Aircraft fuel servo control system

Abstract

The invention discloses an aircraft fuel servo control system which comprises an oil way integration module, a three-position servo valve, an actuator switching block, an ECU control module and a measurement and control module. Oil flows into the oil path integration module through the fuel oil pressure supply port and then is divided into two paths, the first path directly enters a PCR oil supply port of the actuator switching block, the second path enters the three-position servo valve, and the three-position servo valve conducts high-low pressure switching according to instructions of the ECU control module and then enters a PHPTC oil supply port of the actuator switching block. The ECU control module obtains the pressure of the PHPTC cavity and the pressure of the PCR cavity, after comparison, a position instruction is fed back to the three-position servo valve through the LVDT ratio meter, the three-position servo valve is controlled to adjust the oil supply pressure of the PHPTC cavity, the value of the LVDT ratio meter is made to be stable, then the position of the actuator module is controlled to be stable, and a closed loop is achieved. According to the system, various researches can be carried out on the actuator under closed-loop control, the operation is simple, the response time is short, and the fault rate is low.

Description

Technical Field

[0001] The present invention relates to the technical field of servo control, and in particular to an aircraft fuel servo control system. Background Art

[0002] The servo controller of the aircraft fuel system plays an important role in fuel flow, pressure, temperature control, fault detection and protection, and is a key component to ensure the normal operation of the aircraft fuel system and flight safety.

[0003] At present, aircraft fuel servo control systems widely use a combination of electromagnetic shut-off valves, overflow valves, angle sensors, and PLC (programmable logic controller) wireless communication modules to control fuel flow. However, this traditional control system has the following problems: (1) Complicated operation: There are many system components, and the connection and debugging between the components are complicated, which makes the operation process cumbersome and increases the workload of maintenance personnel. (2) Long response time: The response speed of the electromagnetic shut-off valve and the overflow valve is limited, resulting in a lag in the system's regulation of fuel flow, affecting the accuracy and real-time performance of fuel control. (3) Low integration: The integration between the components of the existing fuel servo control system is low, making it difficult to achieve efficient data transmission and resource sharing, limiting the improvement of system performance. (4) High failure rate: Due to the large number of system components and complex connections, the probability of failure increases, reducing the reliability and stability of the system.

[0004] In summary, the existing aircraft fuel servo control system has obvious deficiencies in terms of operational convenience, response speed, integration and failure rate, and further research is needed to meet the needs of the modern aviation industry for efficient, stable and intelligent fuel control systems. Summary of the invention

[0005] The problem to be solved by the present invention is to provide an aircraft fuel servo control system for improving the accuracy and real-time performance of aircraft fuel control and reducing the failure rate.

[0006] The present invention adopts the following technical solution: an aircraft fuel servo control system, comprising: an oil circuit integration module, a servo valve module, an actuator module, a fuel pipeline module, an ECU control module, and a measurement and control module;

[0007] The actuator module mainly includes a cylinder housing and a piston, and is connected to an oil circuit integration module and a servo valve module through an actuator adapter block.

[0008] The actuator adapter block includes P CR Oil supply interface and P HPTC The oil supply interface and the seal exhaust interface are connected to the actuator’s P CR Cavity and P HPTCThe cavity and the air discharge are used to connect to the fuel delivery pipeline of the fuel servo control system, and the sealed discharge interface is used to check the oil leakage of the actuator module;

[0009] The oil flows into the oil circuit integrated module through the fuel supply pressure port and the fuel supply pressure pipeline, and is divided into the first output oil circuit and the second output oil circuit in the oil circuit integrated module. The first output oil circuit directly enters the PCR oil supply port, and the second output oil circuit outputs the oil to the P through the servo valve module. HPTC The oil supply port, the oil return oil flows out from the fuel return port through the fuel return pipeline.

[0010] The ECU control module includes: an industrial computer, a PLC and a 485 communication board, a power supply, an LVDT load circuit, an LVDT ratiometer, a digital display and a position control unit. The control signal is sent to the industrial computer through the LVDT ratiometer or the digital display and the position control unit to control the actuator position.

[0011] Preferably, the servo valve module includes a three-position electro-hydraulic servo valve, and the second output oil circuit is divided into two circuits in the oil circuit integration module, which are respectively input to the P and P of the three-position electro-hydraulic servo valve. HPTC(LO) and P HPTC(HI) Port, the three-position electro-hydraulic servo valve operates at P according to the instruction of the load control module. HPTC(LO) and P HPTC(HI) The high and low pressures are switched between the ports, and the oil is output to the P HPTC Oil supply port.

