Aircraft reverse jet thermal protection method, system and equipment for determining jet position

Abstract

The invention provides an aircraft reverse jet thermal protection method, system and device for determining a jet position, and the method comprises the steps: obtaining the trajectory working condition of an aircraft and a preset jet parameter range; based on the first agent model, determining the jet flow position of the aircraft under the trajectory working condition; and based on the second agent model, the jet position of the aircraft and a preset jet parameter range, obtaining an actual jet parameter range of the aircraft under the ballistic working condition. According to the embodiment of the invention, through the first agent model and the second agent model, the jet flow position of the aircraft can be quickly determined, the local heat flux density is reduced, and the energy utilization efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft reverse jet thermal protection method, system and equipment for determining a jet position. Background Art

[0002] In recent years, the research on hypersonic aircraft has gradually become one of the hot areas of technological development. Among them, hypersonic aircraft face complex technical challenges in aerodynamic heating. Under hypersonic flight conditions, the shock wave effect of the airflow on the aircraft will cause a heat flux concentration area near the stagnation point, and at the same time, a heat flux concentration area will also appear at the shoulder and corner due to flow separation.

[0003] In the prior art, low-temperature gas / liquid is sprayed on local positions of the aircraft, such as shoulders and corners, through reverse jet technology to push shock waves away from the surface, change the local flow field structure of the aircraft, form a low-temperature reflow zone, and thus play a role in reducing the heat flux density on the aircraft surface. At present, there are still some problems that need to be solved in reverse jet technology. Summary of the invention

[0004] In view of this, the object of the present invention is to provide an aircraft reverse jet thermal protection method, system and equipment for determining the jet position, so as to quickly locate the position where the peak heat flux of the aircraft occurs, reduce the local heat flux density, and improve energy utilization efficiency.

[0005] In a first aspect, the present invention provides a method for aircraft reverse jet thermal protection for determining a jet position, comprising:

[0006] Obtaining the trajectory conditions of the aircraft and the preset range of jet parameters;

[0007] Based on the first proxy model, determining the jet position of the aircraft under the ballistic condition;

[0008] Based on the second proxy model, the jet position of the aircraft and the preset jet parameter range, the actual jet parameter range of the aircraft under the ballistic condition is obtained.

[0009] Optionally, the first proxy model is constructed according to the following steps:

[0010] Obtaining the structural shape parameters and operating condition parameters of the aircraft;

[0011] Sampling the structural shape parameters and working condition parameters to obtain several sample points;

[0012] Based on a number of sample points, a first proxy model is constructed.

[0013] Optionally, determining the jet position of the aircraft under the ballistic condition based on the first proxy model includes:

[0014] Inputting the ballistic working condition into the first proxy model, obtaining a first head heat flux density value and a first shoulder heat flux density value of the aircraft;

[0015] The heat flux density value of the first head portion is compared with the heat flux density value of the first shoulder portion to determine the jet position of the aircraft.

[0016] Optionally, comparing the first head heat flux density value with the first shoulder heat flux density value to determine the jet position of the aircraft, further comprising:

[0017] When the first head heat flux density value is greater than the first shoulder heat flux density value, the jet position of the aircraft is the head jet;

[0018] When the first head heat flux density value is less than the first shoulder heat flux density value, the jet position of the aircraft is the shoulder jet.

[0019] Optionally, construct a second proxy model according to the following steps:

[0020] Obtaining a preset jet position, where the preset jet position includes the head and shoulders;

[0021] Determine the basic parameters of the reverse jet, including jet flow rate, jet angle and jet temperature;

[0022] Based on the preset jet position, basic parameters and the first proxy model, a second proxy model is constructed.

[0023] Optionally, based on the second proxy model, the jet position of the aircraft and the preset jet parameter range, the actual jet parameter range of the aircraft under the ballistic condition is obtained, including:

[0024] Based on the jet position, determining a preset jet parameter range;

[0025] Inputting the preset jet parameter range into the second proxy model to obtain a second head heat flux density value and a second shoulder heat flux density value;

[0026] The heat flux density value of the first head portion is compared with the heat flux density value of the second head portion, and the heat flux density value of the first shoulder portion is compared with the heat flux density value of the second shoulder portion to determine the actual jet parameter range.

