Method, system and equipment for acquiring intensity check parameters of hypersonic flight vehicle

Abstract

The invention provides a hypersonic flight vehicle strength check parameter acquisition method, system and equipment wherein the hypersonic flight vehicle strength check parameter acquisition method comprises the following steps: acquiring the aerodynamic load of a flight vehicle target structure at each moment in the test time, and forming first data about the time and the aerodynamic load, meanwhile, flight parameters corresponding to the aircraft at each moment are recorded; forming second data about time and ultimate strength based on a temperature value corresponding to each moment of the aircraft target structure in the test time and a relationship between the ultimate strength and the temperature value; according to the first data and the second data, the ratio of the aerodynamic load to the ultimate strength at each moment is calculated; and taking the flight parameter, the temperature value and the ultimate strength of the moment corresponding to the maximum ratio in all the ratios as the structural strength checking parameters of the aircraft. The problem that when the structural strength of a traditional aircraft is checked, only the state with the maximum aerodynamic force is referred, and the influence of the temperature on the bearing performance of the structure is neglected is solved.

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] In the aerodynamic load assessment of traditional aircraft, various parameters when the aerodynamic force is the largest for the whole or a certain component during the test are generally selected as the basis for the structural strength verification of the aircraft; however, with the emergence of hypersonic aircraft, the aerodynamic heating of the aircraft causes a significant increase in the temperature of the structural load-bearing components, which will significantly affect the strength and stiffness characteristics of the structure; the maximum aerodynamic state and the worst load-bearing performance are often not at the same time, especially in the case of intense heating, the temperature change of the aircraft may reduce the strength and stiffness characteristics of the material. Therefore, evaluation based only on the maximum aerodynamic force may not reflect the true load-bearing capacity.

[0003] The time point of the maximum aerodynamic state during the flight test is inconsistent with the worst time point of the aircraft's load-bearing performance caused by actual temperature, which leads to inaccurate test parameters finally selected 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 a traditional aircraft structure, only the state with the maximum aerodynamic force is referred to, and the influence of temperature on the bearing performance of the structure 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, which includes:

[0006] The aerodynamic loads on the target structure of the aircraft at each moment during the test time are obtained, and first data on the time and the aerodynamic loads are formed, and 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 on the time and the ultimate strength are formed 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; 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 combination 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 the target time in the test time are obtained to form flight status data; a first standard 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 time in the flight status data is traversed in the first standard table to obtain the aerodynamic load at the target time, and linearly interpolated to obtain first data on time and aerodynamic load.

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

[0010] The two adjacent target times are recorded as t1 and t2 respectively, and any time between the two adjacent target times 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 implementation, 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 respectively to obtain the Mach number, altitude, angle of attack, sideslip angle and rudder angle corresponding to each moment; then, according to the material heat transfer characteristics of the target structure of the aircraft, the aerodynamic thermal engineering algorithm is used to calculate the temperature value corresponding to the target structure of the aircraft at each moment.

[0013] In conjunction with the first aspect, in one implementation, 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 at the target moment, and the temperature value at the target moment is linearly interpolated to obtain the temperature value of the aircraft target structure at each moment.

[0015] In combination with the first aspect, in one implementation, a linear interpolation calculation is performed on a temperature value of a target structure of an aircraft at a target time, which 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 target structure of the aircraft 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 target structure of the aircraft with the ultimate strength is obtained, and the ultimate strength of the target structure of the aircraft 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 combination with the first aspect, in one implementation, 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:

[0019] The ratio of aerodynamic load and ultimate strength corresponding to each moment and 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 the time and the aerodynamic load, while recording the corresponding flight parameters of 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 the time and the 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 the aerodynamic load and the 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 verification parameter acquisition device, which includes a processor, a memory, and a hypersonic aircraft strength verification parameter acquisition program stored in the memory and executable by the processor, wherein when the hypersonic aircraft strength verification parameter acquisition program is executed by the processor, the steps of the hypersonic aircraft strength verification parameter acquisition method as described in any one of claims 1 to 8 are implemented.

