Method and device for estimating interstage separation load and jet flame state

Abstract

The present invention provides a method and device for estimating the interstage separation load and the jet flame state. The jet flame state in the interstage separation process is divided into two parts for calculation. The first part is the calculation of the relative distance between the upper stage and the lower stage that changes with time in the interstage separation process. The second part is to determine the calculation area of ​​the jet flame transient flow field based on the relative distance and the separation condition under the condition of determining the relative distance, and use the position change and state change of the jet flame particles to count the jet flame state that changes with time in each calculation area. This scheme fully considers the separation conditions, the change of relative distance and the role of the jet flame particles, and can effectively reflect the jet flame state in the interstage separation process. In addition, since the jet flame particles are a large number of particles released at one time, the position change and state change of these jet flame particles are used to estimate the jet flame state, without the need for repeated iterative processing by continuously releasing particles, and the calculation efficiency is high.

Description

Technical Field

[0001] The embodiments of the present invention relate to the field of aerospace technology, and in particular to a method and device for estimating interstage separation load and jet flame state. Background Art

[0002] The stage separation of a flying target is a transient process involving flow and motion coupling, with complex flow morphology and evolution mechanism. It is difficult to fully describe and predict its state using theoretical or empirical models. Therefore, it is urgent to provide a method that can quickly and effectively predict the stage separation load and flame state. Summary of the invention

[0003] The embodiment of the present invention provides a method and device for estimating an inter-stage separation load and a jet flame state, which can quickly and effectively estimate an inter-stage separation load and a jet flame state.

[0004] In a first aspect, an embodiment of the present invention provides a method for estimating interstage separation load and flame state, comprising:

[0005] Calculating an upper stage separation load and a lower stage separation load during an interstage separation process based on a separation condition of the aircraft; the separation condition includes at least one of an aerodynamic parameter, a mass parameter, and a separation engine operating parameter;

[0006] Calculating a relative distance between the upper stage and the lower stage during the interstage separation process that varies with time according to the upper stage separation load and the lower stage separation load;

[0007] Determining a calculation area of ​​a transient flow field of a jet flame according to the separation condition and the relative distance;

[0008] The position change and state change of the flame particles in each calculation area are determined, and the flame state changing with time in each calculation area is determined based on the position change and state change of the flame particles in each calculation area.

[0009] Preferably, the calculation of the upper stage separation load and the lower stage separation load in the interstage separation process based on the separation condition of the aircraft includes: dividing the interstage separation process into a first separation stage, a second separation stage and a third separation stage in chronological order based on the variation law of the separation load, and respectively calculating the upper stage separation load and the lower stage separation load that vary with time in each separation stage; the first separation stage is a stage in which the inflowing gas of the interstage section is greater than the outflowing gas, the second separation stage is a stage in which the outflowing gas of the interstage section is greater than the inflowing gas, and the third separation stage is a stage in which the gas flow directly impacts the front end face of the lower stage;

[0010] The method of calculating the relative distance between the upper stage and the lower stage that varies with time during the inter-stage separation process according to the upper stage separation load and the lower stage separation load comprises: calculating the relative distance between the upper stage and the lower stage that varies with time in each separation stage by using a dynamic equation according to the upper stage separation load and the lower stage separation load that vary with time in each separation stage.

[0011] Preferably, the calculation of the upper stage separation load and the lower stage separation load varying with time in each separation stage comprises:

[0012] The upper stage separation load and the lower stage separation load varying with time in the first separation stage and the second separation stage are respectively:

[0013]

[0014]

[0015]

[0016] The upper stage separation load and the lower stage separation load that vary with time in the third separation stage are respectively:

[0017] f 1 =F T

[0018]

[0019] Among them, f 1 、f 2 are the upper stage separation load and the lower stage separation load, respectively, D is the separation surface diameter, p is the pressure of the first separation stage and the second separation stage, m 0 is the initial gas mass, is the gas flow rate of the upper stage that changes with time, C is the intermediate parameter, s(t) is the separation distance that changes with time, V s is the initial volume of the interstage, k is the gas adiabatic index, R is the gas constant, T 0 is the initial temperature, F T is the thrust of the upper stage engine, p(s) is the jet impact pressure with the separation distance transformation;

[0020] The method of using the kinetic equation to calculate the relative distance between the upper stage and the lower stage in each separation stage over time includes:

[0021]

[0022]

[0023] s=s 1 +s2

[0024] Where s is the relative distance between the upper stage and the lower stage that changes with time at each separation stage, s 1 、s 2 are the separation distances of the upper and lower stages that vary with time, F 1 、F 2 are the axial aerodynamic forces on the upper stage and lower stage structures under specified flight conditions, m 1 、m 2 are the masses of the upper stage and the lower stage respectively.

[0025] Preferably, the determining of the position change and state change of the flame particles in each calculation area includes:

[0026] For each calculation area, the following steps are performed: determining the initial state parameters of the flame particles in the current calculation area, and iteratively updating the position change and state change of the flame particles in the current calculation area every time step according to the initial state parameters and the iterative update time step.

[0027] Preferably, the state change includes at least one of a speed change, a temperature change, a pressure change and a density change;

[0028] Iteratively updating the position change of the flame particles in the current calculation area includes:

[0029] The position change of the flame particle after each iteration update is S: S = u(t)·Δt; wherein u(t) is the velocity of the flame particle after the last iteration update, and Δt is the time step;

[0030] Iteratively updating the state change of the flame particles in the current calculation area includes:

[0031] When the state change is a speed change, the speed u(t+Δt) of the flame particles after each iterative update is: u(t+Δt)=u(t)+u′+Δu; wherein u′ is a turbulent speed update, and the turbulent speed update is used to characterize the speed change caused by the turbulent pulsation of the flame; Δu is an unbalanced speed update, and the unbalanced speed update is used to characterize the speed change caused by the inconsistency between the flow parameters of the flame particles and the local flow parameters;

[0032] When the state change is a temperature change, the temperature of the flame particles is updated based on the energy change caused by the change in the velocity of the flame particles after each iterative update by using the energy conservation method;

[0033] When the state change is a pressure change or a density change, the pressure and temperature of the flame particles are updated based on the temperature change of the flame particles after each iterative update.

