Track generation method, system and equipment of variable-dip-angle spiral groove for thrust chamber

Abstract

The invention discloses a track generation method, system and equipment for a variable-dip-angle spiral groove used for a thrust chamber, and relates to the technical field of thrust chamber spiral groove design, and the method comprises the steps: determining an equation set used for describing a variable-dip-angle spiral line on a rotary body generated according to any bus; according to the equation set and the values of the multiple design parameters of the variable-dip-angle spiral groove between the inner wall and the outer wall of the thrust chamber, the curve track of the variable-dip-angle spiral groove is obtained through calculation, and design of the variable-dip-angle spiral groove is completed. According to the method, the variable-dip-angle spiral groove between the inner wall and the outer wall of the thrust chamber can be designed in a short time, the design efficiency is high, and the precision is high.

Description

Background Art

[0002] Regenerative cooling is one of the main cooling technologies currently used in thrust chambers. A cooling channel is formed by milling grooves between the inner and outer walls of the thrust chamber. The fuel or oxidizer or both flow through the cooling channel to cool the inner wall of the thrust chamber. After absorbing heat, the propellant flows out of the cooling channel and re-enters the thrust chamber to participate in combustion, thereby achieving heat regeneration.

[0003] like Figure 1 and Figure 2 As shown in the figure, according to the form of the cooling groove, it can be divided into a straight groove and a spiral groove. The straight groove is: the cooling groove does not change the angle in the circumferential direction along the thrust chamber busbar, and the spiral groove is: the cooling groove changes the angle in the circumferential direction along the thrust chamber busbar at the same time. Compared with the straight groove, the spiral groove has a spiral inclination. On the same axial length, the spiral groove has a larger heat exchange area, which makes the heat exchange between the coolant and the thrust chamber more sufficient and the cooling effect better. In addition, adjusting the size of the spiral inclination at different axial positions can control the size of the heat exchange area of ​​the coolant at the local position. Therefore, the heat exchange amount at the local position can be adjusted in a targeted manner according to the size of the heat flux density at different positions on the inner wall of the thrust chamber, so that the cooling efficiency is higher.

[0004] However, since the generatrix of the thrust chamber is a convergent-divergent nozzle with a complex profile, it is difficult to determine the generatrix of the spiral groove on the complex profile rotating body, especially for the variable inclination spiral groove, the inclination angle also changes with the axial position, and the spiral groove line is more difficult to design. Therefore, the spiral groove channel is rarely used in the thrust chamber, or only the equal-inclination spiral groove is used on the cylindrical segment with a simple profile. Summary of the invention

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

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

[0007] Determine the system of equations used to describe the variable inclination helix on a body of revolution generated from any generatrix;

[0008] 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.

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

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

[0011] On the basis of the above scheme, the trajectory generation method of the variable inclination angle spiral groove used in the 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, 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: r is a function of z, substitute z into the function, and 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.

[0013] Furthermore, according to the equation group and the values ​​of multiple design parameters of the variable inclination angle spiral groove between the inner and outer walls of the thrust chamber, the curve trajectory of the variable inclination angle spiral groove is calculated, including:

[0014] The target line segment is discretized, and the corresponding value of each discrete point is calculated by combining the third formula and the values ​​of multiple design parameters of the variable-angle spiral groove. value;

[0015] According to the corresponding The x value and the y value of each discrete point are calculated using the first formula and the second formula to obtain the x value and the y value corresponding to each z value, thereby obtaining multiple position coordinate points on the curve track of the variable inclination spiral groove;

[0016] The target line segment refers to a 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 x value and y value corresponding to the z value constitute a position coordinate point.

[0017] Further, 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;

[0018] Discretize the target line segment, including:

[0019] Divide the length of the first local line segment, the second local line segment and the third local line segment to obtain a plurality of discrete points;

[0020] When the expansion segment 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.

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

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

[0023] 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;

[0024] 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.

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

[0026] Further, the system of equations 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: r is a function of z, substitute z into the function, and 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.