[0012] Preferably, in the ECU control module, the power supply is used to provide AC power to the LVDT primary coil, and the LVDT load circuit forms an electronic circuit through a plurality of resistors and capacitors for stabilizing the signal;

[0013] The LVDT ratio or digital display and position control unit sends a control signal. After the signal is stabilized by the LVDT load circuit, it is transmitted to the industrial computer through the PLC and 485 communication board. The program of the industrial computer controls the speed of the frequency converter in the oil circuit integrated module based on this signal, thereby changing the oil pressure P in the pipeline. HPTC Size, to achieve the position control of the actuator.

[0014] The LVDT ratio or digital display and position control signal threshold can be set manually or controlled by an industrial computer system to control the frequency converter to adjust P HPTC The oil supply pressure of the cavity stabilizes the LVDT ratio meter value or position signal, thereby controlling the position of the actuator module to be stable, forming an actuator control loop.

[0015] Preferably, the industrial computer is based on the WINDOWS operating system and includes a human-computer interaction interface, a PLC and a 485 communication board, which are used for input and output processing of digital and analog signals; the industrial computer and the PLC and the 485 communication board are connected by a wired or wireless network.

[0016] Preferably, the oil circuit integrated module mainly includes an oil tank, an oil pump, a frequency converter, an oil pipe, etc.

[0017] Preferably, the actuator adapter block is also provided with a plurality of sealed discharge ports for discharging oil into the air, so as to check the oil leakage of the actuator module.

[0018] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:

[0019] The aircraft fuel servo control system of the present invention increases the integration level, integrates multiple functions, adopts a three-position servo valve for high and low pressure switching, utilizes an LVDT ratiometer or position signal and a PLC wireless communication module to realize a closed-loop test, and can solve the problems of long response time, complicated operation, and high failure rate of existing equipment, while making the operation simpler. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a structural block diagram of the aircraft fuel servo control system of the present invention;

[0021] Figure 2 This is a schematic diagram of the three-position servo valve of the present invention;

[0022] Figure 3 This is a structural diagram of the LVDT load circuit of the present invention;

[0023] Figure 4 This is the principle diagram of the LVDT ratiometer of the present invention. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the application is further elaborated in detail below in conjunction with the accompanying drawings. The described embodiments are only a part of the embodiments involved in the present invention. All non-innovative embodiments of other researchers in the field on this embodiment belong to the protection scope of the present invention. At the same time, for the step numbering in the embodiment of the present invention, it is only set for the convenience of explanation, and the order between the steps is not limited in any way. The execution order of each step in the embodiment can be adaptively adjusted according to the understanding of those skilled in the art.

[0025] Embodiment 1:

[0026] Construct an aircraft fuel servo control system, such as Figure 1As shown, it includes: an oil circuit integration module, a servo valve module, an actuator module, a fuel pipeline module, and an ECU control module.

[0027] The fuel pipeline module includes a fuel pressure supply pipeline and a fuel return pipeline. The oil is input from the fuel pressure supply port, flows into the oil circuit integrated module through the fuel pressure supply pipeline, and is output to the load end through the actuator module. The oil return flows out from the fuel return port through the fuel return pipeline.

[0028] The actuator module mainly includes a cylinder housing and a piston, and an external actuator adapter block.

[0029] The actuator adapter block is connected to the oil circuit integration module, servo valve module and ECU control module. The actuator adapter block includes P CR Oil supply interface and P HPTC Oil supply connection and seal drain connection, P CR Oil supply interface and P HPTC The oil supply interface is connected to the actuator's P CR Cavity and P HPTC cavity; the sealed discharge interface is discharged to the air and is used to connect to the fuel delivery pipeline of the fuel servo control system. The sealed discharge interface is used to check the oil leakage of the actuator module.

[0030] Specifically, after the oil flows into the oil circuit integrated module, it is divided into two paths in the oil circuit integrated module, namely the first output oil circuit and the second output oil circuit. The first output oil circuit directly enters the PCR oil supply port in the actuator adapter block, and the second output oil circuit is output to the P of the actuator adapter block through the servo valve module. HPTC Oil supply port.

[0031] The oil circuit integrated module mainly includes oil tank, oil pump, frequency converter, oil pipe, etc.

[0032] Further, in this embodiment, the servo valve module, such as Figure 2 As shown, it includes a three-position electro-hydraulic servo valve. The second output oil circuit is divided into two circuits in the oil circuit integrated module and enters the P of the three-position electro-hydraulic servo valve respectively. HPTC(LO) and P HPTC(HI) The three-position electro-hydraulic servo valve operates at P according to the instruction of the ECU control module. HPTC(LO) and P HPTC(HI) The high and low pressures are switched between the ports, and the oil is then output to P HPTC Oil supply port.