[0034] Preferably, the non-equilibrium speed is updated to any one of the following three speed changes or the sum of at least two speed changes: a first speed change caused by the difference between the pressure of the jet flame particles and the local pressure, a second speed change caused by the difference between the speed of the jet flame particles and the local speed, and a third speed change caused by the collision of the jet flame particles with the wall.

[0035] The first speed change Δu 1 for:

[0036]

[0037] Among them, k p is the pressure difference conversion coefficient, ranging from 0 to 1; p p is the pressure of the flame particles, p c is the local pressure, ρ p is the density of the flame particles;

[0038] The second speed change Δu 2 for:

[0039]

[0040] Among them, k u is the speed difference conversion coefficient, ranging from 0 to 1; ρ c is the local density, u p is the velocity of the flame particles, u c is the local speed;

[0041] The third speed change Δu 3 for:

[0042]

[0043]

[0044] Among them, β 1 is the angle between the velocity of the jet particle before collision and the wall, β 2 k is the angle between the velocity of the jet particles after the collision and the wall; a is the collision reflection angle coefficient, ranging from 0.15 to 1.

[0045] Preferably, the calculation area is: the upper stage interstage, the interstage gap, the lower stage interstage, the upper stage body section, the upper stage empty shell section, the interstage gap outer field section, the lower stage empty shell section, the lower stage body section, the lower stage rear outer field section or the lower stage rear section;

[0046] and / or,

[0047] A particle cluster formed by a plurality of jet particles is determined as a whole jet particle, and the particle cluster is used to perform the determination of the position change and state change of the jet particles in each calculation area.

[0048] In a second aspect, an embodiment of the present invention further provides a device for estimating interstage separation load and flame state, comprising:

[0049] A load calculation unit, used to calculate the upper stage separation load and the lower stage separation load during the interstage separation process based on the separation conditions of the aircraft; the separation conditions include at least one of aerodynamic parameters, mass parameters and separation engine operating parameters;

[0050] a distance calculation unit, for calculating a relative distance between the upper stage and the lower stage that varies with time during the interstage separation process according to the upper stage separation load and the lower stage separation load;

[0051] A calculation region determination unit, used for determining a calculation region of a transient flow field of a jet flame according to the separation condition and the relative distance;

[0052] The flame state determination unit is used to determine the position change and state change of the flame particles in each calculation area, and determine the flame state changing with time in each calculation area according to the position change and state change of the flame particles in each calculation area.

[0053] In a third aspect, an embodiment of the present invention further provides a computing device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method described in any embodiment of this specification is implemented.

[0054] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, enables the computer to execute the method described in any embodiment of this specification.

[0055] The embodiment of the present invention provides a method and device for estimating the interstage separation load and the jet flame state. The jet flame state in the interstage separation process is divided into two parts for calculation. The first part is the calculation of the relative distance between the upper stage and the lower stage that changes with time in the interstage separation process. The second part is to determine the calculation area of ​​the jet flame transient flow field based on the relative distance and the separation condition under the condition of determining the relative distance, and use the position change and state change of the jet flame particles to count the jet flame state that changes with time in each calculation area. This scheme fully considers the separation conditions, the change of relative distance and the role of the jet flame particles, and can effectively reflect the jet flame state in the interstage separation process. In addition, since the jet flame particles are a large number of particles released at one time, the position change and state change of these jet flame particles are used to estimate the jet flame state, without the need for repeated iterative processing by continuously releasing particles, and the calculation efficiency is high. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0057] Figure 1 This is a flow chart of a method for estimating interstage separation load and jet flame state provided by one embodiment of the present invention;

[0058] Figure 2-Figure 3 They are schematic diagrams of the speed states in the X direction and the Y direction at a certain moment;

[0059] Figure 4-5 They are schematic diagrams of Mach number state and temperature state at a certain moment respectively;

[0060] Figure 6 is a hardware architecture diagram of a computing device provided by an embodiment of the present invention;

[0061] Figure 7 It is a structural diagram of an interstage separation load and flame state estimation device provided by one embodiment of the present invention. DETAILED DESCRIPTION

[0062] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0063] Please refer to Figure 1 The embodiment of the present invention provides a method for estimating interstage separation load and flame state, the method comprising:

[0064] Step 100, calculating the upper stage separation load and the lower stage separation load during the interstage separation process based on the separation condition of the aircraft; the separation condition includes at least one of an aerodynamic parameter, a mass parameter, and a separation engine operating parameter;

[0065] Step 102, calculating the relative distance between the upper stage and the lower stage that varies with time during the interstage separation process according to the upper stage separation load and the lower stage separation load;

[0066] Step 104, determining a calculation area of ​​the transient flow field of the jet flame according to the separation condition and the relative distance;

[0067] Step 106, determining the position change and state change of the flame particles in each calculation area, and determining the flame state that changes with time in each calculation area based on the position change and state change of the flame particles in each calculation area.

