Ground starting system of aero-engine

Abstract

The utility model relates to a ground starting system of an aero-engine. Comprising a control module used for controlling starting of the aero-engine, a power module used for transmitting power to the aero-engine and providing starting force for the aero-engine, a measuring module used for measuring operation data of the aero-engine and feeding back the operation data to the control module, and an oil supply module used for providing fuel oil for the aero-engine. The separation opportunity of the starting device and the engine is accurately controlled in a mode of combining the PLC and the electric control clutch, abrasion to equipment in the starting process is reduced, and the starting device can be universally used for engines with different separation rotating speeds.

Description

Technical Field

[0001] The utility model relates to the field of aviation engines, in particular to a ground starting system for aviation engines. Background Art

[0002] The starting process of traditional aircraft engines relies on aircraft accessories such as integrated regulators, aircraft accessory casings and starting devices, which are difficult to meet the requirements for ground reuse of retired aircraft engines. At present, the starting of reused aircraft engines is mainly through hydraulic motors or high-power motors. The starting process lacks monitoring, and the timing of the separation of the starting device and the engine cannot be controlled. It is difficult to accurately control the engine starting process and cannot get rid of the dependence on aircraft accessories. In addition, the starting parameters are fixed and cannot be adaptively changed according to the aircraft model and environmental conditions, which will cause engine start failure, resulting in equipment damage and casualties.

[0003] Currently, ground starting of aircraft engines uses a hydraulic system to provide the power required for engine starting, which can only provide starting torque. The separation between the starting system and the engine requires the support of aircraft accessories such as a clutch. The aircraft engine starting process cannot be accurately controlled and relies on components such as an integrated regulator, aircraft accessory casing and starting device. In addition, the starting parameters are fixed and cannot be adaptively changed according to the aircraft model and environmental conditions, which can cause engine starting failure, resulting in equipment damage and casualties.

[0004] Therefore, how to accurately control the aircraft engine starting process is more important. Utility Model Content

[0005] In view of this, the utility model proposes an aircraft engine ground starting system, aiming to solve the problems existing in the prior art.

[0006] Specifically, the utility model provides an aircraft engine ground starting system, comprising: a control module for controlling the starting of the aircraft engine; a power module for transmitting power to the aircraft engine to provide starting force for it; a measuring module for measuring the operating data of the aircraft engine and feeding it back to the control module; and a fuel supply module for providing fuel to the aircraft engine.

[0007] On the basis of the above scheme, the control module includes: an HMI system; a PLC controller connected to the HMI system signal for controlling the start of the aircraft engine; a rocker mechanism for rotating the rocker arm of the fuel pump regulator to a desired angle to adjust the fuel supply of the aircraft engine; a servo motor for driving the rocker mechanism to rotate to a desired angle; a driver for receiving the control signal of the PLC controller and driving the servo motor to rotate to a corresponding angle at a set speed; a solenoid valve for controlling the on-off of the aircraft engine fuel supply oil circuit and an electric push rod for controlling the power module to disengage from the transmission mechanism of the aircraft engine.

[0008] On the basis of the above scheme, the power module includes: a power input device for providing power; a hydraulic pump for using the power provided by the power input device to pressurize low-pressure hydraulic oil into high-pressure oil; a hydraulic oil tank for providing hydraulic oil to the hydraulic pump; a hydraulic motor for converting the high-pressure oil provided by the hydraulic pump into high-speed rotation and providing starting power for the aircraft engine, and a clutch for transmitting the power provided by the hydraulic motor to the aircraft engine.

[0009] On the basis of the above scheme, the measuring module includes: a sensor for measuring ambient temperature, humidity and pressure to provide support for adjusting the starting parameters of the aircraft engine; a fuel level gauge for monitoring the amount of fuel in the fuel supply module; a hydraulic level gauge for monitoring the amount of hydraulic oil in the hydraulic oil tank; an oil level gauge for monitoring the amount of lubricating oil in the lubricating oil tank of the aircraft engine; an oil pressure sensor for measuring the fuel pressure in front of the aircraft engine oil delivery port and a torque speed sensor for measuring the torque and speed provided by the hydraulic motor when the aircraft engine is started.

[0010] Based on the above solution, the fuel supply module includes: a fuel tank for holding the fuel required for starting and operating the aircraft engine; a fuel pump for providing fuel with suitable pressure to the aircraft engine and a fuel filter for filtering impurities in the fuel.

