CN117432529B - Control method and system for high-altitude quick start of aircraft and aircraft - Google Patents
Control method and system for high-altitude quick start of aircraft and aircraft Download PDFInfo
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- CN117432529B CN117432529B CN202311753413.2A CN202311753413A CN117432529B CN 117432529 B CN117432529 B CN 117432529B CN 202311753413 A CN202311753413 A CN 202311753413A CN 117432529 B CN117432529 B CN 117432529B
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- 238000000034 method Methods 0.000 title claims abstract description 26
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 85
- 239000001301 oxygen Substances 0.000 claims abstract description 85
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 85
- 239000000446 fuel Substances 0.000 claims description 20
- 238000002485 combustion reaction Methods 0.000 claims description 19
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 10
- 230000007246 mechanism Effects 0.000 claims description 8
- 239000002828 fuel tank Substances 0.000 claims description 6
- 230000001502 supplementing effect Effects 0.000 claims description 6
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 36
- 238000006243 chemical reaction Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000006213 oxygenation reaction Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 210000004556 brain Anatomy 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 239000011259 mixed solution Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
- Control Of Turbines (AREA)
Abstract
The invention relates to the technical field of quick start of a turbojet engine of an aircraft, and discloses a control method and a system for quick start of the aircraft at high altitude, and the aircraft comprises the turbojet engine, an oxygen combustion-supporting system and an oil circuit system which are connected with the turbojet engine, wherein the control method comprises the following steps: acquiring altitude data of the aircraft; when the height data of the aircraft is determined to be greater than a set value, the oxygen combustion-supporting system is controlled to be started, and oxygen is supplied to the turbojet engine, so that the operation data of the aircraft reach a preset value. The invention can realize that the turbojet engine can be more rapid and stable when being started by adding auxiliary oxygen, and is also beneficial to solving the problem of difficult starting of the turbojet engine at high altitude and on a plateau.
Description
Technical Field
The invention relates to the technical field of quick start of an aircraft turbojet engine, in particular to a control method and system for quick start of an aircraft in high altitude and an aircraft.
Background
The altitude starting is one of important examination contents in the design and shaping stage of the aeroengine, the starting performance reflects the starting adaptive capacity of the engine to the altitude pressure environment, and whether the engine can smoothly run under various environmental conditions is also determined. In plateau areas or high altitudes, the atmospheric pressure, density and oxygen content are significantly lower than the sea level, so that the air flow rate that the engine can inhale at the same rotational speed during the starting process is much smaller. And simultaneously, the fuel oil and lubrication system efficiency of the engine are reduced. The above factors all make the engine start-up difficulty on the highland far higher than that of the sea level or low altitude atmosphere. The present invention has been made in view of the above-mentioned difficulties in starting the turbojet engine at high altitude.
Disclosure of Invention
The invention aims to provide a control method and system for quick high-altitude starting of an aircraft and the aircraft, so as to solve the problems in the prior art.
In order to achieve the above object, the present invention provides the following solutions: the invention provides a control method for quick high-altitude starting of an aircraft, wherein the aircraft comprises a turbojet engine, an oxygen combustion-supporting system and an oil circuit system, wherein the oxygen combustion-supporting system and the oil circuit system are connected with the turbojet engine, and the control method comprises the following steps:
Acquiring altitude data of the aircraft;
when the height data of the aircraft is determined to be greater than a set value, the oxygen combustion-supporting system is controlled to be started, and oxygen is supplied to the turbojet engine, so that the operation data of the aircraft reach a preset value.
Preferably, the aircraft includes a motor connected to the turbojet engine, and when the altitude data of the aircraft is initial altitude data, the control method further includes:
Starting the turbojet engine by controlling the motor to start, and enabling the rotating speed of the turbojet engine to reach a first preset value;
And controlling the motor to be closed and supplying oil through the oil way system so as to enable the rotating speed of the turbojet engine to reach a second preset value.