[0068] In the embodiment of the present invention, the jet flame state in the interstage separation process is divided into two parts for calculation. The first part is the calculation of the relative distance between the upper stage and the lower stage that changes with time in the interstage separation process. The second part is to determine the calculation area of ​​the jet flame transient flow field based on the relative distance and the separation condition under the condition of determining the relative distance, and use the position change and state change of the jet flame particles to count the jet flame state that changes with time in each calculation area. This scheme fully considers the separation conditions, the change of relative distance and the role of the jet flame particles, and can effectively reflect the jet flame state in the interstage separation process. In addition, since the jet flame particles are a large number of particles released at one time, the position change and state change of these jet flame particles are used to estimate the jet flame state, without the need to repeatedly iterate by continuously releasing particles, and the calculation efficiency is high.

[0069] Described below Figure 1 How the various steps are performed.

[0070] First, the first part of the calculation process is described. The first part of the calculation process includes step 100 and step 102.

[0071] The aircraft in this embodiment is an aircraft in the field of aerospace that needs to perform interstage separation during flight. The parameters in the separation conditions are all known parameters or parameters that can be obtained by calculation.

[0072] In one embodiment of the present invention, the upper stage separation load and the lower stage separation load in the inter-stage separation process can be calculated through the following steps S1-S2:

[0073] S1. Based on the variation law of separation load, the interstage separation process is divided into the first separation stage, the second separation stage and the third separation stage in chronological order; the first separation stage is the stage in which the inflowing gas of the interstage section is greater than the outflowing gas (the load rises rapidly in this separation stage), the second separation stage is the stage in which the outflowing gas of the interstage section is greater than the inflowing gas (the load drops rapidly in this separation stage), and the third separation stage is the stage in which the gas flow directly impacts the front end face of the lower stage (the relative distance between the upper stage and the lower stage increases in this separation stage, and the load drops slowly).

[0074] S2. Calculate the upper stage separation load and the lower stage separation load that change with time in each separation stage.

[0075] Among them, the upper stage separation load and the lower stage separation load that change with time in the first separation stage and the second separation stage are:

[0076]

[0077]

[0078]

[0079] The upper stage separation load and the lower stage separation load that change with time in the third separation stage are:

[0080] f 1 =FT

[0081]

[0082] Among them, f 1 、f 2 are the upper stage separation load and the lower stage separation load, respectively, D is the separation surface diameter, p is the pressure of the first separation stage and the second separation stage, m 0 is the initial gas mass, is the gas flow rate of the upper stage that changes with time, C is the intermediate parameter, s(t) is the separation distance that changes with time, V s is the initial volume of the interstage, k is the gas adiabatic index, R is the gas constant, T 0 is the initial temperature, F T is the thrust of the upper stage engine, p(s) is the jet impact pressure transformed by the separation distance, and the jet impact pressure can be determined by the jet impact calculation method.

[0083] Since the relative distance between the upper stage and the lower stage is small in the first and second separation stages, the separation load borne by the upper stage and the separation load borne by the lower stage can be set equal at the same time. In the third separation stage, the relative distance between the upper stage and the lower stage increases, so the upper stage separation load is equal to the upper stage engine thrust, while the lower stage separation load changes with the change of the relative distance. In this way, the upper stage separation load and the lower stage separation load that change with time can be obtained.

[0084] Next, in the embodiment of the present invention, the relative distance between the upper stage and the lower stage that varies with time in each separation stage can be calculated using a dynamic equation based on the upper stage separation load and the lower stage separation load that vary with time in each separation stage.

[0085] Specifically, the kinetic equation is as follows:

[0086]

[0087]

[0088] s=s 1 +s 2

[0089] Where s is the relative distance between the upper stage and the lower stage that changes with time at each separation stage, s 1 、s 2 are the separation distances of the upper and lower stages that vary with time, F 1 、F 2 are the axial aerodynamic forces on the upper stage and lower stage structures under specified flight conditions, m 1 、m 2 are the masses of the upper stage and the lower stage respectively.

[0090] In this way, the above dynamic equation is coupled with the separation load calculation formula of each separation stage to solve, so that the upper stage separation load, the lower stage separation load and the relative distance between the upper stage and the lower stage of the inter-stage separation can be quickly estimated.

[0091] It should be noted that when calculating the upper stage separation load and the lower stage separation load during the inter-stage separation process, in addition to the above-mentioned method of dividing the separation stages and calculating them separately, other methods can also be used for calculation, such as directly iteratively calculating the upper stage separation load and the lower stage separation load at each moment according to the time change, and calculating the relative distance between the upper stage and the lower stage at each moment during the iteration process.

[0092] Then, the second part of the calculation process is described. The second part of the calculation process includes step 104 and step 106.

[0093] The second part of the calculation process is the calculation process of the transient flow field of the flame under the relative distance. The second part of the calculation process is explained as follows: the flame gas ejected by the upper stage engine is composed of a large number of flame particles, each of which carries information such as the flow rate, temperature, speed and composition of the flame. The flame particles change position and state during the movement. By pre-dividing each calculation area, the flame particles will move to a certain calculation area. For each calculation area, the number and state of the flame particles in the calculation area can be used to obtain the flow field information of the calculation area, and the position and state of the flame particles can be updated accordingly; in addition, near the wall, the flame particles will return to the calculation area by collision.

[0094] In step 104, the calculation area of ​​the transient flow field of the jet flame can be determined according to the separation condition and the relative distance. In a preferred embodiment, the divided calculation areas are respectively upper stage interstage, interstage gap, lower stage interstage, upper stage body section, upper stage empty shell section, interstage gap external field section, lower stage empty shell section, lower stage body section, lower stage rear external field section and lower stage rear section. This division method fully considers the movement area of ​​the jet flame particles, can effectively describe the physical process of the flow field, and makes the output of the jet flame state at any time accurate.

