CN115027663B - Wing fusion control method realized through jet flow - Google Patents
Wing fusion control method realized through jet flow Download PDFInfo
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- CN115027663B CN115027663B CN202210953725.7A CN202210953725A CN115027663B CN 115027663 B CN115027663 B CN 115027663B CN 202210953725 A CN202210953725 A CN 202210953725A CN 115027663 B CN115027663 B CN 115027663B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a wing fusion control method realized by jet flow, which judges whether wings and a morphing empennage are in a fusion state or not by monitoring an actual value of a parameter of a flight state of a target aircraft and based on the actual value; if the judgment result is negative, inputting the actual value into a preset jet flow calculation model to obtain the target flow of the jet flow calculation model; the jet drive section is controlled to adjust the flow rate of the jet ejected from the jet outlet to a target flow rate. The method can enlarge the design space of the fusion type variant empennage, avoid applying excessive constraint on the design of the aerodynamic shape of the variant empennage for fusion, and further improve the heading control capability of the variant empennage after being opened. By means of the jet flow control, the wing is designed in a shape-preserving manner, the problem of appearance discontinuity caused by the deformation process of the morphing aircraft is effectively solved, and the loss of the original aerodynamic performance is avoided.
Description
Technical Field
The application belongs to the field of aircraft research, and particularly relates to a wing fusion control method realized through jet flow.
Background
At present, the common aerodynamic layouts (such as conventional layouts, canard layouts and three-wing-surface layouts) of the airplane generally comprise wings, a cylindrical fuselage, vertical tails, horizontal tails, canard parts and the like, and after decades of researches, the performance potentials of the layouts are almost thoroughly excavated, and the aerodynamic performance of the layouts is difficult to greatly improve. In addition, from military aircraft demands, the layout has the advantages of more edges, larger radar scattering surface, no infrared shielding, easy radar detection, poor stealth performance and weak survival ability on a battlefield.
Therefore, how to further improve the lift force and the aerodynamic efficiency of the airplane during flying becomes a problem to be solved urgently.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides a wing fusion control method realized by jet flow, which can enlarge the design space of a fusion type variable tail wing, avoid applying too much constraint on the design of the aerodynamic shape of the variable tail wing for fusion, and further improve the heading control capability of the variable tail wing after being opened. By means of the jet flow control, the wing is designed in a shape-preserving manner, the problem of appearance discontinuity caused by the deformation process of the morphing aircraft is effectively solved, and the loss of the original aerodynamic performance is avoided. The method of the invention replaces the lost fixed wall surface after the original wing is deformed with the flowing boundary formed by the jet flow, so that the frictional resistance is greatly reduced, the airflow on the upper surface of the wing is driven by the jet flow to leave the upper surface at a higher speed, the lift force is improved to a certain extent, and the long-range ability of the airplane is improved. In addition, the method can adjust the jet flow rate aiming at different flight states to form different flow boundaries, namely wings with different shapes can be integrally formed, so that higher aerodynamic characteristics can be obtained in a wide speed range of low/sub/span/supersonic speed, which is difficult to realize by the original fixed-shape wing.
The technical effect to be achieved by the invention is realized by the following scheme:
in a first aspect, the invention provides a wing fusion control method realized by jet flow, which is based on a target aircraft, wherein the target aircraft comprises a wing and a morphing empennage, the relative positions of the wing and the morphing empennage are adjustable, and the wing fusion control method is in a fusion state when the edge of the morphing empennage smoothly transitions to the edge of the wing; the target aircraft further includes a fusion adjustment component configured to: when the wing and the morphing empennage are in the non-fused state, jetting the jet along the designated edge so that the jet at least partially replaces the position of the wing and/or the morphing empennage when the wing and the morphing empennage are in the fused state; wherein the designated edge is an edge of the wing adjacent to the morphing tail, or the designated edge is an edge of the morphing tail adjacent to the wing; the fusion adjusting assembly comprises an air inlet, a jet flow outlet and a jet flow driving part, wherein the jet flow driving part is arranged in an air passage comprising the air inlet and the jet flow outlet and is used for controlling the flow of jet flow jetted from the jet flow outlet; the method comprises the following steps:
monitoring actual values of parameters of a flight state of the target aircraft;
judging whether the wings and the morphing empennage are in a fusion state or not based on the actual value;
if the judgment result is negative, inputting the actual value into a preset jet flow calculation model to obtain the target flow of the jet flow calculation model;
controlling the jet drive section to adjust the flow rate of the jet ejected from the jet outlet to the target flow rate.