[0027] Optionally, comparing the heat flux density value of the first head with the heat flux density value of the second head, and the heat flux density value of the first shoulder with the heat flux density value of the second shoulder to determine the actual jet parameter range, further comprising:

[0028] When the heat flux density value of the first head is greater than the heat flux density value of the second head, and the heat flux density value of the first shoulder is greater than the heat flux density value of the second shoulder, the preset jet parameter range is re-determined;

[0029] Based on the re-determination of the preset jet parameters, the jet position and the second proxy model, the actual jet parameter range is determined.

[0030] In a second aspect, the present invention provides an aircraft reverse jet thermal protection system for determining a jet position, comprising:

[0031] An acquisition module, used to acquire the trajectory condition of the aircraft and the preset range of jet parameters;

[0032] A jet position determination module, used for determining the jet position of the aircraft under the ballistic condition based on the first proxy model;

[0033] The jet parameter determination module is used to obtain the actual jet parameter range of the aircraft under ballistic conditions based on the second proxy model, the jet position of the aircraft and the preset jet parameter range.

[0034] In a third aspect, the present invention further provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, the steps of the above-mentioned aircraft reverse jet thermal protection method for determining the jet position are implemented.

[0035] In a fourth aspect, the present invention further provides a computer-readable storage medium, which stores machine-executable instructions. When the machine-executable instructions are called and executed by a processor, the machine-executable instructions prompt the processor to execute the above-mentioned aircraft reverse jet thermal protection method for determining the jet position.

[0036] The aircraft reverse jet thermal protection method, system and equipment for determining the jet position provided in the embodiments of the present invention adopt a first proxy model and a second proxy model to determine the jet position and the jet parameter range corresponding to the impact condition. Compared with the prior art of adjusting the target setting parameters of the aircraft based on the target flight status data, the position where the peak heat flux of the aircraft occurs can be quickly determined, and the local heat flux density can be reduced, thereby improving energy utilization efficiency.

[0037] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0039] Figure 1 A flow chart of a method for reverse jet thermal protection of an aircraft for determining a jet position provided by an embodiment of the present invention is shown;

[0040] Figure 2 A schematic diagram of a process for constructing an agent model provided by an embodiment of the present invention is shown;

[0041] Figure 3 A schematic diagram of a process for determining a jet position and a jet parameter range provided by an embodiment of the present invention is shown;

[0042] Figure 4 A schematic structural diagram of an aircraft reverse jet thermal protection system for determining a jet position provided by an embodiment of the present invention is shown;

[0043] Figure 5 A schematic structural diagram of an electronic device provided by an embodiment of the present invention is shown. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The components of the embodiments of the present invention generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present invention.

[0045] In the current prior art, adjusting the target setting parameters of the aircraft based on the target aircraft state data can effectively reduce the aerodynamic heat and drag of the aircraft at non-zero angles of attack, improve the aerodynamic performance of the aircraft, and greatly increase the maneuverability. However, this method does not clearly indicate how to determine the initial position of the aircraft jet and the flow parameter setting. Based on this, the present invention provides an aircraft reverse jet thermal protection method, system and device for determining the jet position. The jet position and jet parameter range of the aircraft are determined by a first proxy model and a second proxy model, thereby improving the accuracy of the prediction of the peak value of the heat flux density on the aircraft surface, avoiding the ablation problem caused by exceeding the bearing limit of the heat protection material due to insufficient prediction; and shortening the numerical simulation calculation time to meet the demand for rapid prediction of the peak heat flux density during the optimization of the aircraft aerodynamic shape; and, according to different working conditions, the jet is turned on in the part with more severe thermal environment to achieve efficient heat reduction effect and effectively ensure the safety and performance of the aircraft.

[0046] Figure 1 The present invention provides a flow chart of a method for determining the position of a jet for thermal protection of an aircraft reverse jet provided in an embodiment of the present invention. Figure 1 As shown, the method comprises the following steps:

[0047] Step S110, obtaining the trajectory condition of the aircraft and the preset jet parameter range.

[0048] Among them, the ballistic condition refers to the state where the aircraft runs along a parabolic trajectory under ideal conditions of no resistance and no aerodynamic heating. In this case, the aircraft is only affected by gravity, and other factors such as air resistance and heating are ignored. The shape and trajectory of the trajectory can be approximated as a parabola. In actual engineering applications, the ballistic condition is usually considered as a reference state, and the states in other complex environments can be analyzed and calculated by deviating from this ideal state.

