Trajectory Generation Method, System and Equipment for Variable-Inclination Spiral Grooves Used in Thrust Chambers

Abstract

The present invention discloses a method, system and device for generating the trajectory of a variable-inclination spiral groove used in a thrust chamber, relating to the technical field of thrust chamber spiral groove design. The method includes: determining an equation set for describing a variable-inclination spiral line on a revolving body generated according to any generatrix; calculating the curve trajectory of the variable-inclination spiral groove based on the equation set and the values of a plurality of design parameters of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber, so as to complete the design of the variable-inclination spiral groove. The present invention can complete the design of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber in a short time, with high design efficiency and high accuracy.

Description

Background Art

[0002] Regenerative cooling is one of the main cooling technologies currently used in thrust chambers. By milling grooves between the inner and outer walls of the thrust chamber to form cooling channels, fuel or oxidizer or both flow through the cooling channels simultaneously to cool the inner wall of the thrust chamber. After absorbing heat, the propellant flows out of the cooling channels and then re-enters the interior of the thrust chamber to participate in combustion, thus achieving heat regeneration.

[0003] As Figure 1 and Figure 2 shown, according to the form of the cooling channels, they can be divided into straight grooves and spiral grooves. The straight groove channels are such that the cooling channels do not change in the circumferential angle along the generatrix of the thrust chamber. The spiral groove channels are such that the cooling channels change in the circumferential angle along the generatrix of the thrust chamber simultaneously. Compared with the straight grooves, due to the presence of a spiral inclination angle, the spiral groove channels have a larger heat transfer area on the same axial length, enabling the coolant to exchange heat with the thrust chamber more fully, resulting in better cooling effect. Moreover, by adjusting the magnitude of the spiral inclination angle at different axial positions, the heat transfer area of the coolant at local positions can be controlled. Therefore, the heat transfer amount at local positions can be adjusted according to the magnitude of the heat flux density at different positions on the inner wall of the thrust chamber, making the cooling efficiency higher.

[0004] However, since the generatrix of the thrust chamber is a contraction-expansion nozzle with a complex profile, it is difficult to determine the spiral groove generatrix on the complex-profile of the surface of revolution, especially for variable-inclination spiral grooves where the inclination angle also changes with different axial positions, making the spiral groove line even more difficult to design. Therefore, currently, spiral groove channels are less used in thrust chambers, or only equal-inclination spiral grooves are used on the cylindrical section with a simple profile. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a method, system and device for generating the trajectory of a variable-inclination spiral groove used in a thrust chamber in view of the deficiencies of the prior art, specifically as follows:

[0006] 1) In the first aspect, the present invention provides a method for generating the trajectory of a variable-inclination spiral groove used in a thrust chamber, and the specific technical solution is as follows:

[0007] Determine the system of equations for describing the variable-inclination spiral line on the surface of revolution generated according to any generatrix;

[0008] According to the system of equations and the values of multiple design parameters of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber, calculate the curve trajectory of the variable-inclination spiral groove to complete the design of the variable-inclination spiral groove.

[0009] The beneficial effects of the method for generating the trajectory of a variable-inclination spiral groove used in a thrust chamber provided by the present invention are as follows:

[0010] It can complete the design of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber in a short time, with high design efficiency and high precision.

[0011] On the basis of the above solution, the trajectory generation method of the variable-inclination spiral groove used in a thrust chamber of the present invention can also be improved as follows.

[0012] Further, the system of equations includes a first formula, a second formula, and a third formula. The first formula is: The second formula is: The third formula is: x represents the X-axis coordinate value in the preset three-dimensional coordinate system, y represents the Y-axis coordinate value in the preset three-dimensional coordinate system, z represents the Z-axis coordinate value in the preset three-dimensional coordinate system. The Z-axis of the preset three-dimensional coordinate system is coaxial with the rotation center axis of the rotating body. r(z) represents a function of r with respect to z. Substitute z into this function to calculate the corresponding r. r represents the radius of the rotating body in the XOY plane of the preset three-dimensional coordinate system. is a constant term. is an intermediate variable. β(z) represents a function of β with respect to z. Substitute z into this function to calculate the corresponding β. β is the inclination angle of the variable-inclination spiral line.

[0013] Further, according to the system of equations and the values of multiple design parameters of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber, the curve trajectory of the variable-inclination spiral groove is calculated, including:

[0014] Discretize the target line segment. Combine the third formula and the values of multiple design parameters of the variable-inclination spiral groove to calculate the corresponding value for each discrete point;

[0015] According to the corresponding value for each discrete point, the z value of each discrete point, and the first formula and the second formula, calculate the x value and y value corresponding to each z value, and obtain multiple position coordinate points on the curve trajectory of the variable-inclination spiral groove;

[0016] Among them, the target line segment refers to the line segment between the combustion chamber inlet and the nozzle outlet of the thrust chamber and on the axis of the thrust chamber. Any z value and the corresponding x value and y value form a position coordinate point.

