CN116398300B - Control method and system for air stopping and restarting of turboshaft engine - Google Patents
Control method and system for air stopping and restarting of turboshaft engine Download PDFInfo
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/262—Restarting after flame-out
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention provides a control method and a system for restarting a turboshaft engine by parking in the air, wherein the method comprises the following steps: when the engine is monitored to stop in the air, acquiring a plurality of flight parameters and relative flight heights of the aircraft, and if the flight parameters are smaller than corresponding preset limit values, performing ignition and restarting; if the gas generator is still not started successfully when the rotating speed of the gas generator is reduced to the preset restarting maximum rotating speed, calculating the preset restarting time and the free falling time according to the relative flying height, and judging whether the preset restarting condition is met; if the preset restart condition is met, determining a manual or automatic restart mode by judging whether the PMS band switch is operated, and controlling the engine to restart to the rotating speed in the air slow-running state. The invention provides a manual and automatic engine air restarting control logic, which can shorten the engine restarting time, increase the intelligent control degree of the engine and improve the self-rescue capability under emergency conditions, thereby ensuring the flight safety.
Description
Technical Field
The invention relates to the technical field of aircraft engine air stopping and restarting, in particular to a control method and a system for the air stopping and restarting of a turboshaft engine.
Background
The helicopter loses power when the turboshaft engine is stopped in the air, so that the engine needs to be restarted to quickly recover power to ensure flight safety, and enough lift force is provided for the helicopter.
The existing control logic needs to wait for the speed n g of the gas generator to drop to the maximum speed n g- Restarting allowed for restarting before starting the restarting procedure, and no restarting measures exist in the process from the stopping time of the engine to the maximum speed n g- Restarting allowed for restarting, thus wasting time. In fact, during the process of reducing the rotation speed, the control system always supplies oil to the engine, and if the ignition system is started, a certain probability of successful ignition is provided, so that the restarting time is shortened.
Secondly, when the gasifier speed n g drops to the maximum speed n g- Restarting allowed for restart, the existing over-the-air restart requires manual operation, i.e. "manual restart": the artificial wave PMS band switch dials the switch from flying to stopping and then to flying. In some emergency situations, however, the pilot has the possibility of being unable to operate the PMS band switch due to unreliability. In addition, whether the helicopter can perform an air restart is mainly affected by factors such as flying height, atmospheric temperature, flying mach number, and the like. If the time t 1 from the restarting of the engine to the slow-flight vehicle (hereinafter referred to as restarting time) is less than the free-fall time t 2 of the helicopter and there is a sufficient time margin, the restarting condition is provided, whereas if t 1 is greater than t 2 or there is no time margin, the restarting condition is not provided. At present, whether the helicopter is restarted or not needs a pilot to judge the relative flying height, and the restarting time t 1 is estimated empirically and can be determined after being weighed. Therefore, in the emergency when the engine is stopped, the pilot is required to pay attention to the flying height at the moment, so that the pilot energy is dispersed, and the flying risk is increased.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to solve the limitation of the engine air-stop restarting control logic in the prior art, so as to provide a control method and a system for the turboshaft engine air-stop restarting, which can shorten the engine restarting time, increase the intelligent control degree of the engine, improve the self-rescue capability under emergency and ensure the flight safety through the manual and automatic restarting control logic.
The technical scheme for solving the technical problems is as follows:
in a first aspect, the present invention provides a control method for restarting a turboshaft engine by parking in air, comprising the steps of:
When the engine is monitored to stop in the air, a plurality of flight parameters and relative flight heights of the aircraft are obtained, if the flight parameters are smaller than corresponding preset limiting values, an ignition system is started to perform ignition and restarting, and the flight parameters comprise: the gas generator rotating speed, the power turbine rotating speed, the output shaft torque and the fuel oil flow;
if the gas generator is still not started successfully when the rotation speed of the gas generator is reduced to the preset maximum rotation speed for restarting, calculating preset restarting time and free falling time according to the relative flying height, and judging whether the preset restarting time and free falling time meet preset restarting conditions or not;
if the preset restart condition is satisfied, determining to execute a manual restart mode or an automatic restart mode by judging whether a PMS band switch is operated, and controlling the engine to restart to a rotational speed in an on-air coasting state based on the determined restart mode.