[0049] The preset jet parameter range refers to a series of possible jet parameters pre-set at a determined jet position, and the jet parameters include but are not limited to the initial velocity of the jet, the jet angle, the jet density, the jet heat flux, etc. By setting the preset jet parameter range, the actual jet behavior can be simulated more accurately in numerical simulation and engineering applications, and the optimal jet scheme can be determined by screening and optimizing the preset jet parameters.

[0050] Step S120: Determine the jet position of the aircraft under the ballistic condition based on the first proxy model.

[0051] In an optional embodiment, in step S120, the first proxy model is constructed according to the following steps:

[0052] S210, obtaining structural shape parameters and operating condition parameters of the aircraft;

[0053] S220, sampling and processing the structural shape parameters and the operating condition parameters to obtain a plurality of sample points;

[0054] S230: construct a first proxy model based on a number of sample points.

[0055] Specifically, Figure 2 As shown in FIG. 1 , since the structural shape and working condition are the main parameters that affect the aerodynamic simulation and heat flux density calculation of the aircraft, it is necessary to obtain the structural shape parameters and working condition parameters of the aircraft, where the structural shape parameters include but are not limited to the head radius, shoulder radius and total length, that is, the structural shape parameters are X = (x1, x2, ...}, x1∈(x 1p , x 1q ), where x1 and x2 are single structural parameters, such as x1 can be the head radius, x 1p , x1q are the upper and lower boundaries of the range of structural shape parameters;

[0056] The operating parameters include but are not limited to flight altitude, flight Mach and angle of attack, that is, the operating parameters are Y = {y1, y2, ...}, y1∈(y 1p ,y 1q ), where y1, y2 are single operating parameters, y 1p ,y 1q The upper and lower boundaries of the range of the operating parameters are determined, and the parameter range of each parameter is determined;

[0057] Based on the orthogonal experimental design method, sampling is carried out within each parameter range to obtain several sample points;

[0058] According to several sample points of structural shape parameters and working condition parameters, CFD (Computational Fluid Dynamics) numerical simulation is performed under the non-jet state to obtain the first proxy model, wherein the expression of the first proxy model is:

[0059] Q t =f t (x1, x2, y1, y2, ...)

[0060] QUR t =g t (x1, x2, y1, y2, ...)

[0061] In the formula, Qo t is the heat flux density of the head without jet addition, f t is the proxy model mapping function corresponding to the head without jet addition, Qr t is the heat flux density of the shoulder without jet addition, g t It is the proxy model mapping function corresponding to the shoulder without jet added.

[0062] The specific steps of CFD numerical simulation for the non-jet state are as follows:

[0063] 1. Set the geometric model: build the geometric model according to the specific parameters of each sample point;

[0064] 2. Mesh generation: Use appropriate mesh generation techniques such as Del method, hexahedral mesh, etc. to generate high-quality meshes for the geometric model;

[0065] 3. Boundary condition setting: set boundary conditions such as air flow velocity and boundary layer;

[0066] 4. Physical model selection: Select a suitable physical model such as the standard k-ε model, RNG k-ε model, etc.

[0067] 5. Grid independence test: obtain the solution that converges on the grid dependence;

[0068] 6. Calculation: Perform CFD calculations to obtain results such as surface pressure and heat flux.

[0069] The above method can be used to construct a model with the structural shape parameters and working condition parameters as input and the head heat flux density Qo t and shoulder heat flux Qr t The first proxy model for CFD numerical simulation under the output non-jet state can be selected from proxy models such as radial basis, Kriging, BP neural network, etc.

[0070] In an optional embodiment, in step S120, determining the jet position of the aircraft under the ballistic condition based on the first proxy model includes:

[0071] S121, inputting the trajectory working condition into the first proxy model to obtain a first head heat flux density value and a first shoulder heat flux density value of the aircraft;

[0072] S122, comparing the first head heat flux density value with the first shoulder heat flux density value to determine the jet position of the aircraft.

[0073] In an optional embodiment, in step S122, the first head heat flux density value and the first shoulder heat flux density value are compared to determine the jet position of the aircraft, further comprising:

[0074] When the first head heat flux density value is greater than the first shoulder heat flux density value, the jet position of the aircraft is the head jet;

[0075] When the first head heat flux density value is less than the first shoulder heat flux density value, the jet position of the aircraft is the shoulder jet.