[0017] Further, between the combustion chamber inlet and the nozzle outlet in the thrust chamber, there are successively arranged a cylindrical section, a converging section, a throat, and a diverging section. The target line segments include: a first partial line segment, a second partial line segment, a third partial line segment, and a fourth partial line segment. The first partial line segment refers to the line segment of the cylindrical section on the axis of the thrust chamber. The second partial line segment refers to the line segment of the converging section on the axis of the thrust chamber. The third partial line segment refers to the line segment of the throat on the axis of the thrust chamber. The fourth partial line segment refers to the line segment of the diverging section on the axis of the thrust chamber.

[0018] Discretizing the target line segments includes:

[0019] Dividing the lengths of the first partial line segment, the second partial line segment, and the third partial line segment to obtain a plurality of discrete points;

[0020] When designing the diverging section using the maximum thrust principle, the fourth partial line segment consists of a plurality of initial discrete points. The initial discrete points are all used as the discrete points obtained by dividing the length of the fourth partial line segment, or all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain a plurality of discrete points.

[0021] 2) In a second aspect, the present invention also provides a trajectory generation system for a variable-inclination spiral groove used in a thrust chamber. The specific technical solution is as follows:

[0022] It includes an equation system determination module and a curve trajectory acquisition module;

[0023] The equation system determination module is used to: determine the equation system for describing the variable-inclination spiral on the surface of the solid of revolution generated according to any generatrix;

[0024] The curve trajectory acquisition module is used to: calculate the curve trajectory of the variable-inclination spiral groove according to the equation system and the values of a plurality of design parameters of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber, and complete the design of the variable-inclination spiral groove.

[0025] On the basis of the above solution, the trajectory generation system for a variable-inclination spiral groove used in a thrust chamber of the present invention can also be improved as follows.

[0026] Further, the equation system includes a first formula, a second formula, and a third formula. The first formula is: The second formula is: The third formula is: x represents: the X-axis coordinate value in a preset three-dimensional coordinate system; y represents: the Y-axis coordinate value in the preset three-dimensional coordinate system; z represents: the Z-axis coordinate value in the preset three-dimensional coordinate system. The Z-axis of the preset three-dimensional coordinate system is coaxial with the rotation center axis of the rotating body. r(z) represents: the function of r with respect to z. Substitute z into this function to calculate the corresponding r. r represents: the radius of the rotating body on the XOY plane in the preset three-dimensional coordinate system. is a constant term; is an intermediate variable. β(z) represents: the function of β with respect to z. Substitute z into this function to calculate the corresponding β. β is the inclination angle of the variable-inclination spiral groove.

[0027] Furthermore, the curve trajectory acquisition module is specifically used for:

[0028] Discretize the target line segment, and combine the values of multiple design parameters of the variable-inclination spiral groove with the third formula to calculate the corresponding value for each discrete point;

[0029] According to the corresponding value for each discrete point, the z value of each discrete point, and the first formula and the second formula, calculate the corresponding x value and y value for each z value, and obtain multiple position coordinate points on the curve trajectory of the variable-inclination spiral groove;

[0030] Among them, the target line segment refers to: the line segment between the combustion chamber inlet and the nozzle outlet of the thrust chamber and on the axis of the thrust chamber. Any z value and the corresponding x value and y value form a position coordinate point.

[0031] Furthermore, from the combustion chamber inlet to the nozzle outlet in the thrust chamber, there are successively arranged a cylindrical section, a converging section, a throat, and a diverging section. The target line segment includes: a first local line segment, a second local line segment, a third local line segment, and a fourth local line segment; the first local line segment refers to: the line segment of the cylindrical section on the axis of the thrust chamber; the second local line segment refers to: the line segment of the converging section on the axis of the thrust chamber; the third local line segment refers to: the line segment of the throat on the axis of the thrust chamber; the fourth local line segment refers to: the line segment of the diverging section on the axis of the thrust chamber;

[0032] The curve trajectory acquisition module is also specifically used for:

[0033] Divide the first local line segment, the second local line segment, and the third local line segment into lengths to obtain multiple discrete points;

[0034] When designing the diverging section using the maximum thrust principle, the fourth local line segment consists of multiple initial discrete points. Take all the initial discrete points as the discrete points obtained by dividing the length of the fourth local line segment, or fit all the initial discrete points, and then discretize the fitted line segment to obtain multiple discrete points.

[0035] 3) In a third aspect, the present invention further provides an electronic device, which includes a processor coupled to a memory. At least one computer program is stored in the memory and is loaded and executed by the processor to enable the electronic device to implement the trajectory generation method of the variable-inclination spiral groove used in any one of the above-mentioned thrust chambers.

