal software logic of the busbar power controller 302 is as follows:

[0032] If the DC generator 100 is in the power generation state, the busbar power controller 302 converts the current signal collected by the current sensor 303 into the current value of the DC generator power generation current, and directly assigns the DC generator starting current value to "0".

[0033] If the DC generator 100 is in the starting state, the busbar power controller 302 assigns the absolute value of the current signal collected by the current sensor 303 as the starting current value of the DC generator, and directly assigns the generating current of the DC generator as "0".

[0034] In one possible embodiment, in step S4, the formula for converting the current signal collected by the current sensor 303 into a current value is as follows:

[0035] When the current signal is -10V to 0V, the linearly corresponding current is -900A to 0A; when the current signal is 0V to 10V, the linearly corresponding current is 0A to 900A. Therefore, I = 90 × V, where I represents the charging current or the supply current, and V represents the voltage signal received by the current sensor 303 from the busbar power controller 302.

[0036] The beneficial effects of this invention are:

[0037] The aircraft DC generator operating current acquisition system and algorithm of this invention, through a combination of special acquisition circuit design and software logic and algorithms, can reduce the number of imported high-precision current sensors and their acquisition circuits used for acquiring DC generator operating current by half, effectively simplifying the parameter acquisition circuit, significantly reducing the cost of the parameter acquisition system, and reducing the system weight. The method includes the placement of the current sensor on the circuit, the acquisition and judgment of the DC generator's power generation and starting states by the busbar power controller, and specific software logic and algorithms for assigning values ​​to the DC generator's supply current and starting current based on the power generation or starting state. Attached Figure Description

[0038] Figure 1 This is a diagram of the aircraft DC generator operating current acquisition architecture of the present invention.

[0039] Figure 2 This is a flowchart of the method of the present invention.

[0040] in:

[0041] 100-DC generator; 200-Starter box; 300-Intelligent power distribution cabinet; 400-DC generator control box; 500-Control panel; 600-Aviation display; 700-Electrical display and control box; 101-Power supply circuit; 201-Starting circuit; 110-Common section; 301-Central busbar; 302-Busbar power controller; 303-Current sensor; 304-First contactor; 305-Second contactor. Detailed Implementation

[0042] The calculation methods in 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, other embodiments obtained by those skilled in the art without creative effort are all within the scope of protection of the present invention.

[0043] See appendix Figure 1 An aircraft DC generator operating current acquisition system is characterized by comprising a DC generator 100, a starter box 200, an intelligent power distribution cabinet 300, a DC generator control box 400, a control panel 500, an avionics display 600, and an electrical display and control box 700.

[0044] The intelligent power distribution cabinet 300 is used to control the starting engine and power generation of the DC generator 100 according to certain logic, including a central busbar 301, a busbar power controller 302, a current sensor 303, a first contactor 304, and a second contactor 305;

[0045] The DC generator 100 is used during the start-up phase when the starter motor is used to start the engine; and after the engine starts, the DC generator 100 is used to generate DC power, which is connected to the central busbar 301 in the intelligent power distribution cabinet 300 through the power supply circuit 101.

[0046] The starter box 200 is used to provide starting power to the DC generator 100 and is connected to the DC generator 100 through the starter circuit 201;

[0047] The power supply circuit 101 and the starting circuit 201 share a common section 110;

[0048] The DC generator control box 400 is used to control the excitation to ensure the normal operation of the DC generator, and at the same time to control the contactor to control the connection and disconnection of the power supply circuit. The DC generator control box 400 is connected to the busbar power controller 302 and also to the second contactor 305.

[0049] The control panel 500 is used to operate the DC generator switch, start switch and ground power switch, and communicates with the electrical display and control box 700 to send the DC generator switch, start switch and ground power switch signals to the electrical display and control box 700. The control panel 500 is connected to the electrical display and control box 700 and the intelligent power distribution cabinet 300 through circuits respectively.

[0050] The avionics display 600 is used to display key parameters of the DC generator system and is connected to the intelligent power distribution cabinet 300 via a circuit.