[0095] Furthermore, in order to ensure that the outputted flame state at any time is more accurate, the divided calculation areas are connected to each other.

[0096] In step 106, the position change and state change of the flame particles in each calculation area can be determined according to the following method, including: for each calculation area, the following is performed: determining the initial state parameters of the flame particles in the current calculation area, and iteratively updating the position change and state change of the flame particles in the current calculation area every time step according to the initial state parameters and the iterative update time step.

[0097] In an embodiment of the present invention, the state change includes at least one of a speed change, a temperature change, a pressure change, and a density change.

[0098] The initial state parameters of the flame particles may include velocity, temperature, pressure and density, etc., which may be determined by the upper stage engine nozzle parameters. In addition, each flame particle also represents a certain flow state, and the sum of the flows represented by all the flame particles is the same as the nozzle flow.

[0099] During the calculation process, the following methods can be used to update the motion position and motion state of the flame particles:

[0100] The position change of the flame particles in the current calculation area is iteratively updated: the position change of the flame particles after each iterative update is S: S = u(t)·Δt; wherein u(t) is the velocity of the flame particles after the last iterative update, and Δt is the time step.

[0101] Iteratively update the state change of the flame particles in the current calculation area (since the state change includes at least one of speed change, temperature change, pressure change and density change, it is necessary to update the corresponding states respectively):

[0102] When the state change is a speed change, the speed u(t+Δt) of the flame particles after each iterative update is: u(t+Δt)=u(t)+u′+Δu; wherein u′ is a turbulent speed update, and the turbulent speed update is used to characterize the speed change caused by the turbulent pulsation of the flame; Δu is an unbalanced speed update, and the unbalanced speed update is used to characterize the speed change caused by the inconsistency between the flow parameters of the flame particles and the local flow parameters;

[0103] When the state change is a temperature change, the temperature of the flame particles is updated based on the energy change caused by the change in the velocity of the flame particles after each iterative update by using the energy conservation method;

[0104] When the state change is a pressure change or a density change, the pressure and temperature of the flame particles are updated based on the temperature change of the flame particles after each iterative update.

[0105] When the velocity change is iteratively updated as described above, the velocity of the flame particles is updated at each time step.

[0106] In one embodiment of the present invention, the turbulent velocity update u′ can be determined by the turbulent disturbance coefficient k′ and the random variable δ. In one embodiment, the turbulent velocity update u′ is calculated by the formula u′=k′·δ·u(t), where k′ ranges from 0 to 0.08, which is equivalent to the common turbulence intensity coefficient, and δ ranges from a random number between (-1,1).

[0107] In one embodiment of the present invention, the unbalanced velocity update Δu can be any one of the following three velocity changes or the sum of at least two velocity changes: a first velocity change caused by the difference between the pressure of the flame particles and the local pressure, a second velocity change caused by the difference between the velocity of the flame particles and the local velocity, and a third velocity change caused by the collision of the flame particles with the wall.

[0108] Preferably, in order to ensure the calculation accuracy of the unbalanced speed update Δu, the unbalanced speed update Δu is the sum of the above three speed changes, that is, Δu = Δu 1 +Δu2 +Δu 3 .

[0109] Among them, the above three speed changes are calculated as follows:

[0110] The first speed change Δu 1 for:

[0111]

[0112] Among them, k p is the pressure difference conversion coefficient, ranging from 0 to 1; p p is the pressure of the flame particles, p c is the local pressure, ρ p is the density of the flame particles;

[0113] The second speed change Δu 2 for:

[0114]

[0115] Among them, k u is the velocity difference conversion coefficient, ranging from 0 to 1, representing the relaxation state from the current velocity to the equilibrium velocity; ρ c is the local density, u p is the velocity of the flame particles, u c is the local speed;

[0116] The third speed change Δu 3 for:

[0117]

[0118]

[0119] Among them, β 1 is the angle between the velocity of the jet particle before collision and the wall, β 2 k is the angle between the velocity of the jet particles after the collision and the wall; a It is the collision reflection angle coefficient, which indicates the difference between the collision angle of the jet flame gas and the jet flame particles after colliding with the wall. Its value range is 0.15~1. The smaller the value, the more obvious the jet flame particle sticking to the wall effect.

[0120] When the temperature change, pressure change or density change is updated, the speed change of the flame particles may be used as the basis for the update according to the isentropic relationship. Specifically, the temperature of the flame particles may be updated based on the energy change caused by the speed change of the flame particles after each iterative update by using the energy conservation method; and then the pressure and temperature of the flame particles may be updated based on the temperature change of the flame particles after each iterative update combined with the Mach number change.

[0121] In one implementation, the temperature, pressure, and density of the flame particles can be updated respectively by the following formulas:

[0122]

[0123]

[0124]

[0125] Wherein, T(t+Δt), ρ(t+Δt), and p(t+Δt) are the temperature, density, and pressure of the flame particles after each iteration update; T(t), ρ(t), and p(t) are the temperature, density, and pressure of the flame particles after the last iteration update; c p is the specific heat capacity at constant pressure, and γ is the specific heat ratio.

[0126] In the flow field calculation, in addition to updating the position and state of the jet particles at each time step, it is also necessary to update and count the flow parameters of the unit where the jet particles are located (the calculation area is divided into several units) to provide conditions for the output of the flow field parameters. Among them, the local flow parameters are updated according to the flow represented by the jet particles and the resulting flux conservation principle, which is expressed as:

[0127]

[0128]

[0129]

[0130] Among them, ρ c (t+Δt),u c (t+Δt), T c (t+Δt) are the local density, local velocity, and local temperature of the flame particles after each iteration update, respectively. c (t),u c T(t) and T(t) are respectively the local density, local velocity and local temperature of the jet particles after the last iteration update, V is the local unit volume where the jet particles are located, and A is the headwind area of ​​the unit where the jet particles are located.