According to the control method for the in-flight stop and restart of the turboshaft engine, after the in-flight stop of the engine is monitored, the ignition system is started to perform ignition and restart according to whether the flight parameter is smaller than the corresponding preset limiting value, if the starting is still unsuccessful when the rotating speed of the gas generator is continuously reduced to the preset restarting rotating speed, whether the preset restarting condition is met is judged through the relative flight height, if the preset restarting condition is met, the restarting mode is determined through judging whether the PMS band switch is operated, and the engine is controlled to restart to the rotating speed in an in-flight slow-running state. The invention provides a manual and automatic engine air restarting control logic, which can shorten the engine restarting time, increase the intelligent control degree of the engine and improve the self-rescue capability under emergency conditions, thereby ensuring the flight safety.
Optionally, the process of calculating the preset restart time and the free fall time according to the relative flying height comprises the following steps: the method comprises the steps of obtaining preset restarting time from the maximum continuous state parking restarting to the air slow vehicle state under the conditions of different absolute flight heights, different temperatures and different flight Mach numbers of an airplane through a high-altitude simulation experiment in advance; determining the current absolute flight height according to the relative flight height, and acquiring the corresponding preset restarting time under the current flight height according to the absolute flight height; and calculating the free falling time of the aircraft at the current altitude according to the relative flying altitude.
According to the invention, whether the helicopter can execute the air restarting is considered, and the helicopter is mainly influenced by factors such as flight altitude, atmospheric temperature, flight Mach number and the like, so that the restarting time required by the aircraft to stop and restart to an air slow-car state in a maximum continuous state after the engine is stopped in air under different absolute flight altitudes and corresponding flight conditions is obtained through an overhead simulation experiment, and the preset restarting time required by the aircraft to restart to the air slow-car state under the relative flight altitude can be simulated after the aircraft is stopped in air in a sudden engine under a real flight state. And then calculating the free falling time when the aircraft is not restarted at the relative flying height, and judging whether the aircraft can be restarted at the current relative flying height according to the two time calculation results.
Optionally, the preset restart conditions include: calculating the time difference ratio between the preset restarting time and the free falling time, wherein the calculation formula is as follows:
wherein the formula is preset restarting time, free falling time and time difference ratio; and if the time difference ratio is larger than a preset time margin, a restarting condition is provided.
The invention calculates the preset restarting time and free falling time under the height by the relative flying height, and judges whether the restarting condition is provided at the moment according to the preset restarting condition. If the time t 1 from restarting the engine to the slow-flying vehicle (hereinafter referred to as restarting time) is less than the free falling time t 2 of the helicopter and a sufficient time margin exists, a restarting condition is provided; if t 1 is greater than t 2, or there is no time margin, the restart condition is not provided, and even if the restart is performed, the aircraft continues to drop due to insufficient engine speed before the restart is successful, so that the aircraft does not start successfully when reaching the ground, and serious accidents occur. Therefore, before restarting, whether the current relative flight altitude meets the preset restarting condition is judged, and the flight safety can be improved.
Optionally, the preset time margin ranges from 0.5 to 1.0.
According to the invention, whether the restarting condition is provided under the relative flying height of the air parking of the aircraft engine is judged by setting the time margin, so that the sufficient restarting time under the current height can be ensured. The time margin can be adjusted according to actual conditions, errors in pilot experience judgment can be avoided, and flight risks are reduced.
Optionally, the process of determining whether to perform the manual restart mode or the automatic restart mode by judging whether the PMS band switch is operated, and controlling the engine restart to the rotational speed in the on-air slow vehicle state based on the determined restart mode includes: if the PMS band switch is operated before the rotation speed of the gas generator is reduced to the preset maximum restart rotation speed, a manual restart mode is executed, a pilot manually dials the PMS band switch, dials the switch from flying to stopping and then to flying, an ignition system, a fuel system and a starting system of the airplane start to work, and a numerical control system controls the engine to start to rotate at the speed in an air slow-running state; if the PMS band switch is not operated before the rotation speed of the gas generator is reduced to the preset maximum restart rotation speed, an automatic restart mode is executed, the PMS band switch is not required to be manually stirred, an ignition system, a fuel system and a starting system of the aircraft automatically start to work, and a numerical control system controls the engine to start to rotate at the air slow-running state.