[0011] On the basis of the above scheme, the clutch is respectively connected to the torque speed sensor, the drive shaft of the aircraft engine and the electric push rod to transmit the power provided by the hydraulic motor to the aircraft engine and to disengage the clutch from the drive shaft of the aircraft engine at a specified time under the action of the electric push rod according to the needs of the aircraft engine starting process.

[0012] Compared with the existing technology system, the utility model can start the aircraft engine by combining a PLC controller, a servo motor, a power input device, a hydraulic pump, a hydraulic motor, an electric control clutch, and a torque speed sensor, avoiding the dependence of the aircraft engine ground start on the integrated regulator, the aircraft accessory casing, and the starting device; by monitoring the aircraft engine starting state parameters and accurately controlling the aircraft engine starting process, it can effectively prevent equipment damage and casualties caused by the failure of the aircraft engine to start; by accurately controlling the separation time of the starting device and the aircraft engine through the electric control clutch, it can reduce the wear of the equipment during the starting process, and it can be used for engines with different separation speeds. In addition, the starting process parameters are converted and corrected according to different environmental conditions, and the aircraft engine starting timing is accurately adjusted, which greatly improves the starting efficiency and success rate of the aircraft engine under different environmental conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] By reading the detailed description of the preferred embodiment below, various other advantages and benefits will become clear to those of ordinary skill in the art. The accompanying drawings are only used for the purpose of illustrating the preferred embodiment and are not considered to be limiting of the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0014] Figure 1 This is a schematic diagram of the structure of the aircraft engine ground starting system in Embodiment 1 of the utility model;

[0015] Figure 2 This is a working principle diagram of the aircraft engine ground starting system in Embodiment 1 of the utility model;

[0016] Figure 3 This is a schematic diagram of the assembly structure of the hydraulic motor, clutch and torque speed sensor in Example 1 of the utility model. DETAILED DESCRIPTION

[0017] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments in the present utility model and the features in the embodiments can be combined with each other. The present utility model will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0018] Example 1

[0019] like Figure 1 As shown, the utility model provides an aircraft engine ground starting system, including an aircraft engine, and further comprising: a control module 10 for controlling the starting of the aircraft engine, a power module 20 for transmitting power to the aircraft engine, a measuring module 30 for measuring the operating data of the aircraft engine and feeding back to the control module 10, and a fuel supply module 40 for providing fuel to the aircraft engine;

[0020] Specifically, the control module 10 includes an HMI system 11 (human-machine interface), a PLC controller 12 connected to the HMI system 11 by signal for controlling the start of the aircraft engine, a rocker mechanism 15 for rotating a fuel pump regulator rocker arm (installed on an engine accessory casing, which is an adjustment mechanism for the amount of fuel in the aircraft engine, and is connected to the throttle handle in the cab by a steel cable. The angle of the fuel pump regulator rocker arm can be adjusted by the throttle handle to adjust the engine fuel supply) to a desired angle to adjust the fuel supply of the aircraft engine, a servo motor 14 for driving the rocker mechanism 15 to rotate to a desired angle, a servo driver 13 for receiving a control signal from the PLC controller 12 and driving the servo motor 14 to rotate to a corresponding angle at a set speed, a solenoid valve 16 for controlling the on-off of the aircraft engine fuel supply oil circuit, and an electric push rod 17 for controlling the clutch 25 to disengage from the transmission mechanism of the aircraft engine.

[0021] Among them, the HMI system 11 is connected to the PLC controller 12 through a signal line, which is used to set the aircraft engine starting parameters, perform aircraft engine starting and state control, and display engine state parameters, sensor measurement data, alarm signals and logs. The PLC controller 12 is the control core of the engine ground starting system, and is connected to the engine bus, HMI system 11, driver 13, solenoid valve 16, electric push rod 17, sensor 31, fuel level gauge 32, hydraulic level gauge 33, lubricating oil level gauge 34, oil pressure sensor 35, torque speed sensor 36, oil pump 42, etc. through signal lines. It has an engine starting program and over-limit judgment criteria, and controls the engine starting process through input and output signals. The driver 13 is connected to the PLC controller 12 and the servo motor 14, and is used to receive the control signal of the PLC controller 12 and drive the servo motor 14 to rotate to the corresponding angle according to the set speed. The servo motor 14 is electrically connected to the driver 13, and the servo motor 14 is connected to the rocker mechanism 15 through a transmission shaft, and is used to drive the rocker mechanism 15 to rotate to the desired angle. The upper and lower ends of the rocker arm mechanism 15 are respectively connected to the servo motor 14 and the fuel pump regulator rocker arm. Driven by the servo motor 14, the fuel pump regulator rocker arm is rotated to a desired angle, thereby adjusting the engine fuel supply and controlling the engine starting process.

