A method, system and device for obtaining strength calibration parameters of hypersonic aircraft

Abstract

The present invention provides a method, system, and device for obtaining hypersonic aircraft strength verification parameters. The method comprises obtaining the aerodynamic loads applied to the target structure of the aircraft at each moment during the test, generating first data related to the time and aerodynamic loads, and simultaneously recording the corresponding flight parameters of the aircraft at each moment; generating second data related to the time and ultimate strength based on the temperature value of the target structure of the aircraft at each moment during the test, and the relationship between the ultimate strength and the temperature value; calculating the ratio of the aerodynamic load to the ultimate strength at each moment based on the first and second data; and using the flight parameters, temperature values, and ultimate strength corresponding to the moment with the largest ratio among all ratios as the aircraft structure strength verification parameters. This method solves the problem that conventional aircraft structure strength verification only refers to the state with the maximum aerodynamic force and ignores the impact of temperature on the structural load-bearing performance.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft design, and in particular to a method, system and device for obtaining standard parameters for strength verification of a hypersonic aircraft. Background Art

[0002] Traditional aircraft aerodynamic load assessments typically use parameters from the moment the vehicle, or a specific component, experiences maximum aerodynamic forces during testing as the basis for verifying the vehicle's structural strength. However, with the advent of hypersonic aircraft, aerodynamic heating of the vehicle causes significant temperature increases in load-bearing components, significantly impacting the structure's strength and stiffness. The maximum aerodynamic force state and the point at which the load-bearing performance is at its worst are often different. Especially under conditions of intense heating, temperature fluctuations can degrade the material's strength and stiffness. Therefore, assessments based solely on maximum aerodynamic force may not reflect the true load-bearing capacity.

[0003] The time point of the maximum aerodynamic force during the flight test is inconsistent with the worst time point of the aircraft's load-bearing performance caused by actual temperature, resulting in inaccurate test parameters and unreasonable safety margin assessment. Summary of the Invention

[0004] The present application provides a method, system and device for obtaining strength verification parameters of a hypersonic aircraft, which can solve the problem that when verifying the strength of traditional aircraft structures, only the state with the maximum aerodynamic force is referred to, and the influence of temperature on the structural bearing performance is ignored.

[0005] In a first aspect, an embodiment of the present application provides a method for obtaining strength verification parameters of a hypersonic aircraft, comprising:

[0006] The aerodynamic load on the target structure of the aircraft at each moment during the test time is obtained, and first data related to the time and the aerodynamic load is generated, while the corresponding flight parameters of the aircraft at each moment are recorded; the temperature value corresponding to the target structure of the aircraft at each moment during the test time is obtained, and second data related to the time and the ultimate strength are generated based on the relationship between the ultimate strength and the temperature value; the ratio of the aerodynamic load to the ultimate strength at each moment is calculated based on the first data and the second data; and the flight parameters, temperature values, and ultimate strength at the moment corresponding to the largest ratio among all the ratios are used as aircraft structure strength verification parameters.

[0007] In conjunction with the first aspect, in one embodiment, the flight parameters include Mach number, altitude, angle of attack, sideslip angle, and rudder angle; forming first data about time and aerodynamic loads includes the following steps:

[0008] According to the flight envelope, the Mach number, altitude, angle of attack, sideslip angle and rudder angle at a target moment in the test time are obtained to form flight status data; a first standard number table correlating the Mach number, angle of attack, sideslip angle and rudder angle with the aerodynamic load on the target structure of the aircraft is obtained; the aerodynamic load corresponding to the Mach number, altitude, angle of attack, sideslip angle and rudder angle at the target moment in the flight status data is traversed in the first standard number table to obtain the aerodynamic load at the target moment, and linearly interpolated the aerodynamic load to obtain first data related to time and aerodynamic load.

[0009] In conjunction with the first aspect, in one embodiment, linear interpolation is performed on the obtained aerodynamic load at the target moment, which includes the following steps:

[0010] The two adjacent target moments are recorded as t1 and t2 respectively, and any moment between the two adjacent target moments is recorded as t0. The aerodynamic load corresponding to t0 is recorded as Y0, the aerodynamic load corresponding to t1 is recorded as Y1, and the aerodynamic load corresponding to t2 is recorded as Y2. Based on the linear interpolation formula The aerodynamic loads on the target structure of the aircraft at each moment during the test are obtained.