Preferably, the method for controlling the motor to be turned off and supplying oil through the oil path system so that the rotation speed of the turbojet engine reaches a second preset value further comprises:
When the oil way system supplies oil and the height data of the aircraft is larger than a set value, the oxygen combustion-supporting system is controlled to be started and oxygen is supplied to the turbojet engine, so that the rotating speed of the turbojet engine reaches a second preset value.
Preferably, when the operation data of the turbojet engine is determined not to reach a preset value, the oxygen combustion-supporting system is controlled to be started, and oxygen is supplied to the turbojet engine.
Preferably, the operation data includes at least rotational speed data and temperature data.
A control system, comprising:
The acquisition unit is used for acquiring the altitude data of the aircraft;
the judging unit is used for judging whether the height data of the aircraft is larger than a set value or not;
And the first executing mechanism is used for controlling the oxygen combustion-supporting system to be started and supplying oxygen to the turbojet engine when the height data of the aircraft is determined to be larger than a set value, so that the operation parameters of the aircraft reach a preset value.
Preferably, the method further comprises:
and the second executing mechanism is used for acquiring the operation data of the turbojet engine and controlling the oil supply of the oil way system.
An aircraft, comprising:
The turbojet engine;
the oxygen combustion-supporting system is connected with the turbojet engine;
the oil circuit system is connected with the turbojet engine;
The control system.
Preferably, the oxygen combustion-supporting system comprises:
An oxygen bottle for storing oxygen;
The annular air dispersing pipe is fixedly connected to a combustion chamber of the turbojet engine through a bracket, and a plurality of long branch pipes and short branch pipes are circumferentially and equidistantly communicated on the annular air dispersing pipe;
The oxygen bottle is communicated with the annular air dispersing pipe through an air passage pipeline, and the air passage pipeline is provided with a fire control valve and a constant pressure valve.
Preferably, the oil path system includes:
The fuel tank is used for storing fuel;
And the gear pump is used for feeding the fuel pump in the fuel tank into the combustion chamber of the turbojet engine.
The invention discloses the following technical effects: when the turbojet engine of the aircraft is started, after the height data is judged, sufficient and continuous oxygen is provided for the turbojet engine through the oxygen combustion-supporting system, and the oil circuit system provides sufficient fuel under the condition that the conditions are met. When the proportion of fuel and oxygen in the turbojet engine is proper, the internal part of the turbojet engine can burst violent chemical reaction, the fuel burns to do work, and the turbojet engine can be more rapid and stable when started due to the addition of auxiliary oxygen, so that the problem that the turbojet engine is difficult to start at high altitude and on a high altitude can be solved.
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 embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a control system for high altitude quick start of an aircraft according to the present invention;
FIG. 2 is a schematic view of the structure of the annular diffuser pipe according to the present invention;
Wherein, 1, turbojet engine; 2. an ECU electronic control unit; 3. a flight control computer; 4. an oil tank; 5. a gear pump; 6. an oxygen cylinder; 7. a fire control valve; 8. a constant pressure valve; 9. annular air dispersing pipe.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. 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 order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Referring to fig. 1-2, the invention provides a control method for quick high altitude starting of an aircraft, which is characterized in that the aircraft comprises a turbojet engine 1, an oxygen combustion-supporting system and an oil circuit system which are connected with the turbojet engine 1, and the control method comprises the following steps:
acquiring altitude data of an aircraft;
When the height data of the aircraft is determined to be greater than a set value, the oxygen combustion-supporting system is controlled to be started and oxygen is supplied to the turbojet engine 1, so that the operation data of the aircraft reach a preset value.
