Solid attitude and trajectory control engine gas valve stem profile design method and device

Abstract

The present invention provides a solid attitude and orbit control engine gas valve stem profile design method and device, given a solid attitude and orbit control engine nozzle profile curve and target equivalent throat area curve requirements; on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, determine the tangent point between the valve stem local profile corresponding to the first valve stem displacement step and the nozzle profile, and use local linear expansion to determine the valve stem profile coordinate point on the valve stem local profile corresponding to the first valve stem displacement step near the tangent point; based on the target equivalent throat area curve, and using a binary search method to calculate the local Taylor expansion slope, determine the valve stem profile coordinate point on the valve stem local profile corresponding to the next valve stem displacement step, continue to recursively iterate until the valve stem displacement reaches the maximum stroke, obtain all valve stem profile coordinate points, and finally obtain the valve stem profile curve. The present invention can ensure the linear relationship between the valve stem displacement and the equivalent throat area.

Description

Technical Field

[0001] The invention belongs to the technical field of valve face profile design, and in particular relates to a method and a device for designing a valve stem profile of a solid attitude and trajectory control engine gas valve. Background Art

[0002] As the actuator of the kinetic interceptor, the gas-fired solid attitude control engine has a simple structure, is safe and reliable, and is particularly suitable for air-based and sea-based interception weapon systems with high safety requirements. For gas-fired solid attitude control engines, the thrust control process depends largely on the geometric configuration of the valve stem in the valve, the nozzle profile, and the relative relationship between the valve stem and the nozzle. When the opening of a single valve changes nonlinearly with the valve stem stroke, it is difficult to keep the total opening of the valve constant during the movement of each valve stem from the current position to the next position, resulting in the combustion chamber pressure changing with the change of the movement position of each valve stem, which increases the control difficulty. Therefore, it is urgent to carry out the valve stem profile optimization design with the goal of highly linear single valve opening with valve stem stroke under the given nozzle throat diameter, so as to simplify the complexity of the control system as much as possible.

[0003] The commonly used valve profile design methods are:

[0004] Based on the existing surface design scheme, the design scheme with similar working conditions is adopted or fine-tuned. This method is simple and convenient, easy to implement, and effectively avoids complex calculation processes. However, this method requires the participation of experienced engineers, and the linearity of the design results is difficult to guarantee.

[0005] The valve profile is optimized based on the optimization algorithm. This method usually takes the size parameters of the nozzle and the throat plug as the design variables, and establishes an optimization model with the error between the obtained valve stem displacement-opening curve and the target curve as the objective function, and solves it based on the intelligent optimization algorithm. This method can realize the automatic optimization design of the profile parameters, and the design results are relatively accurate. However, although this method can realize the automation of the optimization process, it requires additional information such as the valve profile curve equation. In addition, this method requires reasonable planning of the profile control parameters. If there are fewer parameters, the control of the profile shape is limited, which makes it difficult to ensure the linearity of the optimization design results; if there are more parameters, the optimization model will be complicated, the calculation cost will be unacceptable, and it will be difficult to directly apply it to engineering practice. Summary of the invention

[0006] Aiming at the technical problems of complicated profile design process and poor design results in the process of linearizing the valve stem displacement and valve equivalent throat area of ​​solid attitude control gas power valve, the present invention proposes a valve stem profile design method and device for solid attitude and trajectory control engine gas valve. The method does not need to pre-set the valve stem profile equation form, can realize the valve stem profile design with high efficiency, and ensure that the linearity of valve opening and valve stem stroke meets the design requirements.

[0007] In order to achieve the above technical objectives, the technical solution proposed by the present invention is:

[0008] In one aspect, the present invention provides a method for designing a valve stem profile of a solid attitude and trajectory control engine gas valve, comprising:

[0009] Given the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements, and the valve stem profile coordinate point set P is given as an empty set;

[0010] According to the target equivalent throat area curve, on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, determine the tangent point between the valve stem local profile corresponding to the first valve stem displacement step and the nozzle profile, and use local linear expansion to determine the valve stem profile coordinate point on the valve stem local profile corresponding to the first valve stem displacement step near the tangent point, and add it to the valve stem profile coordinate point set P;

[0011] Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method to determine the valve stem surface coordinate point on the local surface of the valve stem corresponding to the next valve stem displacement step, and add it to the valve stem surface coordinate point set P, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke, and all valve stem surface coordinate points are obtained;

[0012] The valve stem profile curve is obtained by adding the valve stem profile head arc to all valve stem profile coordinate points.