[0011] In conjunction with the first aspect, in one embodiment, obtaining the temperature value corresponding to each moment of the aircraft target structure during the test time includes the following steps:

[0012] The Mach number, altitude, angle of attack, sideslip angle, and rudder angle of the target structure of the aircraft at the target moment during the test time are obtained, and linear interpolation is performed on them to obtain the Mach number, altitude, angle of attack, sideslip angle, and rudder angle corresponding to each moment; then, based on the material heat transfer characteristics of the target structure of the aircraft, the aerodynamic thermal engineering algorithm is used to calculate the temperature value of the target structure of the aircraft at each moment.

[0013] In conjunction with the first aspect, in one embodiment, obtaining the temperature value corresponding to each moment of the aircraft target structure during the test time includes the following steps:

[0014] According to the material heat transfer characteristics of the aircraft target structure and based on the flight status data of the aircraft target structure at the target moment, the aerodynamic thermal engineering algorithm is used to calculate the temperature value of the aircraft target structure corresponding to the target moment, and the temperature value at the target moment is linearly interpolated to obtain the temperature value of the aircraft target structure corresponding to each moment.

[0015] In conjunction with the first aspect, in one embodiment, performing a linear interpolation calculation on the temperature value of the target structure of the aircraft at the target time includes the following steps:

[0016] The two adjacent target moments are recorded as t1 and t2 respectively, and any moment between the two adjacent target moments is recorded as t0. The temperature value of the aircraft target structure corresponding to t0 is recorded as T0, the temperature value of the aircraft target structure calculated at t1 is recorded as T1, and the temperature value of the aircraft target structure calculated at t2 is recorded as T2. Based on the linear interpolation formula The temperature value of the aircraft target structure corresponding to each moment in the test time is obtained.

[0017] In combination with the first aspect, in one embodiment, a second standard table associating the temperature of the aircraft target structure with the ultimate strength is obtained, and the ultimate strength of the aircraft target structure corresponding to the temperature value at each moment in the test time is traversed in the second standard table to obtain second data on time and ultimate strength.

[0018] In conjunction with the first aspect, in one embodiment, the flight parameters, temperature values, and ultimate strength at the moment corresponding to the largest ratio among all ratios are used as aircraft structure strength verification parameters, which includes the following steps:

[0019] The ratio of the aerodynamic load and the ultimate strength corresponding to each moment, as well as the flight parameters, temperature values, and ultimate strength corresponding to that moment are recorded as a unit. All units are traversed to find the unit with the maximum absolute value of the ratio, and the flight parameters, temperature values, and ultimate strength in the unit are output as the aircraft structure strength verification parameters.

[0020] In a second aspect, an embodiment of the present application provides a hypersonic aircraft strength verification parameter acquisition system, which includes: a data storage system, which is used to obtain the aerodynamic load on the aircraft target structure at each moment during the test time, and form first data about time and aerodynamic load, while recording the flight parameters corresponding to the aircraft at each moment; based on the temperature value corresponding to the aircraft target structure at each moment during the test time, and the relationship between the ultimate strength and the temperature value, second data about time and ultimate strength are formed; the flight parameters, temperature values, and ultimate strength at the moment corresponding to the maximum ratio are obtained as aircraft structure strength verification parameters; a data processing system, which is used to calculate the ratio of aerodynamic load and ultimate strength at each moment based on the first data and the second data.

[0021] In a third aspect, an embodiment of the present application provides a hypersonic aircraft strength calibration parameter acquisition device, which includes a processor, a memory, and a hypersonic aircraft strength calibration parameter acquisition program stored in the memory and executable by the processor, wherein when the hypersonic aircraft strength calibration parameter acquisition program is executed by the processor, the steps of the hypersonic aircraft strength calibration parameter acquisition method as described in any one of claims 1 to 8 are implemented.