[0051] The electrical display and control box 700 is used to collect the switch status on the control panel and send it to the busbar power controller 302 in the intelligent distribution cabinet 300. At the same time, it records the key parameters of the DC power generation system transmitted by the busbar power controller 302 in the intelligent distribution cabinet 300. It is connected to the intelligent distribution cabinet 300 through a circuit.

[0052] The busbar power controller 302 is installed inside the intelligent power distribution cabinet 300; the current sensor 303 is installed on the common section 110; the central busbar 301 is electrically connected to the DC generator 100 through the second contactor 305; the second contactor 305 cannot be installed on the common section 110; the busbar power controller 302 is connected to the second contactor 305 to collect the state of the second contactor 305, and the busbar power controller 302 is connected to the DC generator control box 400 to control the engagement and disengagement of the second contactor 305 through the DC generator control box 400;

[0053] The DC generator 100 is electrically connected to the starter box 200 through the first contactor 304; the first contactor 304 cannot be installed on the common section 110; the busbar power controller 302 is connected to the first contactor 304 to collect the status of the first contactor 304 and control the engagement and disengagement of the first contactor 304;

[0054] The current sensor 303 has a measurement range of -900A to 400A and an acquisition accuracy of not less than 1%FS;

[0055] The communication protocol between the intelligent power distribution cabinet 300 and the electrical display and control box 700 is CAN communication, with a transmission rate of not less than 10Hz;

[0056] The intelligent power distribution cabinet 300 and the avionics display 600 use the 429 communication protocol with a transmission rate of 1-2Hz.

[0057] According to a second aspect of the present invention, a method for acquiring the operating current of an aircraft DC generator is provided, such as... Figure 2 As shown, the aircraft DC generator operating current acquisition system described above is characterized by the following steps:

[0058] S1: The electrical display and control box 700 collects the status of the DC generator switch, starter switch and ground power switch on the control panel 500 and sends them to the busbar power controller 302 in the intelligent power distribution cabinet 300 via bus;

[0059] S2: The busbar power controller 302 controls the second contactor 305 on the power supply circuit 101 between the DC generator 100 and the central busbar 301 to engage or disengage according to the switch position on the control panel 500, and controls the second contactor 304 on the starting circuit 201 between the DC generator 100 and the starting box 200 to engage or disengage, based on the switch position on the control panel 500.

[0060] S3: The starting current and power supply current signals of the DC generator 100 are collected by the current sensor 303 in the intelligent power distribution cabinet 300, and the collected current signals are sent to the busbar power controller 302.

[0061] S4: The busbar power controller 302 calculates the starting current and supply current of the DC generator 100 according to the relevant logic, calculation formula and the starting or supplying state of the DC generator in the internal software, and sends the calculated supply current value and starting current value of the DC generator 100 to the avionics display 600 so that the pilot can grasp the key parameters of the aircraft DC power generation system.

[0062] S5: The busbar power controller 302 sends the calculated starting current value and supply current value of the DC generator 100 to the electrical display and control box 700 for storage, so that maintenance personnel can view and refer to it for analysis when performing maintenance or troubleshooting.

[0063] In step S2:

[0064] When the DC generator switch on the control panel 500 is in the off position, the ground power switch is in the on position, and the start switch is in the on position, the busbar power controller 302 in the intelligent power distribution cabinet 300 controls the first contactor 304 to engage and the DC generator control box 400 controls the second contactor 305 to release, so that the DC generator 100 and the starter box 200 are connected through the starter circuit 201, and the power supply circuit 101 between the DC generator 100 and the central busbar 301 is disconnected, so that the DC generator 100 is in the starting state and the engine is started.

[0065] When the DC generator switch on the control panel 500 is in the ON position, the ground power switch is in the on-machine position, and the start switch is in the OFF position, the busbar power controller 302 in the intelligent distribution cabinet 300 controls the first contactor 304 to release and controls the second contactor 305 to engage via the DC generator control box 400. This disconnects the starting circuit 201 between the DC generator 100 and the starter box 200, connecting the DC generator 100 and the central busbar 301 through the power supply circuit 101. The DC generator 100 is then in power generation mode, enabling it to supply power to the central busbar.