[0013] In some preferred embodiments of the present invention, the tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step is determined by the following steps:

[0014] (2.1) Calculate the target equivalent throat area at the first valve stem displacement step according to the target equivalent throat area curve

[0015] (2.2) Initialize the binary search interval [x min ,x max ]=[x con ,0], where x con is the horizontal coordinate of the tangent point between the nozzle convergence section and the transition arc of the nozzle profile curve;

[0016] (2.3) Obtain the midpoint of the binary search interval search interval Then calculate the surface height of the point and transition arc slope

[0017] (2.4) At the coordinate point Slope Perform a local first-order Taylor expansion to obtain the valve stem local profile equation corresponding to the first valve stem displacement step, where ds is the valve stem displacement step;

[0018] (2.5) Calculate the current valve equivalent throat area based on the valve stem local profile equation and nozzle profile equation corresponding to the first valve stem displacement step obtained in step (2.4) And the coordinate point with the minimum target equivalent throat area on the local surface of the valve stem corresponding to the first valve stem displacement step

[0019] (2.6) Convergence judgment: If Then terminate the binary division cycle and As the tangent point between the valve profile and the nozzle profile; otherwise, go to step (2.7);

[0020] (2.7) Update search interval: If Then Then go to step (2.3) and continue iterating; if Then Then go to step (2.3) and continue iterating; if Then As the tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step, the corresponding horizontal coordinate is the effective stroke end point corresponding to the first valve stem displacement step of the gas valve stem, that is,

[0021] Furthermore, the valve stem profile coordinate point on the local valve stem profile corresponding to the first valve stem displacement step is and Add the valve stem surface coordinate point set P and As the starting point of the local valve stem profile corresponding to the next valve stem displacement step.

[0022] Furthermore, the first valve stem displacement step is s max -ds, where s max is the maximum displacement of the valve stem.

[0023] In some preferred embodiments of the present invention, the target equivalent throat area curve is used, and the local Taylor expansion slope is calculated by binary search method, the valve stem profile coordinate point on the local profile of the valve stem corresponding to the next valve stem displacement step is determined, and it is added to the valve stem profile coordinate point set P, and the recursive iteration is continued until the valve stem displacement reaches the maximum stroke, and all the valve stem profile coordinate points are obtained, which is achieved by the following steps:

[0024] (3.1) Calculate the next valve stem displacement step s according to the target equivalent throat area curve maxTarget equivalent throat area at -(g+1)·ds Where g is a recursive algebra, and the initial value of g is 1;

[0025] (3.2) Initialize the slope search interval [k min ,k max ] = [-10, 0];

[0026] (3.3) Determine the current local expansion point Get the midpoint of the slope search interval And at the current local expansion point with slope First-order Taylor expansion is performed to obtain the local surface equation of the current valve stem;

[0027] (3.4) Calculate the current valve equivalent throat area based on the current valve stem local profile equation and nozzle profile equation obtained in step (3.3) And the coordinate point with the minimum target equivalent throat area on the current valve stem local profile

[0028] (3.5) Convergence judgment of the binary method: If Then terminate the binary division cycle and As the local Taylor expansion slope, go to step (3.7); otherwise go to step (3.6);

[0029] (3.6) Update search interval: If Then Then go to step (3.3) and continue iterating; if Then Then go to step (3.3) and continue iterating; if Then As the local Taylor expansion slope, go to step (3.7);

[0030] (3.7) All coordinates in the valve stem profile data point set P are translated to the left by ds, and the points Add it and go to step (3.8);

[0031] (3.8) Convergence judgment: Let g = g + 1, if s max -(g+1)·ds<0, then exit and output the current valve stem profile coordinate point set P; otherwise, go to step (3.1) to continue iterating.

[0032] In some preferred embodiments of the present invention, a circle with a center (x pintle +k mid ·y pintle ,0), the radius is The arc of the valve stem profile head is obtained to obtain the valve stem profile curve.

[0033] Furthermore, the present invention calculates the corresponding actual equivalent throat area curve based on the valve stem profile curve and the nozzle profile curve.

