High-altitude high-speed jet stream interference data space-ground difference correction method

Abstract

The application provides a high-altitude high-speed jet flow interference data space-ground difference correction method, which takes jet flow interference data obtained by a wind tunnel test as a reference, adjusts the total temperature and total pressure of a wind tunnel inflow and replaces a wind tunnel nozzle, adopts a wind tunnel test method to obtain three groups of wind tunnel test jet flow interference data, solves derivatives of jet flow interference data to Mach number and Reynolds number, adjusts jet flow gas temperature and specific heat ratio, adopts a numerical calculation method to obtain two groups of numerical calculation jet flow interference data, solves derivatives of jet flow interference data to jet flow momentum, and realizes high-altitude high-speed jet flow interference data space-ground difference correction according to known Mach number, Reynolds number and jet flow momentum difference. The application reduces space-ground difference correction error, decouples Mach number influence, Reynolds number influence and jet flow momentum influence, and solves the space-ground difference correction problem under the condition that a wind tunnel cannot simulate real flight conditions and hot jet flow conditions.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aircraft wind tunnel test technology, and particularly relates to a high-altitude high-speed jet flow interference data space-ground difference correction method. BACKGROUND

[0002] With the development of high-speed aircrafts in China, various aircraft indicators are developing towards higher altitudes and higher speeds. For gliding high-speed aircrafts, the booster is separated at high altitude and high speed. In order to improve safety, a reverse rocket is often installed on the booster. The negative thrust generated by the reverse rocket accelerates the interstage separation process, but in this process, the jet flow of the reverse rocket will produce strong aerodynamic interference on the main aircraft. The controllable demand of the main aircraft attitude during the interstage separation process puts forward higher precision requirements for the prediction of this indirect jet flow interference.

[0003] The interference flow field formed by the lateral jet flow in the high-speed incoming flow and the incoming flow is very complex. The jet flow forms various shock wave structures near the outlet, and interferes with the wave system structure generated by the external flow field of the aircraft, so that the respective flow fields change to form an interference flow field. Near the nozzle, a series of complex flows such as separated flow and vortex are also generated. Current research shows that this complex interference flow field is the result of the joint influence of various factors, including aircraft shape, incoming flow parameters, flight Mach number, flight angle of attack, nozzle position, nozzle number, and jet flow pressure.

[0004] Existing jet flow interference research results are mostly concentrated in lower altitude and lower speed flight conditions, and mainly focus on lateral jet flow for attitude control and orbit control. Under high-altitude high-speed flight conditions, due to the significant reduction of incoming flow density and dynamic pressure, the coupling interference between jet flow and incoming flow environment is significantly enhanced.

[0005] Current aerodynamic performance prediction mainly relies on wind tunnel tests and numerical calculations. For wind tunnel tests, high-speed wind tunnel tests can only be carried out in low-density wind tunnels. Due to the power limitation of heating equipment, the matching height has a lower limit for each Mach number step, mainly suitable for spacecraft flight environments such as return capsules. For gliding-cruising aircrafts flying in relatively dense atmosphere, ground tests cannot cover the flight mission profile. In addition, in the current scaled model of wind tunnel tests, the small rocket engine ignition process cannot be simulated, and only high-pressure gas at room temperature can be used to simulate the jet flow field. The composition and temperature of the jet flow gas will also have a significant impact on the jet flow interference data.

[0006] On the other hand, numerical calculation often has reference deviation, different grid topologies and different settings will obtain different results. For the engineering practice of aircraft development, the prediction of gas performance generally needs to adopt the principle of combining wind tunnel test and numerical calculation, the wind tunnel test is responsible for obtaining the reference, and the numerical calculation is responsible for obtaining the increment, so as to eliminate the difference between the wind tunnel test state and the real flight condition. For the jet flow interference of high-speed flight condition, due to the limitation of wind tunnel condition, multiple parameters such as Mach number, Reynolds number and jet flow parameter need to be corrected in space and on earth, otherwise the moment characteristics and real deviation will be too large, and in serious cases, the aircraft control scheme design may be misled, resulting in loss of control. SUMMARY

[0007] The present application aims to at least solve one of the technical problems existing in the prior art.