When the turbojet engine 1 of the aircraft is started, after the altitude data is judged, sufficient and continuous oxygen is provided for the turbojet engine 1 through the oxygen combustion-supporting system, and the oil circuit system provides sufficient fuel under the condition that the condition is met. When the proportion of fuel and oxygen in the turbojet engine 1 is proper, the internal part of the turbojet engine 1 can burst a severe chemical reaction, the fuel burns to do work, and the turbojet engine 1 can be more rapid and stable when started due to the addition of auxiliary oxygen, so that the problem that the turbojet engine 1 is difficult to start at high altitude and on a high altitude can be solved.
In one embodiment of the control method, the aircraft comprises a motor connected with the turbojet engine 1, and when the altitude data of the aircraft is the initial altitude data, the control method further comprises:
Starting the turbojet engine 1 by controlling the motor to start, and enabling the rotating speed of the turbojet engine 1 to reach a first preset value;
The motor is controlled to be turned off and oil is supplied through the oil passage system so that the rotation speed of the turbojet engine 1 reaches a second preset value.
In the starting stage, the turbojet engine 1 drives the turbine to start to rotate from the motor, meanwhile, the oil circuit system starts to supply oil, after the rotating speed reaches a first preset value, the motor stops, the fuel is ignited to push the turbine to rotate, and after the turbine reaches a second preset value (cruising rotating speed), the oil circuit system continuously and independently works, so that the aircraft runs stably.
In another embodiment of the control method, the method for controlling the motor to be turned off and supplying oil through the oil path system so that the rotation speed of the turbojet engine 1 reaches a second preset value further includes:
When the oil way system supplies oil and the height data of the aircraft is greater than a set value, the oxygen combustion-supporting system is controlled to be started and oxygen is supplied to the turbojet engine 1, so that the rotating speed of the turbojet engine 1 reaches a second preset value.
In the starting stage, the turbojet engine 1 drives the turbine to start to rotate from a starting motor, meanwhile, an oil circuit system starts to supply oil, the motor stops after the rotating speed is brought to a first preset value, a GPS (global positioning system) carried by the aircraft is utilized for detecting height data, when the GPS detects that the current height is greater than a set value (greater than 3000 m), a fire control valve 7 is opened for oxygen supplementing and combustion supporting in a short time to push the turbine to rotate, and after the second preset value (cruising rotating speed) is reached, the oil circuit system starts to independently work, and oxygen is not needed to enable the aircraft to stably run.
In another embodiment of the control method, when it is determined that the operation data of the turbojet engine 1 does not reach the preset value, the oxygen combustion supporting system is controlled to be started and oxygen is supplied to the turbojet engine 1.
In a further preferred embodiment, the operating data at least include rotational speed data and temperature data.
When the aircraft is in the air and the turbojet engine 1 is in flameout due to accidents, the control system collects the cruising rotation speed, if the turbojet engine 1 is detected to be flameout due to the fact that the rotation speed is reduced by 20% of the current rotation speed within 1 second or the temperature is reduced by more than 20% of the current temperature, the turbojet engine 1 is judged to be flameout, secondary starting is needed, the altitude is judged again due to the fact that the turbojet engine 1 is in the high altitude, and if the oxygenation condition is met, the turbojet engine is restarted.
A control system, comprising:
the acquisition unit is used for acquiring the altitude data of the aircraft;
the judging unit is used for judging whether the height data of the aircraft is larger than a set value or not;
and the first executing mechanism is used for controlling the oxygen combustion-supporting system to be started and supplying oxygen to the turbojet engine 1 when the height data of the aircraft is determined to be greater than a set value, so that the operation parameters of the aircraft reach a preset value.
Further optimizing scheme, still include:
And the second executing mechanism is used for acquiring the operation data of the turbojet engine 1 and controlling the oil supply of the oil way system.