[0022] The beneficial effects of the technical solutions provided in the embodiments of the present application include:

[0023] A method for obtaining strength verification parameters for hypersonic vehicles simultaneously considers the effects of aerodynamic loads and temperature to establish a more accurate model of the relationship between stress and strength. By combining aerodynamic loads with corresponding high-temperature conditions, the load combination that simultaneously produces maximum stress and minimum load-bearing capacity is selected to determine the most severe operating conditions. Based on the ultimate strength corresponding to the stress and temperature, the ratio of aerodynamic load to ultimate strength is calculated at each moment. This ratio reflects the safety of the vehicle structure under specific conditions. Generally, a smaller ratio indicates a safer structure. Conversely, the moment corresponding to the maximum ratio is identified. The maximum value of this ratio often indicates the critical state of the vehicle under extreme conditions. The flight parameters, temperature values, and corresponding ultimate strength at that moment are extracted as the final structural strength verification parameters. These parameters will be helpful for subsequent structural analysis and design optimization. In summary, this method of obtaining strength verification parameters utilizes the interrelationship between aerodynamic loads, temperature, and material properties to ensure the structural safety of hypersonic aircraft under different flight conditions, thereby providing safety guarantees for their design and application. It also solves the problem that when verifying the structural strength of traditional aircraft, only the state with the maximum aerodynamic force is referred to, while ignoring the impact of temperature on the structural bearing performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 Schematic diagram of the process of obtaining the strength verification parameters of a hypersonic vehicle in an embodiment of the present application;

[0025] Figure 2 This is a schematic diagram of the change of the control surface bending moment and time in an embodiment of the present application;

[0026] Figure 3 This is a schematic diagram of the change in temperature value at the root of the operating surface over time in an embodiment of the present application;

[0027] Figure 4 This is a schematic diagram of the change in the ultimate strength of the operating surface root over time in an embodiment of the present application;

[0028] Figure 5 This is a schematic diagram of how the ratio of the control surface bending moment to the ultimate strength of the control surface root changes over time in an embodiment of the present application. DETAILED DESCRIPTION

[0029] In order to enable those skilled in the art to better understand the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0030] In order to make the objectives, technical solutions and advantages of this application clearer, the implementation methods of this application will be further described in detail below with reference to the accompanying drawings.

[0031] In the first aspect, the embodiment of the present application provides a method for obtaining strength calibration parameters of a hypersonic aircraft, referring to Figure 1 , Figure 1 FIG. 1 is a flow chart of a method for obtaining strength verification parameters of a hypersonic vehicle in an embodiment of the present application. Figure 1 As shown, the method for obtaining the strength verification parameters of a hypersonic aircraft includes:

[0032] S1. Acquire the aerodynamic load on the target structure of the aircraft at each moment during the test time, generate first data related to time and aerodynamic load, and simultaneously record the corresponding flight parameters of the aircraft at each moment.

[0033] In this step, the aerodynamic loads and corresponding flight parameters at each moment are recorded in real time to ensure that the aerodynamic loads at each moment correspond to the flight parameters. After data collection is completed, the data can be used for subsequent analysis to improve the design and performance of the aircraft.

[0034] S2. Obtain the temperature value corresponding to each moment of the aircraft target structure during the test time, and form second data related to time and ultimate strength based on the relationship between ultimate strength and temperature value.

[0035] In this step, the relationship between the ultimate strength and temperature of the target structure is determined, and the calculated ultimate strength values ​​and the corresponding time and temperature are sorted and stored in the standby data for subsequent analysis.

[0036] S3. Calculate the ratio of the aerodynamic load to the ultimate strength at each moment based on the first data and the second data.

[0037] In this step, the ratio reflects the relative relationship between aerodynamic load and structural ultimate strength. A smaller ratio indicates a higher structural safety. Further analysis of the dynamic changes in the ratio over time can be used to determine the safety of the structure under specific loads.

[0038] S4. The flight parameters, temperature values, and ultimate strength at the moment corresponding to the largest ratio among all ratios are used as aircraft structure strength verification parameters.

[0039] In this step, by traversing the ratio data, the maximum ratio and its corresponding moment are identified, and the parameters corresponding to this moment are obtained. These parameters can be used as key indicators for aircraft structural strength verification to better evaluate the performance of the structure under specific flight conditions.

[0040] By simultaneously considering the effects of aerodynamic loads and temperature throughout S1-S4, a more accurate model of the relationship between stress and strength can be established. By combining aerodynamic loads with corresponding high-temperature conditions, the load combination that simultaneously produces maximum stress and minimum load-bearing capacity is selected to determine the most severe operating conditions. Based on the ultimate strength corresponding to the stress and temperature, the ratio of aerodynamic load to ultimate strength is calculated at each moment. This ratio reflects the safety margin of the aircraft structure under specific conditions. Generally, the smaller the ratio, the safer the structure. Conversely, the moment at which the maximum ratio is achieved is identified. The maximum value of this ratio often indicates the critical state of the aircraft under extreme conditions. The flight parameters, temperature values, and corresponding ultimate strength at that moment are extracted as the final structural strength verification parameters. These parameters will facilitate subsequent structural analysis and design optimization. In summary, this method for obtaining strength verification parameters leverages the interrelationship between aerodynamic loads, temperature, and material properties to ensure the structural safety of hypersonic vehicles under different flight conditions, thereby providing a safer approach to their design and application. This method addresses the problem of traditional aircraft structural strength verification, which focuses solely on the state with the maximum aerodynamic force and ignores the impact of temperature on the structural load-bearing performance.