[0008] The present application provides a high-altitude high-speed jet flow interference data space-ground difference correction method, which comprises:

[0009] The jet flow interference data obtained by the wind tunnel test is taken as the reference, three groups of wind tunnel test jet flow interference data are obtained by adjusting the total temperature and total pressure of the wind tunnel inflow and replacing the wind tunnel nozzle by using the wind tunnel test method;

[0010] The derivatives of the jet flow interference data with respect to the Mach number and the Reynolds number are solved according to the three groups of wind tunnel test jet flow interference data respectively;

[0011] Two groups of numerical calculation jet flow interference data are obtained by adjusting the jet flow gas temperature and the specific heat ratio by using the numerical calculation method;

[0012] The derivative of the jet flow interference data with respect to the jet flow momentum is solved according to the two groups of numerical calculation jet flow interference data;

[0013] Based on the derivative of the jet flow interference data with respect to the Mach number and the Reynolds number, the derivative of the jet flow interference data with respect to the jet flow momentum, and according to the known space-ground Mach number, height, jet flow total temperature and jet flow specific heat ratio, the high-altitude high-speed jet flow interference data is corrected for space-ground difference.

[0014] Further, the first group of wind tunnel test jet flow interference data is set as the aerodynamic reference data obtained based on the wind tunnel test, the Mach number is Ma0, the Reynolds number is Re0, and the jet flow momentum is C0; on the basis of the first group of wind tunnel test, the Mach number Ma0 is kept unchanged, and the second group of wind tunnel test jet flow interference data is obtained by adjusting the total temperature and total pressure to carry out wind tunnel test, corresponding to the Reynolds number Re1; on the basis of the first group of wind tunnel test, the Reynolds number Re0 is kept unchanged, and the third group of wind tunnel test jet flow interference data is obtained by replacing the nozzle and adjusting the total temperature and total pressure to carry out wind tunnel test, corresponding to the Mach number of the aircraft Ma2.

[0015] Further, according to the derivative of the jet flow interference data with respect to the Mach number and the Reynolds number, the derivative of the jet flow interference data with respect to the jet flow momentum, and the known space-ground Mach number, height, jet flow total temperature and jet flow specific heat ratio, the high-altitude high-speed jet flow interference data is corrected for space-ground difference. Derivative of jet interaction data with respect to Mach number According to Derivative of jet interaction data with respect to Reynolds number Where ΔF 风洞 (Ma0, Re0, C0), ΔF 风洞 (Ma0, Re1, C0), and ΔF 风洞 (Ma2, Re0, C0) are the first to third sets of wind tunnel test jet interaction data, respectively.

[0016] Further, the first set of numerical calculation jet interaction data is set to have the same working conditions as the first set of wind tunnel test jet interaction data, the Mach number of the first set of numerical calculation jet interaction data is Ma0, the Reynolds number is Re0, the jet total temperature is T j0 , and the jet specific heat ratio is γ j0 ; on the basis of the first set of numerical calculation, the jet total temperature is adjusted to the actual temperature T j1 , and the jet specific heat ratio is adjusted to the actual γ j1 , to obtain the second set of numerical calculation jet interaction data, the Mach number of which is Ma0, the Reynolds number is Re0, the jet total temperature is T j1 , and the jet specific heat ratio is γ j1 .

[0017] Further, according to Derivative of jet interaction data with respect to jet momentum Where ΔF 计算 (Ma0, Re0, C0) and ΔF 计算 (Ma0, Re0, C1) are the first and second sets of numerical calculation jet interaction data, respectively, the jet momentum C0 is derived from the jet gas total temperature T j0 and the specific heat ratio γ j0 , and the jet momentum C1 is derived from the jet gas total temperature T j1 and the specific heat ratio γ j1 .