[0036] 4) In a fourth aspect, the present invention further provides a computer-readable storage medium in which at least one computer program is stored. The at least one computer program is loaded and executed by a processor to enable a computer to implement the trajectory generation method of the variable-inclination spiral groove used in any one of the above-mentioned thrust chambers.

[0037] It should be noted that for the beneficial effects achieved by the technical solutions of the second to fourth aspects of the present invention and their corresponding possible implementation manners, reference may be made to the technical effects of the first aspect and its corresponding possible implementation manners described above, which will not be elaborated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Other features, objects, and advantages of the present invention will become more apparent by reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0039] Figure 1 It is a schematic diagram of the spiral groove of the thrust chamber;

[0040] Figure 2 It is a schematic diagram of the straight groove of the thrust chamber;

[0041] Figure 3 It is a schematic flow chart of the trajectory generation method of the variable-inclination spiral groove used in a thrust chamber according to an embodiment of the present invention;

[0042] Figure 4 It is a schematic structural diagram of a trajectory generation system of the variable-inclination spiral groove used in a thrust chamber according to an embodiment of the present invention;

[0043] Figure 5 It is a schematic structural diagram of an electronic device according to an embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0045] As Figure 3 shown, a trajectory generation method of a variable-inclination spiral groove used in a thrust chamber according to an embodiment of the present invention includes the following steps:

[0046] S1. Determine the equations for describing the variable-inclination spiral on the surface of revolution generated according to any generatrix;

[0047] S2. Calculate the curve trajectory of the variable-inclination spiral groove based on the values of multiple design parameters of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber, and complete the design of the variable-inclination spiral groove.

[0048] Optionally, in the above technical solution, the system of equations includes a first formula, a second formula, and a third formula. The first formula is: The second formula is: The third formula is: x represents the X-axis coordinate value in the preset three-dimensional coordinate system, y represents the Y-axis coordinate value in the preset three-dimensional coordinate system, z represents the Z-axis coordinate value in the preset three-dimensional coordinate system. The Z-axis of the preset three-dimensional coordinate system is coaxial with the rotation center axis of the rotating body. r(z) represents a function of r with respect to z. Substitute z into this function to calculate the corresponding r. r represents the radius of the rotating body on the XOY plane in the preset three-dimensional coordinate system. is a constant term. is an intermediate variable. β(z) represents a function of β with respect to z. Substitute z into this function to calculate the corresponding β. β is the inclination angle of the variable-inclination spiral line.

[0049] Among them, the functional expression of r(z) can be obtained through mathematical derivation according to the position of the generatrix in the preset three-dimensional coordinate system, and the functional expression of β(z) can be given by the designer and can be set according to the actual situation.

[0050] Optionally, in S2, calculating the curve trajectory of the variable-inclination spiral groove based on the values of multiple design parameters of the variable-inclination spiral groove between the inner and outer walls of the thrust chamber includes:

[0051] S20. Discretize the target line segment, and calculate the corresponding value for each discrete point in combination with the third formula and the values of multiple design parameters of the variable-inclination spiral groove;

[0052] S21. Calculate the x value and y value corresponding to each z value based on the corresponding value for each discrete point, the z value of each discrete point, and the first formula and the second formula, to obtain multiple position coordinate points on the curve trajectory of the variable-inclination spiral groove;

[0053] Among them, the target line segment refers to the line segment between the combustion chamber inlet and the nozzle outlet of the thrust chamber and on the axis of the thrust chamber. Any z value and the corresponding x value and y value form a position coordinate point.

[0054] Optionally, in the above technical solution, the thrust chamber includes, in sequence from the combustion chamber inlet to the nozzle outlet, a cylindrical section, a convergent section, a throat, and a divergent section. The target line segment includes: a first partial line segment, a second partial line segment, a third partial line segment, and a fourth partial line segment; the first partial line segment refers to the line segment of the cylindrical section on the axis of the thrust chamber, the second partial line segment refers to the line segment of the convergent section on the axis of the thrust chamber, the third partial line segment refers to the line segment of the throat on the axis of the thrust chamber; the fourth partial line segment refers to the line segment of the divergent section on the axis of the thrust chamber;

[0055] In S20, discretizing the target line segment includes:

[0056] S201. Divide the lengths of the first partial line segment, the second partial line segment, and the third partial line segment to obtain a plurality of discrete points;

[0057] S202. When designing the divergent section using the maximum thrust principle, the fourth partial line segment consists of a plurality of initial discrete points. Take all the initial discrete points as the discrete points obtained by dividing the length of the fourth partial line segment, or fit all the initial discrete points and then discretize the fitted line segment to obtain a plurality of discrete points.