In an optional embodiment of the present invention, before inputting the actual value into a preset jet flow calculation model to obtain a target flow of the jet flow calculation model, the method further includes:
acquiring sample data;
training a preset nonlinear interpolation model based on the sample data to obtain the jet flow calculation model; the jet flow calculation model is used for predicting the corresponding relation between the parameters of the flight state and the flow.
In an alternative embodiment of the invention, the parameter of the flight state comprises at least one of: mach number, angle of attack, sideslip angle, altitude of flight.
In an optional embodiment of the present invention, after controlling the jet driving part to adjust the flow rate of the jet ejected from the jet outlet to the target flow rate, the method further includes:
continuing to monitor actual values of the parameters of the flight state of the target aircraft;
judging whether the wings and the morphing empennage are in a fusion state or not based on the actual value;
and if so, controlling the jet flow driving part to adjust the flow rate of the jet flow jetted from the jet flow outlet to zero.
In an alternative embodiment of the present invention, the fusion adjusting assembly has a plurality of air inlets and/or a plurality of jet outlets.
In an optional embodiment of the present invention, in a case that the jet flow calculation model includes a plurality of jet outlets, the jet flow calculation model is configured to predict a correspondence between a parameter of a flight state and respective target flows of the different jet outlets.
In an alternative embodiment of the invention, the edge of the wing which interfaces with the morphing tail presents an interface, and the jet outlets are provided on a first edge and/or a second edge of the interface which are opposite in the direction of adjustment of the position of the wing relative to the morphing tail.
In a second aspect, the invention provides a control terminal for controlling wing fusion through jet flow, which is used for implementing the method in the first aspect.
In a third aspect, the present invention provides an electronic device comprising:
a processor; and
a memory arranged to store computer executable instructions that, when executed, cause the processor to perform the method of the first aspect.
In a fourth aspect, the invention provides a computer readable storage medium storing one or more programs which, when executed by an electronic device comprising a plurality of application programs, cause the electronic device to perform the method of the first aspect.
Drawings
In order to more clearly illustrate the embodiments or prior art solutions of the present invention, the drawings used in the embodiments or prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and for those skilled in the art, other drawings can be obtained according to the drawings without inventive labor.
FIG. 1 is a schematic illustration of a target aircraft wing and a morphing tail in a fused state in one embodiment of the present application;
FIG. 2 is a schematic view of a morphing empennage of a target aircraft in an unfused state, deflected by 20 relative to the wing in an embodiment of the present application;
FIG. 3 is a schematic view of a morphing empennage of a target aircraft in an unfused state, deflected by 40 relative to the wing in an embodiment of the application;
FIG. 4 is a schematic layout of a fusion control module of a target aircraft in an embodiment of the present application;
FIG. 5 is a schematic diagram illustrating a fusion effect achieved by a method for controlling wing fusion through jet flow in an embodiment of the present application;
FIG. 6 is a flow chart of a method for controlling airfoil fusion by jet flow in an embodiment of the present application;
fig. 7 is a schematic structural diagram of a control terminal for controlling wing fusion through jet flow in an embodiment of the present application;
FIG. 8 is a schematic structural diagram of an electronic device according to an embodiment of the present application;
wherein the content of the first and second substances,
the part number 1 is: an interface of the morphing tail leading edge and the wing;
the part number 2 is: a trailing edge of the airfoil;
the part number 3 is: a compressor;
part No. 4 is: a flow valve.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following embodiments and accompanying drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.
The present invention will be described in further detail with reference to the following detailed description and accompanying drawings. Wherein like elements in different embodiments are numbered with like associated elements. In the following description, numerous specific details are set forth in order to provide a better understanding of the present application. However, those skilled in the art will readily recognize that some of the features may be omitted or replaced with other elements, materials, methods in different instances. In some instances, certain operations related to the present application have not been shown or described in detail in order to avoid obscuring the core of the present application from excessive description, and it is not necessary for those skilled in the art to describe these operations in detail, so that they may be fully understood from the description in the specification and the general knowledge in the art.
Furthermore, the features, operations, or characteristics described in the specification may be combined in any suitable manner to form various embodiments. Also, the various steps or actions in the description of the methods may be transposed or transposed in order, as will be apparent to a person skilled in the art. Thus, the various sequences in the specification and drawings are for the purpose of describing certain embodiments only and are not intended to imply a required sequence unless otherwise indicated where such sequence must be followed.