[0018] The technical scheme of the application provides a high-altitude high-speed jet flow interference data ground-to-space difference correction method, which takes jet flow interference data obtained through wind tunnel test as a reference, obtains three groups of wind tunnel test jet flow interference data through adjusting total temperature and total pressure and replacing a jet pipe, solves derivatives of jet flow interference data with respect to Mach number and Reynolds number, obtains two groups of numerical calculation jet flow interference data through adjusting jet flow gas temperature and specific heat ratio, solves derivatives of jet flow interference data with respect to jet flow momentum, and realizes high-altitude high-speed jet flow interference data ground-to-space difference correction according to known differences of Mach number, Reynolds number and jet flow momentum. The application makes jet flow interference data have linear characteristics with respect to similar parameters through similar parameter transformation, reduces ground-to-space difference correction error, and solves the ground-to-space difference correction problem under conditions that a wind tunnel cannot simulate real flight conditions and hot jet flow conditions through wind tunnel test and data calculation, decouples Mach number influence, Reynolds number influence and jet flow momentum influence. BRIEF DESCRIPTION OF DRAWINGS

[0019] The accompanying drawings, which are included to provide a further understanding of the embodiments of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application. It is readily understood that the drawings are merely illustrative of some embodiments of the application and therefore should not be taken to limit the scope of the application, as described throughout variously herein. In the drawings:

[0020] Figure 1 Fig. 1 shows a flowchart of a high-altitude high-speed jet flow interference data ground-to-space difference correction method according to a specific embodiment of the application. DETAILED DESCRIPTION

[0021] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings of the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. The description of the at least one exemplary embodiment is actually only illustrative, but not as any limitation on the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0022] It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and / or "comprising," when used in this specification, specify the presence of stated features, steps, operations, elements, components, and / or groups thereof, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and / or groups thereof.

[0023] The relative arrangement of components and steps, numerical expressions, and numerical values set forth in the examples are not meant to limit the scope of the application unless otherwise specifically stated. Techniques, methods, and equipment known to those of ordinary skill are not discussed in detail because such methods, techniques, and equipment should be considered as part of the description unless otherwise expressly stated. In all examples shown and discussed herein, any specific value should be interpreted as merely an example and not as a limitation.

[0024] As Figure 1 According to specific embodiments of the present application, a high-altitude high-speed jet flow interference data space-time difference correction method is provided, which comprises:

[0025] Based on the jet flow interference data obtained from the wind tunnel test, three groups of wind tunnel test jet flow interference data are obtained by adjusting the total temperature and total pressure of the wind tunnel inflow and replacing the wind tunnel nozzle;

[0026] The derivatives of the jet flow interference data with respect to Mach number and Reynolds number are solved according to the three groups of wind tunnel test jet flow interference data;

[0027] Two groups of numerical calculation jet flow interference data are obtained by adjusting the jet flow gas temperature and specific heat ratio using numerical calculation method;

[0028] The derivative of the jet flow interference data with respect to jet flow momentum is solved according to the two groups of numerical calculation jet flow interference data;

[0029] Based on the derivatives of the jet flow interference data with respect to Mach number and Reynolds number, the derivative of the jet flow interference data with respect to jet flow momentum, and according to the known space-time Mach number, altitude, jet flow total temperature, and jet flow specific heat ratio, the high-altitude high-speed jet flow interference data is corrected for space-time difference.

[0030] With the configuration, a high-altitude high-speed jet flow interference data space-ground difference correction method is provided, which takes the jet flow interference data obtained by wind tunnel test as a reference, obtains three groups of wind tunnel test jet flow interference data by adjusting total temperature and total pressure and replacing the nozzle through wind tunnel test method, solves the derivatives of the jet flow interference data to Mach number and Reynolds number, obtains two groups of numerical calculation jet flow interference data by adjusting jet gas temperature and specific heat ratio through numerical calculation method, solves the derivative of the jet flow interference data to jet flow momentum, and realizes high-altitude high-speed jet flow interference data space-ground difference correction according to the known Mach number, Reynolds number and jet flow momentum difference.