[0058] The present invention is illustrated by the following embodiments, including:

[0059] S101. Determine the equations for describing the variable-angle helical line on the surface of the solid of revolution generated according to any generatrix. The equations include a first formula, a second formula, and a third formula. The first formula is: The second formula is: The third formula is: x represents the X-axis coordinate value in the preset three-dimensional coordinate system, y represents the Y-axis coordinate value in the preset three-dimensional coordinate system, z represents the Z-axis coordinate value in the preset three-dimensional coordinate system. The Z-axis of the preset three-dimensional coordinate system is coaxial with the rotation center axis of the solid of revolution. r(z) represents a function of r with respect to z. Substitute z into this function to calculate the corresponding r. r represents the radius of the solid of revolution in the XOY plane of the preset three-dimensional coordinate system. is a constant term, is an intermediate variable. β(z) represents a function of β with respect to z. Substitute z into this function to calculate the corresponding β. β is the inclination angle of the variable-angle helical line.

[0060] Since the throat of the thrust chamber is a key position when designing the thrust chamber, a preset three-dimensional coordinate system is established with the center of the throat as the origin. The axis of the thrust chamber is coaxial with the Z-axis of the preset three-dimensional coordinate system, and the nozzle outlet direction is the positive direction of the Z-axis of the preset three-dimensional coordinate system.

[0061] S102. Determine the curve trajectory of the variable-inclination spiral groove:

[0062] Six parameters (x, y, z, r, β, and ) and three equations (the first formula, the second formula, and the third formula) are involved in S101. Therefore, three parameters need to be determined to solve the system of equations. Among them, both z and r are profile parameters of the thrust chamber. When designing the variable-inclination spiral groove of the thrust chamber, the value range of z of the thrust chamber, the functional expression of r(z), and the functional expression of β(z) are known. β is a parameter that affects the heat transfer area of different regions of the variable-inclination spiral groove and is given by the designer. By the given value range of z, the functional expression of r(z), and the functional expression of β(z), solve for x, y, and , and the specific calculation process is as follows:

[0063] S1020. Parameter discretization:

[0064] In the system of equations, the third formula involves the indefinite integral of a function. Since the profile of the thrust chamber is relatively complex, it is difficult to obtain the curve trajectory of the variable-inclination spiral groove if directly solved. Therefore, it is necessary to discretize the target line segment (i.e., the line segment between the combustion chamber inlet and the nozzle outlet of the thrust chamber and on the axis of the thrust chamber), transforming the problem from the process of solving a continuous equation to the process of solving the function values of several discrete points. The specific discretization process is as follows:

[0065] Between the combustion chamber inlet and the nozzle outlet in the thrust chamber, there are successively arranged a cylindrical section, a convergent section, a throat, and a divergent section. The target line segment includes: the first local line segment, the second local line segment, the third local line segment, and the fourth local line segment; the first local line segment refers to: the line segment of the cylindrical section on the axis of the thrust chamber, the second local line segment refers to: the line segment of the convergent section on the axis of the thrust chamber, the third local line segment refers to: the line segment of the throat on the axis of the thrust chamber; the fourth local line segment refers to: the line segment of the divergent section on the axis of the thrust chamber;

[0066] The specific process of discretizing the target line segment is as follows:

[0067] ① Divide the lengths of the first local line segment, the second local line segment, and the third local line segment to obtain multiple discrete points. Specifically:

[0068] The first local line segment, the second local line segment, and the third local line segment can be divided into equal lengths, and the length of each divided segment can also be set according to the actual situation.

[0069] ② When designing the thrust chamber, in order to improve the nozzle efficiency, the profile of the divergent section of the thrust chamber is usually a special profile formed by several discrete points. When designing the divergent section using the maximum thrust principle, the fourth local line segment consists of multiple initial discrete points. All the initial discrete points are regarded as the discrete points obtained by dividing the length of the fourth local line segment, or all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain multiple discrete points. Among them, the fitted line segment is actually the fourth local line segment. This process is equivalent to fitting all the discrete initial discrete points into a continuous fourth local line segment, and then discretizing the continuous fourth local line segment to obtain multiple discrete points. The continuous fourth local line segment can be divided into equal lengths, or discretized according to the actual situation.

[0070] After discretizing the target line segment, the target line segment is divided into m parts, and a total of m + 1 discrete points are obtained. The first discrete point is the point on the axis of the combustion chamber inlet of the thrust chamber, and the z value of the first discrete point is z 0 , the (m + 1)-th discrete point is the point on the axis of the nozzle outlet of the thrust chamber, and the z value of the (m + 1)-th discrete point is z m . The value of m determines the fitting accuracy between the curve trajectory of the variable inclination spiral groove obtained from the discrete points and the profile of the thrust chamber. The larger m is, the higher the fitting accuracy. Since the curvature change in the upstream and downstream regions of the throat of the thrust chamber is relatively large, more discrete points can be added in this region to improve the fitting accuracy.