The ordinal numbers used herein for the components, such as "first," "second," etc., are used merely to distinguish between the objects described, and do not have any sequential or technical meaning. The term "connected" and "coupled" when used in this application, unless otherwise indicated, includes both direct and indirect connections (couplings).
Aircraft (flight vehicle) is an instrument that flies in the atmosphere or in an extraterrestrial space (space). Aircraft fall into 3 categories: aircraft, spacecraft, rockets, and missiles. Flying in the atmosphere is referred to as an aircraft, such as a balloon, airship, airplane, etc. They fly by the static buoyancy of air or the aerodynamic force generated by the relative movement of air. In space flight, the space vehicle is called a spacecraft, such as an artificial earth satellite, a manned spacecraft, a space probe, a space shuttle and the like. They are propelled by a launch vehicle to obtain the necessary velocity to enter space and then rely on inertia to make orbital motion similar to celestial bodies.
At present, the common aerodynamic layouts (such as conventional layouts, canard layouts and three-wing-surface layouts) of the airplane generally comprise wings, a cylindrical fuselage, vertical tails, horizontal tails, canard parts and the like, and after decades of researches, the performance potentials of the layouts are almost thoroughly excavated, and the aerodynamic performance of the layouts is difficult to greatly improve. In addition, from military aircraft demands, the layout has the advantages of more edges, larger radar scattering surface, no infrared shielding, easy radar detection, poor stealth performance and weak survival ability on a battlefield.
To further exploit the potential for aerodynamic and stealth performance of aircraft, fusion technology-based aircraft (e.g., flying wing aircraft) have come into force. The layout of aircraft based on fusion technology and flat fusion tailless layout similar to flying wing layout are receiving wide attention and high favor of the aviation industry. Because the layout does not have components which do not generate lift force but generate resistance, such as a cylindrical body, a horizontal tail and a vertical tail, the cruise lift-drag ratio can be effectively increased, the cruise aerodynamic efficiency is improved, the radar scattering cross section is greatly reduced, and the stealth characteristic of the layout is greatly improved.
At present, the variant empennage integrated with the height of the wing gradually becomes a research hotspot, and the heading control capability of the tailless/flying wing layout aircraft during low/sub/cross/supersonic cruise or maneuvering flight can be effectively improved. However, the 'fusion' two-character greatly limits the design space of the aerodynamic shape of the wing and the vertical tail, and the aerodynamic performance of the aircraft needs to be fully considered in the deformation process of the aircraft, so that the rough and discontinuous deformation is avoided as far as possible.
Various non-limiting embodiments of the present application are described in detail below with reference to the attached drawing figures.
The method is based on a target aircraft, and the target aircraft is an aircraft based on a wing body fusion technology and can be an aircraft, a flying wing and other aviation equipment. The target aircraft in the present invention includes wings and morphing empennages. For example, the relative position relationship between the wing and the morphing tail may be as shown in fig. 1 to 5.
The relative positions of the wing and the variant tail are adjustable, and the process that the deflection angle of the variant tail relative to the wing is gradually increased is shown in figures 1 to 3. When the edge of the morphing empennage smoothly transitions to the edge of the wing, the morphing empennage and the wing are in a fused state, as shown in fig. 1. When the edges of the morphing tail no longer transition smoothly (e.g., an angle such as a "V" shape occurs therebetween) to the edges of the wing, or a significant gap occurs between the edges of the morphing tail and the wings, the morphing tail and wings are no longer in a fused state. The relative positions of the morphing empennage and the wings are adjusted according to the flight state of the target aircraft during the flight process of the target aircraft.
It should be noted that in an alternative embodiment of the invention, the target aircraft is an in-line, in-service, real aircraft; in another alternative embodiment of the present invention, the target aircraft is a virtual aircraft model, and data required for research, display and other services can be obtained through the aircraft model.
In addition, the target aircraft in the present invention further includes a fusion adjustment component configured to: when the wing and the morphing tail are in the non-fused state, the jet is ejected along the designated edge, so that the jet at least partially replaces the position of the wing and/or the morphing tail when the wing and the morphing tail are in the fused state, and the fusion between the wing and the morphing tail can be realized through the jet, as shown in fig. 5. Wherein the designated edge is the edge of the wing adjacent to the morphing tail, in this embodiment the jet is ejected along the edge of the wing; or the designated edge is the edge of the morphing tail adjacent the wing, in which case the jet is ejected along the edge of the morphing tail.