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

[0023] A method for obtaining strength verification parameters of hypersonic aircraft can establish a more accurate force and strength relationship model by simultaneously considering the influence of aerodynamic load and temperature, combining aerodynamic load with corresponding high temperature conditions, selecting a load combination that simultaneously produces maximum stress and minimum bearing capacity to determine the most severe working conditions, and calculating the ratio of aerodynamic load to ultimate strength at each moment according to the ultimate strength corresponding to force and temperature. This ratio reflects the safety of the aircraft structure under specific conditions. In general, the smaller the ratio, the safer the structure. On the contrary, find the moment corresponding to the maximum ratio. The maximization of this ratio often shows the critical state of the aircraft under extreme conditions, and extracts the flight parameters, temperature values ​​and corresponding ultimate strength at that moment 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 relationship between aerodynamic loads, temperature and material properties to ensure the structural safety of hypersonic vehicles under different flight conditions, thereby providing safety guarantees for their design and application; it solves the problem that when verifying the structural strength of traditional aircraft, only the state with the maximum aerodynamic force is referred to, and the influence of temperature on the structural bearing performance is ignored. 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 the embodiment of the present application;

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

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

[0028] Figure 5 This is a schematic diagram of how the ratio of the bending moment of the control surface to the ultimate strength of the root of the control surface 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 solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, 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 the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0031] In a first aspect, the present application provides a method for obtaining strength verification parameters of a hypersonic vehicle, 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 vehicle includes:

[0032] S1. Acquire the aerodynamic load on the target structure of the aircraft at each moment during the test time, and form first data about time and aerodynamic load, while recording 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 completing data collection, 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 target structure of the aircraft during the test time, and form second data on time and ultimate strength according to 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 value 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 the aerodynamic load and the ultimate strength of the structure. The smaller the ratio, the higher the structural safety. The dynamic change of the ratio over time can be further analyzed to determine the safety of the structure under specific loads.

[0038] S4. The flight parameters, temperature values ​​and ultimate strength at the time corresponding to the largest ratio among all ratios are used as the 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 the moment are obtained. These parameters can be used as key indicators for aircraft structure strength verification to better evaluate the performance of the structure under specific flight conditions.

[0040] Throughout S1-S4, by considering the influence of aerodynamic load and temperature at the same time, a more accurate model of the relationship between force and strength can be established. The aerodynamic load is combined with the corresponding high temperature conditions, and the load combination that simultaneously produces the maximum stress and the minimum bearing capacity is selected to determine the most severe working conditions. According to the ultimate strength corresponding to the force and temperature, the ratio of the aerodynamic load to the ultimate strength at each moment is calculated. This ratio reflects the safety margin of the aircraft structure under specific conditions. In general, the smaller the ratio, the safer the structure. On the contrary, find the moment corresponding to the maximum ratio. The maximization of this ratio often shows the critical state of the aircraft under extreme conditions. The flight parameters, temperature values ​​and corresponding ultimate strength at this 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 mutual relationship between aerodynamic load, temperature and material properties to ensure the structural safety of hypersonic aircraft under different flight conditions, thereby providing safety guarantees for its design and application; it solves the problem that when verifying the strength of the traditional aircraft structure, only the state with the maximum aerodynamic force is referred to, and the influence of temperature on the structural bearing performance is ignored.

[0041] Further, 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 load includes the following steps:

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

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

[0044] S12, traversing 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 in the first standard number table, obtaining the aerodynamic load at the target time, and performing linear interpolation on the aerodynamic loads to obtain first data on time and aerodynamic loads.

[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, the parameters related to the aircraft flight are defined and obtained, and these parameters generally include time, flight altitude, speed, angle of attack, temperature, etc.; then, CFD simulation analysis or wind tunnel test 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 of 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, and the first data on time and aerodynamic loads are obtained based on the forces of the aircraft target structure and the flight status corresponding to each moment, and the flight parameters used to obtain the aerodynamic loads of the aircraft target structure at each moment are stored.

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

[0047] The two adjacent target times are recorded as t1 and t2 respectively, and any time between the two adjacent target times 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 target structure of the aircraft at each moment during the test time.