[0131] In one embodiment of the present invention, in order to reduce the amount of calculation and improve the calculation efficiency, a particle cluster formed by a plurality of flame-jet particles may be determined as a whole of flame-jet particles, and the above step 106 may be performed using the particle cluster.

[0132] It should be noted that when the jet particles are updated, the number of the jet particles has a certain influence on the update result. When the number of the jet particles is too small, it is difficult to characterize the complete jet state. When the number of the jet particles increases, the fineness of the flow field that can be characterized increases, and the amount of calculation will also increase accordingly. In the embodiment of the present invention, a number of more than 1000 jet particles is selected.

[0133] When the flame state of each calculation area at a certain moment needs to be output, the number of flame particles in each calculation area at that moment can be calculated, and the flame state in the calculation area can be obtained based on the state and number of flame particles in the calculation area at that moment.

[0134] Please refer to Figure 2 to Figure 5 , respectively, are the corresponding flame states at a certain moment. Among them, Figure 2 , Figure 3 are the speed states in the X and Y directions respectively, Figure 4 , Figure 5 They are Mach number (density or pressure) state and temperature state respectively.

[0135] like Figure 6 , Figure 7 As shown, an embodiment of the present invention provides a device for estimating interstage separation load and jet flame state. The device embodiment can be implemented by software, or by hardware or a combination of software and hardware. From the hardware level, Figure 6 As shown, it is a hardware architecture diagram of a computing device where a device for estimating interstage separation load and jet flame state provided by an embodiment of the present invention is located, except Figure 6 In addition to the processor, memory, network interface, and non-volatile memory shown in the figure, the computing device in which the device is located in the embodiment may also generally include other hardware, such as a forwarding chip responsible for processing messages, etc. Taking software implementation as an example, Figure 7 As shown, as a device in a logical sense, the CPU of the computing device in which it is located reads the corresponding computer program in the non-volatile memory into the memory and runs it. This embodiment provides a device for estimating the interstage separation load and the flame state, including:

[0136] A load calculation unit 701 is used to calculate the upper stage separation load and the lower stage separation load during the interstage separation process based on the separation condition of the aircraft; the separation condition includes at least one of an aerodynamic parameter, a mass parameter and a separation engine operating parameter;

[0137] A distance calculation unit 702, configured to calculate a relative distance between the upper stage and the lower stage that varies with time during the interstage separation process according to the upper stage separation load and the lower stage separation load;

[0138] A calculation region determination unit 703, configured to determine a calculation region of a transient flow field of a jet flame according to the separation condition and the relative distance;

[0139] The flame state determination unit 704 is used to determine the position change and state change of the flame particles in each calculation area, and determine the flame state changing with time in each calculation area according to the position change and state change of the flame particles in each calculation area.

[0140] In one embodiment of the present invention, the load calculation unit 701 is specifically used to: divide the interstage separation process into a first separation stage, a second separation stage and a third separation stage in chronological order based on the variation law of the separation load, and respectively calculate the upper stage separation load and the lower stage separation load that vary with time in each separation stage; the first separation stage is a stage in which the inflow gas of the interstage section is greater than the outflow gas, the second separation stage is a stage in which the outflow gas of the interstage section is greater than the inflow gas, and the third separation stage is a stage in which the gas flow directly impacts the front end face of the lower stage;

[0141] The distance calculation unit 702 is specifically used to calculate the relative distance between the upper stage and the lower stage in each separation stage according to the upper stage separation load and the lower stage separation load that change with time in each separation stage using the dynamic equation.

[0142] In one embodiment of the present invention, when the load calculation unit 701 calculates the upper stage separation load and the lower stage separation load that vary with time in each separation stage, the steps specifically include:

[0143] The upper stage separation load and the lower stage separation load varying with time in the first separation stage and the second separation stage are respectively:

[0144]

[0145]

[0146]

[0147] The upper stage separation load and the lower stage separation load that vary with time in the third separation stage are respectively:

[0148] f 1 =F T

[0149]

[0150] Among them, f 1 、f 2are the upper stage separation load and the lower stage separation load, respectively, D is the separation surface diameter, p is the pressure of the first separation stage and the second separation stage, m 0 is the initial gas mass, is the gas flow rate of the upper stage that changes with time, C is the intermediate parameter, s(t) is the separation distance that changes with time, V s is the initial volume of the interstage, k is the gas adiabatic index, R is the gas constant, T 0 is the initial temperature, F T is the thrust of the upper stage engine, p(s) is the jet impact pressure with the separation distance transformation;

[0151] In one embodiment of the present invention, when the distance calculation unit 702 uses the kinetic equation to calculate the relative distance between the upper stage and the lower stage in each separation stage over time, the method specifically includes:

[0152]

[0153]

[0154] s=s 1 +s 2

[0155] Where s is the relative distance between the upper stage and the lower stage that changes with time at each separation stage, s 1 、s 2 are the separation distances of the upper and lower stages that vary with time, F 1 、F 2 are the axial aerodynamic forces on the upper stage and lower stage structures under specified flight conditions, m 1 、m 2 are the masses of the upper stage and the lower stage respectively.

[0156] In one embodiment of the present invention, when the flame state determination unit 704 determines the position change and state change of the flame particles in each calculation area, the steps specifically include:

[0157] For each calculation area, the following steps are performed: determining the initial state parameters of the flame particles in the current calculation area, and iteratively updating the position change and state change of the flame particles in the current calculation area every time step according to the initial state parameters and the iterative update time step.