The whole control system consists of a flight control computer 3 and a control unit, wherein the flight control computer 3 carried by the aircraft participates in the control of the turbojet engine 1 besides controlling the attitude and navigation guidance of the aircraft. In the invention, before the turbojet engine 1 is started, the flight control computer 3 sends the air pressure height value of the current aircraft to the control unit (the control unit is set as the ECU electronic control unit 2, hereinafter referred to as ECU) of the turbojet engine 1 (the air pressure height value can be manually adjusted, the use is convenient under special conditions, such as low altitude, quick start is needed, the air pressure height value can be increased), and the ECU logically judges that the current height value does not need to use an oxygen supplementing function. When the ECU judges that the oxygen supplementing function is needed to be used, the flight control computer 3 sends down an opening instruction of the fire control valve 7, and the oxygen combustion-supporting system supplements oxygen for the turbojet engine 1; when starting, the ECU outputs an instruction to the motor, the gear pump 5 starts to work, the set rotating speed is reached, the motor is separated from the turbojet engine 1, the high-pressure high-temperature gas in the combustion chamber pushes the turbine to rotate, and in the acceleration stage, the ECU judges that no oxygen is added to the turbojet engine 1. If the current aircraft is located at a height of 5000 meters and is greater than the autonomous start (3000 meters) boundary, the turbojet engine 1 is started up to a predetermined rotational speed to perform the oxygenation operation. When the rotational speed of the turbojet engine 1 rises to a set value, information is fed back to the ECU, and the ECU outputs an instruction to open the fire control valve 7. While opening the fire control valve 7, the pump power is increased to supply sufficient fuel to the engine.
The ECU is a part of the ECU in the prior art, and the acquisition unit, the judgment unit, the first execution mechanism and the second execution mechanism are all special microcomputer controllers for engines in terms of application, and the ECU is composed of a microprocessor, a storage, an input/output interface, an analog-to-digital converter, a large-scale integrated circuit for shaping, driving and the like, as a common computer. The whole system plays the role of the engine brain. In the system operation, information such as the air pressure height value and the engine rotating speed from the flight control computer 3 is respectively received, whether the turbojet engine 1 needs to be opened to perform an oxygen supplementing program at the current height and the current rotating speed is judged according to the internally stored parameters, if the current height of the aircraft is 5000 meters and is greater than an autonomous starting (3000 meters) boundary, the turbojet engine 1 is started to reach the preset rotating speed to perform the oxygen supplementing operation. When the rotational speed of the turbojet engine 1 increases to a set value, a command is issued to the flight control computer 3, and the flight control computer 3 opens the fire control valve 7. While opening the fire control valve 7, the power of the gear pump 5 is increased to supply sufficient fuel to the turbojet engine 1.
An aircraft, comprising:
A turbojet engine 1;
The oxygen combustion-supporting system is connected with the turbojet engine 1;
The oil circuit system is connected with the turbojet engine 1;
And a control system.
Further optimizing scheme, oxygen combustion-supporting system includes:
An oxygen bottle 6 for storing oxygen;
the annular air dispersing pipe 9 is fixedly connected to a combustion chamber of the turbojet engine 1 through a bracket, and a plurality of long branch pipes and short branch pipes are circumferentially and equidistantly communicated on the annular air dispersing pipe 9;
Wherein the oxygen bottle 6 is communicated with the annular air dispersing pipe 9 through an air passage pipeline, and the air passage pipeline is provided with a fire control valve 7 and a constant pressure valve 8.
The oxygen bottle 6 is used for storing oxygen, and the oxygen bottle 6 is formed by spinning and welding a stainless steel plate. The working pressure of the oxygen cylinder 6 can reach 6Mpa, and the volume is customized according to the requirement of the turbojet engine 1; the fire control valve 7/electromagnetic valve controls the opening of the air circuit according to the instruction of the flight control computer 3 carried by the aircraft; the constant pressure valve 8 can regulate the oxygen pressure to about 0.4Mpa while reducing the flow rate to provide sufficient and continuous oxygen during the start-up phase of the turbojet engine 1. The combustion environment inside the turbojet engine 1 is prevented from being damaged due to the fact that the oxygen pressure is too high and the flow speed is too high, and the turbojet engine 1 is prevented from flameout. The annular air dispersing pipe 9 is fixedly connected to the combustion chamber of the turbojet engine 1 through a bracket, so that the whole oxygen combustion-supporting system is directly connected to the inside of the turbojet engine 1, and fewer devices are arranged in the oxygen combustion-supporting system, so that the air-supporting system is convenient to place in an aircraft with a small space.