[0076] Specifically, Figure 3 As shown, by inputting the trajectory parameters into the first proxy model, the heat flux density Qo of the first head of the aircraft in the non-jet state can be obtained. t and the first shoulder heat flux Qr t The value of

[0077] By judging the heat flux density Qo of the first head t and the first shoulder heat flux Qr t The numerical value determines the jet position of the aircraft. When the heat flux density Qo of the first head t Greater than the first shoulder heat flux Qr t When the jet position of the aircraft is the head position; when the first head heat flux density Qo tLess than the first shoulder heat flux Qr t When the jet position of the aircraft is the shoulder position; when the heat flux density Qo t Equal to the first shoulder heat flux Qr t When , the jet position of the aircraft is the head position and the shoulder position.

[0078] Through the above-mentioned first proxy model, the prediction accuracy of the peak value of the heat flux density on the aircraft surface can be improved, so the jet position of the aircraft can be quickly determined, avoiding the ablation problem caused by exceeding the tolerance limit of the heat protection material due to insufficient prediction.

[0079] Step S130: Based on the second proxy model, the jet position of the aircraft and the preset jet parameter range, the actual jet parameter range of the aircraft under the ballistic condition is obtained.

[0080] In an optional embodiment, in step S130, the second proxy model is constructed according to the following steps:

[0081] S310, obtaining a preset jet position, where the preset jet position includes the head and shoulders;

[0082] S320, determining basic parameters of the reverse jet, the basic parameters including jet flow, jet angle and jet temperature;

[0083] S330: construct a second proxy model based on the preset jet position, basic parameters and the first proxy model.

[0084] Specifically, Figure 2 As shown, a reverse jet is added to several sample points of the structural shape parameters and working condition parameters determined above, and a preset jet position is first selected, and the preset jet position includes the head O and the shoulder R;

[0085] Then, the basic parameters required for introducing the reverse jet are determined, which include but are not limited to the jet flow rate, jet angle, and jet temperature, that is, Z = {z1, z2, ...}, z1∈(z 1p , z 1q ), where z1, z2 are single basic parameters, z 1p , z 1q are the upper and lower boundaries of the basic parameters;

[0086] Finally, based on the preset jet position, basic parameters and data of the first proxy model, CFD numerical simulation is performed under the jet state to obtain the second proxy model, where the expression of the second proxy model is:

[0087] Q s =f s (x1, x2, y1, y2, ...)

[0088] QUR s =g s (x1, x2, y1, y2, ...)

[0089] In the formula, Qo s is the heat flux density of the head after the jet is added, f s is the proxy model mapping function corresponding to the head after adding the jet, Qr s is the heat flux density of the shoulder after the jet is added, g s It is the proxy model mapping function corresponding to the shoulder after adding the jet.

[0090] The above method can be used to construct a model with the structural shape parameters and working condition parameters as input and the head heat flux density Qo t and shoulder heat flux Qr t The second proxy model for CFD numerical simulation under the output jet state can be selected from radial basis, Kriging, BP neural network and other proxy models.

[0091] In an optional embodiment, in step S130, based on the second proxy model, the jet position of the aircraft and the preset jet parameter range, the actual jet parameter range of the aircraft under the ballistic condition is obtained, including:

[0092] S131, determining a preset jet parameter range based on the jet position;

[0093] S132, inputting the preset jet parameter range into the second proxy model to obtain a second head heat flux density value and a second shoulder heat flux density value;

[0094] S133, comparing the heat flux density value of the first head with the heat flux density value of the second head, the heat flux density value of the first shoulder with the heat flux density value of the second shoulder, and determining the actual jet parameter range.

[0095] In an optional embodiment, in step S133, the first head heat flux value and the second head heat flux value, the first shoulder heat flux value and the second shoulder heat flux value are compared to determine the actual jet parameter range, further comprising:

[0096] When the heat flux density value of the first head is greater than the heat flux density value of the second head, and the heat flux density value of the first shoulder is greater than the heat flux density value of the second shoulder, the preset jet parameter range is re-determined;

[0097] Based on the re-determination of the preset jet parameters, the jet position and the second proxy model, the actual jet parameter range is determined.