[0034] In another aspect, the present invention provides a device for designing a valve stem profile of a solid attitude and trajectory control engine gas valve, comprising:

[0035] The first module is used to give the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements;

[0036] The second module is used to determine the tangent point between the local stem profile corresponding to the first stem displacement step and the nozzle profile according to the target equivalent throat area curve and the equivalent throat area corresponding to the first stem displacement step on the nozzle convergence section profile curve, and determine the stem profile coordinate point on the local stem profile corresponding to the first stem displacement step near the tangent point by using local linear expansion;

[0037] The third module is used to calculate the local Taylor expansion slope based on the target equivalent throat area curve and use the binary search method to determine the valve stem surface coordinate point on the local valve stem surface corresponding to the next valve stem displacement step, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke to obtain all valve stem surface coordinate points;

[0038] The fourth module is used to add a valve stem profile head arc based on all valve stem profile coordinate points to obtain a valve stem profile curve.

[0039] In another aspect, the present invention provides a computer device, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the following steps are implemented:

[0040] Given the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements, and the valve stem profile coordinate point set P is given as an empty set;

[0041] According to the target equivalent throat area curve, on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, determine the tangent point between the valve stem local profile corresponding to the first valve stem displacement step and the nozzle profile, and use local linear expansion to determine the valve stem profile coordinate point on the valve stem local profile corresponding to the first valve stem displacement step near the tangent point, and add it to the valve stem profile coordinate point set P;

[0042] Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method to determine the valve stem surface coordinate point on the local surface of the valve stem corresponding to the next valve stem displacement step, and add it to the valve stem surface coordinate point set P, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke, and all valve stem surface coordinate points are obtained;

[0043] The valve stem profile curve is obtained by adding the valve stem profile head arc to all valve stem profile coordinate points.

[0044] In another aspect, a computer readable storage medium stores a computer program, which, when executed by a processor, implements the following steps:

[0045] Given the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements, and the valve stem profile coordinate point set P is given as an empty set;

[0046] According to the target equivalent throat area curve, on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, determine the tangent point between the valve stem local profile corresponding to the first valve stem displacement step and the nozzle profile, and use local linear expansion to determine the valve stem profile coordinate point on the valve stem local profile corresponding to the first valve stem displacement step near the tangent point, and add it to the valve stem profile coordinate point set P;

[0047] Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method to determine the valve stem surface coordinate point on the local surface of the valve stem corresponding to the next valve stem displacement step, and add it to the valve stem surface coordinate point set P, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke, and all valve stem surface coordinate points are obtained;

[0048] The valve stem profile curve is obtained by adding the valve stem profile head arc to all valve stem profile coordinate points.

[0049] The present invention is based on the target equivalent throat area curve. After the tangent point between the valve stem profile and the nozzle profile is obtained by binary search method, the local slope of the valve stem profile is calculated by using binary search method and first-order Taylor expansion formula, and recursive matching design is gradually performed to achieve the linear proportional valve design under given nozzle profile conditions. Compared with the prior art, the advantages of the present invention are:

[0050] 1. Compared with the use or fine-tuning of existing design solutions, the present invention is more robust and the design results are more stable and reliable;

[0051] 2. Compared with the valve profile optimization design method using optimization algorithm, the present invention does not require additional information and can ensure the linearity of the design results at a lower calculation cost;

[0052] The present invention has been applied in the design of multi-type solid attitude control power gas valve profiles. Compared with existing methods, it does not require additional information and can better meet design requirements while effectively improving design efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0054] Figure 1 is a general flow chart of an embodiment of the present invention;

[0055] Figure 2 is a specific flow chart of an embodiment of the present invention;

[0056] Figure 3 It is a schematic diagram of the design principle of a linear gas valve profile based on recursive optimization in one embodiment of the present invention;

[0057] Figure 4 Schematic diagram of the geometric configuration of a solid attitude control power gas valve in one embodiment of the present invention;

[0058] Figure 5 This is a diagram of the valve stem profile design result obtained in one embodiment of the present invention;

[0059] Figure 6 yes Figure 5 The equivalent throat area diagram corresponding to the valve stem profile design result is shown;

[0060] Figure 7 This is a diagram of the valve stem profile design result obtained in one embodiment of the present invention;

[0061] Figure 8 yes Figure 7 The equivalent throat area diagram corresponding to the valve stem profile design result is shown;

[0062] Fig. 9 It is a structural schematic diagram of an embodiment of the present invention. DETAILED DESCRIPTION

[0063] In order to make the purpose, technical scheme and advantages of the embodiments of the present invention more clearly understood, the following will be used with drawings and detailed descriptions to clearly illustrate the spirit of the contents disclosed by the present invention. After understanding the embodiments of the contents of the present invention, any person skilled in the art can change and modify the techniques taught by the contents of the present invention without departing from the spirit and scope of the contents of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention, but are not intended to limit the present invention.