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

[0028] The target line segment is discretized, and the corresponding value of each discrete point is calculated by combining the third formula and the values ​​of multiple design parameters of the variable-angle spiral groove. value;

[0029] According to the corresponding The x value and the y value of each discrete point are calculated using the first formula and the second formula to obtain the x value and the y value corresponding to each z value, thereby obtaining multiple position coordinate points on the curve track of the variable inclination spiral groove;

[0030] The target line segment refers to a 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 x value and y value corresponding to the z value constitute a position coordinate point.

[0031] Further, 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;

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

[0033] Divide the length of the first local line segment, the second local line segment and the third local line segment to obtain a plurality of discrete points;

[0034] When the expansion segment 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.

[0035] 3) In a third aspect, the present invention further provides an electronic device, comprising a processor, the processor being coupled to a memory, the memory storing at least one computer program, the at least one computer program being loaded and executed by the processor so that the electronic device can implement any of the above-mentioned methods for generating a trajectory of a variable-angle spiral groove used in a thrust chamber.

[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, and the at least one computer program is loaded and executed by a processor so that the computer implements any of the above-mentioned methods for generating trajectories of variable-angle spiral grooves used in thrust chambers.

[0037] It should be noted that the beneficial effects achieved by the technical solutions of the second to fourth aspects of the present invention and the corresponding possible implementation methods can be found in the above-mentioned technical effects of the first aspect and its corresponding possible implementation methods, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

[0041] Figure 3 A schematic flow chart of a method for generating a trajectory of a variable-angle spiral groove used in a thrust chamber according to an embodiment of the present invention;

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

[0043] Figure 5 The figure is a schematic diagram of the structure of an electronic device according to an embodiment of the present invention. DETAILED DESCRIPTION

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

[0045] like Figure 3 As shown, a method for generating a trajectory of a variable-angle spiral groove used in a thrust chamber according to an embodiment of the present invention comprises the following steps:

[0046] S1. Determine a set of equations for describing a helix of varying inclination angle on a body of revolution generated according to any generatrix;

[0047] S2. 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.

[0048] Optionally, in the above technical solution, 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: r is a function of z, substitute z into the function, and 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.

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

[0050] Optionally, in S2, the curve trajectory of the variable-angle spiral groove is calculated based on 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, including:

[0051] S20, discretize the target line segment, and calculate the corresponding value of each discrete point by combining the third formula and the values ​​of multiple design parameters of the variable inclination spiral groove. value;

[0052] S21, according to each discrete point corresponding to The x value and the y value of each discrete point are calculated using the first formula and the second formula to obtain the x value and the y value corresponding to each z value, thereby obtaining multiple position coordinate points on the curve track of the variable inclination spiral groove;

[0053] The target line segment refers to a 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 x value and y value corresponding to the z value constitute a position coordinate point.

[0054] Optionally, in the above technical solution, 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;

[0055] In S20, the target line segment is discretized, including:

[0056] S201, dividing 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;

[0057] S202. When the expansion segment is designed using the maximum thrust principle, the fourth local line segment is composed of a plurality of 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. Alternatively, all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain a plurality of discrete points.

[0058] The present invention is described by the following examples, including:

[0059] S101, determining an equation group for describing a variable inclination helix on a rotating body generated according to any generatrix, the equation group comprising a first formula, a second formula and a third formula, the first formula being: 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: r is a function of z, substitute z into the function, and 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.

[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, determining the curve trajectory of the variable inclination angle spiral groove:

[0062] S101 involves 6 parameters (x, y, z, r, β and ) and 3 equations (the first formula, the second formula and the third formula), so it is necessary to determine 3 parameters to solve the equations. Among them, z and r are the profile parameters of the thrust chamber. When designing the variable-angle spiral groove used in the thrust chamber, the range of z values ​​of the thrust chamber, the function expression of r(z), and the function expression of β(z) are known. β is a parameter that affects the heat exchange area of ​​different areas of the variable-angle spiral groove and is given by the designer. By using the given range of z values, the function expression of r(z) and the function expression of β(z), solve x, y and , the specific calculation process is as follows:

[0063] S1020, parameter discretization:

[0064] In the equation group, the third formula involves the indefinite integral of the function. Since the thrust chamber has a relatively complex profile, it is difficult to obtain the curve trajectory of the variable-angle spiral groove if it is solved directly. 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) to transform the problem from the process of solving a continuity equation to the process of solving the function value of several discrete points. The specific discretization process is as follows:

[0065] 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;

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

[0067] ① Divide the length 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 may be divided into equal lengths, and the length of each segment may also be set according to actual conditions.