According to the invention, the automatic restarting mode is set on the basis of keeping the manual restarting mode, so that a pilot can keep the right of controlling the aircraft, the intelligent control degree of the aircraft can be increased, the energy of the pilot can not be dispersed additionally, the defect of fault countermeasures in emergency is overcome, and the flight risk is reduced.
Optionally, the on-air slow-car condition characterizes an operating condition of engine minimum thrust during an aircraft on-air flight descent.
The invention can control the engine to restart to an air slow vehicle state through the control logic of the engine air stop restarting. The air stopping restarting is to regain lift force, after the rotation speed of the gas generator is reduced to the maximum rotation speed allowed by restarting, a restarting mode is selected and the engine is controlled to restart to an air slow-running state, at the moment, the rotation speed of the power turbine of the airplane is 100%, the load rod is at the lowest position, the corresponding rotation speed of the gas generator is the slow-running rotation speed, the airplane has certain flight thrust, the airplane is successfully started, and at the moment, the rotation speed can be continuously increased to reach a normal flight state.
Optionally, the method further comprises: if the preset restarting condition is not met, the automatic restarting mode is canceled regardless of whether the PMS band switch is operated, the manual restarting mode is reserved, and early warning reminding is carried out.
The invention judges whether the current altitude has the restarting condition or not according to the relative altitude of the airplane when the engine is stopped in the air, if the current altitude does not have the restarting condition, the automatic restarting mode is directly forbidden, and the manual restarting mode is reserved, but the pilot is reminded of 'the current altitude is unsuitable for restarting', and the pilot can perform the next operation according to the current reminding. The device can not only reserve the right of the pilot to control the aircraft, but also inform the pilot of the current judgment result for the pilot to refer to, thereby improving the self-rescue capability in the emergency situation.
In a second aspect, embodiments of the present invention provide a control system for an over-the-air stop restart of a turboshaft engine, the system comprising:
the ignition restarting module is used for acquiring a plurality of flight parameters and relative flight heights of the aircraft after the engine is monitored to stop in the air, and starting an ignition system to perform ignition restarting if the flight parameters are smaller than corresponding preset limiting values, wherein the flight parameters comprise: the gas generator rotating speed, the power turbine rotating speed, the output shaft torque and the fuel oil flow;
The condition judging module is used for calculating preset restarting time and free falling time according to the relative flying height if the gas generator is still not started successfully when the rotating speed of the gas generator is reduced to the preset restarting maximum rotating speed, and judging whether the preset restarting time and free falling time meet preset restarting conditions or not;
And a restarting module for determining to execute a manual restarting mode or an automatic restarting mode by judging whether the PMS band switch is operated if the preset restarting condition is satisfied, and controlling the engine to restart to a rotational speed in an on-air slow-running state based on the determined restarting mode.
According to the control system for the in-flight stop and restart of the turboshaft engine, after the in-flight stop of the engine is monitored, the ignition system is started to perform ignition and restart according to whether the flight parameter is smaller than the corresponding preset limiting value, if the starting is still unsuccessful when the rotating speed of the gas generator is continuously reduced to the preset restarting rotating speed, whether the preset restarting condition is met is judged through the relative flight height, if the preset restarting condition is met, the restarting mode is determined through judging whether the PMS band switch is operated, and the engine is controlled to restart to the rotating speed in an in-flight slow-running state. The invention provides a manual and automatic engine air restarting control logic, which can shorten the engine restarting time, increase the intelligent control degree of the engine and improve the self-rescue capability under emergency conditions, thereby ensuring the flight safety.
In a third aspect, an embodiment of the present invention provides a computer apparatus, including: the system comprises a memory and a processor, wherein the memory and the processor are in communication connection, the memory stores computer instructions, and the processor executes the computer instructions, thereby executing the method in the first aspect or any optional implementation manner of the first aspect.