[0064] Aiming at the problem that it is difficult to achieve a highly linear relationship between the valve stem displacement and the valve equivalent throat area during the design of the solid attitude control gas power valve profile, the present invention proposes a linear flow regulation gas valve profile design method based on recursive optimization. This method does not require pre-setting the valve stem profile equation form, and can achieve valve stem profile design with high efficiency while ensuring that the linearity of the valve opening and the valve stem stroke meets the design requirements.

[0065] The present invention is based on the binary search method and the first-order Taylor local expansion. It is oriented to the equivalent throat area required, and the valve stem profile coordinate point set is gradually recursively deduced with the calculation step length as the interval. That is, the tangent point between the valve profile and the nozzle profile is first determined on the transition arc of the nozzle convergence section to meet the change of the equivalent throat area of ​​the valve stem from the fully closed state to the first calculation step length; on this basis, the local expansion slope is calculated by the binary search method, and the coordinate points of the equivalent throat area formed on the valve stem profile are added to the coordinate point set and then the recursive iteration is continued until the valve stem displacement reaches the maximum stroke. Compared with other implementation schemes, the present invention can ensure a highly linear relationship between the valve stem displacement and the equivalent throat area while realizing efficient valve stem design.

[0066] In one embodiment, referring to Figure 1 , a method for designing a valve stem profile of a solid attitude and orbit control engine gas valve is provided, comprising the following steps:

[0067] (S1) A solid attitude and orbit control engine gas valve nozzle profile curve and a target equivalent throat area curve are given, and a valve stem profile coordinate point set P is given as an empty set;

[0068] (S2) according to the target equivalent throat area curve, on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, determine the tangent point between the valve stem local profile corresponding to the first valve stem displacement step and the nozzle profile, and use local linear expansion to determine the valve stem profile coordinate point on the valve stem local profile corresponding to the first valve stem displacement step near the tangent point, and add it to the valve stem profile coordinate point set P;

[0069] (S3) Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method, the valve stem profile coordinate point on the local profile of the valve stem corresponding to the next valve stem displacement step is determined, and the valve stem profile coordinate point is added to the valve stem profile coordinate point set P, and the recursive iteration is continued until the valve stem displacement reaches the maximum stroke, and all the valve stem profile coordinate points are obtained;

[0070] (S4) A valve stem profile head arc is added to all valve stem profile coordinate points to obtain a valve stem profile curve.

[0071] In some preferred embodiments of the present invention, the tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step in step (S2) is determined by the following steps:

[0072] (S2.1) Calculate the target equivalent throat area at the first valve stem displacement step according to the target equivalent throat area curve The first valve stem displacement step is s max -ds, where s max is the maximum displacement of the valve stem.

[0073] (S2.2) Initialize the binary search interval [x min ,x max ]=[x con ,0], where x con is the horizontal coordinate of the tangent point between the nozzle convergence section and the transition arc of the nozzle profile curve;

[0074] (S2.3) Obtain the midpoint of the binary search interval Then calculate the surface height of the point and transition arc slope

[0075] (S2.4) At the coordinate point Slope Perform a local first-order Taylor expansion to obtain the valve stem local profile equation corresponding to the first valve stem displacement step, where ds is the valve stem displacement step;

[0076] (S2.5) Calculate the current valve equivalent throat area based on the valve stem local profile equation corresponding to the first valve stem displacement step obtained in step (S2.4) and the nozzle profile equation And the coordinate point with the minimum target equivalent throat area on the local surface of the valve stem corresponding to the first valve stem displacement step

[0077] (S2.6) Convergence judgment: If Then terminate the binary division cycle and as the tangent point between the valve profile and the nozzle profile; otherwise, go to step (S2.7);

[0078] (S2.7) Update search interval: If Then Then go to step (S2.3) to continue iteration; if Then Then go to step (S2.3) to continue iteration; if Then As the tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step, the corresponding horizontal coordinate is the effective stroke end point corresponding to the first valve stem displacement step of the gas valve stem, that is,

[0079] (S2.8) The valve stem profile coordinate point on the local valve stem profile corresponding to the first valve stem displacement step and Add the valve stem surface coordinate point set P and As the starting point of the local valve stem profile corresponding to the next valve stem displacement step.