[0066] In step S4, the internal software logic of the busbar power controller 302 is as follows:

[0067] If the DC generator 100 is in the power generation state, the busbar power controller 302 converts the current signal collected by the current sensor 303 into the current value of the DC generator power generation current, and directly assigns the DC generator starting current value to "0".

[0068] If the DC generator 100 is in the starting state, the busbar power controller 302 assigns the absolute value of the current signal collected by the current sensor 303 after conversion to the current value of the DC generator starting current, and directly assigns the DC generator generating current to "0".

[0069] In step S4, the formula for calculating the current value by converting the current signal collected by the current sensor 303 into a current value is as follows:

[0070] When the current signal is -10V to 0V, the linearly corresponding current is -900A to 0A; when the current signal is 0V to 10V, the linearly corresponding current is 0A to 900A. Therefore, I = 90 × V, where I represents the charging current or the supply current, and V represents the voltage signal received by the current sensor 303 from the busbar power controller 302.

[0071] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A system for acquiring the operating current of an aircraft DC generator, characterized in that, Includes a DC generator (100), a starter box (200), an intelligent power distribution cabinet (300), a DC generator control box (400), a control panel (500), an avionics display (600), and an electrical display and control box (700); The intelligent power distribution cabinet (300) is used to control the starting engine and power generation of the DC generator according to certain logic, including a central busbar (301), a busbar power controller (302), a current sensor (303), a first contactor (304), and a second contactor (305); The DC generator (100) is used during the start-up phase when the starter motor is used to start the engine; and after the engine is started, when the DC generator is used to generate DC power, it is connected to the central busbar (301) in the intelligent power distribution cabinet (300) via the power supply circuit (101). The starter box (200) is used to provide starting power to the DC generator and is connected to the DC generator (100) through the starting circuit (201); The power supply circuit (101) and the starting circuit (201) share a common section (110); The DC generator control box (400) is used to control the excitation voltage to ensure the normal operation of the DC generator, and at the same time to control the contactor to control the opening and closing of the power supply circuit. The DC generator control box (400) is connected to the busbar power controller (302) and also to the second contactor (305). The control panel (500) is used to operate the DC generator switch and the ground power switch, communicates with the electrical display and control box, and sends the generator switch and ground power switch signals to the electrical display and control box. The control panel (500) is connected to the electrical display and control box (700) and the intelligent power distribution cabinet (300) respectively through circuits. The avionics display (600) is used to display key parameters of the DC generator system and is connected to the intelligent power distribution cabinet (300) via a circuit. The electrical display and control box (700) is used to collect the switch status on the control panel and send it to the intelligent power distribution cabinet. At the same time, it records the key parameters of the DC generator system transmitted by the intelligent power distribution cabinet. It is connected to the intelligent power distribution cabinet (300) through a circuit. The busbar power controller (302) is located inside the intelligent power distribution cabinet (300); The current sensor (303) is disposed on the common section (110); The central busbar (301) is electrically connected to the DC generator (100) via the second contactor (305); the second contactor (305) cannot be installed on the common section (110); the busbar power controller (302) is connected to the second contactor (305) and controls the engagement and disengagement of the second contactor (305); The DC generator (100) is electrically connected to the starter box (200) via the first contactor (304); the first contactor (304) cannot be installed on the common section (110); the busbar power controller (302) is connected to the first contactor (304) and controls the closing and releasing of the first contactor (304).

2. The aircraft DC generator operating current acquisition system according to claim 1, characterized in that, The current sensor (303) has a measurement range of -900A to 400A and an acquisition accuracy of not less than 1%FS.

3. The aircraft DC generator operating current acquisition system according to claim 1, characterized in that, The intelligent power distribution cabinet (300) and the electrical display and control box (700) use CAN communication as their communication protocol, with a transmission rate of not less than 10Hz.