[0158] In one embodiment of the present invention, the state change includes at least one of a speed change, a temperature change, a pressure change, and a density change;

[0159] Iteratively updating the position change of the flame particles in the current calculation area includes:

[0160] The position change of the flame particle after each iteration update is S: S = u(t)·Δt; wherein u(t) is the velocity of the flame particle after the last iteration update, and Δt is the time step;

[0161] Iteratively updating the state change of the flame particles in the current calculation area includes:

[0162] When the state change is a speed change, the speed u(t+Δt) of the flame particles after each iterative update is: u(t+Δt)=u(t)+u′+Δu; wherein u′ is a turbulent speed update, and the turbulent speed update is used to characterize the speed change caused by the turbulent pulsation of the flame; Δu is an unbalanced speed update, and the unbalanced speed update is used to characterize the speed change caused by the inconsistency between the flow parameters of the flame particles and the local flow parameters;

[0163] When the state change is a temperature change, the temperature of the flame particles is updated based on the energy change caused by the change in the velocity of the flame particles after each iterative update by using the energy conservation method;

[0164] When the state change is a pressure change or a density change, the pressure and temperature of the flame particles are updated based on the temperature change of the flame particles after each iterative update.

[0165] In one embodiment of the present invention, the non-equilibrium speed is updated to any one of the following three speed changes or the sum of at least two speed changes: a first speed change caused by the difference between the pressure of the jet flame particles and the local pressure, a second speed change caused by the difference between the speed of the jet flame particles and the local speed, and a third speed change caused by the collision of the jet flame particles with the wall.

[0166] The first speed change Δu 1 for:

[0167]

[0168] Among them, k p is the pressure difference conversion coefficient, ranging from 0 to 1; p p is the pressure of the flame particles, p c is the local pressure, ρ p is the density of the flame particles;

[0169] The second speed change Δu 2 for:

[0170]

[0171] Among them, k uis the speed difference conversion coefficient, ranging from 0 to 1; ρ c is the local density, u p is the velocity of the flame particles, u c is the local speed;

[0172] The third speed change Δu 3 for:

[0173]

[0174]

[0175] Among them, β 1 is the angle between the velocity of the jet particle before collision and the wall, β 2 k is the angle between the velocity of the jet particles after the collision and the wall; a is the collision reflection angle coefficient, ranging from 0.15 to 1.

[0176] In one embodiment of the present invention, the calculation area is: the upper stage interstage, the interstage gap, the lower stage interstage, the upper stage body section, the upper stage empty shell section, the interstage gap outer field section, the lower stage empty shell section, the lower stage body section, the lower stage rear outer field section or the lower stage rear section;

[0177] In one embodiment of the present invention, a particle cluster formed by a number of jet particles is determined as a whole jet particle, and the jet state determination unit is triggered to perform its operation using the particle cluster.

[0178] It is to be understood that the structure illustrated in the embodiment of the present invention does not constitute a specific limitation on an inter-stage separation load and jet flame state prediction device. In other embodiments of the present invention, an inter-stage separation load and jet flame state prediction device may include more or fewer components than shown in the figure, or combine some components, or split some components, or arrange the components differently. The components shown in the figure may be implemented in hardware, software, or a combination of software and hardware.

[0179] The information interaction, execution process and other contents between the modules in the above-mentioned device are based on the same concept as the embodiment of the method of the present invention. For the specific contents, please refer to the description in the embodiment of the method of the present invention, and no further description is given here.

[0180] An embodiment of the present invention further provides a computing device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, a method for estimating an inter-stage separation load and a flame state in any embodiment of the present invention is implemented.

[0181] An embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the processor executes a method for estimating an inter-stage separation load and a flame state in any embodiment of the present invention.

[0182] Specifically, a system or device equipped with a storage medium can be provided, on which software program code that implements the functions of any of the above-mentioned embodiments is stored, and a computer (or CPU or MPU) of the system or device can be enabled to read and execute the program code stored in the storage medium.

[0183] In this case, the program code itself read from the storage medium can realize the function of any one of the above-mentioned embodiments, and thus the program code and the storage medium storing the program code constitute a part of the present invention.

[0184] The storage medium embodiments for providing the program code include a floppy disk, a hard disk, a magneto-optical disk, an optical disk (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), a magnetic tape, a non-volatile memory card, and a ROM. Alternatively, the program code can be downloaded from a server computer by a communication network.

[0185] In addition, it should be clear that the functions of any of the above embodiments can be implemented not only by executing the program code read by the computer, but also by enabling an operating system operating on the computer to complete part or all of the actual operations based on instructions from the program code.

[0186] In addition, it can be understood that the program code read from the storage medium is written to a memory provided in an expansion board inserted into the computer or to a memory provided in an expansion module connected to the computer, and then based on the instructions of the program code, a CPU installed on the expansion board or expansion module is enabled to perform part or all of the actual operations, thereby realizing the functions of any of the above-mentioned embodiments.

[0187] It should be noted that, in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical factors in the process, method, article or device including the elements.

[0188] A person of ordinary skill in the art can understand that all or part of the steps of implementing the above method embodiments can be completed by hardware related to program instructions, and the aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it executes the steps of the above method embodiments; and the aforementioned storage medium includes: ROM, RAM, magnetic disk or optical disk, etc., various media that can store program codes.