[0080] In some preferred embodiments of the present invention, the target equivalent throat area curve is used in step (S3), and the local Taylor expansion slope is calculated by using a binary search method to determine the valve stem profile coordinate point corresponding to the next valve stem displacement step, and then the recursive iteration is continued until the valve stem displacement reaches the maximum stroke, and all valve stem profile coordinate points are obtained, which is achieved by the following steps:

[0081] (S3.1) Calculate the next valve stem displacement step s according to the target equivalent throat area curve max Target equivalent throat area at -(g+1)·ds Where g is a recursive algebra, and the initial value of g is 1;

[0082] (S3.2) Initialize the slope search interval [k min ,k max ] = [-10, 0];

[0083] (S3.3) Determine the current local expansion point Get the midpoint of the slope search interval And at the current local expansion point with slope First-order Taylor expansion is performed to obtain the local surface equation of the current valve stem;

[0084] (S3.4) Calculate the current valve equivalent throat area based on the current valve stem local profile equation and nozzle profile equation obtained in step (S3.3) And the coordinate point with the minimum target equivalent throat area on the current valve stem local profile

[0085] (S3.5) Binary method convergence judgment: If Then terminate the binary division cycle and As the local Taylor expansion slope, go to step (S3.7); otherwise go to step (S3.6);

[0086] (S3.6) Update search interval: If Then Then go to step (S3.3) to continue iteration; if Then Then go to step (S3.3) to continue iteration; if Then As the local Taylor expansion slope, go to step (S3.7);

[0087] (S3.7) Shift all coordinates in the valve stem profile data point set P to the left by ds, and Add it and go to step (S3.8);

[0088] (S3.8) Convergence judgment: Let g = g + 1, if s max -(g+1)·ds<0, then exit and output the current valve stem profile coordinate point set P; otherwise, go to step (S3.1) to continue iterating.

[0089] In some preferred embodiments of the present invention, step (S4) adds a circle with a center (x pintle +k mid ·y pintle ,0), the radius is The arc of the valve stem profile head is obtained to obtain the valve stem profile curve.

[0090] In one embodiment, referring to Figure 2 , a method for designing a valve stem profile of a solid attitude and orbit control engine gas valve is provided, comprising the following steps:

[0091] (1) Initialization: Given the nozzle throat diameter, the radius of the upstream transition arc of the nozzle throat, the convergence half angle and the target equivalent throat area curve, the valve stem profile coordinate data set is set to zero. The nozzle convergence section profile curve can be determined based on the nozzle throat diameter, the radius of the upstream transition arc of the nozzle throat and the convergence half angle.

[0092] (2)Reference Figure 3 According to the target equivalent throat area curve, on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, the tangent point between the local stem profile and the nozzle profile corresponding to the first valve stem displacement step is determined, and the stem profile coordinate point on the local stem profile corresponding to the first valve stem displacement step near the tangent point is determined by local linear expansion.

[0093] (2.1) Calculate the target equivalent throat area at the first valve stem displacement step according to the target equivalent throat area curve The first valve stem displacement step is s max -ds, where s max is the maximum displacement of the valve stem.

[0094] (2.2) Initialize the binary search interval [x min ,x max ]=[x con ,0], where x con is the horizontal coordinate of the tangent point between the nozzle convergence section and the transition arc of the nozzle profile curve;

[0095] (2.3) Obtain the midpoint of the binary search interval Then calculate the surface height of the point and transition arc slope

[0096] (2.4) At the coordinate point Slope Perform a local first-order Taylor expansion to obtain the valve stem local profile equation corresponding to the first valve stem displacement step, where ds is the valve stem displacement step;

[0097] (2.5) Calculate the current valve equivalent throat area based on the valve stem local profile equation and nozzle profile equation corresponding to the first valve stem displacement step obtained in step (2.4) And the coordinate point with the minimum target equivalent throat area on the local surface of the valve stem corresponding to the first valve stem displacement step

[0098] (2.6) Convergence judgment: If Then terminate the binary division cycle and As the tangent point between the valve profile and the nozzle profile; otherwise, go to step (2.7);

[0099] (2.7) Update search interval: If Then Then go to step (2.3) and continue iterating; if Then Then go to step (2.3) and continue iterating; if Then As the tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step, the corresponding horizontal coordinate is the effective stroke end point corresponding to the first valve stem displacement step of the gas valve stem, that is,

[0100] (2.8) The two end points of the local surface of the valve stem corresponding to the first valve stem displacement step are and Add the valve stem surface coordinate point set and As the starting point of the local valve stem profile corresponding to the next valve stem displacement step.