The annular air dispersing pipe 9 is fixedly connected to the combustion chamber through a bracket; oxygen is respectively introduced into the preheating pipe of the combustion chamber through the long branch pipe and the short branch pipe, and enters the combustion chamber through the air hole outside the combustion chamber.
Further optimizing scheme, oil circuit system includes:
A fuel tank 4 for storing fuel;
a gear pump 5 for introducing the fuel pump in the fuel tank 4 into the combustion chamber of the turbojet engine 1.
The fuel tank 4 supplies fuel for starting and operating the turbojet engine 1. A mixed solution of 95% aviation kerosene and 5% lubricating oil is generally stored; the oil pump adopts a gear pump 5 driven by a brushless motor, when the motor drives the gear to rotate, the space volume at the disengaging side of the gear is changed from small to large, vacuum is formed, and liquid is sucked into the oil pump; in contrast, the space volume on the engagement side becomes smaller from large to small, squeezing the liquid into the pipeline. Thereby supplying fuel to the turbojet engine 1.
The invention mainly comprises an oxygen combustion-supporting system, an oil way system and a control system. When the turbojet engine 1 is started at high altitude, the control system judges the conditions, and the oxygen combustion-supporting system provides sufficient and continuous oxygen for the turbojet engine 1, and the oil circuit system provides sufficient fuel under the condition that the conditions are met. When the ratio of fuel and oxygen in the turbojet engine 1 is proper, the turbojet engine 1 can explode violently to perform chemical reaction, the fuel burns to do work, and the chemical energy is converted into internal energy to drive the turbine to do work. Generating power for the aircraft to fly.
The quick and stable start of the turbojet engine 1 affects the smooth operation of the aircraft, and under certain specific conditions (such as high altitude or high altitude environment), the turbojet engine 1 needs to be able to be started stably and quickly, in this process, the acceleration time needs to be shortened as much as possible under the condition that the turbojet engine 1 is satisfied from start to smooth operation, so whether the turbojet engine 1 can be started in the shortest time becomes a key technology. The starting time of the aircraft in the prior art at the altitude of 5000 meters is about 50 seconds, and after the method is applied, the starting time can be controlled within 25 seconds, and the starting time can be greatly shortened.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solutions of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (6)
1. The control method for the high-altitude quick start of the aircraft is characterized in that the aircraft comprises a turbojet engine (1), and an oxygen combustion-supporting system and an oil circuit system which are connected with the turbojet engine (1), and the control method comprises the following steps:
Acquiring altitude data of the aircraft;
When the height data of the aircraft is determined to be greater than a set value, controlling the oxygen combustion-supporting system to be started and supplying oxygen to the turbojet engine (1) so that the operation data of the aircraft reach a preset value;
The aircraft comprises a motor connected with the turbojet engine (1), and when the altitude data of the aircraft is initial altitude data, the control method further comprises:
starting the turbojet engine (1) by controlling the motor to be started, and enabling the rotating speed of the turbojet engine (1) to reach a first preset value;
controlling the motor to be closed and supplying oil through the oil way system so as to enable the rotating speed of the turbojet engine (1) to reach a second preset value;
The method for controlling the motor to be closed and supplying oil through the oil way system so that the rotating speed of the turbojet engine (1) reaches a second preset value further comprises the following steps:
When the oil way system supplies oil and the height data of the aircraft is larger than a set value, controlling the oxygen combustion-supporting system to be started and supplying oxygen to the turbojet engine (1) so that the rotating speed of the turbojet engine (1) reaches a second preset value;