Fig. 5 shows a comparison of profiles of typical sections of a front wing and a rear wing of a variant empennage when opened, wherein the front wing is smooth, the local aerodynamic chord length of the opened wing is shortened, and the drag is inevitably increased when there is discontinuous transition on the upper surface near the trailing edge. The jet flow is applied to the interface (shown by the number 1 in figure 3) of the front morphing empennage front edge and the wing and the trailing edge (shown by the number 2 in figure 3) of the morphing rear wing along the tangential direction of the corresponding flow direction, and a flow boundary (a dotted line part of the wing type in figure 5) similar to a fixed wall surface is formed in the area, so that the shape-keeping function is realized on the original wing, the better aerodynamic characteristic is maintained, and meanwhile, different shapes similar to the fixed wall surface can be formed according to the actual flight state, and the better aerodynamic benefit is obtained in the flight stage compared with the original wing.
Optionally, in order to avoid the jet flow from interfering with the airflow around the target aircraft and further avoid interference with the flight control of the target aircraft, when the setting position of the fusion adjusting assembly is determined, or when the jet flow is determined to be ejected by one of the wing and the morphing empennage (in this embodiment, the jet flow outlets of the fusion adjusting assembly are both arranged on the wing and the morphing empennage, and the jet flow is ejected by one of the wing and the morphing empennage), an included angle between the flow direction of the jet flow ejected by the fusion adjusting assembly and the flow direction of the airflow around the jet flow outlet is an acute angle.
For convenience of description, without specific reference, the following description will exemplarily refer to jet flow ejected along the edge of an airfoil, as shown in fig. 4.
Fuse the adjustment subassembly and include air inlet, efflux export and efflux drive division, the efflux drive division set up in containing the air inlet with in the air flue of efflux export, the efflux drive division is used for the control to follow the efflux of efflux that the efflux export was jetted out flows. In the related art, any component capable of controlling the flow rate of the air flow may be used as the jet drive section in the present invention. In an alternative embodiment of the invention, the fluidic drive includes a compressor and flow valve located along the gas path as shown in FIG. 4. Wherein the component numbered 4 in fig. 4 is a flow valve and the component numbered 3 in fig. 4 is a compressor. The compressor powers the flow of the gas stream and the flow valve is used to control the flow of the jet emitted from the jet outlet. In fig. 4, the black solid squares are the jet outlets on the interface between the front edge of the morphing front morphing tail wing and the wing, and the black solid triangles are the jet outlets arranged on the rear edge of the morphing rear wing.
In the case of a jet emitted along the edge of an airfoil, the jet outlet is provided at the edge of the airfoil. In an alternative embodiment, where the jet is ejected along an edge of an airfoil, both the air scoop and the jet drive are provided on the airfoil. The air inlet is arranged on the other edge of the wing opposite to the appointed edge. Optionally, at least part of the jet drive is embedded in the wing and/or the morphing tail.
Optionally, a baffle capable of shielding the air inlet is arranged at the air inlet. When the target flow is not 0, controlling at least partial opening of the baffle plate to remove the shielding of the air inlet so as to expose the air inlet to the environment; when the target flow is 0, the baffle plate can be controlled to be closed so as to shield the air inlet, and further the air inlet is not exposed to the environment.
The invention provides a wing shape-preserving design method suitable for a wing and morphing tail wing height fusion type aircraft. The method is characterized in that an air-entraining device (such as an air inlet) is arranged at the front edge of the wing, a jet device (such as a jet outlet) with adjustable speed is arranged at the interface between the front edge of the morphing front morphing tail wing and the rear edge of the morphing rear wing, and after the morphing tail wing is separated from the wing through rotation, the purpose of shape maintenance of the original wing is achieved through jet control at a certain speed. The method breaks through the limitation of 'fusion' of two characters on the design of the variant empennage and the wing, can effectively consider the characteristics of both aerodynamics and stealth, and has higher aerodynamic performance in low/sub/cross/supersonic cruise or high maneuvering flight stages.
The method for controlling wing fusion through jet flow in the invention is shown in fig. 6, and comprises the following steps:
s600: monitoring actual values of parameters of a flight state of the target aircraft.
The wing fusion control method realized by jet flow is executed by the control terminal. In an optional embodiment of the present invention, the control terminal is disposed non-integrally with the target aircraft, the control terminal is in communication connection with the target aircraft, and the control terminal receives the actual value of the flight status sent by the target aircraft to monitor the flight status of the target aircraft; in another alternative embodiment of the invention, the control terminal is provided integrally with the target aircraft.