[0069] ② When designing the thrust chamber, in order to improve the efficiency of the nozzle, the profile of the expansion section of the thrust chamber is usually a special profile formed by a number of discrete points. When the expansion section is designed using the maximum thrust principle, the fourth local line segment is composed of a plurality of initial discrete points. The initial discrete points are all used as discrete points obtained by dividing the length of the fourth local line segment. Alternatively, all the initial discrete points are fitted, and then the fitted line segment is discretized to obtain a plurality of discrete points, wherein 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 a plurality of discrete points. The continuous fourth local line segment can be divided into equal lengths, or can be discretized according to actual conditions.

[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 thrust chamber at the entrance of the combustion chamber of the thrust chamber, and the z value of the first discrete point is z0. The m+1th discrete point is the point on the axis of the thrust chamber at the exit of the nozzle of the thrust chamber, and the z value of the m+1th discrete point is z m The size of m determines the fitting accuracy between the curved trajectory of the variable-angle spiral groove obtained by the discrete points and the profile of the thrust chamber. The larger the m, the higher the fitting accuracy. Since the curvature of the upstream and downstream areas of the throat of the thrust chamber varies greatly, more discrete points can be added in this area 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, i.e., z0, r0 and β0 are calculated, and according to the z value of the second discrete point, i.e., z1, r1 and β1 are calculated, and so on. According to the z value of the m+1th discrete point, i.e., z m , calculate r m and β m .

[0072] S1022, using the third formula to calculate each discrete point Then, the x and y values ​​corresponding to the z value of each discrete point are calculated using the first and second formulas. Specifically:

[0073] 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. However, since the integrand is relatively complex, it cannot be solved directly. According to the idea of ​​calculus, the calculation interval (between the starting point and the end point of the definite integral) is discretized into n infinitesimals, and the third formula is converted into the fourth formula. The fourth formula is:

[0074]

[0075] 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 spiral groove at the entrance of the combustion chamber of the thrust chamber is determined, and the coordinate position of the curve trajectory of the variable inclination spiral groove at the entrance of the combustion chamber of the thrust chamber can be adjusted according to the specific design requirements. Assign values; when j=0 and i=1, z0 is the z value at the entrance of the thrust chamber combustion chamber. When designing the variable-angle spiral groove used in the thrust chamber, z0 is a constant.

[0076] The fourth formula can be 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.

[0077] In the above embodiments, although the steps are numbered S1, S2, etc., these are only specific embodiments given by the present invention. Those skilled in the art may adjust the execution order of S1, S2, etc. according to actual conditions, which is also within the protection scope of the present invention. It can be understood that in some embodiments, some or all of the above embodiments may be included.

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

[0079] The equation group determination module 201 is used to: determine an equation group for describing a variable inclination angle helix on a rotating body generated according to any generatrix;

[0080] The curve trajectory acquisition module 202 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.

[0081] Optionally, in the above technical solution, 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: r is a function of z, substitute z into the function, and 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.

[0082] Optionally, in the above technical solution, the curve trajectory acquisition module 202 is specifically used for:

[0083] The target line segment is discretized, and the corresponding value of each discrete point is calculated by combining the third formula and the values ​​of multiple design parameters of the variable-angle spiral groove. value;

[0084] According to the corresponding The x value and the y value of each discrete point are calculated using the first formula and the second formula to obtain the x value and the y value corresponding to each z value, thereby obtaining multiple position coordinate points on the curve track of the variable inclination spiral groove;

[0085] The target line segment refers to a 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 x value and y value corresponding to the z value constitute a position coordinate point.