In a fourth aspect, embodiments of the present invention provide a computer-readable storage medium storing computer instructions for causing a computer to perform the method of the first aspect, or any one of the alternative embodiments of the first aspect.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a control method for air stopping and restarting of a turboshaft engine according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a control system for air-stop restarting of a turboshaft engine according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a computer device according to an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The embodiment of the invention provides a control method for restarting a turboshaft engine by stopping in the air, which takes a slit extrusion type coating die head as an example, as shown in figure 1, and specifically comprises the following steps:
Step S1: when the engine is monitored to stop in the air, a plurality of flight parameters and relative flight heights of the aircraft are obtained, if the flight parameters are smaller than corresponding preset limiting values, an ignition system is started to perform ignition and restarting, and the flight parameters comprise: the gas generator rotation speed, the power turbine rotation speed, the output shaft torque and the fuel oil flow.
Specifically, in embodiments of the present invention, the power turbine rotor and the gasifier rotor are at a higher rotational speed during normal flight of the aircraft. When an aircraft is flying in the air, the engine may be stopped due to mechanical failure, electronic system failure, flight operation failure, foreign matter influence (bird strike), and the like. After the engine is shut down in air, the power turbine speed n p and the gas generator speed n g of the engine gradually decrease. The output shaft torque Mkp, the fuel flow wf of the aircraft will also be relatively low at this time, but the control system still supplies the engine with fuel. Therefore, after the engine is monitored to stop in the air, the flight parameters of the aircraft at the moment are acquired: power turbine speed n p, gas generator speed n g, output shaft torque Mkp, and fuel flow wf. At this time, each flight parameter falls within the limit value, which is a prerequisite for restarting. For example: if the output shaft torque Mkp is greater than the limit value after stopping, the numerical control system restarts at this time, the oil supply amount is reduced because the output shaft torque Mkp is greater than the limit value, or the engine is damaged more seriously at this time, and the self-rotation and downslide time of the helicopter is delayed. Therefore, if all the flight parameters are smaller than the corresponding preset limit values, the starting electromagnetic valve and the ignition system are directly opened, and the fuel system continues to supply fuel. If the starting is successful, the subsequent control procedure is terminated.
Step S2: if the gas generator is still not started successfully when the rotation speed of the gas generator is reduced to the preset maximum rotation speed for restarting, calculating preset restarting time and free falling time according to the relative flying height, and judging whether the preset restarting time and free falling time meet preset restarting conditions.
Specifically, in the embodiment of the present invention, if after starting the ignition system, the rotation speed n g of the gas generator continues to decrease, and when the gas generator has not been started successfully when decreasing to the preset restart maximum rotation speed n g- Restarting , the current relative flight height H 2 is obtained, and the preset restart time t 1 and the free fall time t 2 are calculated according to the relative flight height H 2, and the calculation process is as follows:
1. The preset restarting time T 1 from the maximum continuous state parking restarting to the air slow state under the conditions of different absolute flying heights H 1 (for example, 1km, 2km … … liter limit H max, but not limited to the above) and different temperatures T (for example, ISA-45, ISA, ISA+35 … …, but not limited to the above) is obtained in advance through a high altitude simulation experiment, and the preset restarting time T 1 is formed as follows:
2. Determining the current absolute flight altitude according to the relative flight altitude, calculating the corresponding restarting time under the current flight altitude by adopting a quadratic linear interpolation method according to the absolute flight altitude and the atmospheric temperature based on the table. For example, the aircraft is stopped under the conditions of 1.5km and ISA+37.5deg.C, the height of 1.5km is linearly interpolated by the table above, the restarting time t 1(1.5km、ISA+35)、t1(1.5km、ISA+40) is linearly interpolated by t 1(1.5km、ISA+35)、t1(1.5km、ISA+40) under the conditions of ISA+35 and ISA+40 respectively, and then t 1(1.5km、ISA+37.5) is linearly interpolated by t 1(1.5km、ISA+35)、t1(1.5km、ISA+40), and the value is taken as the restarting time of the current height.
3. And calculating the free falling time of the aircraft at the current altitude according to the relative flying altitude. Taking the free falling body as the limit of the aircraft descent, calculating the free falling body time of the aircraft at the current relative altitude, wherein the formula is as follows:
Where g is the gravitational acceleration.