[0041] Furthermore, in one embodiment, the flight parameters include Mach number, altitude, angle of attack, sideslip angle, and rudder angle; and forming first data related to time and aerodynamic loads includes the following steps:

[0042] S10. According to the flight envelope, the Mach number, altitude, angle of attack, sideslip angle, and rudder angle at the target time during the test are obtained to form flight status data;

[0043] S11, obtaining a first standard table of correlations between Mach number, angle of attack, sideslip angle, and rudder deflection angle and aerodynamic loads on a target structure of the aircraft;

[0044] S12. Traverse the aerodynamic loads corresponding to the Mach number, altitude, angle of attack, sideslip angle, and rudder angle at the target time in the flight state data in the first standard number table to obtain the aerodynamic load at the target time, and perform linear interpolation on the aerodynamic loads to obtain first data related to time and aerodynamic load.

[0045] In the steps of this embodiment, first, the flight parameters of the aircraft target structure at each moment during the test time are obtained, that is, parameters related to the aircraft flight are defined and obtained, which generally include time, flight altitude, speed, angle of attack, temperature, etc.; then, CFD simulation analysis or wind tunnel testing is performed on the aircraft target structure to obtain the aerodynamic characteristics of the aircraft target structure, and then a first standard table of forces and flight parameters of the aircraft target structure is obtained. In this step, data related to the forces on the aircraft need to be obtained, including the forces at each moment, to provide a data basis for the subsequent acquisition of aerodynamic loads; finally, the aerodynamic loads are obtained based on the flight status data and the first standard table. According to the forces on the aircraft target structure and the flight status corresponding to each moment, first data on time and aerodynamic loads are calculated, and the flight parameters used to obtain the aerodynamic loads of the aircraft target structure at each moment are stored.

[0046] Furthermore, in one embodiment, linear interpolation is performed on the obtained aerodynamic load at the target moment, which includes the following steps:

[0047] The two adjacent target moments are recorded as t1 and t2 respectively, and any moment between the two adjacent target moments is recorded as t0. The aerodynamic load corresponding to t0 is recorded as Y0, the aerodynamic load corresponding to t1 is recorded as Y1, and the aerodynamic load corresponding to t2 is recorded as Y2. Based on the linear interpolation formula The aerodynamic load Y0 at time t0 is obtained, that is, the aerodynamic load of the aircraft target structure at each moment during the test time.

[0048] In this embodiment, according to the aerodynamic load at the target moment, the linear interpolation formula Get the aerodynamic load at each moment.

[0049] Furthermore, in one embodiment, obtaining the temperature value corresponding to each moment of the aircraft target structure during the test time includes the following steps:

[0050] Obtain the Mach number, altitude, angle of attack, sideslip angle, and rudder angle of the target structure of the aircraft at the target moment during the test time, and perform linear interpolation on them to obtain the Mach number, altitude, angle of attack, sideslip angle, and rudder angle corresponding to each moment;

[0051] Then, according to the heat transfer characteristics of the material of the aircraft target structure, the aerodynamic thermal engineering algorithm is used to calculate the temperature value of the aircraft target structure at each moment.

[0052] In this embodiment, the thermal environment characteristics of the target structure of the aircraft are first obtained through CFD simulation and wind tunnel testing. Using part of the flight status data that has been obtained, the Mach number, altitude, angle of attack, sideslip angle, and rudder angle of the target structure of the aircraft at target moments during the test time are linearly interpolated to obtain the Mach number, altitude, angle of attack, sideslip angle, and rudder angle corresponding to each moment. The aerodynamic thermal engineering algorithm is then used to calculate the temperature value of the target structure of the aircraft at each moment.

