CN109026396B - Supersonic three-dimensional air inlet channel pneumatic control method - Google Patents
Supersonic three-dimensional air inlet channel pneumatic control method Download PDFInfo
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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Abstract
The invention relates to a supersonic three-dimensional air inlet channel pneumatic control method, which comprises the following steps: a. constructing a pneumatic simulation model; b. simulating and calculating the pneumatic characteristic; c. designing an air inlet structure according to the simulation calculation result in the step b; d. calibrating and debugging a controller for controlling the pneumatic state of the air inlet structure; e. and monitoring the pressure in the air inlet structure and controlling the blowing/sucking state in the air inlet mechanism in real time. According to the pneumatic control method for the supersonic three-dimensional air inlet, the structural design of the air inlet can be optimized, the structural performance of the air inlet is improved, and the stable working range of the air inlet structure is widened.
Description
Technical Field
The invention relates to a pneumatic control method for a supersonic three-dimensional air inlet channel, in particular to a pneumatic simulation active control method for a supersonic three-dimensional air inlet channel based on an air flow blowing and sucking adjusting means.
Background
In recent years, air-breathing hypersonic aircrafts are becoming the hot point of research and the key point of research in all military and strong countries. One of the most central components of the air-breathing hypersonic aerocraft is a scramjet engine which mainly comprises an air inlet, an isolation section, a combustion chamber, a tail nozzle and the like. The air inlet channel is positioned at the foremost end of the scramjet engine, compresses supersonic incoming flow, plays a role in speed reduction and pressurization, and simultaneously improves the temperature of air flow to enable the air flow to meet the requirement of a working window of a combustion chamber. When the scramjet engine normally works, airflow is compressed through an air inlet channel and still keeps supersonic flow, the supersonic airflow and fuel are mixed and combusted in a combustion chamber, and the combusted high-temperature high-pressure airflow expands through a tail nozzle and is sprayed out, so that thrust is provided for an aircraft. The aerodynamic performance of the air inlet channel has direct influence on the quality of air flow entering the combustion chamber, and further has direct relation to the performance of the scramjet engine and even the whole aircraft.
The supersonic air inlet channel is designed for supersonic speeds and even hypersonic cruise sections, and cannot normally work under the condition of low Mach number. Under the low-mach-number flight working condition, due to the comprehensive effects of back pressure, a wave system structure, boundary layer separation and the like, the supersonic air inlet channel can enter an un-started shock wave oscillation mode, a large separation area exists at the inlet of the air inlet channel, an arched shock wave exists in front of the air inlet channel, and the shock wave position moves back and forth abnormally, so that the aerodynamic performance of the aircraft is changed violently, uncertain factors are brought to the attitude control of the aircraft, and even the organism structure of the aircraft is damaged. In 1998, the United states and Russia jointly performed supersonic combustion flight tests, and the tests partially failed. The research and analysis after the fact show that the problem that the air inlet of the test aircraft cannot start at the Mach number of about 3.5 exists, although the air inlet starts automatically when the flight Mach number is increased to about 5, the air inlet amount of the air inlet is insufficient due to the existence of a large separation area at the throat of the air inlet, the controller judges that the air inlet does not start, and fuel injection cannot be carried out according to expectation. In 2004, in the united states, in an X-43A flight test, in order to improve the success rate of the test, a valve actuating mechanism is adopted to gradually open an air inlet channel, so that the starting state of the air inlet channel is ensured. In a HyCAUSE flight test jointly performed in Australia and the United states in 2007, the attack angle and the sideslip angle of a test aircraft have large variation ranges, an air inlet channel undergoes multiple starting-non-starting-self-starting state variation, and combustion of a combustion chamber is insufficient. In the 2011 United states X-51A flight test, the problem of air inlet non-starting also occurs. Therefore, the research on the active control technology of the air inlet flow has important significance for optimizing the design of the air inlet, improving the performance of the air inlet and widening the stable working range of the air inlet.
Disclosure of Invention
The invention aims to solve the problems and provides a supersonic three-dimensional air inlet channel pneumatic control method based on an air flow blowing and sucking adjusting means.
In order to achieve the aim, the invention provides a supersonic three-dimensional air inlet channel pneumatic control method, which comprises the following steps:
a. constructing a pneumatic simulation model;
b. simulating and calculating the pneumatic characteristic;
c. designing an air inlet structure according to the simulation calculation result in the step b;
d. calibrating and debugging a controller for controlling the pneumatic state of the air inlet structure;
e. and monitoring the pressure in the air inlet structure and controlling the blowing/sucking state in the air inlet mechanism in real time.
