Method for correcting air-ground difference of high-altitude high-speed jet flow interference data

Abstract

The invention provides a heaven and earth difference correction method for high-altitude high-speed jet flow interference data, and the method comprises the steps: taking jet flow interference data obtained through a wind tunnel test as a reference, obtaining three groups of wind tunnel test jet flow interference data through adjusting the total temperature and total pressure of a wind tunnel incoming flow and replacing a wind tunnel nozzle, and employing a wind tunnel test method; the derivatives of the jet flow interference data to the Mach number and the Reynolds number are solved; two groups of numerical calculation jet flow interference data are obtained by adjusting the jet flow gas temperature and the specific heat ratio and adopting a numerical calculation method, and the derivative of the jet flow interference data to the jet flow momentum is solved; according to the known heaven and earth Mach number, Reynolds number and jet flow momentum difference, heaven and earth difference correction of high-altitude high-speed jet flow interference data is realized. According to the method, the heaven and earth difference correction error is reduced, the Mach number influence, the Reynolds number influence and the jet flow momentum influence are decoupled, and the heaven and earth difference correction problem under the real flight condition and the thermal jet flow condition cannot be simulated in the wind tunnel is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft wind tunnel tests, and in particular relates to a method for correcting the sky-ground difference of high-altitude high-speed jet interference data. Background Art

[0002] With the development of high-speed aircraft in my country, the indicators of various aircraft are developing towards higher airspace and higher speed domains. For gliding high-speed aircraft, the booster separation is carried out at high altitude and high speed. In order to improve safety, reverse thrust rockets are often installed on the boosters, and the negative thrust generated by the reverse thrust rocket is used to accelerate the interstage separation process. However, in this process, the reverse thrust rocket jet will produce strong aerodynamic interference to the main aircraft. The controllable requirement of the main aircraft attitude during the interstage separation process puts forward higher accuracy requirements for the prediction of this type of indirect jet interference.

[0003] The interference flow field formed by the lateral jet and the incoming flow in the high-speed incoming flow is very complex. The jet forms various shock wave structures near the exit, and interferes with the wave structure generated by the external flow field of the aircraft, causing the respective flow fields to change and form an interference flow field. A series of complex flows such as separation flow and vortex are also generated near the nozzle. Current research points out that this complex interference flow field is the result of the combined influence of multiple factors, including aircraft shape, incoming flow parameters, flight Mach number, flight angle of attack, nozzle position, number of nozzles, jet pressure, etc.

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

[0005] At present, the prediction of aerodynamic performance 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 limitation of the power of the heating equipment, there is a lower limit on the matching height for each Mach number step in low-density wind tunnels. It is mainly suitable for the flight environment of spacecraft such as return capsules. For gliding-cruising aircraft flying in a relatively dense atmosphere, ground tests cannot cover the flight mission profile. In addition, in the current scaled model of wind tunnel tests, it is impossible to truly simulate the ignition process of a small rocket engine. The jet flow field can only be simulated by a normal temperature high-pressure gas source. The different components and temperatures of the jet gas will also have a significant impact on the jet interference data.

[0006] On the other hand, numerical calculations often have benchmark offsets, and different grid topologies and different settings will produce different results. From the engineering practice of aircraft development, gas performance prediction generally requires the principle of combining wind tunnel tests and numerical calculations. Wind tunnel tests are responsible for obtaining benchmarks, while numerical calculations are responsible for obtaining increments, thereby eliminating the difference between wind tunnel test conditions and actual flight conditions. For jet interference under high-speed flight conditions, due to the limitations of wind tunnel conditions, it is necessary to carry out earth-to-sky corrections on multiple parameters such as Mach number, Reynolds number, and jet parameters. Otherwise, the torque characteristics will deviate too much from the actual deviation, which may mislead the design of the aircraft control scheme in severe cases and lead to loss of control. Summary of the invention

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

[0008] The present invention provides a method for correcting the difference between the sky and the ground of high-altitude high-speed jet interference data, and the method for correcting the difference between the sky and the ground of high-altitude high-speed jet interference data comprises:

[0009] Based on the jet interference data obtained from the wind tunnel test, 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 using the wind tunnel test method.

[0010] 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 solved respectively.

[0011] By adjusting the jet gas temperature and specific heat ratio, two sets of numerical calculation jet interference data are obtained using numerical calculation methods.

[0012] The derivative of the jet interference data with respect to the jet momentum is solved based on two sets of numerical calculations of the jet interference data;

[0013] Based on the derivatives of the jet interference data with respect to the Mach number and Reynolds number, and the derivative of the jet interference data with respect to the jet momentum, and according to the known sky and earth Mach number, altitude, jet total temperature and jet specific heat ratio, the high-altitude high-speed jet interference data are corrected for the sky and earth differences.

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

[0015] Further, according to Obtain the derivative of the jet interference data with respect to the 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) are the jet interference data of the first to third groups of wind tunnel tests respectively.