[0053] Furthermore, in one embodiment, obtaining the temperature value corresponding to each moment of the aircraft target structure during the test time includes the following steps:

[0054] According to the material heat transfer characteristics of the aircraft target structure and based on the flight status data of the aircraft target structure at the target moment, the aerodynamic thermal engineering algorithm is used to calculate the temperature value of the aircraft target structure corresponding to the target moment, and the temperature value at the target moment is linearly interpolated to obtain the temperature value of the aircraft target structure corresponding to each moment.

[0055] This embodiment is another calculation method of the previous embodiment, the difference being that the flight status data obtained is different. In this embodiment, the Mach number, altitude, and angle of attack at the target moment are obtained, rather than the more uncertain Mach number, altitude, and angle of attack at each moment obtained through linear interpolation. Then, based on the heat transfer characteristics of the material and according to the aerodynamic thermal engineering algorithm, the temperature value of the target structure of the aircraft at the target moment is calculated, and the temperature value is linearly interpolated to obtain the temperature value corresponding to each moment. This approach can improve the accuracy of the data compared to the previous embodiment.

[0056] Furthermore, in one embodiment, performing a linear interpolation calculation on the temperature value of the target structure of the aircraft at the target time includes the following steps:

[0057] The two adjacent target moments are recorded as t1 and t2 respectively, and any moment between the two adjacent target moments is recorded as t0. The temperature value of the aircraft target structure corresponding to t0 is recorded as T0, the temperature value of the aircraft target structure calculated at t1 is recorded as T1, and the temperature value of the aircraft target structure calculated at t2 is recorded as T2. Based on the linear interpolation formula The temperature value of the aircraft target structure corresponding to each moment in the test time is calculated.

[0058] In this embodiment, interpolation allows for continuous data acquisition, facilitating more comprehensive data. Compared to using only discrete measurement data, interpolation can effectively improve the accuracy of temperature estimates at intermediate moments. Through the aforementioned calculation process, corresponding temperature values ​​can be constructed for each target moment, thereby generating a complete temperature set. This process effectively reflects the temperature trends of target aircraft structures over time.

[0059] Furthermore, in one embodiment, obtaining second data on time and ultimate strength includes the following steps:

[0060] A second standard table associating the temperature and ultimate strength of the aircraft target structure is obtained, and the ultimate strength of the aircraft target structure corresponding to the temperature value at each moment in the test time is traversed in the second standard table to obtain second data on time and ultimate strength.

[0061] In this embodiment, the temperature value of the aircraft target structure at each moment during the test is collected and recorded, and the collected temperature data is associated with the test time one by one to form a data table of time-temperature values; a relationship between the temperature value and the ultimate strength is established to form a second standard table, that is, the ultimate strength data of the target structure at different temperatures is obtained through experiments or reference to relevant literature for easy analysis; the obtained time-temperature data and temperature data-ultimate strength data are used for conversion to obtain second data on time and ultimate strength.

[0062] Furthermore, in one embodiment, the flight parameters, temperature values, and ultimate strength at the time corresponding to the largest ratio among all ratios are used as aircraft structure strength verification parameters, which includes the following steps:

[0063] The ratio of the aerodynamic load and the ultimate strength corresponding to each moment, as well as the flight parameters, temperature values, and ultimate strength corresponding to that moment are recorded as a unit. All units are traversed to find the unit with the maximum absolute value of the ratio, and the flight parameters, temperature values, and ultimate strength in the unit are output as the aircraft structure strength verification parameters.

[0064] In this embodiment, the ratio of the aerodynamic load to the corresponding ultimate strength at each moment is first calculated to generate ratio data, and the ratio value at each moment is recorded in a new data table. The ratios in the data table are then traversed to find the absolute maximum value of the ratio. The maximum value and its corresponding time are recorded, and the flight parameters, temperature values, and ultimate strength at that moment are obtained. The obtained parameters are recorded in the structural strength verification report for subsequent analysis. Through the implementation of these three steps, the relationship between aerodynamic load, temperature, ultimate strength, and time can be effectively utilized to provide the necessary data support for aircraft structural strength verification. This helps to understand the safety of the structure during flight and also provides an important basis for subsequent design optimization.

[0065] In a second aspect, an embodiment of the present application also provides a hypersonic aircraft strength verification parameter acquisition system, which includes a data storage system for acquiring the aerodynamic load borne by the aircraft target structure at each moment during the test time, and forming first data about the time and aerodynamic load, while recording the corresponding flight parameters of the aircraft at each moment; the temperature value corresponding to the aircraft target structure at each moment during the test time, and forming second data about the time and ultimate strength based on the relationship between the ultimate strength and the temperature value; obtaining the flight parameters, temperature values, and ultimate strength corresponding to the moment with the maximum ratio as an aircraft structure strength verification parameter data processing system, which is used to calculate the ratio of the aerodynamic load and the ultimate strength at each moment based on the first data and the second data.