According to one aspect of the invention, in the step a, the total area of the shape of the three-dimensional air inlet is divided into a plurality of sub-areas, then the hexahedral mesh is respectively established for each sub-area, the transmission of the solution of each sub-area on the inner boundary is realized by interpolation, and then a proper numerical value discrete method and a turbulence model are selected, the space discrete adopts the Roe format, the time discrete adopts the implicit L U-SGS format, and the turbulence model adopts the Menter SST two turbulence equation model.
According to an aspect of the invention, in the step c, designing the air inlet structure comprises designing a sensitive area of an inner wall surface of the air inlet and designing an opening position, a hole diameter size and a pressure measuring point arrangement scheme.
According to an aspect of the present invention, in the step c, the design method for designing the air inlet structure includes:
1) arranging an opening, a valve and a pressure measuring point for a separation area and a wall surface high-pressure area of the air inlet structure;
2) determining the pore size and the arrangement scheme of pressure measuring points according to the distribution rules of the separation area and the high-pressure area under different working conditions;
for areas with more distributed separation areas and high-pressure areas, the hole opening aperture needs to be enlarged, and pressure measuring points need to be arranged in an encrypted manner;
3) at least two pressure measuring points are arranged at the front and rear positions of each opening.
According to one aspect of the invention, in the step d, a plurality of working conditions which are the same as the numerical simulation in the step b are selected, the controller is used for performing blowing/sucking operation, pressure distribution and change rules measured by the pressure measuring points are recorded, then the pressure distribution and change rules are compared with the numerical simulation result, calibration, correction and correction of the numerical simulation result are realized, the controller is used for performing blowing/sucking operation, the mass flow of the position of the opening is measured, and the mass flow of the air flow is compared with the mass flow of the air flow expected by the controller control, so that calibration and debugging of the controller are completed.
According to one aspect of the invention, in the step e, monitoring the pressure in the air inlet passage structure is realized according to a pressure threshold value set on the basis of CFD numerical simulation.
According to an aspect of the present invention, in the e step, controlling the blowing/suctioning state in the inlet mechanism in real time includes:
in a low-pressure area, the controller performs blowing operation to inject high-pressure high-energy gas into the gas inlet channel mechanism;
in the high-pressure area, the controller performs air suction operation to lead high-pressure air out of the air inlet channel mechanism.
According to one scheme of the invention, an active control method for air inlet channel flow based on an air flow blowing and sucking adjusting means is designed. According to the flowing characteristic of the three-dimensional supersonic air inlet, the inner wall surface of the air inlet is reasonably provided with an opening, the opening is communicated with the outside of the aircraft through a pipeline, and a valve is arranged in the opening and used for controlling the opening and the closing of the pipeline. Meanwhile, pressure and temperature sensors are arranged near the opening, the flow state in the air inlet channel is monitored in real time, the sensors are connected with the controller, and control instructions are sent to the pipeline valve through the controller, so that the active control effect of the air inlet channel is achieved. When a large separation area appears at the inlet of the air inlet channel, the pressure of the airflow in the separation area is low, the controller sends an instruction to open the valve at the moment, the inner wall surface of the air inlet channel is opened to be in a blowing state because the external pressure is greater than the pressure in the separation area, and the introduced high-pressure high-energy gas can effectively enhance the capacity of the airflow in the air inlet channel for resisting separation, so that the flow separation is weakened or eliminated; when the high-pressure area in the air inlet channel obstructs inflow, the controller sends an instruction to open the valve, the inner wall surface of the air inlet channel is open and is in an air suction state, high-pressure airflow in the air inlet channel is discharged through the diversion of the open hole, and the separation and the flow of the air inlet channel caused by high back pressure are weakened or avoided.
According to the pneumatic control method for the supersonic three-dimensional air inlet, the structural design of the air inlet can be optimized, the structural performance of the air inlet is improved, and the stable working range of the air inlet structure is widened.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 schematically illustrates a flow chart of a supersonic three-dimensional inlet aerodynamic control method according to the present invention;
fig. 2 is a schematic diagram showing the structural arrangement of an air intake duct according to an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a flow chart of a supersonic three-dimensional air inlet channel pneumatic control method according to the invention. As shown in fig. 1, the supersonic three-dimensional air inlet channel pneumatic control method according to the present invention includes the following steps:
a. constructing a pneumatic simulation model;
b. simulating and calculating the pneumatic characteristic;
c. designing an air inlet structure according to the simulation calculation result in the step b;
d. calibrating and debugging a controller for controlling the pneumatic state of the air inlet structure;
e. and monitoring the pressure in the air inlet structure and controlling the blowing/sucking state in the air inlet mechanism in real time.
According to an embodiment of the invention, in the steps a and b, aiming at the appearance of the specific three-dimensional air inlet, according to the appearance and the flight trajectory of the hypersonic aircraft, a hexahedral structured partitioned docking grid is generated, and a pneumatic simulation model is constructed to obtain the starting characteristic of the air inlet, the pressure distribution of the inner wall surface of the air inlet and the shock wave flow structure in the air inlet, so as to provide reference for the design of the arrangement scheme of the holes and the measuring points.