In the embodiment of the invention, whether the restarting time and the free fall time meet the preset restarting conditions is judged, wherein the preset restarting conditions are as follows: and calculating a time difference value between the restarting time and the free falling time, and if the time difference value A 1 is larger than a preset time margin, providing restarting conditions. The calculation formula of the time difference ratio is as follows:
the value range of the preset time margin is 0.5-1.0, but the preset time margin is not limited to the value range, and the preset time margin can be adjusted according to actual conditions.
Step S3: if the preset restart condition is satisfied, determining to execute a manual restart mode or an automatic restart mode by judging whether a PMS band switch is operated, and controlling the engine to restart to a rotational speed in an on-air coasting state based on the determined restart mode.
Specifically, in the embodiment of the present invention, when n g drops to n g- Restarting , if a >0.5, the restart mode is determined by determining whether the current PMS band switch is operated. The restarting mode comprises a manual restarting mode and an automatic restarting mode.
1. If the PMS band switch is operated before the rotation speed of the gas generator is reduced to the preset maximum restart rotation speed, the automatic restart mode is canceled, the manual restart mode is executed, the pilot manually dials the PMS band switch, dials the switch from flying to stopping and then to flying, an ignition system, a fuel system and a starting system of the airplane start to work, and the numerical control system controls the rotation speed of the engine in an air slow-running state.
2. If the PMS band switch is not operated before the rotation speed of the gas generator is reduced to the preset maximum restart rotation speed, a manual restart program is automatically executed, namely, the PMS band switch is not required to be manually stirred, an ignition system, a fuel system and a starting system of the airplane automatically start to work, and a numerical control system controls the engine to start to the rotation speed in an air slow-running state.
In addition, if the preset restarting condition is not met, namely A is less than or equal to 0.5, the automatic restarting mode is canceled regardless of whether the PMS band switch is operated, the manual restarting mode is reserved, and an early warning is carried out to remind the pilot that the current altitude is not suitable for restarting, so that the right of the pilot to control the aircraft is reserved.
According to the control method for the in-flight stop and restart of the turboshaft engine, after the in-flight stop of the engine is monitored, the ignition system is started to perform ignition and restart according to whether the flight parameter is smaller than the corresponding preset limiting value, if the starting is still unsuccessful when the rotating speed of the gas generator is continuously reduced to the preset restarting rotating speed, whether the preset restarting condition is met is judged through the relative flight height, if the preset restarting condition is met, the restarting mode is determined through judging whether the PMS band switch is operated, and the engine is controlled to restart to the rotating speed in an in-flight slow-running state. The invention provides a manual and automatic engine air restarting control logic, which can shorten the engine restarting time, increase the intelligent control degree of the engine and improve the self-rescue capability under emergency conditions, thereby ensuring the flight safety.
The embodiment of the invention provides a control system for air stopping and restarting of a turboshaft engine, as shown in fig. 2, the system comprises:
The ignition restarting module 1 is configured to acquire a plurality of flight parameters and relative flight heights of an aircraft after an engine in-flight stop is monitored, and if the flight parameters are all smaller than corresponding preset limit values, start an ignition system to perform ignition restarting, where the flight parameters include: the gas generator rotation speed, the power turbine rotation speed, the output shaft torque and the fuel oil flow. Details refer to the related description of step S1 in the above method embodiment, and will not be described herein.
And the condition judging module 2 is used for calculating preset restarting time and free falling time according to the relative flying height if the starting is still unsuccessful when the rotating speed of the gas generator is reduced to the preset restarting maximum rotating speed, and judging whether the preset restarting time and free falling time meet preset restarting conditions. For details, refer to the related description of step S2 in the above method embodiment, and no further description is given here.
A restarting module 3 for determining to execute the manual restarting mode or the automatic restarting mode by judging whether the PMS band switch is operated if the preset restarting condition is satisfied, and controlling the engine to restart to the rotational speed in the on-air slow-running state based on the determined restarting mode. For details, refer to the related description of step S3 in the above method embodiment, and no further description is given here.