[0022] As a specific implementation scheme, the power module 20 includes a power input device 21 for providing power to the hydraulic pump 22, a hydraulic pump 22 for increasing the pressure of the low-pressure hydraulic oil provided by the hydraulic oil tank 23 to high-pressure oil by using the power provided by the power input device 21 and transmitting it to the hydraulic motor 24 through a hydraulic pipeline, a hydraulic oil tank 23 for providing hydraulic oil to the hydraulic pump 22, a hydraulic motor 24 for converting the high-pressure oil provided by the hydraulic pump 22 into high-speed rotation and providing starting power for the aircraft engine through a torque speed sensor 36, and a clutch 25 for transmitting the power provided by the hydraulic motor 24 to the aircraft engine. Specifically, the power input device 21 (specifically a three-phase asynchronous motor or a power take-off QH70 installed on a vehicle platform) is connected to the hydraulic pump 22 through a transmission gear or a coupling to provide power to the hydraulic pump 22. The hydraulic pump 22 is connected to the power input device 21, the hydraulic oil tank 23, and the hydraulic motor 24, and increases the pressure of the low-pressure hydraulic oil provided by the hydraulic oil tank 23 to high-pressure oil by using the power provided by the power input device 21, and transmits it to the hydraulic motor 24 through a hydraulic pipeline. The hydraulic oil tank 23 is connected to the hydraulic pump 22 and the hydraulic motor 24 through hydraulic pipelines, and a hydraulic level gauge 33 is installed on it; the hydraulic oil tank 23 is used to provide hydraulic oil to the hydraulic pump 22, recover the hydraulic oil after passing through the hydraulic motor 24, and contain the hydraulic oil required for the normal operation of the power module 20. The hydraulic motor 24 is connected to the hydraulic pump 22, the hydraulic oil tank 23, the torque speed sensor 36, etc., converts the high-pressure oil provided by the hydraulic pump 22 into high-speed rotation, provides starting power for the engine through the torque speed sensor 36, and returns the used hydraulic oil to the hydraulic oil tank 23. Figure 3 As shown, the clutch 25 is connected with the torque speed sensor 36, the transmission shaft of the aircraft engine and the electric push rod 17. On the one hand, it transmits the power provided by the hydraulic motor 24 to the aircraft engine, and on the other hand, according to the needs of the aircraft engine starting process, it quickly disengages from the transmission shaft of the aircraft engine at a specified time under the action of the electric push rod 17 (disengagement time <0.3s). It also includes hydraulic accessories 26, which are necessary components such as fuel filter, overflow valve, one-way valve, temperature and pressure sensor, etc. to keep the power module working normally.

[0023] As another specific implementation of the power module 20, the hydraulic pump 22, hydraulic oil tank 23, hydraulic motor 24, hydraulic level gauge 33, etc. in the power module 20 can keep the equipment that provides power to the engine away from the engine, thereby reducing the volume of the engine starting system. If there is enough space around the engine, the hydraulic pump, hydraulic oil tank, hydraulic motor, hydraulic level gauge, etc. in the power module can be eliminated, and the power input device can be directly connected to the clutch.