[0016] Furthermore, the working conditions of the first set of numerical calculation of jet interference data are set to be the same as those of the first set of wind tunnel test jet interference data. The Mach number of the first set of numerical calculation of jet interference data is Ma0, the Reynolds number is Re0, and the total temperature of the jet is T j0 , the jet specific heat ratio is γ j0 ; Based on the first set of numerical calculations, the total temperature of the jet is adjusted to the real temperature T j1 , adjust the jet specific heat ratio to the real γ j1 , the second set of numerical calculation jet interference data is obtained, whose Mach number is Ma0, Reynolds number is Re0, and jet total temperature is T j1 , the jet specific heat ratio is γ j1 .

[0017] Further, according to Obtain the derivative of jet disturbance 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 groups of numerical calculation of jet interference data, respectively. The jet momentum C0 is determined by the total temperature T of the jet gas. j0 and specific heat ratio γ j0 It is deduced that the jet momentum C1 is determined by the total temperature T of the jet gas. j1 and specific heat ratio γ j1 Deduced.

[0018] By applying the technical solution of the present invention, a method for correcting the sky-ground difference of high-altitude high-speed jet interference data is provided. The method uses the jet interference data obtained by the wind tunnel test as a benchmark, adjusts the total temperature and total pressure and replaces the nozzle, and adopts the wind tunnel test method to obtain three groups of wind tunnel test jet interference data, and solves the derivatives of the jet interference data to the Mach number and the Reynolds number; by adjusting the jet gas temperature and the specific heat ratio, a numerical calculation method is adopted to obtain two groups of numerical calculation jet interference data, and solves the derivative of the jet interference data to the jet momentum; the sky-ground difference correction of high-altitude high-speed jet interference data can be realized by the known sky-ground Mach number, Reynolds number, and jet momentum difference. The present invention makes the jet interference data have linear characteristics for similar parameters through similar parameter transformation, and reduces the sky-ground difference correction error; through wind tunnel tests and data calculations, the influence of Mach number, Reynolds number and jet momentum are decoupled, and the problem of sky-ground difference correction under the conditions that the wind tunnel cannot simulate real flight conditions and thermal jet conditions is solved. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 A schematic flow chart of a method for correcting the sky-ground difference of high-altitude high-speed jet interference data provided according to a specific embodiment of the present invention is shown. DETAILED DESCRIPTION

[0021] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0023] Unless otherwise specifically stated, the relative arrangement of the parts and steps set forth in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. The techniques, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the techniques, methods and equipment should be considered as part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation.

[0024] like Figure 1 As shown, according to a specific embodiment of the present invention, a method for correcting the sky-ground difference of high-altitude high-speed jet interference data is provided, and the method includes:

[0025] Based on the jet interference data obtained from the wind tunnel test, 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 using the wind tunnel test method.

[0026] 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 solved respectively.

[0027] By adjusting the jet gas temperature and specific heat ratio, two sets of numerical calculation jet interference data are obtained using numerical calculation methods.

[0028] The derivative of the jet interference data with respect to the jet momentum is solved based on two sets of numerical calculations of the jet interference data;

[0029] Based on the derivatives of the jet interference data with respect to the Mach number and Reynolds number, and the derivative of the jet interference data with respect to the jet momentum, and according to the known sky and earth Mach number, altitude, jet total temperature and jet specific heat ratio, the high-altitude high-speed jet interference data are corrected for the sky and earth differences.

[0030] By applying this configuration, a method for correcting the sky-to-ground difference of high-altitude high-speed jet interference data is provided. The method uses the jet interference data obtained by the wind tunnel test as a benchmark, adjusts the total temperature and total pressure and replaces the nozzle, and adopts the wind tunnel test method to obtain three sets of wind tunnel test jet interference data, and solves the derivatives of the jet interference data to the Mach number and the Reynolds number; by adjusting the jet gas temperature and the specific heat ratio, a numerical calculation method is adopted to obtain two sets of numerical calculation jet interference data, and solves the derivatives of the jet interference data to the jet momentum; the sky-to-ground difference correction of high-altitude high-speed jet interference data can be realized by the known sky-to-ground Mach number, Reynolds number, and jet momentum difference. The present invention makes the jet interference data have linear characteristics for similar parameters through similar parameter transformation, and reduces the sky-to-ground difference correction error; through wind tunnel tests and data calculations, the influence of Mach number, Reynolds number and jet momentum are decoupled, and the problem of sky-to-ground difference correction under the conditions that the wind tunnel cannot simulate real flight conditions and thermal jet conditions is solved.

[0031] Firstly, in the present invention, taking the jet interference data obtained from the wind tunnel test as a benchmark, three sets of wind tunnel test jet interference data are obtained by adjusting the total temperature and total pressure and replacing the nozzle using the wind tunnel test method.