when the operation data of the turbojet engine (1) is determined not to reach a preset value, controlling the oxygen combustion-supporting system to be started and supplying oxygen to the turbojet engine (1);
The operation data at least comprise rotating speed data and temperature data;
When the turbojet engine (1) is flameout due to accidents, the control system collects the cruising rotation speed, judges that the turbojet engine (1) is flameout, needs to be started for the second time, judges the height, and starts restarting to add oxygen if the oxygen adding conditions are met;
Before the turbojet engine (1) is started, the flight control computer (3) transmits an air pressure height value of the current aircraft to a control unit of the turbojet engine (1), the air pressure height value is manually adjusted, when the turbojet engine needs to be started quickly, the air pressure height value is increased, and the control unit logically judges that the current height value does not need to use an oxygen supplementing function;
the oxygen combustion-supporting system comprises:
The annular air dispersing pipe (9) is provided with a plurality of long branch pipes and short branch pipes which are communicated with each other at equal intervals in the circumferential direction; oxygen is respectively introduced into the preheating pipe of the combustion chamber through the long branch pipe and the short branch pipe, and enters the combustion chamber through the air hole outside the combustion chamber.
2. A control system for implementing a control method for the rapid start of an aircraft in altitude according to claim 1, comprising:
The acquisition unit is used for acquiring the altitude data of the aircraft;
the judging unit is used for judging whether the height data of the aircraft is larger than a set value or not;
and the first executing mechanism is used for controlling the oxygen combustion-supporting system to be started and supplying oxygen to the turbojet engine (1) when the height data of the aircraft is determined to be larger than a set value, so that the operation parameters of the aircraft reach a preset value.
3. A control system according to claim 2, further comprising:
and the second executing mechanism is used for acquiring the operation data of the turbojet engine (1) and controlling the oil supply of the oil way system.
4. An aircraft, comprising:
A turbojet engine (1);
an oxygen combustion-supporting system connected with the turbojet engine (1);
an oil path system connected with the turbojet engine (1);
a control system according to any one of claims 2-3.
5. The aircraft of claim 4, wherein the oxygen combustion system further comprises:
an oxygen bottle (6) for storing oxygen;
the annular air dispersing pipe (9) is fixedly connected to a combustion chamber of the turbojet engine (1) through a bracket;
the oxygen bottle (6) is communicated with the annular air dispersing pipe (9) through an air passage pipeline, and a fire control valve (7) and a constant pressure valve (8) are arranged on the air passage pipeline.
6. The aircraft of claim 4, wherein the oil circuit system comprises:
-a tank (4) for storing fuel;
And a gear pump (5) for introducing the fuel pump in the fuel tank (4) into the combustion chamber of the turbojet engine (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202311753413.2A CN117432529B (en) | 2023-12-20 | 2023-12-20 | Control method and system for high-altitude quick start of aircraft and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311753413.2A CN117432529B (en) | 2023-12-20 | 2023-12-20 | Control method and system for high-altitude quick start of aircraft and aircraft |
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| CN117432529A CN117432529A (en) | 2024-01-23 |
| CN117432529B true CN117432529B (en) | 2024-05-24 |
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| CN115059934A (en) * | 2022-05-26 | 2022-09-16 | 中国人民解放军总参谋部第六十研究所 | High-altitude quick start ignition system based on evaporating pipe combustion chamber |
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| CN215408888U (en) * | 2021-07-21 | 2022-01-04 | 上海睿瑞航空设备科技有限公司 | Micro-miniature aviation turbine engine device started by oxygen supplementation in plateau |
| CN115059934A (en) * | 2022-05-26 | 2022-09-16 | 中国人民解放军总参谋部第六十研究所 | High-altitude quick start ignition system based on evaporating pipe combustion chamber |
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| CN117432529A (en) | 2024-01-23 |
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