[0024] As a specific implementation scheme, the measurement module 30 includes a sensor 31 for measuring ambient temperature, humidity and pressure to provide support for adjusting the starting parameters of the aircraft engine, a fuel level gauge 32 for monitoring the amount of fuel in the fuel tank 41, a hydraulic level gauge 33 for monitoring the amount of hydraulic oil in the hydraulic oil tank 23, a lubricating oil level gauge 34 for monitoring the amount of lubricating oil in the lubricating oil tank of the aircraft engine, an oil pressure sensor 35 for measuring the fuel pressure before the oil delivery port of the aircraft engine, and a torque speed sensor 36 for measuring the torque and speed provided by the hydraulic motor 24 when the aircraft engine is started. Among them, the sensor 31 can measure the ambient temperature, humidity and pressure. Specifically, the sensor 31 is connected to the PLC controller 12 through a signal line, and is used to measure the ambient temperature, humidity and pressure to provide support for adjusting the starting parameters of the aircraft engine. The fuel level gauge 32 is connected to the PLC controller 12 through a signal line, installed on the fuel tank 41, and is used to monitor the amount of fuel in the fuel tank 41. The hydraulic level gauge 33 is connected to the PLC controller 12 via a signal line and is installed in the hydraulic oil tank 23 to monitor the amount of hydraulic oil in the hydraulic oil tank 23. The lubricating oil level gauge 34 is connected to the PLC controller 12 via a signal line to monitor the amount of lubricating oil in the engine lubricating oil tank. The oil pressure sensor 35 is connected to the PLC controller 12 via a signal line and is installed on the oil pipeline between the oil supply module 40 and the engine to measure the fuel pressure before the engine oil pump. The torque speed sensor 36 is connected to the PLC controller 12 via a signal line and is installed between the hydraulic motor 24 and the clutch 25 to measure the torque and speed provided by the hydraulic motor 24 when the engine is started.

[0025] As a specific implementation scheme, the fuel supply module 40 includes a fuel tank 41 for holding the fuel required for starting and working the aircraft engine, a pump 42 for providing fuel at a suitable pressure for the aircraft engine, and a fuel filter 43 for filtering impurities in the fuel. Specifically, the fuel tank 41 is connected to the pump 42 through an oil pipe with a flange, on which a fuel level gauge 32 is installed. The fuel tank 41 is used to hold the fuel required for starting and working the engine. The two ends of the pump 42 are connected to the fuel tank 41 and the fuel filter 43 through an oil pipe with a flange, respectively, to provide fuel at a suitable pressure for the engine. The two ends of the fuel filter 43 are connected to the pump 42 and the engine through an oil pipe with a flange, respectively, to filter impurities in the fuel and provide the engine with high-quality fuel that meets the standards. The oil circuit accessories are necessary components such as a shut-off valve, a one-way valve, a fire switch, and a temperature sensor to keep the fuel supply module working properly.

[0026] As another specific implementation scheme, the required number and models of sensors and power input devices can be added and adjusted according to actual conditions.

[0027] The servo motor can be replaced by a stepper motor or a push rod motor.

[0028] In this embodiment, the aircraft engine includes conventional structures such as a transmission shaft, a transmission mechanism, a fuel pump regulator, and a fuel pump regulator rocker arm, which do not belong to the innovation of the present utility model and will not be described in detail here.

[0029] Example 2

[0030] A method for starting an aircraft engine on the ground, using the aircraft engine ground starting system in Embodiment 1, specifically comprises the following steps:

[0031] (1) Setting the starting parameters on the HMI system 11: idling angle a1, ignition speed N1, fuel supply speed N2, disengagement speed N3, idling speed N4 and aircraft engine warning parameters (exhaust temperature T p0 , fuel pressure P r0 , fuel temperature T r0 , fuel level H r0 , hydraulic pressure P y0 , hydraulic temperature P y0 , hydraulic level H y0 , lubricating oil pressure P h0 , lubricating oil temperature T h0 , lubricating oil level H h0 , motor torque M0, hydraulic motor N y0 );

[0032] (2) The PLC controller 12 receives the atmospheric temperature T0, humidity d0, and pressure P0, and converts and corrects the aircraft engine starting parameters;

[0033] (3) Selecting the start option on the HMI system 11 to open the solenoid valve 16, the oil pump 42, etc.;

[0034] (4) The PLC controller 12 executes a self-diagnosis program and a start-up condition check program to check whether the measured parameters of the aircraft engine, the power module 20, the fuel supply module 40, the lubricating oil system, etc. are normal, various switches and counters are in the initial position, the electric push rod 17 is powered, and the clutch 25 is in the engaged position; if the check results are normal, a start-up permission signal is displayed on the HMI system 11; if a fault is found or the start-up condition is not met, an alarm signal is displayed on the HMI system 11;