4. The aircraft DC generator operating current acquisition system according to claim 1, characterized in that, The communication protocol between the intelligent power distribution cabinet (300) and the avionics display (600) is 429 communication, with a transmission rate of 1-2Hz.

5. A method for acquiring the operating current of an aircraft DC generator, employing the aircraft DC generator operating current acquisition system according to any one of claims 1-4, characterized in that, Specifically, the steps include the following: S1: The electrical display and control box (700) collects the status of the DC generator switch, starter switch and ground power switch on the control panel (500) and sends them to the busbar power controller (302) in the intelligent power distribution cabinet (300) via bus; S2: The busbar power controller (302) controls the first contactor (304) on the power supply circuit (101) between the DC generator (100) and the central busbar (301) to engage or disengage according to the switch position on the control panel (500), and controls the second contactor (305) on the starting circuit (201) between the DC generator (100) and the starter box (200) to engage or disengage; S3: The starting current and power supply current signals of the DC generator (100) are collected by the current sensor (303) of the intelligent power distribution cabinet (300), and the collected current signals are sent to the busbar power controller (302); S4: The busbar power controller (302) calculates the starting current and power supply current of the DC generator (100) according to the relevant logic, calculation formula and the starting or power supply state of the DC generator in the internal software, and sends the calculated power supply current and starting current of the DC generator (100) to the avionics display (600) so that the pilot can grasp the key parameters of the aircraft DC generator system. S5: The busbar power controller (302) sends the calculated starting current value and supply current value of the DC generator (100) to the electrical display and control box (700) for storage, so that maintenance personnel can view and refer to it for analysis when performing maintenance or troubleshooting.

6. The method for acquiring the operating current of an aircraft DC generator according to claim 5, characterized in that, In step S2: When the DC generator switch on the control panel (500) is in the off position, the ground power switch is in the on position, and the start switch is in the on position, the busbar power controller (302) in the intelligent power distribution cabinet (300) controls the first contactor (304) to engage and controls the second contactor (305) to release through the DC generator control box (400), so that the DC generator (100) and the starter box (200) are connected through the starter circuit (201), so that the power supply circuit (101) between the DC generator (100) and the central busbar (301) is disconnected, and the DC generator (100) is in the starting state, realizing engine starting; When the DC generator switch on the control panel (500) is in the ON position, the ground power switch is in the on-machine position, and the start switch is in the OFF position, the busbar power controller (302) in the intelligent power distribution cabinet (300) controls the first contactor (304) to release and controls the second contactor (305) to engage through the DC generator control box (400), thereby disconnecting the start circuit (201) between the DC generator (100) and the starter box (200), and connecting the DC generator (100) and the central busbar (301) through the power supply circuit (101), the DC generator (100) is in the power generation state, realizing the DC generator supplying power to the central busbar.

7. The method for acquiring the operating current of an aircraft DC generator according to claim 5, characterized in that, In step S4, the internal software logic of the busbar power controller (302) is as follows: If the DC generator (100) is in the power generation state, the busbar power controller (302) converts the current signal collected by the current sensor (303) into the current value of the DC generator power generation current and directly assigns the DC generator starting current value to "0". If the DC generator (100) is in the starting state, the busbar power controller (302) assigns the absolute value of the current signal collected by the current sensor (303) as the starting current value of the DC generator, and directly assigns the generating current of the DC generator as "0".

8. The method for acquiring the operating current of an aircraft DC generator according to claim 5, characterized in that, In step S4, the formula for calculating the current value by converting the current signal collected by the current sensor (303) into a current value is as follows: When the current signal is -10V to 0V, the linearly corresponding current is -900A to 0A; when the current signal is 0V to 10V, the linearly corresponding current is 0A to 900A. Therefore, I = 90 × V, where I represents the charging current or the power supply current, and V represents the voltage signal from the current sensor (303) received by the busbar power controller (302).

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