[0066] This system includes two specific modules. The data storage system collects or calculates aerodynamic loads, flight parameters, and target structure temperature in real time during hypersonic vehicle testing or simulated flight. The collected data is stored in the data storage system and organized into first and second data in chronological order. The data processing system calculates the ratio of aerodynamic load to ultimate strength moment by moment based on the stored first and second data. It iterates through the calculated ratios, identifies the maximum ratio, and records the time, flight parameters, temperature, and ultimate strength corresponding to this ratio. Finally, it outputs the aircraft structure strength verification parameters corresponding to the maximum ratio for subsequent analysis. This system integrates data acquisition, storage, and processing, aiming to obtain structural strength verification parameters to ensure the structural safety of aircraft under extreme conditions.

[0067] In a third aspect, an embodiment of the present application provides a device for obtaining strength calibration parameters of a hypersonic aircraft. The device for obtaining strength calibration parameters of a hypersonic aircraft can be a personal computer (PC), a laptop computer, a server, or other device with data processing capabilities.

[0068] In an embodiment of the present application, a hypersonic aircraft strength verification parameter acquisition device may include a processor, a memory, a communication interface, and a communication bus.

[0069] The communication bus may be of any type and is used to interconnect the processor, memory, and communication interface.

[0070] Communication interfaces include input / output (I / O) interfaces, physical interfaces, and logical interfaces, used to interconnect components within the hypersonic aircraft strength calibration parameter acquisition device, as well as interfaces used to interconnect the hypersonic aircraft strength calibration parameter acquisition device with other devices (such as other computing devices or user devices). Physical interfaces can be Ethernet, fiber optic, or ATM interfaces; user devices can be displays, keyboards, and other devices.

[0071] The memory can be various types of storage media, such as random access memory (RAM), read-only memory (ROM), non-volatile RAM (NVRAM), flash memory, optical storage, hard disk, programmable ROM (PROM), erasable PROM (EPROM), electrically erasable PROM (EEPROM), etc.

[0072] The processor may be a general-purpose processor that can call a hypersonic aircraft strength calibration parameter acquisition program stored in a memory and execute the hypersonic aircraft strength calibration parameter acquisition method provided in the embodiments of the present application. For example, the general-purpose processor may be a central processing unit (CPU). The method executed when the hypersonic aircraft strength calibration parameter acquisition program is called can be referred to in the various embodiments of the hypersonic aircraft strength calibration parameter acquisition method of the present application, and will not be further described here.

[0073] Next, a method, system, and device for obtaining strength calibration parameters of a hypersonic aircraft proposed in this application will be clearly demonstrated. Taking the strength calibration of the control surface root structure of a certain hypersonic aircraft as an example, the root of the control surface is selected as the target structure. Since the gas load is proportional to the maximum stress, and the maximum stress is approximately proportional to the bending moment at the root of the control surface, the gas load data is converted into data for obtaining the bending moment at the root of the control surface. Figure 2-5 , Figure 2-5 The horizontal axis in the table represents the time axis t, where Figure 2 The vertical axis represents the operating surface bending moment M, Figure 3 The vertical axis represents the temperature value T, Figure 4 The vertical axis represents the ultimate strength Sigma_b of the operating surface root. Figure 5 The vertical axis represents the ratio of the operating surface bending moment to the ultimate strength M / Sigma_b.

[0074] According to the traditional load design method, the first data about time and control surface bending moment can be obtained through the above steps, that is, the parameters of the control surface bending moment changing with time, such as Figure 2 As shown; Through the above steps, the data on the temperature value and time of the root of the operating surface are obtained, that is, the parameters of the temperature value of the root of the operating surface changing with time, such as Figure 3 As shown; through the above steps, the second data of the ultimate strength and time of the operating surface root is obtained, that is, the ultimate strength of the operating surface root changes with time parameters, such as Figure 4 As shown; Finally, through the above steps, the ratio of the operating surface bending moment to the ultimate strength of the operating surface root and the time data are obtained, that is, the parameters of the ratio of the operating surface bending moment to the ultimate strength of the operating surface root over time, as shown Figure 5 As shown;