[0098] Specifically, Figure 3As shown, after determining the jet position of the aircraft based on the first proxy model, a preset jet parameter range is set based on the jet position;

[0099] By inputting the preset jet parameter range into the second proxy model, the heat flux density Qo of the second head of the aircraft in the jet state can be obtained. s and the second shoulder heat flux Qr s The value of

[0100] By judging the heat flux density Qo of the second head s and the first shoulder heat flux Qr t The numerical value determines the actual jet parameter range of the aircraft. When the heat flux density Qo t Less than the second head heat flux Qo s When the heat flux density Qr of the first shoulder t Less than the heat flux Qr of the second shoulder s When the heat flux density Qo of the first head is t Greater than or equal to the second head heat flux Qo s When the heat flux density Qr of the first shoulder t Greater than or equal to the second shoulder heat flux Qr s When the preset jet parameter range is reset, the jet parameters are recalculated until the heat flux density Qo of the first head is t Less than the second head heat flux Qo s When the heat flux density Qr of the first shoulder t Less than the heat flux Qr of the second shoulder s , output the actual jet parameter range.

[0101] Furthermore, when the heat flux density Qo of the first head t Less than the second head heat flux Qo s When the heat flux density Qr of the first shoulder t Less than the heat flux Qr of the second shoulder s When , it means that the added reverse jet can reduce its heat flux, which proves that the added reverse jet plays a role of thermal protection.

[0102] The jet position is determined by the first proxy model, and the jet parameter range is determined by the second proxy model, so that the corresponding jet position and jet parameters can be given in the actual flight later.

[0103] The present invention provides a method, system and device for aircraft reverse jet thermal protection for determining the jet position, which has the following beneficial effects:

[0104] 1. Based on the first proxy model, the jet position can be quickly determined, the jet position can be more accurately positioned, the jet flow consumption can be reduced, and the energy utilization efficiency can be improved;

[0105] 2. Based on the second proxy model, the jet position and jet parameters of the aircraft under ballistic conditions can be quickly predicted, and the aircraft jet plan can be formed to achieve effective thermal protection;

[0106] 3. The first proxy model and the second proxy model use numerical simulation to directly construct the relationship between input parameters and output performance parameters, effectively reducing calculation time, reducing the use of computing resources, and improving computing efficiency.

[0107] Figure 4 A schematic diagram of the structure of an aircraft reverse jet thermal protection system for determining a jet position provided by an embodiment of the present invention is shown in FIG. Figure 4 As shown, the system includes:

[0108] An acquisition module 100 is used to acquire the trajectory condition of the aircraft and a preset jet parameter range;

[0109] The jet position determination module 200 is used to determine the jet position of the aircraft under the ballistic condition based on the first proxy model;

[0110] The jet parameter determination module 300 is used to obtain the actual jet parameter range of the aircraft under the ballistic condition based on the second proxy model, the jet position of the aircraft and the preset jet parameter range.

[0111] In an optional embodiment, the jet position determination module 200 is further configured to:

[0112] Obtaining the structural shape parameters and operating condition parameters of the aircraft;

[0113] Sampling the structural shape parameters and working condition parameters to obtain several sample points;

[0114] Based on a number of sample points, a first proxy model is constructed.

[0115] In an optional embodiment, the jet position determination module 200 is further configured to:

[0116] Based on the first proxy model, the jet position of the aircraft under the ballistic condition is determined, including:

[0117] Inputting the ballistic working condition into the first proxy model, obtaining a first head heat flux density value and a first shoulder heat flux density value of the aircraft;

[0118] The heat flux density value of the first head portion is compared with the heat flux density value of the first shoulder portion to determine the jet position of the aircraft.

[0119] In an optional embodiment, the jet position determination module 200 is further configured to:

[0120] The method further comprises: comparing the heat flux density value of the first head portion with the heat flux density value of the first shoulder portion to determine the jet position of the aircraft;

[0121] When the first head heat flux density value is greater than the first shoulder heat flux density value, the jet position of the aircraft is the head jet;

[0122] When the first head heat flux density value is less than the first shoulder heat flux density value, the jet position of the aircraft is the shoulder jet.