[0035] (5) The PLC controller 12 controls the servo motor 14 through the driver 13 to drive the rocker mechanism 15 to rotate, so that the aircraft engine fuel pump regulator rocker arm (installed on the engine accessory casing, it is the adjustment mechanism for the amount of fuel in the aircraft engine, and is connected to the throttle handle in the cab through a steel cable. The angle of the fuel pump regulator rocker arm can be adjusted through the throttle handle to adjust the engine fuel supply) is in the slow position;

[0036] (6) Press the start button of the HMI system 11 for 1 to 2 seconds, and the PLC controller 12 enters the start procedure;

[0037] (7) The PLC controller 12 turns on the power input device 21, which drives the hydraulic pump 22 to work, provides high-pressure oil, drives the hydraulic motor 24 to rotate, and the hydraulic pressure and output torque gradually increase, driving the transmission shaft of the aircraft engine to rotate through the torque speed sensor 36 and the clutch 25;

[0038] (8) The PLC controller 12 starts timing, the start signal light on the HMI system 11 lights up, and the PLC controller 12 monitors the exhaust temperature T p , fuel tank level H r1 , fuel pressure P r1 , fuel temperature T r0 , hydraulic oil tank level H y1 , hydraulic pressure P y1 , hydraulic temperature P y1 , Lubricating oil tank level H h1 , lubricating oil pressure P h1 , lubricating oil temperature T h , low pressure rotor speed N L , high pressure rotor speed N H 、Hydraulic motor 24 speed N y1 , torque of hydraulic motor 24 and other measurement data. If the measurement data exceeds the limit (exceeds the alarm parameter), it will be displayed in red and flashing on the HMI system 11, and the PLC controller 12 will start the termination startup procedure;

[0039] (9) Timing T1 second, high pressure rotor speed N H When the ignition speed N1 is reached, the PLC controller 12 sends an aircraft engine ignition control signal according to the starting program, which is automatically disconnected after T2 seconds;

[0040] (10) Timing T3 seconds, high pressure rotor speed N H When the fuel supply speed N2 is reached, the PLC controller 12 sends the aircraft engine fuel supply signal according to the starting procedure, and disconnects after T4 seconds;

[0041] (11) High-pressure rotor speed N H When the disengagement speed N3 is reached, the PLC controller 12 controls the push rod motor 17 to cut off the power, the clutch 25 is disengaged from the aircraft engine under the action of centrifugal force, the aircraft engine is started successfully, and the start signal light on the HMI system 11 is turned off;

[0042] (12) Timing T4 seconds, high pressure rotor speed N H When the idle speed N4 is reached, the starting procedure is reset.

[0043] Method for converting and correcting engine starting parameters:

[0044] The conversion correction method of the slow car angle a1 is:

[0045]

[0046] The conversion correction method of ignition speed N1 is:

[0047] N1=910-(T0-25)×4

[0048] The conversion correction method of ignition duration T2 is:

[0049]

[0050] The conversion correction method of the fuel supply speed N2 is:

[0051]

[0052] The conversion correction method for the disengagement speed N3 is:

[0053]

[0054] The conversion correction method for the slow speed N4 is:

[0055]

[0056] Where T0 is the atmospheric temperature, d0 is the atmospheric humidity, and P0 is the atmospheric pressure.

[0057] Example 3

[0058] A method for a ground abort start of an aircraft engine, using the aircraft engine ground start system in Embodiment 1, specifically comprising the following steps:

[0059] (1) The PLC controller 12 controls the servo motor 14 through the driver 13 to drive the rocker mechanism 15 to rotate, adjust the fuel pump regulator of the aircraft engine to the parking position, and stop the fuel supply to the aircraft engine;

[0060] (2) The PLC controller 12 turns off the power input device 21, the solenoid valve 16, the oil pump 42, etc.;

[0061] (3) The PLC controller 12 turns off the fuel supply signal of the aircraft engine and stops the starting fuel supply;

[0062] (4) The PLC controller 12 turns off the aircraft engine ignition control signal and stops ignition;

[0063] (5) The HMI system 11 turns off the start signal light;

[0064] (6) The PLC controller 12 starts the program reset and waits for the next start.