[0075] In this embodiment, according to the traditional method, see Figure 2 , only the 240s corresponding to the maximum bending moment of the operating surface is used as the evaluation standard for the structural safety margin, and the flight parameters corresponding to this moment are obtained as the aircraft structure strength verification parameters. According to the more accurate method of this application, see Figure 5 The ratio of the operating surface bending moment corresponding to 1160s to the ultimate strength of the operating surface root corresponds to the minimum safety margin of the structure. The flight parameters, temperature values ​​and ultimate strength corresponding to this moment should be obtained as the aircraft structure strength verification parameters, and a mechanical and thermal coupling evaluation should be performed on the load and temperature conditions at this point.

[0076] The terms "including" and "having" and any variations thereof in the specification and claims of this application and the above-mentioned drawings are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not limited to the listed steps or units, but optionally includes steps or units that are not listed, or optionally includes other steps or units inherent to these processes, methods, products or devices. The terms "first", "second" and "third" are used to distinguish different objects, etc., and do not represent a sequence, nor do they limit the "first", "second" and "third" to different types.

[0077] In the description of the embodiments of this application, the words "exemplary," "for example," or "for example" are used to indicate examples, illustrations, or descriptions. Any embodiment or design described as "exemplary," "for example," or "for example" in the embodiments of this application should not be construed as being preferred or advantageous over other embodiments or designs. Rather, the use of words such as "exemplary," "for example," or "for example" is intended to present the relevant concepts in a concrete manner.

[0078] In the description of the embodiments of the present application, unless otherwise specified, “ / ” means or, for example, A / B can mean A or B; “and / or” in the text is merely a description of the association relationship of associated objects, indicating that three relationships may exist, for example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone. In addition, in the description of the embodiments of the present application, “multiple” refers to two or more than two.

[0079] In some processes described in the embodiments of the present application, multiple operations or steps are included that appear in a specific order. However, it should be understood that these operations or steps may not be performed in the order in which they appear in the embodiments of the present application or may be performed in parallel. The sequence numbers of the operations are only used to distinguish between different operations, and the sequence numbers themselves do not represent any order of execution. In addition, these processes may include more or fewer operations, and these operations or steps may be performed in sequence or in parallel, and these operations or steps may be combined.

[0080] Through the description of the above implementation methods, those skilled in the art can clearly understand that the above-mentioned embodiment methods can be implemented by means of software plus the necessary general hardware platform, of course, it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk) as described above, and includes a number of instructions for enabling a terminal device to execute the methods described in each embodiment of the present application.

[0081] The above are only preferred embodiments of the present application and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A method for obtaining strength calibration parameters of a hypersonic vehicle, characterized in that: It includes: Acquiring the aerodynamic loads on the target structure of the aircraft at each moment during the test time, generating first data related to the time and the aerodynamic loads, and simultaneously recording the corresponding flight parameters of the aircraft at each moment; Acquiring a temperature value corresponding to each moment of the aircraft target structure during the test time, and generating second data related to time and ultimate strength based on a relationship between ultimate strength and temperature values; Calculating the ratio of the aerodynamic load to the ultimate strength at each moment based on the first data and the second data; The flight parameters, temperature values ​​and ultimate strength at the moment corresponding to the largest ratio among all the ratios are used as aircraft structure strength verification parameters.

2. The method for obtaining strength verification parameters of a hypersonic aircraft according to claim 1, wherein: The flight parameters include Mach number, altitude, angle of attack, sideslip angle and rudder angle; The first data on time and aerodynamic load is formed, which comprises the following steps: According to the flight envelope, the Mach number, altitude, angle of attack, sideslip angle and rudder angle at the target moment in the test time are obtained to form flight status data; Obtaining a first standard table of correlations between Mach number, angle of attack, sideslip angle, and rudder deflection angle and aerodynamic loads on a target structure of an aircraft; The aerodynamic loads corresponding to the Mach number, altitude, angle of attack, sideslip angle, and rudder angle at the target time in the flight status data are traversed in the first standard number table to obtain the aerodynamic load at the target time, and linear interpolation is performed on the aerodynamic loads to obtain first data on time and aerodynamic loads.