[0123] In an optional embodiment, the jet parameter determination module 300 is further configured to:

[0124] Build the second agent model according to the following steps:

[0125] Obtaining a preset jet position, where the preset jet position includes the head and shoulders;

[0126] Determine the basic parameters of the reverse jet, including jet flow rate, jet angle and jet temperature;

[0127] Based on the preset jet position, basic parameters and the first proxy model, a second proxy model is constructed.

[0128] In an optional embodiment, the jet parameter determination module 300 is further configured to:

[0129] Based on the jet position, determining a preset jet parameter range;

[0130] Inputting the preset jet parameter range into the second proxy model to obtain a second head heat flux density value and a second shoulder heat flux density value;

[0131] The heat flux density value of the first head portion is compared with the heat flux density value of the second head portion, and the heat flux density value of the first shoulder portion is compared with the heat flux density value of the second shoulder portion to determine the actual jet parameter range.

[0132] In an optional embodiment, the jet parameter determination module 300 is further configured to:

[0133] When the heat flux density value of the first head is greater than the heat flux density value of the second head, and the heat flux density value of the first shoulder is greater than the heat flux density value of the second shoulder, the preset jet parameter range is re-determined;

[0134] Based on the re-determination of the preset jet parameters, the jet position and the second proxy model, the actual jet parameter range is determined.

[0135] The implementation principle and technical effects of the system provided in the embodiment of the present application are the same as those of the aforementioned method embodiment. For the sake of brief description, for matters not mentioned in the system embodiment, reference may be made to the corresponding contents in the aforementioned method embodiment.

[0136] like Figure 5 As shown, an electronic device 600 provided in an embodiment of the present application includes: a processor 601, a memory 602 and a bus, the memory 602 stores machine-readable instructions executable by the processor 601, when the electronic device is running, the processor 601 and the memory 602 communicate through the bus, the processor 601 executes the machine-readable instructions to perform the steps of the aircraft reverse jet thermal protection method for determining the jet position as described above.

[0137] Specifically, the above-mentioned memory 602 and processor 601 can be general-purpose memories and processors, which are not specifically limited here. When the processor 601 runs the computer program stored in the memory 602, it can execute the above-mentioned aircraft reverse jet thermal protection method for determining the jet position.

[0138] The processor 601 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the hardware integrated logic circuit or software instructions in the processor 601. The above processor 601 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present application can be implemented or executed. The general processor can be a microprocessor or the processor can also be any conventional processor, etc. The steps of the method disclosed in the embodiments of the present application can be directly embodied as a hardware decoding processor for execution, or a combination of hardware and software modules in the decoding processor for execution. The software module may be located in a storage medium mature in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory 602, and the processor 601 reads the information in the memory 602 and completes the steps of the above method in combination with its hardware.

[0139] Corresponding to the above-mentioned aircraft reverse jet thermal protection method for determining the jet position, an embodiment of the present application also provides a computer-readable storage medium, which stores machine-executable instructions. When the computer-executable instructions are called and executed by the processor, the computer-executable instructions prompt the processor to execute the steps of the above-mentioned aircraft reverse jet thermal protection method for determining the jet position.

[0140] The aircraft reverse jet thermal protection system for determining the jet position provided in the embodiment of the present application can be specific hardware on the device or software or firmware installed on the device. The system provided in the embodiment of the present application, its implementation principle and the technical effect produced are the same as those in the aforementioned method embodiment. For the sake of brief description, the parts not mentioned in the system embodiment can refer to the corresponding contents in the aforementioned method embodiment. Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working processes of the systems, devices and units described above can all refer to the corresponding processes in the aforementioned method embodiment, and will not be repeated here.

[0141] In the embodiments provided in the present application, it should be understood that the disclosed devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of units is only a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some communication interfaces, and the indirect coupling or communication connection of devices or units can be electrical, mechanical or other forms.

[0142] For another example, the flowchart and block diagram in the accompanying drawings show the possible architecture, functions and operations of the device, method and computer program product according to multiple embodiments of the present application. In this regard, each box in the flowchart or block diagram can represent a module, a program segment or a part of the code, and a part of the module, program segment or code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order from the order marked in the accompanying drawings. For example, two consecutive boxes can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flowchart, and the combination of the boxes in the block diagram and / or flowchart can be implemented with a dedicated hardware-based system that performs a specified function or action, or can be implemented with a combination of dedicated hardware and computer instructions.