The flight state of the target aircraft has certain relevance with the relative position relation between the wings and the morphing empennage, and the flight state of the target aircraft is determined, namely the relative position relation between the wings and the morphing empennage can be determined to a certain degree. Illustratively, the wing and the morphing tail are in an altitude fusion state when the target aircraft is in long-range flight or in altitude stealth near-destination flight; when the target aircraft is in low-speed take-off and landing flight, maneuvering flight or supersonic-crossing flight, the variant empennage rotates around the chord line of the root part of the variant empennage by different angles to meet different requirements of course control, and the wing and the variant empennage are probably not in a fusion state due to the change of relative positions.
In an optional embodiment of the invention, the flight state of the target aircraft may be characterized by at least one of the following parameters: mach number, angle of attack, sideslip angle, altitude of flight. The values of these monitored parameters are the actual values.
S602: and judging whether the wing and the morphing empennage are in a fusion state or not based on the actual value.
In an optional embodiment of the present invention, a fusion state determination database may be established in advance, and the fusion state determination database records a correspondence between a value of a parameter of a flight state and a fusion state, so that it is possible to determine whether the wing and the variant empennage are in the fusion state by searching data in the fusion state determination database. The embodiment does not need to occupy the calculation resources of the jet flow calculation model in the following when the judgment of the step is carried out.
In another alternative embodiment of the present invention, a jet flow calculation model may be used to determine whether the wing and the morphing tail are in a fused state. If the target flow output by the jet flow calculation model is 0, whether the wings and the morphing empennage are in a fusion state or not is judged; and if the target flow output by the jet flow calculation model is not 0, judging whether the wings and the variant empennage are in a non-fusion state or not. The embodiment does not need to establish a fusion state judgment database.
S604: and if the judgment result is negative, inputting the actual value into a preset jet flow calculation model to obtain the target flow of the jet flow calculation model.
In an optional embodiment of the present invention, the jet flow calculation model may be a database in which a correspondence relationship between the value of the flight state parameter and the target flow is recorded, and the target flow may be obtained by searching the database.
In another alternative embodiment of the present invention, the jet flow calculation model may be a non-linear interpolation model, such as Kriging, neural network, etc. Hereinafter, how to obtain the jet flow calculation model will be explained.
S606: controlling the jet drive section to adjust the flow rate of the jet ejected from the jet outlet to the target flow rate.
Through the steps, a flow boundary similar to a fixed wall surface can be formed in the boundary area of the wing and the morphing empennage, the original wing is protected, the better aerodynamic characteristic is maintained, and meanwhile, different appearances similar to the fixed wall surface can be formed according to the actual flight state, so that the better aerodynamic benefit is obtained in the flight stage compared with the original wing.
In the related art, the advantages of high aerodynamic efficiency, high stealth performance and the like of a flat fusion tailless layout of a flying wing layout and similar flying wing layouts are retained, the flying capability of high maneuvering or supersonic cruise is realized, and the control coordination problem during sub/cross/supersonic flying/maneuvering is faced on the aerodynamic layout design. Because an aircraft has no tail, so that the stability and the maneuverability of the aircraft are reduced drastically, the main challenges in design are: there is no yaw control device with sufficient control efficiency to replace the conventional rudder or full-motion vertical fin, thereby facing the problem of how to generate yaw control forces and to address multi-axis instability.
By the method, the design space of the fused variant empennage can be enlarged, excessive constraint on the design of the aerodynamic shape of the variant empennage for fusion is avoided, and the heading control capability of the variant empennage after being opened can be further improved. By means of the jet flow control, the wing is designed in a shape-preserving manner, the problem of appearance discontinuity caused by the deformation process of the morphing aircraft is effectively solved, and the loss of the original aerodynamic performance is avoided. The method of the invention replaces the lost fixed wall surface after the original wing is deformed with the flowing boundary formed by the jet flow, so that the frictional resistance is greatly reduced, the airflow on the upper surface of the wing is driven by the jet flow to leave the upper surface at a higher speed, the lift force is improved to a certain extent, and the long-range ability of the airplane is improved. In addition, the method can adjust the jet flow rate aiming at different flight states to form different flow boundaries, namely wings with different shapes can be integrally formed, so that higher aerodynamic characteristics can be obtained in a wide speed range of low/sub/span/supersonic speed, which is difficult to realize by the original fixed-shape wing.