[0101] (3) Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method, and the valve stem profile coordinate point on the local profile of the valve stem corresponding to the next valve stem displacement step is determined, and then the recursive iteration is continued until the valve stem displacement reaches the maximum stroke, and all the valve stem profile coordinate points are obtained;

[0102] (3.1) Initialize the recursive algebra g = 1;

[0103] (3.2) Calculate the next valve stem displacement step s according to the target equivalent throat area curve max Target equivalent throat area at -(g+1)·ds

[0104] (3.3) Calculate the local Taylor expansion slope based on the binary search method;

[0105] (3.3.1) Initialize the slope search interval [k min ,k max ]=[-10,0], current local expansion point

[0106] (3.3.2) Get the midpoint of the slope search interval And at the current local expansion point with slope First-order Taylor expansion is performed to obtain the local surface equation of the current valve stem;

[0107] (3.3.3) Calculate the current valve equivalent throat area based on the current valve stem local profile equation and nozzle profile equation obtained in step (3.3.2) And the coordinate point with the minimum target equivalent throat area on the current valve stem local profile

[0108] (3.3.4) Convergence judgment of binary search: If Then terminate the binary division cycle and As the local Taylor expansion slope, go to step (3.3.6); otherwise go to step (3.3.5);

[0109] (3.3.5) Update search interval: If Then Then go to step (3.3.1) and continue iterating; if Then Then go to step (3.3.1) and continue iterating; if Then As the local Taylor expansion slope, go to step (3.3.6);

[0110] (3.3.6) Shift all coordinates in the valve stem profile data set to the left by ds, and Add it and go to step (3.4);

[0111] (3.4) Convergence judgment: Let g = g + 1, if s max -(g+1)·ds<0, then exit, output the current valve stem profile coordinate point set, and go to step (4); otherwise go to step (3.2) to continue iteration.

[0112] (4) Add a circle with the center (x pintle +k mid ·y pintle ,0), the radius is The arc of the valve stem profile head is obtained to obtain the valve stem profile curve.

[0113] (5) The corresponding actual equivalent throat area curve is calculated based on the valve stem profile curve and the nozzle profile curve.

[0114] Taking two solid attitude control power gas valves as an example, a specific implementation plan for the valve stem profile design is given. The geometric configurations of the two solid attitude control power gas valves are as follows: Figure 4 As shown, the design parameters and working parameters of the valve part given in Case 1 are shown in Table 1, and the design parameters and working parameters of the valve part given in Case 2 are shown in Table 2.

[0115] Table 1 Case 1 Valve Partial Design Parameters and Working Parameters

[0116]

[0117] Table 2 Design parameters and working parameters of valve in case 2

[0118]

[0119] The solid attitude control engine gas valve stem profile design method provided by the present invention is adopted, and based on the valve part design parameters and working parameters given in Table 1 and Table 2, the valve stem profiles of the solid attitude control gas power valves in the above two cases are designed respectively.

[0120] Based on the design parameters and working parameters of the valve in case 1 shown in Table 1, the valve stem profile design results are as follows: Figure 5 As shown, the corresponding equivalent throat area is Figure 6 shown. Figure 6 The design results of the existing optimization method (the valve stem profile is set as a cubic curve) are also given. The simulation calculation results show that the valve stem profile obtained by the design method of the linear flow regulating gas valve of the solid attitude and orbit control engine based on the recursive optimization method can ensure the highly linear change of the displacement-equivalent throat area. Under this profile condition, the actual equivalent throat area completely coincides with the required equivalent throat area, and the design results meet the requirements. At the same time, the linearity of the optimization method design result is also good, but as can be seen from Table 3, the calculation efficiency of the method of the present invention is greatly improved.