[0031] Firstly, in the application, the jet flow interference data obtained by wind tunnel test is taken as a reference, three groups of wind tunnel test jet flow interference data are obtained by adjusting total temperature and total pressure and replacing the nozzle through wind tunnel test method.

[0032] Specifically, the first group of wind tunnel test jet flow interference data is set as the aerodynamic reference data obtained based on wind tunnel test, the Mach number is Ma0, the Reynolds number is Re0, and the jet flow momentum is C0.

[0033] On the basis of the first group of wind tunnel test, the Mach number Ma0 is kept unchanged, and the second group of wind tunnel test jet flow interference data is obtained by adjusting the total temperature and total pressure of the wind tunnel inflow through wind tunnel test, corresponding to the Reynolds number Re1.

[0034] On the basis of the first group of wind tunnel test, the Reynolds number Re0 is kept unchanged, and the third group of wind tunnel test jet flow interference data is obtained by replacing the wind tunnel nozzle and adjusting the total temperature and total pressure of the wind tunnel inflow through wind tunnel test, corresponding to the Mach number Ma2 of the aircraft.

[0035] Further, in the application, the derivatives of the jet flow interference data to Mach number and Reynolds number are solved according to the three groups of wind tunnel test jet flow interference data.

[0036] Specifically, according to the derivative of the jet flow interference data to Mach number is obtained according to the derivative of the jet flow interference data to Reynolds number is obtained wherein, ΔF 风洞 (Ma0, Re0, C0), ΔF 风洞 (Ma0, Re1, C0), ΔF 风洞 (Ma2, Re0, C0) are the first to third groups of wind tunnel test jet flow interference data.

[0037] Furthermore, in this invention, by adjusting the jet gas temperature and specific heat ratio, two sets of numerically calculated jet interference data are obtained using a numerical calculation method.

[0038] Specifically, the operating conditions for the first set of numerical calculations of jet interference data are set to be the same as those for the first set of wind tunnel test jet interference data, i.e., Mach number Ma0 and Reynolds number Re0. Furthermore, the total jet temperature for the first set of numerical calculations of jet interference data is set to T. j0 The specific heat ratio of the jet is γ j0 .

[0039] Based on the first set of numerical calculations, the total jet temperature was adjusted to the actual temperature T. j1 Adjust the jet specific heat ratio to the true γ j1 The second set of numerical calculations yielded jet interference data with a Mach number of Ma0, a Reynolds number of Re0, and a total jet temperature of T. j1 The specific heat ratio of the jet is γ j1 .

[0040] Furthermore, in this invention, the derivative of the jet flow interference data with respect to the jet flow momentum is calculated based on two sets of numerical calculations of the jet flow interference data.

[0041] Specifically, according to Obtain the derivative of jet interference data with respect to jet momentum Where, ΔF 计算 (Ma0, Re0, C0) and ΔF 计算 (Ma0, Re0, C1) represent the jet interference data calculated in the first and second groups, respectively. The jet momentum C0 can be obtained from the total temperature T of the jet gas. j0 Compared with specific heat ratio γ j0 It is derived that the jet flow rate C1 can be determined by the total temperature T of the jet gas. j1 Compared with specific heat ratio γ j1 It is derived that...

[0042] This invention transforms similar parameters to make the jet interference data linear with respect to similar parameters, thus reducing the error in correcting for differences between the ground and the air. Through wind tunnel testing and data calculation, it decouples the effects of Mach number, Reynolds number, and jet momentum, solving the problem of correcting for differences between the ground and the air when wind tunnels cannot simulate real flight conditions and hot jet conditions.