The control mode of the jet flow can be designed according to the actual arrangement condition of the fusion adjusting component. Illustratively, in the embodiment where the aforementioned fusion adjustment assembly includes a compressor and a flow valve, the adjustment of the jet flow rate may be achieved by separate control of the compressor and the flow valve. For example, the greater the output power of the compressor, the greater the jet flow rate; the smaller the output power of the compressor, the smaller the jet flow. For another example, the larger the opening degree of the flow valve is, the larger the jet flow is; the smaller the flow valve opening, the smaller the jet flow.
As to how the control of the compressor and the flow valves is quantified, in an alternative embodiment of the invention, a database of the correspondence between the jet flow and the compressor power, the opening of the flow valves, can be established beforehand. Alternatively, an artificial intelligence model for predicting the correspondence between the jet flow rate and the compressor power, the opening degree of the flow valve, and the like are trained in advance.
Furthermore, in an alternative embodiment of the present invention, the fusion adjusting assembly has a plurality of air inlets, and/or the jet outlet has a plurality of jet outlets. Illustratively, as shown in fig. 4, the blending adjustment assembly includes a plurality of gas inlets and a plurality of fluid outlets that together form a gas path of the blending adjustment assembly, and the gas path is supplied with compressed gas by a single compressor (in alternative embodiments, the blending adjustment assembly may include more than one compressor). Optionally, the jet flow outlets and the flow valves are arranged in a one-to-one correspondence manner, so that different jet flow outlets can be controlled respectively, and the target flow rates corresponding to different jet flow outlets can be different.
Optionally, an interface exists at the edge where the wing interfaces with the morphing tail, as shown in fig. 3. The jet outlets are disposed on first and/or second opposing edges of the interface in a direction of adjustment of the position of the airfoil relative to the morphing tail. An example of a first edge and a second edge each provided with a jet outlet is shown in fig. 4.
And under the condition that the jet flow outlets are multiple, the jet flow calculation model is used for predicting the corresponding relation between the parameters of the flight state and the respective target flows of different jet flow outlets.
In a further alternative embodiment of the invention, the control terminal continues to monitor the actual values of the parameters of the flight state of the target aircraft. And judging whether the wings and the variant empennage are in a fusion state or not based on the actual value. And if so, controlling the jet flow driving part to adjust the flow of the jet flow ejected from the jet flow outlet to zero.
Specifically, the output power of the compressor may be adjusted to 0; and/or adjusting the opening degree of the flow valve to the minimum opening degree; and/or the air inlet and/or the jet flow outlet are/is provided with a baffle for controlling the opening and closing of the mouth part of the air inlet and/or the jet flow outlet, so that the position of the baffle can be controlled to close the corresponding air inlet and/or the corresponding jet flow outlet.
How to obtain the jet flow calculation model will now be described. In an optional embodiment of the present invention, the process of obtaining the jet flow calculation model may be to first obtain sample data. Then, based on the sample data, training a preset nonlinear interpolation model to obtain the jet flow calculation model.
The jet flow calculation model is used for predicting the corresponding relation between the parameters of the flight state and the flow. Aiming at a typical flight state, a numerical simulation and a test are carried out by using a Computational Fluid Dynamics (CFD) solver and a wind tunnel respectively, and jet flow required by each flight state is obtained so as to achieve the purpose of wing shape maintenance. Because errors such as numerical value formats exist in CFD calculation, uncertainty such as supporting interference exists in wind tunnel tests, certain deviation exists in flow data obtained by the CFD calculation and the wind tunnel tests, correlation correction needs to be carried out on the obtained calculation and test data, and jet flow data required under real flight conditions are obtained. And finally, establishing a corresponding relation between the flight state and the jet flow based on the existing nonlinear interpolation model (such as Kriging, a neural network and the like), and storing the corresponding relation in an aircraft control terminal.
Based on the same idea, the embodiment of the invention also provides a control terminal for controlling wing fusion through jet flow, which corresponds to the partial process shown in fig. 6.
As shown in fig. 7, a control terminal for controlling wing fusion by means of jet in the present invention may include one or more of the following modules:
a monitoring module 700 configured to: monitoring actual values of parameters of a flight state of the target aircraft.
A determination module 702 configured to: and judging whether the wings and the variant empennage are in a fusion state or not based on the actual value.
A target flow calculation module 704 configured to: and if the judgment result is negative, inputting the actual value into a preset jet flow calculation model to obtain the target flow of the jet flow calculation model.