The control system for the air stop and restart of the turboshaft engine provided by the embodiment of the invention provides an engine air restart control logic with both manual and automatic functions, which can shorten the engine restart time, increase the intelligent control degree of the engine and improve the self-rescue capability under emergency conditions, thereby ensuring the flight safety.
Fig. 3 shows a schematic structural diagram of a computer device according to an embodiment of the present invention, including: a processor 901 and a memory 902, wherein the processor 901 and the memory 902 may be connected by a bus or otherwise, for example in fig. 3.
The processor 901 may be a central processing unit (Central Processing Unit, CPU). The Processor 901 may also be other general purpose processors, digital signal processors (DIGITAL SIGNAL processors, DSPs), application SPECIFIC INTEGRATED Circuits (ASICs), field-Programmable gate arrays (Field-Programmable GATE ARRAY, FPGA) or other Programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or combinations thereof.
The memory 902 is used as a non-transitory computer readable storage medium for storing a non-transitory server program, a non-transitory computer executable program, and modules, such as program instructions/modules corresponding to the methods in the above method embodiments. The processor 901 executes various functional applications of the processor and data processing, i.e., implements the methods in the above-described method embodiments, by running non-transitory server programs, instructions, and modules stored in the memory 902.
The memory 902 may include a storage program area and a storage data area, wherein the storage program area may store an operating system, at least one application program required for a function; the storage data area may store data created by the processor 901, and the like. In addition, the memory 902 may include high-speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid state storage device. In some embodiments, memory 902 optionally includes memory remotely located relative to processor 901, which may be connected to processor 901 via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
One or more modules are stored in the memory 902 that, when executed by the processor 901, perform the methods of the method embodiments described above.
The specific details of the computer device may be correspondingly understood by referring to the corresponding related descriptions and effects in the above method embodiments, which are not repeated herein.
It will be appreciated by those skilled in the art that implementing all or part of the above-described methods in the embodiments may be implemented by a computer program for instructing relevant hardware, and the implemented program may be stored in a computer readable storage medium, and the program may include the steps of the embodiments of the above-described methods when executed. The storage medium may be a magnetic disk, an optical disk, a Read-Only Memory (ROM), a random access Memory (Random Access Memory, RAM), a Flash Memory (Flash Memory), a hard disk (HARD DISK DRIVE, abbreviated as HDD), a Solid state disk (Solid-STATE DRIVE, SSD), or the like; the storage medium may also comprise a combination of memories of the kind described above.
Although embodiments of the present invention have been described in connection with the accompanying drawings, various modifications and variations may be made by those skilled in the art without departing from the spirit and scope of the invention, and such modifications and variations are within the scope of the invention as defined by the appended claims.
Claims (10)
1. The control method for the in-flight stopping and restarting of the turboshaft engine is characterized by comprising the following steps:
When the engine is monitored to stop in the air, a plurality of flight parameters and relative flight heights of the aircraft are obtained, if the flight parameters are smaller than corresponding preset limiting values, an ignition system is started to perform ignition and restarting, and the flight parameters comprise: the gas generator rotating speed, the power turbine rotating speed, the output shaft torque and the fuel oil flow;
if the gas generator is still not started successfully when the rotation speed of the gas generator is reduced to the preset maximum rotation speed for restarting, calculating preset restarting time and free falling time according to the relative flying height, and judging whether the preset restarting time and free falling time meet preset restarting conditions or not;
If the preset restart condition is satisfied, it is determined to perform a manual restart mode or an automatic restart mode by determining whether a PMS band switch is operated, and the engine is restarted to a rotational speed in an on-air coasting state based on the determined restart mode.
2. The control method for the over-the-air stop restart of a turboshaft engine according to claim 1, wherein the process of calculating a preset restart time and a free fall time from the relative fly height comprises:
The method comprises the steps of obtaining preset restarting time from the maximum continuous state parking restarting to the air slow vehicle state under the conditions of different absolute flight heights, different temperatures and different flight Mach numbers of an airplane through a high-altitude simulation experiment in advance;
Determining the current absolute flight height according to the relative flight height, and acquiring the corresponding preset restarting time under the current flight height according to the absolute flight height;
and calculating the free falling time of the aircraft at the current altitude according to the relative flying altitude.