[0033] Furthermore, the ECU control module of this embodiment includes: an industrial computer, a PLC and a 485 communication board, a power supply, an LVDT load circuit, an LVDT ratiometer, a digital display and a position control unit.

[0034] The power supply provides AC 6.91 to 7.23 Vrms 2700 to 3300 Hz (sinusoidal) to the primary coil of the LVDT.

[0035] LVDT load circuit, such as Figure 3 As shown, it is an electronic circuit made of resistors and capacitors of certain values ​​connected in a fixed way, and its function is to stabilize the signal.

[0036] LVDT ratiometers, such as Figure 4 As shown, it is used to calculate the ratio of the LVDT according to the following formula:

[0037] (VA-VB)+(VA+VB)=LVDT Gain

[0038] Wherein, LVDT Gain represents the output ratio, VA and VB are the measured voltages at the input of the ratiometer, and in this embodiment, VA corresponds to Figure 4 The output voltage of pins 4 and 5, VB corresponds to Figure 4 Output voltage of middle pins 6 and 5.

[0039] The output ratio calculated by the LVDT ratiometer is transmitted to the industrial computer via the communication board. The program of the industrial computer controls the speed of the inverter in the oil circuit integration module based on this signal, thereby changing the oil pressure in the pipeline and realizing the position control of the actuator.

[0040] It should be noted that in this embodiment, the digital display and position control unit can also send control signals, which are transmitted to the industrial computer via the PLC and 485 communication board to control the position of the actuator. The LVDT ratiometer value can also be manually set at any point, and the ECU control can be used to stabilize the LVDT ratiometer value, thereby stabilizing the position of the actuator module, thus forming a closed loop, and various studies can be performed on the actuator under closed-loop control.

[0041] Furthermore, in this embodiment, the industrial computer is a human-computer interaction interface based on the WINDOWS operating system, the PLC and 485 communication board are input and output processors of digital and analog signals, and the upper computer and the lower computer are connected by a network cable.

[0042] In particular, in this embodiment, the industrial computer is Advantech's industrial computer, the PLC and 485 communication board adopt the CPU component of Siemens PLC, and the program development adopts STEP 7-MicroWIN SMART programming.

[0043] The human-computer interaction interface of the industrial computer is developed using C++builder. The program is based on the Windows visual program interface. The software can be used in winXP or above windows operating systems, has good compatibility and does not require installation.

[0044] The user can test and collect fuel servo control system through the interactive interface, control the status of the system, collect real-time data, and display them in the form of graphics and tables on the user interface. At the same time, the collected data can be automatically recorded or manually recorded according to the needs of the user, and the data recording files are saved in EXCEL or TXT files.

[0045] Embodiment 2:

[0046] Based on the constructed aircraft fuel servo control system and the specific functions of the system's three-position servo valve, the minimum actuating pressure test is carried out. The specific steps are as follows:

[0047] S1, adjust the three-position servo valve so that the oil circuit is connected to P HPTC(LO) Port location, adjust P HPTC(HI) The pressure is 2000~2137kPa;

[0048] S2. Adjust P CR The pressure of the oil supply port is 1000~1069kPa;

[0049] S3, P HPTC(LO) Adjust the pressure to the minimum;

[0050] S4. Ensure that the actuator is in the fully extended position and adjust P HPTC(LO) pressure, making it greater than P CR The pressure at the oil supply port is 310-345 kPa high, at which time the actuator should be in the fully retracted position;

[0051] S5. Adjust P CR and P HPTC to 0;

[0052] S6, keep the oil circuit of the three-position servo valve connected to P HPTC(LO) Port location, adjust P CR The pressure of the oil supply port is minimized;

[0053] S7, adjust P HPTC(LO) The pressure is 1000~1069kPa, adjust P HPTC(HI) The pressure is 1999~2137kPa, at which time the actuator should be in the fully retracted position;

[0054] S8, adjust P CR The pressure ratio of the oil supply port is P CR Oil supply port pressure ratio P HPTC(LO) The pressure is as high as 483-517 kPa;

[0055] S9. At this time, the actuator should be in the fully extended position to complete the minimum actuating pressure test.

[0056] Embodiment three:

[0057] Based on the constructed aircraft fuel servo control system, the load of the actuator module is controlled by the ECU control module.