A traffic adjustment module 706 configured to: controlling the jet drive section to adjust the flow rate of the jet ejected from the jet outlet to the target flow rate.
In an optional embodiment of the present invention, the control terminal further includes a model building module configured to: acquiring sample data; training a preset nonlinear interpolation model based on the sample data to obtain the jet flow calculation model; the jet flow calculation model is used for predicting the corresponding relation between the parameters of the flight state and the flow.
In an alternative embodiment of the invention, the parameter of the flight state comprises at least one of: mach number, angle of attack, sideslip angle, altitude of flight.
In an optional embodiment of the present invention, the control terminal is further configured to: continuing to monitor actual values of the parameters of the flight status of the target aircraft; judging whether the wings and the morphing empennage are in a fusion state or not based on the actual value; and if so, controlling the jet flow driving part to adjust the flow of the jet flow ejected from the jet flow outlet to zero.
In an alternative embodiment of the present invention, the fusion adjusting assembly has a plurality of air inlets and/or a plurality of jet outlets.
In an optional embodiment of the present invention, in a case that the jet flow calculation model includes a plurality of jet outlets, the jet flow calculation model is configured to predict a correspondence between a parameter of a flight state and respective target flows of the different jet outlets.
In an alternative embodiment of the invention, an interface is formed at the interface edge of the wing and the morphing tail, and the jet outlet is arranged at the first edge and/or the second edge which are opposite to each other along the direction of the relative position adjustment of the wing and the morphing tail.
Fig. 8 is a schematic structural diagram of an electronic device according to an embodiment of the present application. Referring to fig. 8, at a hardware level, the electronic device includes a processor, and optionally further includes an internal bus, a network interface, and a memory. The Memory may include a Memory, such as a Random-Access Memory (RAM), and may further include a non-volatile Memory, such as at least 1 disk Memory. Of course, the electronic device may also include hardware required for other services.
The processor, the network interface, and the memory may be connected to each other by an internal bus, which may be an ISA (Industry Standard Architecture) bus, a PCI (Peripheral Component Interconnect) bus, an EISA (Extended Industry Standard Architecture) bus, or the like. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of illustration, only one double-headed arrow is shown in FIG. 8, but that does not indicate only one bus or one type of bus.
And the memory is used for storing programs. In particular, the program may include program code comprising computer operating instructions. The memory may include both memory and non-volatile storage and provides instructions and data to the processor.
And the processor reads a corresponding computer program from the nonvolatile memory into the memory and then runs the computer program to form a wing fusion control method realized by jet flow on a logic level. And the processor is used for executing the program stored in the memory and is specifically used for executing any one of the wing fusion control methods realized through the jet flow.
The wing fusion control method implemented by the jet flow disclosed in the embodiment of fig. 6 of the present application can be applied to or implemented by a processor (i.e., a deletion control module in the present invention). The processor may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or instructions in the form of software. The Processor may be a general-purpose Processor, including a Central Processing Unit (CPU), a Network Processor (NP), and the like; but also Digital Signal Processors (DSPs), application Specific Integrated Circuits (ASICs), field Programmable Gate Arrays (FPGAs) or other Programmable logic devices, discrete Gate or transistor logic devices, discrete hardware components. The various methods, steps, and logic blocks disclosed in the embodiments of the present application may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present application may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module may be located in ram, flash memory, rom, prom, or eprom, registers, etc. storage media as is well known in the art. The storage medium is located in a memory, and a processor reads information in the memory and completes the steps of the method in combination with hardware of the processor.
The electronic device may further execute a method for controlling wing fusion through jet flow in fig. 6, and implement the functions of the embodiment shown in fig. 6, which are not described herein again.
The present application further provides a computer-readable storage medium storing one or more programs, where the one or more programs include instructions, which when executed by an electronic device including a plurality of application programs, enable the electronic device to perform a method performed by a jet-implemented wing fusion control method in the embodiment shown in fig. 6, and in particular to perform any one of the foregoing jet-implemented wing fusion control methods.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and so forth) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
In a typical configuration, a computing device includes one or more processors (CPUs), input/output interfaces, network interfaces, and memory.
The memory may include forms of volatile memory in a computer readable medium, random Access Memory (RAM) and/or non-volatile memory, such as Read Only Memory (ROM) or flash memory (flash RAM). Memory is an example of a computer-readable medium.