[0189] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for estimating interstage separation load and flame state, characterized in that: include: Based on the separation conditions of the aircraft, calculate the upper stage separation load and the lower stage separation load during the interstage separation process; The separation condition includes at least one of an aerodynamic parameter, a mass parameter and a separation engine operating parameter; Calculating a relative distance between the upper stage and the lower stage during the interstage separation process that varies with time according to the upper stage separation load and the lower stage separation load; Determining a calculation area of ​​a transient flow field of a jet flame according to the separation condition and the relative distance; Determine the position change and state change of the flame particles in each calculation area, and determine the flame state that changes with time in each calculation area based on the position change and state change of the flame particles in each calculation area; The calculation of the upper stage separation load and the lower stage separation load in the interstage separation process based on the separation condition of the aircraft includes: dividing the interstage separation process into a first separation stage, a second separation stage and a third separation stage in chronological order based on the variation law of the separation load, and respectively calculating the upper stage separation load and the lower stage separation load that vary with time in each separation stage; the first separation stage is a stage in which the inflowing gas of the interstage section is greater than the outflowing gas, the second separation stage is a stage in which the outflowing gas of the interstage section is greater than the inflowing gas, and the third separation stage is a stage in which the gas flow directly impacts the front end face of the lower stage; The step of calculating the relative distance between the upper stage and the lower stage during the interstage separation process according to the upper stage separation load and the lower stage separation load, comprises: calculating the relative distance between the upper stage and the lower stage during each separation stage according to the upper stage separation load and the lower stage separation load which change with time according to each separation stage by using a dynamic equation; The upper stage separation load and the lower stage separation load varying with time in the first separation stage and the second separation stage are respectively: The upper stage separation load and the lower stage separation load that vary with time in the third separation stage are respectively: f1=F T Wherein, f1 and f2 are the upper stage separation load and the lower stage separation load respectively, D is the separation surface diameter, p is the pressure of the first separation stage and the second separation stage, m0 is the initial gas mass, is the gas flow rate of the upper stage that changes with time, C is the intermediate parameter, s(t) is the separation distance that changes with time, V s is the initial volume of the interstage, k is the gas adiabatic index, R is the gas constant, T0 is the initial temperature, F T is the thrust of the upper stage engine, p(s) is the jet impact pressure with the separation distance transformation; The method of using the kinetic equation to calculate the relative distance between the upper stage and the lower stage in each separation stage over time includes: s=s1+s2 Wherein, s is the relative distance between the upper stage and the lower stage changing with time in each separation stage, s1 and s2 are the separation distances of the upper stage and the lower stage changing with time, F1 and F2 are the axial aerodynamic forces exerted on the external structures of the upper stage and the lower stage under specified flight conditions, m1 and m2 are the masses of the upper stage and the lower stage respectively.

2. The method according to claim 1, characterized in that Determining the position change and state change of the flame particles in each calculation area includes: For each calculation area, the following steps are performed: determining the initial state parameters of the flame particles in the current calculation area, and iteratively updating the position change and state change of the flame particles in the current calculation area every time step according to the initial state parameters and the iterative update time step.

3. The method according to claim 2, characterized in that The state change includes at least one of a speed change, a temperature change, a pressure change, and a density change; Iteratively updating the position change of the flame particles in the current calculation area includes: The position change of the flame particle after each iteration update is S: S = u(t)·Δt; wherein u(t) is the velocity of the flame particle after the last iteration update, and Δt is the time step; Iteratively updating the state change of the flame particles in the current calculation area includes: When the state change is a speed change, the speed u(t+Δt) of the flame particles after each iterative update is: u(t+Δt)=u(t)+u′+Δu; wherein u′ is a turbulent speed update, and the turbulent speed update is used to characterize the speed change caused by the turbulent pulsation of the flame; Δu is an unbalanced speed update, and the unbalanced speed update is used to characterize the speed change caused by the inconsistency between the flow parameters of the flame particles and the local flow parameters; When the state change is a temperature change, the temperature of the flame particles is updated based on the energy change caused by the change in the velocity of the flame particles after each iterative update by using the energy conservation method; When the state change is a pressure change or a density change, the pressure and density of the flame particles are updated based on the temperature change of the flame particles after each iterative update.

4. The method according to claim 3, characterized in that The non-equilibrium speed is updated to any one of the following three speed changes or the sum of at least two speed changes: a first speed change caused by the difference between the pressure of the jet flame particles and the local pressure, a second speed change caused by the difference between the speed of the jet flame particles and the local speed, and a third speed change caused by the collision of the jet flame particles with the wall. The first speed variation Δu1 is: Among them, k p is the pressure difference conversion coefficient, ranging from 0 to 1; p p is the pressure of the flame particles, p c is the local pressure, ρ p is the density of the flame particles; The second speed variation Δu2 is: Among them, k u is the speed difference conversion coefficient, ranging from 0 to 1; ρ c is the local density, u p is the velocity of the flame particles, u c is the local speed; The third speed variation Δu3 is: Where β1 is the angle between the velocity of the jet flame particle and the wall before the collision, and β2 is the angle between the velocity of the jet flame particle and the wall after the collision; k a is the collision reflection angle coefficient, ranging from 0.15 to 1.

5. The method according to any one of claims 1 to 4, characterized in that: The calculation area is: the upper stage gap, the interstage gap, the lower stage gap, the upper stage body section, the upper stage empty shell section, the interstage gap outer field section, the lower stage empty shell section, the lower stage body section, the lower stage rear outer field section or the lower stage rear section; and / or, A particle cluster formed by a plurality of jet particles is determined as a whole jet particle, and the particle cluster is used to perform the determination of the position change and state change of the jet particles in each calculation area.