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

[0049] Further, in one embodiment, obtaining the temperature value corresponding to each moment of the target structure of the aircraft 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 time during the test time, and perform linear interpolation on them respectively to obtain the Mach number, altitude, angle of attack, sideslip angle and rudder angle corresponding to each moment;

[0051] According to the 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.

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

[0053] Further, in one embodiment, obtaining the temperature value corresponding to each moment of the target structure of the aircraft 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 at the target moment, and the temperature value at the target moment is linearly interpolated to obtain the temperature value of the aircraft target structure at 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 relatively uncertain Mach number, altitude and angle of attack at each moment obtained by linear interpolation. Then, based on the heat transfer characteristics of the material and according to the aerodynamic thermal engineering algorithm, the temperature value corresponding to 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, a linear interpolation calculation is performed on the temperature value of the target structure of the aircraft at the target time, which 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 target structure of the aircraft corresponding to each moment in the test time is calculated.

[0058] In this embodiment, continuous data can be obtained through the interpolation method, which helps to obtain more comprehensive data. Compared with using only discrete measurement data, interpolation can effectively improve the estimation accuracy of the temperature at the intermediate moment. Through the above calculation process, a corresponding temperature value can be constructed for each target moment, thereby generating a complete temperature set. This process can effectively reflect the trend of the temperature change of the target structure of the aircraft over time.

[0059] Further, in one embodiment, obtaining second data about 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 process is collected and recorded, and the collected temperature data is matched with the test time one by one to form a data table of time-temperature values; a relationship between temperature values ​​and 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] Further, 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 aerodynamic load and ultimate strength corresponding to each moment and 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 and the corresponding ultimate strength at each moment is first calculated to generate ratio data, and the ratio at each moment is recorded in a new data table; the ratios in the data table are traversed to find the absolute maximum value of the ratio, the maximum value and its corresponding time are recorded, the flight parameters, temperature values ​​and ultimate strength at that moment are obtained, and 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 necessary data support for aircraft structural strength verification. It helps to understand the safety of the structure during flight and also provides an important basis for subsequent design optimization.

[0065] In the second aspect, an embodiment of the present application also 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 the time and the aerodynamic load, and at the same time record the flight parameters corresponding to the aircraft at each moment; the temperature value corresponding to the aircraft target structure at each moment during the test time, and based on the relationship between the ultimate strength and the temperature value, form second data about the time and the ultimate strength; obtain the flight parameters, temperature values, and ultimate strength at the moment corresponding to the maximum ratio as a data processing system for aircraft structure strength verification parameters, 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 module systems, among which the data storage system: during the test or simulated flight of the hypersonic aircraft, the aerodynamic load, flight parameters and target structure temperature are collected or calculated in real time; the collected data is stored in the data storage system, and is sorted into the first data and the second data according to the time sequence; the data processing system calculates the ratio of the aerodynamic load to the ultimate strength moment by moment based on the stored first data and the second data, and traverses the calculated ratio, identifies the maximum ratio, and records the time, flight parameters, temperature and ultimate strength corresponding to the ratio, and finally outputs the aircraft structure strength verification parameters corresponding to the maximum ratio for subsequent analysis. This system integrates data collection, storage and processing, and is designed to process the acquisition of mechanism strength verification parameters to ensure the structural safety of the aircraft under extreme conditions.

[0067] In a third aspect, an embodiment of the present application provides a hypersonic aircraft strength calibration parameter acquisition device, which may 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, the memory, and the communication interface.

[0070] The communication interface includes an input / output (I / O) interface, a physical interface, and a logical interface, etc., which are used to interconnect the devices inside the hypersonic aircraft strength calibration parameter acquisition device, and an interface for interconnecting the hypersonic aircraft strength calibration parameter acquisition device with other devices (such as other computing devices or user devices). The physical interface can be an Ethernet interface, an optical fiber interface, an ATM interface, etc.; the user device can be a display, a keyboard, etc.

[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, which may call the hypersonic aircraft strength calibration parameter acquisition program stored in the memory and execute the hypersonic aircraft strength calibration parameter acquisition method provided in the embodiment 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 may refer to the various embodiments of the hypersonic aircraft strength calibration parameter acquisition method of the present application, which will not be repeated here.