[0043] The method of this invention corrected the difference between the ground and sky in the jet interference data of a certain aircraft wind tunnel test. The data matched well with the data obtained from the flight test and reproduced the jet interference phenomenon of the retro-rocket. It has reference value for the prediction of jet interference of high-altitude and high-speed aircraft.

[0044] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

Claims

1. A method for correcting the difference between sky and ground in high-altitude high-speed jet interference data, characterized in that, The method for correcting the difference between the sky and ground in the high-altitude high-speed jet interference data includes: Based on the jet interference data obtained from wind tunnel tests, three sets of wind tunnel test jet interference data were obtained by adjusting the total temperature and pressure of the wind tunnel inflow and replacing the wind tunnel nozzle. Based on three sets of wind tunnel test jet interference data, the derivatives of the jet interference data with respect to Mach number and Reynolds number are calculated respectively. By adjusting the jet gas temperature and specific heat ratio, two sets of numerical calculation data on jet interference were obtained using numerical calculation methods. Based on the two sets of numerical calculations of jet interference data, the derivative of the jet interference data with respect to jet momentum is solved. Based on the derivatives of jet interference data with respect to Mach number and Reynolds number, and the derivatives of jet interference data with respect to jet momentum, the high-altitude high-speed jet interference data are corrected for differences between the sky and the ground based on known Mach numbers, altitude, total jet temperature, and specific heat ratio of the jet.

2. The method for correcting the difference between sky and ground in high-altitude high-speed jet interference data according to claim 1, characterized in that, The first set of wind tunnel test jet interference data is set as aerodynamic reference data obtained from wind tunnel tests, with Mach number Ma0, Reynolds number Re0, and jet momentum C0. Based on the first set of wind tunnel tests, keeping Mach number Ma0 constant, the second set of wind tunnel test jet interference data is obtained by adjusting the total temperature and total pressure, corresponding to Reynolds number Re1. Based on the first set of wind tunnel tests, keeping Reynolds number Re0 constant, the third set of wind tunnel test jet interference data is obtained by changing the nozzle and adjusting the total temperature and total pressure, corresponding to the aircraft's Mach number Ma2.

3. The method for correcting the difference between sky and ground in high-altitude high-speed jet interference data according to claim 2, characterized in that, according to Obtain the derivative of jet interference data with respect to Mach number. according to Obtain the derivative of the jet interference data with respect to the Reynolds number. Where, ΔF 风洞 (Ma0, Re0, C0), ΔF 风洞 (Ma0, Re1, C0), ΔF 风洞 (Ma2, Re0, C0) represent the jet interference data from the first to the third groups of wind tunnel tests, respectively.

4. The method for correcting the difference between sky and ground in high-altitude high-speed jet interference data according to claim 2, characterized in that, The operating conditions for the first set of numerical calculations of jet interference data are the same as those for the first set of wind tunnel test jet interference data. The Mach number for the first set of numerical calculations of jet interference data is Ma0, the Reynolds number is Re0, and the total jet temperature is T. j0 The specific heat ratio of the jet is γ j0 Based on the first set of numerical calculations, the total jet temperature was adjusted to the actual temperature T. j1 Adjust the jet specific heat ratio to the true γ j1 The second set of numerical calculations yielded jet interference data with a Mach number of Ma0, a Reynolds number of Re0, and a total jet temperature of T. j1 The specific heat ratio of the jet is γ j1 .

5. The method for correcting the difference between sky and ground in high-altitude high-speed jet interference data according to claim 4, characterized in that, according to Obtain the derivative of jet interference data with respect to jet momentum Where, ΔF 计算 (Ma0, Re0, C0) and ΔF 计算 (Ma0, Re0, C1) represent the jet interference data calculated in the first and second groups, respectively. The jet momentum C0 is determined by the total temperature T of the jet gas. j0 Compared with specific heat ratio γ j0 It is derived that the jet flow rate C1 is determined by the total temperature T of the jet gas. j1 Compared with specific heat ratio γ j1 It is derived that...

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