6. A device for estimating interstage separation load and flame state, characterized in that: include: A load calculation unit, used to calculate the upper stage separation load and the lower stage separation load during the interstage separation process based on the separation conditions of the aircraft; The separation condition includes at least one of an aerodynamic parameter, a mass parameter and a separation engine operating parameter; a distance calculation unit, for calculating a relative distance between the upper stage and the lower stage that varies with time during the interstage separation process according to the upper stage separation load and the lower stage separation load; A calculation region determination unit, used for determining a calculation region of a transient flow field of a jet flame according to the separation condition and the relative distance; A flame state determination unit, used to determine the position change and state change of the flame particles in each calculation area, and determine the flame state changing with time in each calculation area according to the position change and state change of the flame particles in each calculation area; The load calculation unit is specifically used to: divide the interstage separation process into a first separation stage, a second separation stage and a third separation stage in chronological order based on the variation law of the separation load, and respectively calculate the upper stage separation load and the lower stage separation load that vary with time in each separation stage; the first separation stage is a stage in which the inflow gas of the interstage section is greater than the outflow gas, the second separation stage is a stage in which the outflow gas of the interstage section is greater than the inflow gas, and the third separation stage is a stage in which the gas flow directly impacts the front end face of the lower stage; The distance calculation unit is specifically used to: calculate the relative distance between the upper stage and the lower stage that varies with time in each separation stage using a dynamic equation according to the upper stage separation load and the lower stage separation load that vary with time in each separation stage; The upper stage separation load and the lower stage separation load varying with time in the first separation stage and the second separation stage are respectively: The upper stage separation load and the lower stage separation load that vary with time in the third separation stage are respectively: f1=F T Wherein, f1 and f2 are the upper stage separation load and the lower stage separation load respectively, D is the separation surface diameter, p is the pressure of the first separation stage and the second separation stage, m0 is the initial gas mass, is the gas flow rate of the upper stage that changes with time, C is the intermediate parameter, s(t) is the separation distance that changes with time, V s is the initial volume of the interstage, k is the gas adiabatic index, R is the gas constant, T0 is the initial temperature, F T is the thrust of the upper stage engine, p(s) is the jet impact pressure with the separation distance transformation; When the distance calculation unit performs the calculation of the relative distance between the upper stage and the lower stage changing with time in each separation stage by using the kinetic equation, the method specifically includes: s=s1+s2 Wherein, s is the relative distance between the upper stage and the lower stage changing with time in each separation stage, s1 and s2 are the separation distances of the upper stage and the lower stage changing with time, F1 and F2 are the axial aerodynamic forces exerted on the external structures of the upper stage and the lower stage under specified flight conditions, m1 and m2 are the masses of the upper stage and the lower stage respectively.

7. The device according to claim 6, characterized in that When the flame state determination unit determines the position change and state change of the flame particles in each calculation area, the method specifically includes: For each calculation area, the following steps are performed: determining the initial state parameters of the flame particles in the current calculation area, and iteratively updating the position change and state change of the flame particles in the current calculation area every time step according to the initial state parameters and the iterative update time step.

8. The device according to claim 7, characterized in that The state change includes at least one of a speed change, a temperature change, a pressure change, and a density change; Iteratively updating the position change of the flame particles in the current calculation area includes: The position change of the flame particle after each iteration update is S: S = u(t)·Δt; wherein u(t) is the velocity of the flame particle after the last iteration update, and Δt is the time step; Iteratively updating the state change of the flame particles in the current calculation area includes: When the state change is a speed change, the speed u(t+Δt) of the flame particles after each iterative update is: u(t+Δt)=u(t)+u′+Δu; wherein u′ is a turbulent speed update, and the turbulent speed update is used to characterize the speed change caused by the turbulent pulsation of the flame; Δu is an unbalanced speed update, and the unbalanced speed update is used to characterize the speed change caused by the inconsistency between the flow parameters of the flame particles and the local flow parameters; When the state change is a temperature change, the temperature of the flame particles is updated based on the energy change caused by the change in the velocity of the flame particles after each iterative update by using the energy conservation method; When the state change is a pressure change or a density change, the pressure and temperature of the flame particles are updated based on the temperature change of the flame particles after each iterative update.

9. The device according to claim 8, characterized in that The non-equilibrium speed is updated to any one of the following three speed changes or the sum of at least two speed changes: a first speed change caused by the difference between the pressure of the jet flame particles and the local pressure, a second speed change caused by the difference between the speed of the jet flame particles and the local speed, and a third speed change caused by the collision of the jet flame particles with the wall. The first speed variation Δu1 is: Among them, k p is the pressure difference conversion coefficient, ranging from 0 to 1; p p is the pressure of the flame particles, p c is the local pressure, ρ p is the density of the flame particles; The second speed variation Δu2 is: Among them, k u is the speed difference conversion coefficient, ranging from 0 to 1; ρ c is the local density, u p is the velocity of the flame particles, u c is the local speed; The third speed variation Δu3 is: Where β1 is the angle between the velocity of the jet flame particle and the wall before the collision, and β2 is the angle between the velocity of the jet flame particle and the wall after the collision; k a is the collision reflection angle coefficient, ranging from 0.15 to 1.

10. The device according to any one of claims 6 to 9, characterized in that: The calculation area is: the upper stage gap, the interstage gap, the lower stage gap, the upper stage body section, the upper stage empty shell section, the interstage gap outer field section, the lower stage empty shell section, the lower stage body section, the lower stage rear outer field section or the lower stage rear section; and / or, A particle cluster formed by a plurality of jet particles is determined as a whole jet particle, and the jet state determination unit is triggered to perform its operation by using the particle cluster.

11. A computing device, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method according to any one of claims 1 to 5 is implemented.

12. A computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to execute the method according to any one of claims 1 to 5.

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