[0065] Example 4

[0066] This embodiment takes a certain type of engine infrared test as an example, and the details are as follows:

[0067] The use process of the aircraft engine ground starting system is:

[0068] (1) Set the starting parameters on the HMI system 11: slow speed angle 12°, ignition speed 900r / min, fuel supply speed 1700r / min, disengagement speed 6000r / min, slow speed 7900r / min and aircraft engine warning parameters (exhaust temperature 600℃, fuel pressure 0.8kg / cm 2 , fuel temperature 80℃, fuel level 500L, hydraulic pressure 35Mpa, hydraulic temperature 80℃, hydraulic level 160L, lubricating oil pressure 1.4kg / cm 2 , lubricating oil temperature 210℃, lubricating oil level 12L, motor torque 237Nm, hydraulic motor 5600r / min);

[0069] (2) The PLC controller 12 receives the atmospheric temperature of 28° C., the relative humidity of 40%, and the pressure of 93500 Pa, and converts and corrects the aircraft engine starting parameters;

[0070] (3) Selecting the start option on the HMI system 11 to open the solenoid valve 16, the oil pump 42, etc.;

[0071] (4) The PLC controller 12 executes a self-diagnosis program and a start-up condition check program to check whether the measured parameters of the aircraft engine, the power module 20, the fuel supply module 40, the lubricating oil system, etc. are normal, various switches and counters are in the initial position, the electric push rod 17 is powered, and the clutch 25 is in the engaged position; if the check results are normal, a start-up permission signal is displayed on the HMI system 11; if a fault is found or the start-up condition is not met, an alarm signal is displayed on the HMI system 11;

[0072] (5) The PLC controller 12 controls the servo motor 14 through the driver 13 to drive the rocker mechanism 15 to rotate, so that the engine fuel pump regulator is in the slow position;

[0073] (6) Press the start button of the HMI system 11 for 1 to 2 seconds, and the PLC controller 12 enters the start procedure;

[0074] (7) The PLC controller 12 turns on the power input device 21, which drives the hydraulic pump 22 to work, provides high-pressure oil, drives the hydraulic motor 24 to rotate, and the hydraulic pressure and output torque gradually increase, driving the transmission shaft of the aircraft engine to rotate through the torque speed sensor 36 and the clutch 25;

[0075] (8) The PLC controller 12 starts timing, the start signal light on the HMI system 11 lights up, and the PLC controller 12 monitors the exhaust temperature T p , fuel tank level H r1 , fuel pressure P r1 , fuel temperature T r0 , hydraulic oil tank level H y1 , hydraulic pressure P y1 , hydraulic temperature P y1 , Lubricating oil tank level H h1 , lubricating oil pressure P h1 , lubricating oil temperature T h , low pressure rotor speed N L , high pressure rotor speed N H 、Hydraulic motor 24 speed N y1 , torque of hydraulic motor 24 and other measurement data. If the measurement data exceeds the limit (exceeds the alarm parameter), it will be displayed in red and flashing on the HMI system 11, and the PLC controller 12 will start and terminate the startup procedure;

[0076] (9) Timing 10 seconds, high pressure rotor speed N H When the speed reaches 900r / min, the PLC controller 12 sends an aircraft engine ignition control signal according to the starting procedure, which is automatically disconnected after 25 seconds;

[0077] (10) Timing 22 seconds, high pressure rotor speed N H When the speed reaches 1700r / min, the PLC controller 12 sends the aircraft engine fuel supply signal according to the starting procedure, and disconnects after 3 seconds;

[0078] (11) High-pressure rotor speed N H When the speed reaches 6000r / min, the PLC controller 12 controls the push rod motor 17 to cut off the power, the clutch 25 is disengaged from the aircraft engine under the action of centrifugal force, the aircraft engine starts successfully, and the start signal light on the HMI system 11 goes out;

[0079] (12) Timing 50 seconds, high pressure rotor speed N H When the speed reaches 7900r / min, the starting procedure is reset.

[0080] The working process of the aircraft engine ground abort start procedure is:

[0081] (1) The PLC controller 12 controls the servo motor 14 through the driver 13 to drive the rocker mechanism 15 to rotate, adjust the fuel pump regulator of the aircraft engine to the parking position, and stop the fuel supply to the aircraft engine;

[0082] (2) The PLC controller 12 turns off the power input device 21, the solenoid valve 16, the oil pump 42, etc.;

[0083] (3) The PLC controller 12 turns off the fuel supply signal of the aircraft engine and stops the starting fuel supply;

[0084] (4) The PLC controller 12 turns off the aircraft engine ignition control signal and stops ignition;

[0085] (5) The HMI system 11 turns off the start signal light;

[0086] (6) The PLC controller 12 starts the program reset, and waits for the next start.