Computer-readable media, including both non-transitory and non-transitory, removable and non-removable media, may implement information storage by any method or technology. The information may be computer readable instructions, data structures, modules of a program, or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static Random Access Memory (SRAM), dynamic Random Access Memory (DRAM), other types of Random Access Memory (RAM), read Only Memory (ROM), electrically Erasable Programmable Read Only Memory (EEPROM), flash memory or other memory technology, compact disc read only memory (CD-ROM), digital Versatile Discs (DVD) or other optical storage, magnetic tape cassettes, magnetic tape magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information that can be accessed by a computing device. As defined herein, a computer readable medium does not include a transitory computer readable medium such as a modulated data signal and a carrier wave.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of other like elements in a process, method, article, or apparatus comprising the element.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The above description is only an example of the present application and is not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement or the like made within the spirit and principle of the present application shall be included in the scope of the claims of the present application.
Claims (10)
1. A method for controlling wing fusion by means of jet flow, characterized in that the method is based on a target aircraft, which is an aircraft based on a wing-body fusion technique; the target aircraft comprises a wing and a morphing empennage, the relative positions of the wing and the morphing empennage are adjustable, and the wing and the morphing empennage are in a fusion state when the edge of the morphing empennage smoothly transitions to the edge of the wing; the target aircraft further includes a fusion adjustment component configured to: when the wing and the morphing tail are in the non-fused state, jetting the jet along a designated edge so that the jet at least partially replaces the position of the wing and/or the morphing tail when the wing and the morphing tail are in the fused state; wherein the designated edge is an edge of the wing adjacent to the morphing tail, or the designated edge is an edge of the morphing tail adjacent to the wing; the fusion adjusting assembly comprises an air inlet, a jet flow outlet and a jet flow driving part, the jet flow driving part is arranged in an air passage comprising the air inlet and the jet flow outlet, the jet flow driving part is used for controlling the flow of jet flow jetted from the jet flow outlet, and at least part of the jet flow driving part is embedded in a wing and/or a variant empennage; the method comprises the following steps:
monitoring actual values of parameters of a flight state of the target aircraft; wherein the parameters include a sideslip angle and a flight height;
judging whether the wing and the morphing empennage are in a fusion state or not based on the actual value;
if the judgment result is negative, inputting the actual value into a preset jet flow calculation model to obtain the target flow of the jet flow calculation model; the jet flow calculation model is used for predicting the corresponding relation between the parameters of the flight state and the flow;
controlling the jet drive section to adjust the flow rate of the jet ejected from the jet outlet to the target flow rate.
2. The method for controlling wing fusion through jet flow of claim 1, wherein before inputting the actual value into a preset jet flow calculation model and obtaining the target flow of the jet flow calculation model, the method further comprises:
acquiring sample data;
and training a preset nonlinear interpolation model based on the sample data to obtain the jet flow calculation model.
3. The method of claim 1, wherein the parameter of the flight condition comprises at least one of: mach number, angle of attack.
4. The method of claim 1, wherein after controlling the jet drive to adjust the flow rate of the jet emitted from the jet outlet to the target flow rate, the method further comprises:
continuing to monitor actual values of the parameters of the flight state of the target aircraft;
judging whether the wing and the morphing empennage are in a fusion state or not based on the actual value;
and if so, controlling the jet flow driving part to adjust the flow of the jet flow ejected from the jet flow outlet to zero.
5. The method of claim 1, wherein the fusion adjustment assembly comprises a plurality of inlets and/or a plurality of outlets.
6. The method for controlling wing fusion through jet flow of claim 5, wherein the jet flow calculation model is used for predicting the corresponding relation between the parameters of the flight state and the respective target flow rates of different jet outlets when the jet outlets are multiple.
7. The method of claim 1, wherein an interface exists at an edge where the wing interfaces with the morphing tail, and the jet outlets are disposed at a first edge and/or a second edge of the interface opposite to each other in a direction of adjusting a position of the wing relative to the morphing tail.
8. A control terminal for wing fusion control through jet flow is characterized in that the control terminal is used for realizing the wing fusion control method through jet flow according to any one of claims 1 to 7.
9. An electronic device, comprising:
a processor; and
a memory arranged to store computer executable instructions that, when executed, cause the processor to perform a method of wing fusion control by jets as claimed in any one of claims 1 to 7.
10. A computer-readable storage medium characterized in that the computer-readable storage medium stores one or more programs which, when executed by an electronic device including a plurality of application programs, cause the electronic device to execute the wing fusion control method by jet according to any one of claims 1 to 7.
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