3. The method for obtaining hypersonic vehicle strength verification parameters according to claim 2, wherein: Performing linear interpolation on the obtained aerodynamic load at the target moment includes the following steps: The two adjacent target moments are recorded as t1 and t2 respectively, and any moment between the two adjacent target moments is recorded as t0. The aerodynamic load corresponding to t0 is recorded as Y0, the aerodynamic load corresponding to t1 is recorded as Y1, and the aerodynamic load corresponding to t2 is recorded as Y2. Based on the linear interpolation formula The aerodynamic loads on the target structure of the aircraft at each moment during the test are obtained.

4. The method for obtaining hypersonic vehicle strength verification parameters according to claim 2, wherein: Obtaining the temperature value of the aircraft target structure at each moment during the test time includes the following steps: Obtain the Mach number, altitude, angle of attack, sideslip angle, and rudder angle of the target structure of the aircraft at the target moment during the test time, and perform linear interpolation on them to obtain the Mach number, altitude, angle of attack, sideslip angle, and rudder angle corresponding to each moment; Then, based on the material heat transfer characteristics of the aircraft target structure, the aerodynamic thermal engineering algorithm is used to calculate the temperature value of the aircraft target structure at each moment.

5. The method for obtaining hypersonic vehicle strength verification parameters according to claim 2, wherein: Obtaining the temperature value of the aircraft target structure at each moment during the test time includes the following steps: According to the material heat transfer characteristics of the aircraft target structure and based on the flight status data of the aircraft target structure at the target moment, the aerodynamic thermal engineering algorithm is used to calculate the temperature value of the aircraft target structure corresponding to the target moment, and the temperature value at the target moment is linearly interpolated to obtain the temperature value of the aircraft target structure corresponding to each moment.

6. The method for obtaining hypersonic vehicle strength verification parameters according to claim 5, wherein: Performing a linear interpolation calculation on the temperature value of the target structure of the aircraft at the target time includes the following steps: The two adjacent target moments are recorded as t1 and t2 respectively, and any moment between the two adjacent target moments is recorded as t0. The temperature value of the aircraft target structure corresponding to t0 is recorded as T0, the temperature value of the aircraft target structure calculated at t1 is recorded as T1, and the temperature value of the aircraft target structure calculated at t2 is recorded as T2. Based on the linear interpolation formula The temperature value of the aircraft target structure corresponding to each moment in the test time is obtained.

7. The method for obtaining strength verification parameters of a hypersonic vehicle according to claim 1, wherein: Obtaining second data on time and ultimate strength comprises the following steps: A second standard table associating the temperature and ultimate strength of the aircraft target structure is obtained, and the ultimate strength of the aircraft target structure corresponding to the temperature value at each moment in the test time is traversed in the second standard table to obtain second data on time and ultimate strength.

8. The method for obtaining strength verification parameters of a hypersonic vehicle according to claim 1, wherein: The flight parameters, temperature values, and ultimate strength at the moment corresponding to the largest ratio among all ratios are used as aircraft structure strength verification parameters, which includes the following steps: The ratio of the aerodynamic load and the ultimate strength corresponding to each moment, as well as the flight parameters, temperature values, and ultimate strength corresponding to that moment are recorded as a unit. All units are traversed to find the unit with the maximum absolute value of the ratio, and the flight parameters, temperature values, and ultimate strength in the unit are output as the aircraft structure strength verification parameters.

9. A hypersonic vehicle strength calibration parameter acquisition system, characterized in that: The hypersonic aircraft strength calibration parameter acquisition system includes: A data storage system is configured to obtain aerodynamic loads applied to a target structure of an aircraft at each moment during a test, generate first data related to the time and aerodynamic loads, and simultaneously record flight parameters corresponding to the aircraft at each moment; generate second data related to the time and ultimate strength based on the temperature value corresponding to the target structure of the aircraft at each moment during the test, as well as the relationship between ultimate strength and temperature; and obtain the flight parameters, temperature value, and ultimate strength at the moment corresponding to the maximum ratio as aircraft structure strength verification parameters; The data processing system is used to calculate the ratio of the aerodynamic load to the ultimate strength at each moment based on the first data and the second data.

10. A hypersonic vehicle strength calibration parameter acquisition device, characterized in that: The hypersonic aircraft strength calibration parameter acquisition device includes a processor, a memory, and a hypersonic aircraft strength calibration parameter acquisition program stored in the memory and executable by the processor, wherein when the hypersonic aircraft strength calibration parameter acquisition program is executed by the processor, the steps of the hypersonic aircraft strength calibration parameter acquisition method according to any one of claims 1 to 8 are implemented.

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