[0071] S1021. Since both r and β are functions of z, after obtaining the z value of each discrete point in S1020, the corresponding r value and β value can be calculated. Specifically, according to the z value of the first discrete point, namely z 0 , r 0 and β 0 are calculated. According to the z value of the second discrete point, namely z 1 , r 1 and β 1 are calculated, until according to the z value of the (m + 1)-th discrete point, namely z m , r m and β m are calculated.

[0072] S1022. Calculate the value of each discrete point using the third formula, and then calculate the x value and y value corresponding to the z value of each discrete point through the first formula and the second formula. Specifically:

[0073] For any z value, the indefinite integral in the third formula can be transformed into a definite integral. The starting point of the definite integral is the z value at the combustion chamber inlet position, and the ending point of the definite integral is this z value. However, since the integrand is relatively complex and cannot be directly solved, according to the idea of calculus, the calculation interval (between the starting point and the ending point of the definite integral) is discretized into n micro-elements, and then the third formula is converted into the fourth formula, and the fourth formula is:

[0074]

[0075] where i = 1, 2, 3... n, j = 0, 1, 2, 3... m, z j,i represents: the i-th micro-element of z j , z j,i-1 represents: the (i - 1)-th micro-element of z j , is a constant term, determines the coordinate position of the curve trajectory of the variable inclination angle spiral groove at the combustion chamber inlet of the thrust chamber. It can be assigned a value according to specific design requirements for ; when j = 0 and i = 1, z 0 is the z value at the combustion chamber inlet of the thrust chamber. When designing the variable inclination angle spiral groove used in the thrust chamber, z 0 is a constant.

[0076] Through the fourth formula, the value of each discrete point can be calculated, that is Then, according to the first formula and the second formula, the x value and y value corresponding to each value are calculated. Denote the x value corresponding to as x 0 , and denote the x value corresponding to as x 1 , until the x value corresponding to is denoted as x m , and denote the y value corresponding to as y 0 , and denote the y value corresponding to as y 1 , until the y value corresponding to is denoted as y m , thus obtaining multiple position coordinate points on the curve trajectory of the variable inclination angle spiral groove: (x 0 , y 0 , z 0 ), (x 1 , y 1 , z 1 )... (x m , y m , z m), the design of the variable - inclination spiral groove is completed.

[0077] In the above - mentioned embodiments, although the steps are numbered as S1, S2, etc., they are only specific embodiments given by the present invention. Those skilled in the art can adjust the execution order of S1, S2, etc. according to the actual situation, and this is also within the protection scope of the present invention. It can be understood that in some embodiments, it may include some or all of the above - mentioned embodiments.

[0078] Such as Figure 4 As shown, a trajectory generation system 200 of a variable - inclination spiral groove used in a thrust chamber according to an embodiment of the present invention includes an equation - set determination module 201 and a curve - trajectory acquisition module 202;

[0079] The equation - set determination module 201 is configured to: determine an equation set for describing a variable - inclination spiral line on a solid of revolution generated according to any generatrix;

[0080] The curve - trajectory acquisition module 202 is configured to: calculate the curve trajectory of the variable - inclination spiral groove according to the equation set and the values of multiple design parameters of the variable - inclination spiral groove between the inner and outer walls of the thrust chamber, and complete the design of the variable - inclination spiral groove.

[0081] Optionally, in the above - mentioned technical solution, the equation set includes a first formula, a second formula, and a third formula. The first formula is: The second formula is: The third formula is: x represents: the X - axis coordinate value in a preset three - dimensional coordinate system, y represents: the Y - axis coordinate value in a preset three - dimensional coordinate system, z represents: the Z - axis coordinate value in a preset three - dimensional coordinate system. The Z - axis of the preset three - dimensional coordinate system is coaxial with the rotation central axis of the solid of revolution. r(z) represents: a function of r with respect to z. Substitute z into this function to calculate the corresponding r. r represents: the radius of the solid of revolution on the XOY plane of the preset three - dimensional coordinate system, is a constant term, is an intermediate variable, β(z) represents: a function of β with respect to z. Substitute z into this function to calculate the corresponding β. β is the inclination angle of the variable - inclination spiral line.

[0082] Optionally, in the above - mentioned technical solution, the curve - trajectory acquisition module 202 is specifically configured to:

[0083] Discretize the target line segment, and combine the third formula and the values of multiple design parameters of the variable - inclination spiral groove to calculate the corresponding value for each discrete point;

[0084] According to the corresponding Based on the value and the z-value of each discrete point, as well as the first formula and the second formula, the x-value and y-value corresponding to each z-value are calculated to obtain multiple position coordinate points on the curve trajectory of the variable-inclination spiral groove;

[0085] Among them, the target line segment refers to: the line segment between the combustion chamber inlet and the nozzle outlet of the thrust chamber and on the axis of the thrust chamber. Any z-value and the corresponding x-value and y-value form a position coordinate point.