[0086] Optionally, in the above technical solution, the thrust chamber includes a cylindrical segment, a convergent segment, a throat and an expansion segment 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 segment on the axis of the thrust chamber, the second local line segment refers to: a line segment of the convergent segment on the axis of the thrust chamber, the third local line segment refers to: a line segment of the throat on the axis of the thrust chamber; the fourth local line segment refers to: a line segment of the expansion segment on the axis of the thrust chamber; the curve trajectory acquisition module 202 is also specifically used for:

[0087] Divide the length of the first local line segment, the second local line segment and the third local line segment to obtain a plurality of discrete points;

[0088] When the expansion segment 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.

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

[0090] like Figure 5 As shown, an electronic device 300 according to an embodiment of the present invention includes a processor 320, the processor 320 is coupled to a memory 310, and the memory 310 stores at least one computer program 330, and the at least one computer program 330 is loaded and executed by the processor 320, so that the electronic device 300 implements any of the above-mentioned methods for generating a trajectory of a variable-angle spiral groove used in a thrust chamber, specifically:

[0091] The electronic device 300 may have relatively large differences due to different configurations or performances, and may include one or more processors 320 (Central Processing Units, CPU) and one or more memories 310, wherein the one or more memories 310 store at least one computer program 330, and 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 any of the trajectory generation methods for the variable inclination spiral groove used in the thrust chamber provided in the above embodiments. Of course, the electronic device 300 may also have components such as a wired or wireless network interface, a keyboard, and an input and output interface for input and output. The electronic device 300 may also include other components for realizing the functions of the device, which will not be described in detail here. The electronic device may specifically be a computer, etc.

[0092] A computer-readable storage medium according to an embodiment of the present invention stores at least one computer program, and the at least one computer program is loaded and executed by a processor so that the computer implements any of the above-mentioned methods for generating a trajectory of a variable-angle spiral groove used in a thrust chamber.

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

[0094] In an exemplary embodiment, a computer program product or a computer program is also provided, the computer program product or the computer program comprising computer instructions, the computer instructions being stored in a computer-readable storage medium. A processor of an 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 any of the above-mentioned methods for generating a trajectory of a variable-angle spiral groove used in a thrust chamber.

[0095] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects and represent the definition of a specific order or sequence. The order of use of similar objects can be interchanged where appropriate, so that the embodiments of the present 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, method or computer program product. Therefore, the present invention can be specifically implemented in the following forms, namely: it can be complete hardware, it can be complete software (including firmware, resident software, microcode, etc.), or it can be 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, and the computer-readable medium contains computer-readable program code.

[0097] Any combination of one or more computer-readable media can be used. The computer-readable medium can be a computer-readable signal medium or a computer-readable storage medium. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media (a non-exhaustive list) 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, a computer-readable storage medium can be any tangible medium containing or storing a program, which can be used by an instruction execution system, device or device or used in combination with it.

[0098] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary 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.

2. The method for generating a trajectory of a variable inclination angle spiral groove used in a thrust chamber according to claim 1, characterized in that: 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.

3. The method for generating a trajectory of a variable-angle spiral groove for a thrust chamber according to claim 2, characterized in that: 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; The target line segment refers to a 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 x value and y value corresponding to the z value constitute a position coordinate point.

4. The method for generating a trajectory of a variable-angle spiral groove for 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; 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.

5. A trajectory generation system for a variable-angle 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, so as to complete the design of the variable-angle spiral groove.

6. The trajectory generation system of a variable inclination angle spiral groove used in a thrust chamber according to claim 5, characterized in that: 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.

7. The trajectory generation system of a variable inclination angle spiral groove used in a thrust chamber according to claim 6, characterized in that: 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; The target line segment refers to a 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 x value and y value corresponding to the z value constitute a position coordinate point.

8. The trajectory generation system of a variable inclination angle spiral groove used in a thrust chamber according to claim 7, 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.

9. An electronic device, characterized in that: The electronic device includes a processor, the processor is coupled to a memory, and at least one computer program is stored in the memory. 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-inclination spiral groove used in a thrust chamber as described in any one of claims 1 to 4.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores at least one computer program, which is loaded and executed by a processor so that the computer implements a trajectory generation method for a variable-angle spiral groove used in a thrust chamber as described in any one of claims 1 to 4.

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