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

[0033] On the basis of the first set of wind tunnel tests, the Mach number Ma0 was kept unchanged and the total temperature and total pressure of the wind tunnel inflow were adjusted to obtain the second set of wind tunnel test jet interference data, corresponding to the Reynolds number Re1.

[0034] On the basis of the first set of wind tunnel tests, the Reynolds number Re0 was kept unchanged, and wind tunnel tests were carried out by replacing the wind tunnel nozzle and adjusting the total temperature and total pressure of the wind tunnel flow to obtain the third set of wind tunnel test jet interference data, corresponding to the Mach number of the aircraft is Ma2.

[0035] Furthermore, in the present invention, the derivatives of the jet interference data with respect to the Mach number and the Reynolds number are respectively solved based on three sets of wind tunnel test jet interference data.

[0036] Specifically, according to Obtain the derivative of the jet interference data with respect to the 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) are the jet interference data of the first to third groups of wind tunnel tests respectively.

[0037] Furthermore, in the present invention, by adjusting the jet gas temperature and the specific heat ratio, a numerical calculation method is used to obtain two sets of numerically calculated jet interference data.

[0038] Specifically, the working conditions of the first set of numerical calculation of jet interference data are set to be the same as those of the first set of wind tunnel test jet interference data, that is, the Mach number is Ma0 and the Reynolds number is Re0. In addition, the total jet temperature of the first set of numerical calculation of jet interference data is set to T j0 , the jet specific heat ratio is γ j0 .

[0039] Based on the first set of numerical calculations, the total temperature of the jet is adjusted to the real temperature T j1 , adjust the jet specific heat ratio to the real γ j1 , the second set of numerical calculation jet interference data is obtained, whose Mach number is Ma0, Reynolds number is Re0, and jet total temperature is T j1 , the jet specific heat ratio is γ j1 .

[0040] Furthermore, in the present invention, the jet interference data is calculated based on two sets of numerical values ​​to obtain the derivative of the jet interference data with respect to the jet momentum.

[0041] Specifically, according to Obtain the derivative of jet disturbance 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 groups of numerical calculation of jet interference data respectively. The jet momentum C0 can be calculated from the total temperature T of the jet gas. j0 and specific heat ratio γ j0 It is deduced that the jet momentum C1 can be obtained from the total temperature of the jet gas T j1 and specific heat ratio γ j1 Deduced.

[0042] The present invention transforms similar parameters so that the jet interference data has linear characteristics for similar parameters, thereby reducing the error of the sky-ground difference correction; through wind tunnel tests and data calculations, the influence of Mach number, Reynolds number and jet momentum are decoupled, solving the problem of sky-ground difference correction when the wind tunnel cannot simulate real flight conditions and thermal jet conditions.

[0043] Through the method of the present invention, the sky-ground difference correction of the jet interference data of a certain aircraft in the wind tunnel test was completed, which was in good agreement with the data obtained from the flight test, and the jet interference phenomenon of the reverse thrust rocket was reproduced, which has a reference significance for the subsequent prediction of jet interference of high-altitude and high-speed aircraft.

[0044] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

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

2. The method for correcting the sky-ground difference of high-altitude high-speed jet interference data according to claim 1 is characterized in that: The first set of wind tunnel test jet interference data is set as the aerodynamic reference data obtained based on the wind tunnel test, with a Mach number Ma0, a Reynolds number Re0, and a jet momentum C0; on the basis of the first set of wind tunnel tests, the Mach number Ma0 is kept unchanged, and the wind tunnel test is carried out by adjusting the total temperature and total pressure to obtain the second set of wind tunnel test jet interference data, and the corresponding Reynolds number is Re1; on the basis of the first set of wind tunnel tests, the Reynolds number Re0 is kept unchanged, and the wind tunnel test is carried out by replacing the nozzle and adjusting the total temperature and total pressure to obtain the third set of wind tunnel test jet interference data, and the corresponding Mach number of the aircraft is Ma2.

3. The method for correcting the sky-ground difference of high-altitude high-speed jet interference data according to claim 2 is characterized in that: according to Obtain the derivative of the jet interference data with respect to the 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) are the jet interference data of the first to third groups of wind tunnel tests respectively.

4. The method for correcting the sky-ground difference of high-altitude high-speed jet interference data according to claim 2 is characterized in that: The working conditions of the first set of numerical calculation of jet interference data are set to be the same as those of the first set of wind tunnel test jet interference data. The Mach number of the first set of numerical calculation of jet interference data is Ma0, the Reynolds number is Re0, and the total temperature of the jet is T j0 , the jet specific heat ratio is γ j0 ; Based on the first set of numerical calculations, the total temperature of the jet is adjusted to the real temperature T j1 , adjust the jet specific heat ratio to the real γ j1 , the second set of numerical calculation jet interference data is obtained, whose Mach number is Ma0, Reynolds number is Re0, and jet total temperature is T j1 , the jet specific heat ratio is γ j1 .

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

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