[0086] Optionally, in the above technical solution, from the combustion chamber inlet to the nozzle outlet in the thrust chamber, there are successively arranged a cylindrical section, a convergent section, a throat, and a divergent section. The target line segment includes: a first local line segment, a second local line segment, a third local line segment, and a fourth local line segment; the first local line segment refers to: the line segment of the cylindrical section on the axis of the thrust chamber, the second local line segment refers to: the line segment of the convergent section on the axis of the thrust chamber, the third local line segment refers to: the line segment of the throat on the axis of the thrust chamber; the fourth local line segment refers to: the line segment of the divergent section on the axis of the thrust chamber; the curve trajectory acquisition module 202 is further specifically used for:

[0087] Divide the first local line segment, the second local line segment, and the third local line segment into lengths to obtain multiple discrete points;

[0088] When designing the divergent section using the maximum thrust principle, the fourth local line segment is composed of multiple initial discrete points. The initial discrete points are all used as the discrete points obtained by dividing the length of the fourth local line segment, or all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain multiple discrete points.

[0089] It should be noted that the beneficial effects of the variable-inclination spiral groove trajectory generation system 200 for a thrust chamber provided in the above embodiments are the same as those of the variable-inclination spiral groove trajectory generation method for a thrust chamber provided above, and will not be elaborated here. In addition, when the system provided in the above embodiments realizes its functions, only the above-mentioned division of each functional module is used as an example. In practical applications, the above functions can be allocated to different functional modules according to needs, that is, the system is divided into different functional modules according to the actual situation to complete all or part of the functions described above. In addition, the system provided in the above embodiments and the method embodiments belong to the same concept, and the specific implementation process is detailed in the method embodiments and will not be elaborated here.

[0090] Such as Figure 5As shown, an electronic device 300 according to an embodiment of the present invention. The electronic device 300 includes a processor 320, and the processor 320 is coupled to a memory 310. At least one computer program 330 is stored in the memory 310. The at least one computer program 330 is loaded and executed by the processor 320 so that the electronic device 300 implements the trajectory generation method of the variable-inclination spiral groove used in any of the above-mentioned thrust chambers. Specifically:

[0091] The electronic device 300 may vary significantly due to configuration or performance differences. It may include one or more processors 320 (Central Processing Units, CPUs) and one or more memories 310. Among them, at least one computer program 330 is stored in the one or more memories 310. The at least one computer program 330 is loaded and executed by the one or more processors 320 so that the electronic device 300 implements the trajectory generation method of the variable-inclination spiral groove used in any of the above-mentioned embodiments of the thrust chamber. Of course, the electronic device 300 may also have components such as a wired or wireless network interface, a keyboard, and an input / output interface for input and output. The electronic device 300 may also include other components for implementing the functions of the device, which will not be elaborated here. The electronic device may specifically be a computer or the like.

[0092] A computer-readable storage medium according to an embodiment of the present invention. At least one computer program is stored in the computer-readable storage medium. The at least one computer program is loaded and executed by a processor so that the computer implements the trajectory generation method of the variable-inclination spiral groove used in any of the above-mentioned thrust chambers.

[0093] Optionally, the computer-readable storage medium may be a read-only memory (ROM), a random access memory (RAM), a compact disc read-only memory (CD-ROM), magnetic tape, floppy disk, and optical data storage device, etc.

[0094] In an exemplary embodiment, a computer program product or a computer program is also provided. The computer program product or the computer program includes computer instructions, and the computer instructions are stored in a computer-readable storage medium. The processor of the electronic device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions so that the electronic device executes the trajectory generation method of the variable-inclination spiral groove used in any of the above-mentioned thrust chambers.

[0095] It should be noted that the terms "first", "second", etc. in the description and claims of this application are used to distinguish similar objects, rather than to limit a specific order or sequence. In appropriate cases, the order of use of similar objects can be interchanged so that the embodiments of this application described herein can be implemented in an order other than the order shown or described.

[0096] Those skilled in the art know that the present invention can be implemented as a system, a method or a computer program product. Therefore, the present invention can be specifically implemented in the following forms, that is: it can be completely hardware, or completely software (including firmware, resident software, microcode, etc.), or a combination of hardware and software, which is generally referred to as "circuit", "module" or "system" herein. In addition, in some embodiments, the present invention can also be implemented in the form of a computer program product in one or more computer-readable media, which contain computer-readable program code.

[0097] Any combination of one or more computer-readable media can be adopted. The computer-readable media can be computer-readable signal media or computer-readable storage media. The computer-readable storage media can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above. More specific examples (non-exhaustive list) of the computer-readable storage media include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present invention, the computer-readable storage media can be any tangible medium that contains or stores a program, and this program can be used by or in combination with an instruction execution system, apparatus, or device.