According to an embodiment of the present invention, in the step b, the total area of the three-dimensional air inlet channel is divided into a plurality of sub-areas, then a hexahedral mesh is respectively established for each sub-area, the transfer of the solutions of the sub-areas on the inner boundary is realized by interpolation, and then a suitable numerical value discrete method and a suitable turbulence model are selected, the spatial discrete method adopts the Roe format, the time discrete method adopts the implicit L U-SGS format, and the turbulence model adopts the Menter SST two-equation turbulence model.
According to an embodiment of the present invention, in the step c, designing the air intake structure according to the simulation calculation result in the step b includes designing a sensitive area of the inner wall surface of the air intake and emphasizing the open hole position, the aperture size and the pressure measuring point arrangement scheme.
FIG. 2 schematically illustrates a structural layout of an air scoop designed according to one embodiment of this invention. In the present embodiment, the method for designing an intake duct structure includes:
1) arranging an opening, a valve and a pressure measuring point for a separation area and a wall surface high-pressure area of the air inlet structure;
2) determining the pore size and the arrangement scheme of pressure measuring points according to the distribution rules of the separation area and the high-pressure area under different working conditions;
for areas with more distributed separation areas and high-pressure areas, the hole opening aperture needs to be enlarged, and pressure measuring points need to be arranged in an encrypted manner;
3) at least two pressure measuring points are arranged at the front and rear positions of each opening.
As shown in fig. 2, the air intake duct structure designed according to the above design method includes an air intake duct main body 1 and an air intake lip cover 2. An intake duct inner passage 3 is formed between the intake duct main body 1 and the intake duct lip cover 2. The starting end of the channel 3 in the air inlet channel is an inlet 4 of the air inlet channel. In the present embodiment, the inlet 4 of the inlet tends to form a large separation area 5 under different working conditions, the separation area 5 is a low-pressure area, and a high-pressure area 6 is formed in the channel 3 in the inlet. In the present embodiment, as shown in fig. 2, openings 7 are arranged on the port body 1 corresponding to the separation region 5 and the high-pressure region 6, respectively, and a valve, and a pressure measuring point are provided at the openings. The controller 8 is connected to the opening 7 with a valve for blowing/sucking operation.
According to an embodiment of the invention, in the step d, a plurality of working conditions which are the same as the numerical simulation in the step b are selected, the controller is used for performing blowing/sucking operation, pressure distribution and change rules measured by the pressure measuring points are recorded, then the pressure distribution and change rules are compared with the numerical simulation result, calibration, correction and correction of the numerical simulation result are realized, the controller is used for performing blowing/sucking operation, the mass flow of the position of the opening is measured, and the mass flow of the air flow is compared with the mass flow of the air flow expected by the controller control, so that calibration and debugging of the controller are completed.
According to an embodiment of the present invention, in the step e, on the basis of CFD (Computational fluid dynamics) numerical simulation, corresponding pressure monitoring thresholds are set, and according to a pressure distribution rule measured at each measuring point, each valve is independently controlled, and opening and closing degrees of the valve are controlled. Meanwhile, in low-pressure areas such as the separation area and the like, the controller performs blowing operation to inject high-pressure high-energy gas into the low-pressure areas so as to enhance the gas separation resistance of the areas, reduce the separation area and improve the problem of non-starting of the gas inlet channel. In a high-pressure area, the controller performs air suction operation to lead out high-pressure gas, so that the back pressure in the air inlet channel is effectively reduced, and the problem that the air inlet channel does not start can be solved. In addition, the flow of the blowing and sucking air is controlled in real time according to the real-time change condition of pressure monitoring.
According to the pneumatic control method of the supersonic three-dimensional air inlet channel, provided by the invention, aiming at the supersonic air inlet channel, an air inlet channel flow active control method based on an air flow adjusting blowing and sucking means is designed. According to the flowing characteristic of the three-dimensional supersonic air inlet, the inner wall surface of the air inlet is reasonably provided with an opening, the opening is communicated with the outside of the aircraft through a pipeline, and a valve is arranged in the opening and used for controlling the opening and the closing of the pipeline. Meanwhile, pressure and temperature sensors are arranged near the opening, the flow state in the air inlet channel is monitored in real time, the sensors are connected with the controller, and control instructions are sent to the pipeline valve through the controller, so that the active control effect of the air inlet channel is achieved. When a large separation area appears at the inlet of the air inlet channel, the pressure of the airflow in the separation area is low, the controller sends an instruction to open the valve at the moment, the inner wall surface of the air inlet channel is opened to be in a blowing state because the external pressure is greater than the pressure in the separation area, and the introduced high-pressure high-energy gas can effectively enhance the capacity of the airflow in the air inlet channel for resisting separation, so that the flow separation is weakened or eliminated; when the high-pressure area in the air inlet channel obstructs inflow, the controller sends an instruction to open the valve, the inner wall surface of the air inlet channel is open and is in an air suction state, high-pressure airflow in the air inlet channel is discharged through the diversion of the open hole, and the separation and the flow of the air inlet channel caused by high back pressure are weakened or avoided.