[0087] Using the system and method of the present embodiment, the aircraft engine is started by combining a PLC controller 12, a servo motor 14, a power input device 21, a hydraulic pump 22, a hydraulic motor 24, an electric control clutch 25, and a torque speed sensor 36, thereby avoiding the dependence of the aircraft engine ground start on the integrated regulator, the aircraft accessory casing, and the starting device. The PLC controller is used to monitor the engine starting state parameters, and the aircraft engine starting process is accurately controlled to effectively prevent equipment damage and casualties caused by engine starting failure. The PLC controller 12 and the electric control clutch 25 are combined to accurately control the disengagement timing of the starting device and the engine, thereby reducing the wear of the equipment during the starting process, and the method is applicable to engines with different disengagement speeds. A starting parameter conversion correction algorithm can be set to convert and correct the starting process parameters according to different environmental conditions, accurately adjust the engine starting timing, and greatly improve the starting efficiency and success rate of the aircraft engine under different environmental conditions.

[0088] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. An aircraft engine ground starting system, characterized in that: include: A control module (10), a power module (20) for transmitting power to an aircraft engine to provide starting power therefor, a measurement module (30) for measuring operating data of the aircraft engine and feeding back the data to the control module (10), and a fuel supply module (40) for supplying fuel to the aircraft engine; The control module (10) comprises: an HMI system (11), a PLC controller (12) connected to the HMI system (11) by signal and used for controlling the start of the aircraft engine, a rocker mechanism (15) used for rotating a rocker arm of a fuel pump regulator to a desired angle so as to adjust the fuel supply amount of the aircraft engine, a servo motor (14) used for driving the rocker mechanism (15) to rotate to a desired angle, a driver (13) used for receiving a control signal from the PLC controller (12) and driving the servo motor (14) to rotate to a corresponding angle at a set speed, a solenoid valve (16) used for controlling the on / off of a fuel supply oil circuit of the aircraft engine, and an electric push rod (17) used for controlling the power module (20) to be disengaged from a transmission mechanism of the aircraft engine.

2. The aircraft engine ground starting system according to claim 1, characterized in that: The power module (20) comprises: A power input device (21) for providing power; A hydraulic pump (22) for increasing the pressure of low-pressure hydraulic oil into high-pressure oil using the power provided by the power input device (21); A hydraulic oil tank (23) for providing hydraulic oil to the hydraulic pump (22); A hydraulic motor (24) for converting the high-pressure oil provided by the hydraulic pump (22) into a high-speed rotating hydraulic motor (24) for providing starting power for the aircraft engine; and a clutch (25) for transmitting the power provided by the hydraulic motor (24) to the aircraft engine.

3. The aircraft engine ground starting system according to claim 2, characterized in that: The measuring module (30) comprises: Sensors for measuring ambient temperature, humidity and pressure to support adjustment of aircraft engine starting parameters (31); a fuel level gauge (32) for monitoring the amount of fuel in the fuel supply module (40); A hydraulic level gauge (33) for monitoring the amount of hydraulic oil in the hydraulic oil tank (23); An oil level gauge (34) for monitoring the amount of oil in an oil tank of an aircraft engine; An oil pressure sensor (35) for measuring the fuel pressure before the fuel delivery port of an aircraft engine; and a torque and speed sensor (36) for measuring the torque and speed provided by the hydraulic motor (24) when the aircraft engine is started.

4. The aircraft engine ground starting system according to claim 1, characterized in that: The oil supply module (40) comprises: A fuel tank (41) for holding fuel required for starting and operating the aircraft engine; A fuel pump (42) for supplying fuel at a suitable pressure to an aircraft engine; and a fuel filter (43) for filtering impurities in the fuel.

5. The aircraft engine ground starting system according to claim 3, characterized in that: The clutch (25) is respectively connected to the torque speed sensor (36), the transmission shaft of the aircraft engine and the electric push rod (17) to transmit the power provided by the hydraulic motor (24) to the aircraft engine and to disengage the clutch (25) from the transmission shaft of the aircraft engine at a specified time under the action of the electric push rod (17) according to the needs of the aircraft engine starting process.

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