[0058] In this embodiment, assuming that the load matched with the actuator module is a ventilation valve, the flow rate of the ventilation valve can be accurately set and controlled by the ECU control module.

[0059] Specifically, the ratio value of the LVDT is set in the fuel servo control system to control the piston of the load module of the actuator module to stop at any position, such as 10%, 20%, 30%, 50%, 60%, 70%, 80%, 90%, 100%.

[0060] It can be seen that based on the aircraft fuel servo control system of the present invention, various studies can be performed on the actuator under closed-loop control, with simple operation, short response time, and low failure rate.

[0061] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. An aircraft fuel servo control system, characterized in that: include: Oil circuit integration module, servo valve module, actuator module, fuel pipeline, ECU control module; The actuator module is connected to the oil circuit integration module and the servo valve module through an actuator adapter block, and the actuator adapter block includes a P CR Oil supply interface, P HPTC Oil supply interface and seal discharge interface, the P CR Oil supply interface, P HPTC The oil supply interface is connected to the actuator's P CR Cavity and P HPTC cavity; The oil flows into the oil circuit integrated module through the fuel supply pressure port and the fuel pipeline, and is divided into a first output oil circuit and a second output oil circuit in the oil circuit integrated module. The first output oil circuit directly enters the P CR The second output oil channel outputs oil to P through the servo valve module HPTC The fuel supply port, the oil return flows out of the fuel return port through the fuel pipeline; The ECU control module sends a control signal to the industrial computer through an LVDT ratiometer or a digital display and a position control unit to control the actuator position.

2. The aircraft fuel servo control system according to claim 1, characterized in that: The servo valve module includes a three-position electro-hydraulic servo valve. The second output oil circuit is divided into two circuits in the oil circuit integration module, and is respectively input to the P of the three-position electro-hydraulic servo valve. HPTC(LO) and P HPTC(HI) The three-position electro-hydraulic servo valve is in P position according to the instruction of the ECU control module. HPTC(LO) and P HPTC(HI) The high and low pressures are switched between the ports, and the oil is output to the P HPTC Oil supply port.

3. The aircraft fuel servo control system according to claim 1, characterized in that: The ECU control module includes: an industrial computer, a PLC and a 485 communication board, a power supply, an LVDT load circuit, an LVDT ratiometer, a digital display and a position control unit; The power supply is used to provide alternating current to the LVDT primary coil, and the LVDT load circuit forms an electronic circuit through a plurality of resistors and capacitors to stabilize the signal; The LVDT ratiometer and / or digital display and position control unit sends a control signal, which is then stabilized by the LVDT load circuit and transmitted to the industrial computer via the PLC and 485 communication board. The industrial computer control program controls the speed of the frequency converter in the oil circuit integrated module based on the received signal.

4. The aircraft fuel servo control system according to claim 3, characterized in that: The oil circuit integrated module includes: an oil tank, an oil pump, a frequency converter, and an oil pipe; the industrial computer changes the oil pressure P in the oil pipe by controlling the speed of the frequency converter. HPTC Size, to control the position of the actuator.

5. The aircraft fuel servo control system according to claim 3, characterized in that: The threshold of the LVDT ratio or digital display and position control signal is set manually or controlled by an industrial computer, and the industrial computer controls the frequency converter to adjust P HPTC The oil supply pressure of the cavity stabilizes the LVDT ratiometer value, thereby controlling the position of the actuator module to be stable, forming an actuator control loop.

6. The aircraft fuel servo control system according to claim 5, characterized in that: The ECU control module includes: the LVDT ratiometer calculates the ratio of the LVDT, the formula is as follows: (VA-VB) / (VA+VB)=LVDT Gain Among them, VA and VB are the measured voltages at the input of the ratiometer, and LVDT Gain represents the output ratio.

7. The aircraft fuel servo control system according to claim 1, characterized in that: The industrial computer is based on the WINDOWS operating system and includes a human-computer interaction interface. The PLC and 485 communication board are used for input and output processing of digital and analog signals. The industrial computer and the PLC and 485 communication board are connected by a wired or wireless network.

8. The aircraft fuel servo control system according to claim 7, characterized in that: The industrial computer is Advantech's industrial computer, and the PLC and 485 communication board are Siemens PLC's 485 communication boards.

9. The aircraft fuel servo control system according to claim 1, characterized in that: The actuator module also includes a cylinder housing and a piston.

10. The aircraft fuel servo control system according to claim 1, characterized in that: The sealed discharge interface discharges to the air, and is used to check the oil leakage of the actuator module.

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