[0121] Table 3 Time consumption of different design methods

[0122]

[0123] Based on the design parameters and working parameters of the valve in case 1 shown in Table 2, the valve stem profile design results are as follows: Figure 7 As shown, the corresponding equivalent throat area is Figure 8 The simulation results show that the design method of the linear flow regulating gas valve of the solid attitude and orbit control engine based on the recursive optimization method takes 389ms to complete the recursive design of the valve stem profile without the need for additional information, and the design result has a strong linearity, which shows that the method of the present invention has strong versatility and can solve practical problems under various working conditions.

[0124] In one embodiment, a solid state attitude and trajectory control engine gas valve stem profile design device is provided, comprising:

[0125] The first module is used to give the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements;

[0126] The second module is used to determine the tangent point between the local stem profile corresponding to the first stem displacement step and the nozzle profile according to the target equivalent throat area curve and the equivalent throat area corresponding to the first stem displacement step on the nozzle convergence section profile curve, and determine the stem profile coordinate point on the local stem profile corresponding to the first stem displacement step near the tangent point by using local linear expansion;

[0127] The third module is used to calculate the local Taylor expansion slope based on the target equivalent throat area curve and use the binary search method to determine the valve stem surface coordinate point on the local valve stem surface corresponding to the next valve stem displacement step, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke to obtain all valve stem surface coordinate points;

[0128] The fourth module is used to add a valve stem profile head arc based on all valve stem profile coordinate points to obtain a valve stem profile curve.

[0129] The methods for implementing the functions of the above modules can be implemented using the same methods as in the above embodiments, which will not be described in detail here.

[0130] In this embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as shown in FIG. Fig. 9As shown. The computer device includes a processor, a memory, a network interface and a database connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store sample data. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, the steps of the solid attitude and orbit control engine gas valve stem profile design method in the above-mentioned embodiment are implemented.

[0131] Those skilled in the art will understand that Fig. 9 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0132] In one embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the steps of the method for designing a valve stem profile of a gas valve of a solid attitude and trajectory control engine in the above embodiment are implemented.

[0133] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps of the method for designing a valve stem profile of a gas valve of a solid attitude and trajectory control engine in the above embodiment are implemented.

[0134] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0135] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0136] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application shall be subject to the attached claims.

Claims

1. A method for designing a solid attitude and orbit control engine gas valve stem profile, characterized in that: include: Given the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements, and the valve stem profile coordinate point set P is given as an empty set; According to the target equivalent throat area curve, on the nozzle convergence section profile curve, according to the equivalent throat area corresponding to the first valve stem displacement step, determine the tangent point between the valve stem local profile corresponding to the first valve stem displacement step and the nozzle profile, and use local linear expansion to determine the valve stem profile coordinate point on the valve stem local profile corresponding to the first valve stem displacement step near the tangent point, and add it to the valve stem profile coordinate point set P; Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method to determine the valve stem surface coordinate point on the local surface of the valve stem corresponding to the next valve stem displacement step, and add it to the valve stem surface coordinate point set P, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke, and all valve stem surface coordinate points are obtained; The valve stem profile curve is obtained by adding the valve stem profile head arc to all valve stem profile coordinate points.

2. The solid attitude and trajectory control engine gas valve stem profile design method according to claim 1, characterized in that: The tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step is determined by the following steps: (2.1) Calculate the target equivalent throat area at the first valve stem displacement step according to the target equivalent throat area curve (2.2) Initialize the binary search interval [x min ,x max ]=[x con ,0], where x con is the horizontal coordinate of the tangent point between the nozzle convergence section and the transition arc of the nozzle profile curve; (2.3) Obtain the midpoint of the binary search interval search interval Then calculate the surface height of the point and transition arc slope (2.4) At the coordinate point Slope Perform a local first-order Taylor expansion to obtain the valve stem local profile equation corresponding to the first valve stem displacement step, where ds is the valve stem displacement step; (2.5) Calculate the current valve equivalent throat area based on the valve stem local profile equation and nozzle profile equation corresponding to the first valve stem displacement step obtained in step (2.4) And the coordinate point with the minimum target equivalent throat area on the local surface of the valve stem corresponding to the first valve stem displacement step (2.6) Convergence judgment: If Then terminate the binary division cycle and As the tangent point between the valve profile and the nozzle profile; otherwise, go to step (2.7); (2.7) Update search interval: If Then Then go to step (2.3) and continue iterating; if Then Then go to step (2.3) and continue iterating; if Then As the tangent point between the local profile of the valve stem and the profile of the nozzle corresponding to the first valve stem displacement step, the corresponding horizontal coordinate is the effective stroke end point corresponding to the first valve stem displacement step of the gas valve stem, that is, 3. The method for designing a valve stem profile of a solid attitude and trajectory control engine gas valve according to claim 2, characterized in that: The valve stem profile coordinate point on the local valve stem profile corresponding to the first valve stem displacement step and Add the valve stem surface coordinate point set P and As the starting point of the local valve stem profile corresponding to the next valve stem displacement step.