[0098] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for generating a trajectory of a variable-angle spiral groove used in a thrust chamber, characterized in that: include: Determine the system of equations used to describe the variable inclination helix on a body of revolution generated from any generatrix; According to the equation group and the values ​​of multiple design parameters of the variable-angle spiral groove between the inner and outer walls of the thrust chamber, the curve trajectory of the variable-angle spiral groove is calculated to complete the design of the variable-angle spiral groove; The equation group includes a first formula, a second formula and a third formula, and the first formula is: The second formula is: The third formula is: x represents: the X-axis coordinate value in the preset three-dimensional coordinate system, y represents: the Y-axis coordinate value in the preset three-dimensional coordinate system, z represents: the Z-axis coordinate value in the preset three-dimensional coordinate system, the Z-axis of the preset three-dimensional coordinate system is coaxial with the rotation center axis of the rotating body, r(z) represents: the function of r with respect to z, substitute z into the function to calculate the corresponding r, r represents: the radius of the rotating body on the XOY plane in the preset three-dimensional coordinate system, is a constant term, is an intermediate variable, β(z) represents: the function of β with respect to z, substituting z into the function, the corresponding β is calculated, and β is the inclination angle of the variable inclination helix; According to the equation group and the values ​​of multiple design parameters of the variable-angle spiral groove between the inner and outer walls of the thrust chamber, the curve trajectory of the variable-angle spiral groove is calculated, including: The target line segment is discretized, and the corresponding angle of each discrete point is calculated by combining the third formula and the values ​​of multiple design parameters of the variable inclination spiral groove. value; According to the corresponding The x value and the y value of each discrete point are calculated by using the first formula and the second formula to obtain the x value and the y value corresponding to each z value, and obtain multiple position coordinate points on the curve trajectory of the variable inclination spiral groove; Wherein, the target line segment refers to: a line segment between the combustion chamber inlet of the thrust chamber and the nozzle outlet and on the axis of the thrust chamber, any z value and the x value and y value corresponding to the z value constitute a position coordinate point; For any z value, the indefinite integral in the third formula can be converted into a definite integral. The starting point of the definite integral is the z value at the combustion chamber inlet, and the end point of the definite integral is the z value. The calculation interval is discretized into n infinitesimals, and the third formula is converted into the fourth formula. The fourth formula is: Where i = 1, 2, 3 ... n, j = 0, 1, 2, 3 ... m, z j,i Indicates: z j The ith infinitesimal element of j,i-1 Indicates: z j The i-1th infinitesimal element of is a constant term, The coordinate position of the curve trajectory of the variable inclination angle spiral groove at the entrance of the combustion chamber of the thrust chamber is determined. When j=0 and i=1, z0 is the z value at the entrance of the combustion chamber of the thrust chamber. When the variable inclination angle spiral groove used in the thrust chamber is designed, z0 is a constant. The calculation interval refers to: between the integral starting point and the integral end point of the definite integral; The fourth formula is used to calculate the value of each discrete point. Value Then calculate each according to the first and second formulas The x and y values ​​corresponding to the value will be The corresponding x value is recorded as x0, and The corresponding x value is recorded as x1 until The corresponding x value is denoted as x m ,Will The corresponding y value is recorded as y0, The corresponding y value is recorded as y1 until The corresponding y value is recorded as y m , thus obtaining multiple position coordinate points on the curve trajectory of the variable inclination spiral groove: (x0, y0, z0), (x1, y1, z1)...(x m ,y m ,z m ) to complete the design of the variable inclination spiral groove.

2. The method for generating a trajectory of a variable-angle spiral groove for a thrust chamber according to claim 1, characterized in that: The thrust chamber includes a cylindrical section, a convergent section, a throat section and an expansion section arranged in sequence from the combustion chamber inlet to the nozzle outlet, and the target line segment includes: a first local line segment, a second local line segment, a third local line segment and a fourth local line segment; the first local line segment refers to: a line segment of the cylindrical section on the axis of the thrust chamber, the second local line segment refers to: a line segment of the convergent section on the axis of the thrust chamber, the third local line segment refers to: a line segment of the throat section on the axis of the thrust chamber; the fourth local line segment refers to: a line segment of the expansion section on the axis of the thrust chamber; Discretize the target line segment, including: Divide the first local line segment, the second local line segment and the third local line segment by length to obtain a plurality of discrete points; When the expansion section is designed using the maximum thrust principle, the fourth local line segment is composed of multiple initial discrete points, and the initial discrete points are all used as discrete points obtained by dividing the length of the fourth local line segment, or all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain multiple discrete points.