3. The control method for the over-the-air stop restart of the turboshaft engine according to claim 2, wherein the preset restart conditions include:
calculating the time difference ratio between the preset restarting time and the free falling time, wherein the calculation formula is as follows:
Wherein t 1 is preset restarting time, t 2 is free falling time, and A is a time difference ratio;
If the time difference ratio A is larger than the preset time margin, a restarting condition is provided.
4. The control method for the over-the-air stop and restart of the turboshaft engine according to claim 3, wherein the preset time margin is in a range of 0.5 to 1.0.
5. The control method for the over-the-air stop restart of the turboshaft engine according to claim 1, wherein the process of determining to execute the manual restart mode or the automatic restart mode by judging whether the PMS band switch is operated, and controlling the engine restart to the rotational speed in the over-the-air slow-running state based on the determined restart mode, comprises:
If the PMS band switch is operated before the rotation speed of the gas generator is reduced to the preset maximum restart rotation speed, a manual restart mode is executed, a pilot manually dials the PMS band switch, dials the switch from flying to stopping and then to flying, an ignition system, a fuel system and a starting system of the airplane start to work, and a numerical control system controls the engine to start to rotate at the speed in an air slow-running state;
If the PMS band switch is not operated before the rotation speed of the gas generator is reduced to the preset maximum restart rotation speed, an automatic restart mode is executed, the PMS band switch is not required to be manually stirred, an ignition system, a fuel system and a starting system of the aircraft automatically start to work, and a numerical control system controls the engine to start to rotate at the air slow-running state.
6. The method for controlling an over-the-air stop-and-restart of a turboshaft engine of claim 5 wherein the over-the-air slow-running condition characterizes an operating condition of engine minimum thrust during an over-the-air flight descent of the aircraft.
7. The control method for the over-the-air stop restart of the turboshaft engine according to claim 5, further comprising: if the preset restarting condition is not met, the automatic restarting mode is canceled regardless of whether the PMS band switch is operated, the manual restarting mode is reserved, and early warning reminding is carried out.
8. A control system for an over-the-air stop restart of a turboshaft engine, comprising:
the ignition restarting module is used for acquiring a plurality of flight parameters and relative flight heights of the aircraft after the engine is monitored to stop in the air, and starting an ignition system to perform ignition restarting if the flight parameters are smaller than corresponding preset limiting values, wherein the flight parameters comprise: the gas generator rotating speed, the power turbine rotating speed, the output shaft torque and the fuel oil flow;
The condition judging module is used for calculating preset restarting time and free falling time according to the relative flying height if the gas generator is still not started successfully when the rotating speed of the gas generator is reduced to the preset restarting maximum rotating speed, and judging whether the preset restarting time and free falling time meet preset restarting conditions or not;
And a restart module for determining to execute a manual restart mode or an automatic restart mode by judging whether the PMS band switch is operated if the preset restart condition is satisfied, and controlling the engine restart to a rotational speed in an on-air coasting state based on the determined restart mode.
9. An electronic device, comprising:
a memory and a processor in communication with each other, the memory having stored therein computer instructions, the processor executing the computer instructions to thereby perform the control method of the over-the-air stop restart of the turboshaft engine of any one of claims 1-7.
10. A computer-readable storage medium storing computer instructions for causing the computer to execute the control method of the turboshaft engine in-flight stop restart of any one of claims 1 to 7.
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| CN106043715A (en) * | 2016-05-27 | 2016-10-26 | 襄阳宏伟航空器有限责任公司 | In-flight auto-ignition control method of engine of unmanned aerial vehicle |
| CN114151208A (en) * | 2020-11-30 | 2022-03-08 | 西安交通大学 | Real-time aerial parking monitoring method for aircraft engine |
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| CN106043715A (en) * | 2016-05-27 | 2016-10-26 | 襄阳宏伟航空器有限责任公司 | In-flight auto-ignition control method of engine of unmanned aerial vehicle |
| CN114151208A (en) * | 2020-11-30 | 2022-03-08 | 西安交通大学 | Real-time aerial parking monitoring method for aircraft engine |
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