According to the pneumatic control method for the supersonic three-dimensional air inlet, the structural design of the air inlet can be optimized, the structural performance of the air inlet is improved, and the stable working range of the air inlet structure is widened.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and it is apparent to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A supersonic three-dimensional air inlet channel pneumatic control method comprises the following steps:
a. constructing a pneumatic simulation model;
b. simulating and calculating the pneumatic characteristic;
c. designing an air inlet structure according to the simulation calculation result in the step b;
d. calibrating and debugging a controller for controlling the pneumatic state of the air inlet structure;
e. monitoring the pressure in the air inlet structure and controlling the blowing/sucking state in the air inlet mechanism in real time;
in the step c, the design method for designing the air inlet structure comprises the following steps:
1) arranging open holes in a separation area and a wall surface high-pressure area of the air inlet structure, and arranging a valve and a pressure measuring point at the open holes;
2) determining the pore size and the arrangement scheme of pressure measuring points according to the distribution rules of the separation area and the high-pressure area under different working conditions;
for areas with more distributed separation areas and high-pressure areas, the hole opening aperture needs to be enlarged, and pressure measuring points need to be arranged in an encrypted manner;
3) at least one pressure measuring point is arranged at the front position and the rear position of each opening;
wherein, the inner wall surface of the air inlet is provided with an opening which is connected to the outside of the aircraft through a pipeline, and the opening and the closing of the pipeline are controlled by a valve in the opening.
2. The pneumatic control method for the supersonic three-dimensional air inlet according to claim 1, wherein in the step a, a hexahedral structured partitioning docking grid is generated according to the shape and the flight trajectory of the hypersonic aircraft for the specific three-dimensional air inlet shape.
3. The pneumatic control method for the supersonic three-dimensional air inlet channel according to claim 2, wherein in the step a, the total area of the shape of the three-dimensional air inlet channel is divided into a plurality of sub-areas, each sub-area is respectively provided with a hexahedral mesh, the transmission of the solution of each sub-area on the inner boundary is realized by interpolation, and then a proper numerical value discrete method and a turbulence model are selected, the spatial discrete method adopts Roe format, the time discrete method adopts implicit L U-SGS format, and the turbulence model adopts Menter SST two-equation turbulence model.
4. The pneumatic control method for the supersonic three-dimensional air inlet channel according to claim 1, wherein in the step c, designing an air inlet channel structure comprises designing a sensitive area of an inner wall surface of the air inlet channel and designing an arrangement scheme of an open hole position, a hole diameter size and a pressure measuring point.
5. The pneumatic control method for the supersonic three-dimensional air inlet passage according to claim 1, wherein in the step d, a plurality of working conditions which are the same as the numerical simulation in the step b are selected, the controller is used for blowing/sucking operation, pressure distribution and change rules measured by the pressure measuring points are recorded, then the pressure distribution and change rules are compared with the numerical simulation result, calibration, correction and correction of the numerical simulation result are realized, the controller is used for blowing/sucking operation, the mass flow of the position of the opening is measured, and the mass flow of the air flow is compared with the mass flow of the air flow expected by the controller control, so that the calibration and debugging of the controller are completed.
6. The pneumatic control method for the supersonic three-dimensional air inlet according to claim 1, wherein in the step e, monitoring of the pressure in the air inlet structure is achieved according to a pressure threshold set on the basis of CFD numerical simulation.
7. The pneumatic control method for the supersonic three-dimensional air inlet according to claim 1, wherein in the step e, the real-time control of the blowing/sucking state in the air inlet mechanism comprises:
in a low-pressure area, the controller performs blowing operation to inject high-pressure high-energy gas into the gas inlet channel mechanism;
in the high-pressure area, the controller performs air suction operation to lead high-pressure air out of the air inlet channel mechanism.
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| CN100430584C (en) * | 2007-03-22 | 2008-11-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| CN102953826B (en) * | 2012-11-22 | 2013-11-27 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for forebody-inner passage circulation |
| CN103953448B (en) * | 2014-04-15 | 2016-05-18 | 南京航空航天大学 | A kind of hypersonic inlet |
| CN104890887B (en) * | 2015-04-20 | 2016-01-13 | 南京航空航天大学 | Adopt supersonic speed, the hypersonic inlet of the inoperative control method of pneumatic type |
| CN107089341B (en) * | 2017-06-05 | 2018-07-27 | 南京航空航天大学 | With aircraft integrated hypersonic inlet external compression face design method |
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