[0073] Next, a method, system and device for obtaining strength verification parameters of a hypersonic aircraft proposed in this application will be demonstrated. Taking the strength verification of the root structure of the control surface 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 of the root of the control surface, the gas load data is converted into data for obtaining the bending moment of the root of the control surface. Figure 2-5 , Figure 2-5 The horizontal axis in the above 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 time-varying parameters of the control surface bending moment, 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 root of the operating surface is obtained, that is, the ultimate strength of the root of the operating surface changes with time, 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 variation 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 value of the operating surface bending moment 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 "first", "second" and "third" to different types.

[0077] In the description of the embodiments of the present application, "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 the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplary", "for example" or "for example" is intended to present related concepts in a specific way.

[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; the “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 that appear in a specific order are included, but it should be understood that these operations or steps may not be executed in the order in which they appear in the embodiments of the present application or in parallel, and the sequence number of the operation is only used to distinguish the different operations, and the sequence number itself does not represent any execution order. In addition, these processes may include more or fewer operations, and these operations or steps may be executed 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 a necessary general hardware platform, and of course by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present application is essentially 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, disk, CD) as described above, and includes a number of instructions for 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 are not intended to 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 verification parameters of a hypersonic vehicle, characterized in that: It includes: Acquire the aerodynamic load on the target structure of the aircraft at each moment during the test time, form first data about time and aerodynamic load, and record the corresponding flight parameters of the aircraft at each moment; Acquire the temperature value corresponding to each moment of the target structure of the aircraft during the test time, and form second data on time and ultimate strength according to the relationship between ultimate strength and temperature value; Calculate the ratio of the aerodynamic load to the ultimate strength at each moment according to 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 the strength verification parameters of a hypersonic vehicle according to claim 1, wherein: The flight parameters include Mach number, altitude, angle of attack, sideslip angle and rudder deflection angle; The first data about 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 time during the test 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 loads at the target time, and linear interpolation is performed to obtain first data on time and aerodynamic loads.

3. The method for obtaining the strength verification parameters of a hypersonic vehicle according to claim 2, wherein: The obtained aerodynamic load at the target time is linearly interpolated, which includes the following steps: The two adjacent target times are recorded as t1 and t2 respectively, and any time between the two adjacent target times 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 time are obtained.

4. The method for obtaining the strength verification parameters of a hypersonic vehicle according to claim 2, wherein: Obtaining the temperature value corresponding to each moment of the target structure of the aircraft 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 time during the test time, and perform linear interpolation on them respectively to obtain the Mach number, altitude, angle of attack, sideslip angle and rudder angle corresponding to each moment; Then, according to 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 the strength verification parameters of a hypersonic vehicle according to claim 2, wherein: Obtaining the temperature value corresponding to each moment of the target structure of the aircraft 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 at the target moment, and the temperature value at the target moment is linearly interpolated to obtain the temperature value of the aircraft target structure at each moment.

6. The method for obtaining the strength verification parameters of a hypersonic vehicle according to claim 5, characterized in that: The temperature value of the target structure of the aircraft at the target time is linearly interpolated and calculated, which 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 target structure of the aircraft corresponding to each moment in the test time is obtained.

7. The method for obtaining the strength verification parameters of a hypersonic vehicle according to claim 1, wherein: The second data on time and ultimate strength is obtained, which 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 the strength verification parameters of a hypersonic vehicle according to claim 1, wherein: The flight parameters, temperature values ​​and ultimate strength at the time corresponding to the largest ratio among all ratios are used as the aircraft structure strength verification parameters, which includes the following steps: The ratio of aerodynamic load and ultimate strength corresponding to each moment and 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 vehicle strength verification parameter acquisition system comprises: A data storage system is used to obtain the aerodynamic loads on the target structure of the aircraft at each moment during the test time, and form first data on the time and the aerodynamic loads, while recording the corresponding flight parameters of the aircraft at each moment; based on the temperature value corresponding to the target structure of the aircraft at each moment during the test time, and the relationship between the ultimate strength and the temperature value, form second data on the time and the ultimate strength; obtain the flight parameters, temperature values, 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 according to 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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