3. A trajectory generation system for a variable inclination spiral groove used in a thrust chamber, characterized in that: It includes an equation group determination module and a curve trajectory acquisition module; The equation group determination module is used to: determine an equation group for describing a variable inclination angle helix on a rotating body generated according to any generatrix; The curve trajectory acquisition module is used to calculate the curve trajectory of the variable-angle spiral groove according to the equation group and the values ​​of multiple design parameters of the variable-angle spiral groove between the inner and outer walls of the thrust chamber, and complete the design of the variable-angle spiral groove; The equation group includes a first formula, a second formula and a third formula, and the first formula is: The second formula is: The third formula is: x represents: the X-axis coordinate value in the preset three-dimensional coordinate system, y represents: the Y-axis coordinate value in the preset three-dimensional coordinate system, z represents: the Z-axis coordinate value in the preset three-dimensional coordinate system, the Z-axis of the preset three-dimensional coordinate system is coaxial with the rotation center axis of the rotating body, r(z) represents: the function of r with respect to z, substitute z into the function to calculate the corresponding r, r represents: the radius of the rotating body on the XOY plane in the preset three-dimensional coordinate system, is a constant term, is an intermediate variable, β(z) represents: the function of β with respect to z, substituting z into the function, the corresponding β is calculated, and β is the inclination angle of the variable inclination helix; The curve trajectory acquisition module is specifically used for: The target line segment is discretized, and the corresponding angle of each discrete point is calculated by combining the third formula and the values ​​of multiple design parameters of the variable inclination spiral groove. value; According to the corresponding The x value and the y value of each discrete point are calculated by using the first formula and the second formula to obtain the x value and the y value corresponding to each z value, and obtain multiple position coordinate points on the curve trajectory of the variable inclination spiral groove; Wherein, the target line segment refers to: a line segment between the combustion chamber inlet of the thrust chamber and the nozzle outlet and on the axis of the thrust chamber, any z value and the x value and y value corresponding to the z value constitute a position coordinate point; For any z value, the indefinite integral in the third formula can be converted into a definite integral. The starting point of the definite integral is the z value at the combustion chamber inlet, and the end point of the definite integral is the z value. The calculation interval is discretized into n infinitesimals, and the third formula is converted into the fourth formula. The fourth formula is: Where i = 1, 2, 3 ... n, j = 0, 1, 2, 3 ... m, z j,i Indicates: z j The ith infinitesimal element of j,i-1 Indicates: z j The i-1th infinitesimal element of is a constant term, The coordinate position of the curve trajectory of the variable inclination angle spiral groove at the entrance of the combustion chamber of the thrust chamber is determined. When j=0 and i=1, z0 is the z value at the entrance of the combustion chamber of the thrust chamber. When the variable inclination angle spiral groove used in the thrust chamber is designed, z0 is a constant. The calculation interval refers to: between the integral starting point and the integral end point of the definite integral; The fourth formula is used to calculate the value of each discrete point. Value Then calculate each according to the first and second formulas The x and y values ​​corresponding to the value will be The corresponding x value is recorded as x0, and The corresponding x value is recorded as x1 until The corresponding x value is denoted as x m ,Will The corresponding y value is recorded as y0, The corresponding y value is recorded as y1 until The corresponding y value is recorded as y m , thus obtaining multiple position coordinate points on the curve trajectory of the variable inclination spiral groove: (x0, y0, z0), (x1, y1, z1)...(x m ,y m ,z m ) to complete the design of the variable inclination spiral groove.

4. The trajectory generation system of a variable inclination angle spiral groove used in a thrust chamber according to claim 3, characterized in that: The thrust chamber includes a cylindrical section, a convergent section, a throat section and an expansion section arranged in sequence from the combustion chamber inlet to the nozzle outlet, and the target line segment includes: a first local line segment, a second local line segment, a third local line segment and a fourth local line segment; the first local line segment refers to: a line segment of the cylindrical section on the axis of the thrust chamber, the second local line segment refers to: a line segment of the convergent section on the axis of the thrust chamber, the third local line segment refers to: a line segment of the throat section on the axis of the thrust chamber; the fourth local line segment refers to: a line segment of the expansion section on the axis of the thrust chamber; The curve trajectory acquisition module is also specifically used for: Divide the first local line segment, the second local line segment and the third local line segment by length to obtain a plurality of discrete points; When the expansion section is designed using the maximum thrust principle, the fourth local line segment is composed of multiple initial discrete points, and the initial discrete points are all used as discrete points obtained by dividing the length of the fourth local line segment, or all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain multiple discrete points.

5. An electronic device, characterized in that: The electronic device includes a processor, the processor is coupled to a memory, at least one computer program is stored in the memory, and the at least one computer program is loaded and executed by the processor so that the electronic device implements the trajectory generation method of a variable-angle spiral groove used in a thrust chamber as described in any one of claims 1 to 2.

6. A computer-readable storage medium, characterized in that: At least one computer program is stored in the computer-readable storage medium, and the at least one computer program is loaded and executed by the processor to enable the computer to implement the trajectory generation method of the variable-inclination spiral groove used in the thrust chamber as described in any one of claims 1 to 2.

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