[0143] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0144] In addition, each functional unit in the embodiments provided in the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0145] If the function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application can essentially or in other words, the part that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium, including a number of instructions for an electronic device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM), random access memory (RAM), disk or optical disk, and other media that can store program codes.

[0146] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0147] In the description of the present invention, it should be noted that the terms "first", "second", "third", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0148] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0149] Finally, it should be noted that the above-mentioned embodiments are only specific implementation methods of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention is described in detail with reference to the above-mentioned embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-mentioned embodiments within the technical scope disclosed by the present invention, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention. They should all be covered within the protection scope of the present invention.

Claims

1. A method for aircraft reverse jet thermal protection for determining jet position, characterized in that: include: Obtaining the trajectory conditions of the aircraft and the preset range of jet parameters; Determining a jet position of the aircraft under the ballistic condition based on the first proxy model; Based on the second proxy model, the jet position of the aircraft and the preset jet parameter range, the actual jet parameter range of the aircraft under the ballistic condition is obtained.

2. The aircraft reverse jet thermal protection method for determining the jet position according to claim 1, characterized in that: The first proxy model is constructed according to the following steps: Acquiring structural parameters and operating parameters of the aircraft; Sampling the structural shape parameters and the operating condition parameters to obtain a plurality of sample points; Based on a number of the sample points, the first proxy model is constructed.

3. The aircraft reverse jet thermal protection method for determining the jet position according to claim 1, characterized in that: The step of determining the jet position of the aircraft under the ballistic condition based on the first proxy model includes: Inputting the ballistic working condition into the first proxy model to obtain a first head heat flux density value and a first shoulder heat flux density value of the aircraft; The first head heat flux density value and the first shoulder heat flux density value are compared to determine the jet position of the aircraft.

4. The aircraft reverse jet thermal protection method for determining the jet position according to claim 3, characterized in that: The first head heat flux density value is compared with the first shoulder heat flux density value to determine the jet position of the aircraft, and further includes: When the first head heat flux density value is greater than the first shoulder heat flux density value, the jet position of the aircraft is the head jet; When the first head heat flux density value is less than the first shoulder heat flux density value, the jet position of the aircraft is a shoulder jet.

5. The aircraft reverse jet thermal protection method for determining the jet position according to claim 1, characterized in that: The second proxy model is constructed according to the following steps: Acquiring a preset jet position, wherein the preset jet position includes the head and shoulders; Determining basic parameters of the reverse jet, wherein the basic parameters include jet flow rate, jet angle and jet temperature; The second proxy model is constructed based on the preset jet position, the basic parameters and the first proxy model.

6. The aircraft reverse jet thermal protection method for determining the jet position according to claim 3, characterized in that: The step of obtaining the actual jet parameter range of the aircraft under the ballistic condition based on the second proxy model, the jet position of the aircraft and the preset jet parameter range includes: Based on the jet position, determining a preset jet parameter range; Inputting the preset jet parameter range into the second proxy model to obtain a second head heat flux density value and a second shoulder heat flux density value; The first head heat flux density value and the second head heat flux density value, the first shoulder heat flux density value and the second shoulder heat flux density value are compared to determine the actual jet parameter range.

7. The aircraft reverse jet thermal protection method for determining the jet position according to claim 6, characterized in that: The first head heat flux density value and the second head heat flux density value, the first shoulder heat flux density value and the second shoulder heat flux density value are compared to determine the actual jet parameter range, further comprising: When the heat flux density value of the first head is greater than the heat flux density value of the second head, and the heat flux density value of the first shoulder is greater than the heat flux density value of the second shoulder, re-determining the preset jet parameter range; Based on the re-determination of the preset jet parameters, the jet position and the second proxy model, an actual jet parameter range is determined.

8. An aircraft reverse jet thermal protection system for determining the jet position, characterized in that: include: An acquisition module, used to acquire the trajectory condition of the aircraft and the preset range of jet parameters; A jet position determination module, used for determining the jet position of the aircraft under the ballistic condition based on the first proxy model; The jet parameter determination module is used to obtain the actual jet parameter range of the aircraft under the ballistic condition based on the second proxy model, the jet position of the aircraft and the preset jet parameter range.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores machine-executable instructions. When the machine-executable instructions are called and executed by a processor, the machine-executable instructions prompt the processor to execute the method according to any one of claims 1 to 7.

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