4. The method for designing a solid attitude and trajectory control engine gas valve stem profile according to claim 2, characterized in that: The first valve stem displacement step is s max -ds, where s max is the maximum displacement of the valve stem.

5. The method for designing the valve stem profile of a solid attitude and trajectory control engine gas valve according to claim 2, 3 or 4, characterized in that: Based on the target equivalent throat area curve, the local Taylor expansion slope is calculated by binary search method, and the valve stem profile coordinate point on the local valve stem profile corresponding to the next valve stem displacement step is determined, and added to the valve stem profile coordinate point set P, and the recursive iteration is continued until the valve stem displacement reaches the maximum stroke, and all valve stem profile coordinate points are obtained, which is achieved by the following steps: (3.1) Calculate the next valve stem displacement step s according to the target equivalent throat area curve max Target equivalent throat area at -(g+1)·ds Where g is a recursive algebra, and the initial value of g is 1; (3.2) Initialize the slope search interval [k min ,k max ] = [-10, 0]; (3.3) Determine the current local expansion point Get the midpoint of the slope search interval And at the current local expansion point with slope First-order Taylor expansion is performed to obtain the local surface equation of the current valve stem; (3.4) Calculate the current valve equivalent throat area based on the current valve stem local profile equation and nozzle profile equation obtained in step (3.3) And the coordinate point with the minimum target equivalent throat area on the current valve stem local profile (3.5) Convergence judgment of the binary method: If Then terminate the binary division cycle and As the local Taylor expansion slope, go to step (3.7); otherwise go to step (3.6); (3.6) Update search interval: If Then Then go to step (3.3) and continue iterating; if Then Then go to step (3.3) and continue iterating; if Then As the local Taylor expansion slope, go to step (3.7); (3.7) All coordinates in the valve stem profile data point set P are translated to the left by ds, and the points Join us, Go to step (3.8); (3.8) Convergence judgment: Let g = g + 1, if s max -(g+1)·ds<0, then exit and output the current valve stem profile coordinate point set P; otherwise, go to step (3.1) to continue iterating.

6. The solid attitude and trajectory control engine gas valve stem profile design method according to claim 5, characterized in that: Add a circle with the center (x pintle +k mid ·y pintle ,0), the radius is The arc of the valve stem profile head is obtained to obtain the valve stem profile curve.

7. The method for designing a solid attitude and trajectory control engine gas valve stem profile according to claim 1, 2, 3, 4, or 6, characterized in that: The corresponding actual equivalent throat area curve is calculated based on the valve stem profile curve and the nozzle profile curve.

8. A solid attitude and trajectory control engine gas valve stem profile design device, characterized in that: include: The first module is used to give the solid attitude and orbit control engine gas valve nozzle profile curve and target equivalent throat area curve requirements; The second module is used to determine the tangent point between the local stem profile corresponding to the first stem displacement step and the nozzle profile according to the target equivalent throat area curve and the equivalent throat area corresponding to the first stem displacement step on the nozzle convergence section profile curve, and determine the stem profile coordinate point on the local stem profile corresponding to the first stem displacement step near the tangent point by using local linear expansion; The third module is used to calculate the local Taylor expansion slope based on the target equivalent throat area curve and use the binary search method to determine the valve stem surface coordinate point on the local valve stem surface corresponding to the next valve stem displacement step, and continue to iterate recursively until the valve stem displacement reaches the maximum stroke to obtain all valve stem surface coordinate points; The fourth module is used to add a valve stem profile head arc based on all valve stem profile coordinate points to obtain a valve stem profile curve.

9. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that: When the processor executes the computer program, the steps of the solid attitude and orbit control engine gas valve stem profile design method described in claim 1 are implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method for designing the valve stem profile of a solid attitude and orbit control engine gas valve as described in claim 1 are implemented.

Images