CN115859492A - Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine - Google Patents

Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine Download PDF

Info

Publication number
CN115859492A
CN115859492A CN202211161938.2A CN202211161938A CN115859492A CN 115859492 A CN115859492 A CN 115859492A CN 202211161938 A CN202211161938 A CN 202211161938A CN 115859492 A CN115859492 A CN 115859492A
Authority
CN
China
Prior art keywords
valve
curve
profile
valve rod
flow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202211161938.2A
Other languages
Chinese (zh)
Other versions
CN115859492B (en
Inventor
王政涛
武泽平
杨家伟
张�杰
李国盛
张为华
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
National University of Defense Technology
Original Assignee
National University of Defense Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by National University of Defense Technology filed Critical National University of Defense Technology
Priority to CN202211161938.2A priority Critical patent/CN115859492B/en
Publication of CN115859492A publication Critical patent/CN115859492A/en
Application granted granted Critical
Publication of CN115859492B publication Critical patent/CN115859492B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Landscapes

  • Lift Valve (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)

Abstract

The invention discloses a method for designing the actual flow matching of a molded surface of a gas valve of a solid attitude orbit control engine, which is based on a theoretical target flow curve, combines a binary search method, taylor local expansion and the like to obtain a valve rod molded surface curve coordinate point set by recursion, corrects the theoretical target flow curve based on the actual maximum flow of a valve and obtains an actual target flow curve, obtains a corresponding valve rod molded surface coordinate point set by adopting the same valve rod molded surface design method, obtains a valve rod displacement-valve flow curve by computational fluid dynamics simulation, corrects the valve rod molded surface curve coordinate point set according to the error between the valve rod displacement-valve flow curve and the target flow curve, and circularly performs the computational fluid dynamics simulation-valve rod molded surface curve coordinate point set correction until the error meets the design requirement. The invention is applied to the field of solid attitude and orbit control engine design, can obviously improve the effectiveness of a design result and ensure that the linearity of the displacement of the valve rod and the actual flow of the valve meets the design requirement.

Description

Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine
Technical Field
The invention relates to the technical field of design of solid attitude and orbit control engines, in particular to a design method for matching actual flow of molded surfaces of gas valves of a solid attitude and orbit control engine.
Background
The gas type solid attitude control engine is used as an actuating mechanism of the kinetic energy interceptor, has the characteristics of simple structure, safety, reliability and the like, and is particularly suitable for an intercepting weapon system with high safety requirements, such as a space foundation, a sea foundation and the like. The thrust adjustment of a solid attitude control engine depends greatly on the geometric configuration of a valve rod in the valve, the profile of a spray pipe and the relative position between the valve rod and the spray pipe. If the flow of a single valve changes along with the stroke of the valve rod in a nonlinear way, the constant total flow of the valve is difficult to ensure in the movement process of each valve rod, so that the pressure of a combustion chamber changes along with the flow, and the difficulty of adjusting the thrust of the solid attitude and orbit control engine and the complexity of a control system are greatly improved. Therefore, it is highly desirable to develop a valve profile optimization design that aims at linear variation of actual flow of a single valve with the displacement height of a valve rod under the condition of a given nozzle profile, so as to simplify the complexity of a control system as much as possible.
The design method of the valve profile which is commonly used at present comprises the following steps:
valve profile design based on existing solutions: based on the valve profile design result which is relatively close to the design requirement, the design scheme which can meet the requirement is obtained by manually modifying the valve profile by a trial and error method. The method is simple and efficient, is easy to implement, effectively avoids complex operation, needs the participation of engineers with higher engineering project practice experience, is difficult to ensure that the design result is the optimal scheme, and is difficult to meet the requirement on linearity.
The valve profile optimization design based on the intelligent optimization algorithm comprises the following steps: the size parameters of the spray pipe molded surface and the valve rod molded surface are used as design variables, the error between a valve rod displacement-valve equivalent throat area curve and a target curve is used as a target function, and the valve molded surface is optimally designed based on an intelligent optimization algorithm. The method can realize automatic optimization design of the valve profile, and the design result is accurate. However, a parametric model of the profiles of the spray pipe and the valve rod needs to be constructed, and profile control parameters need to be reasonably planned, so that the control of the profile is limited due to too few parameters, and a design result meeting the linearity requirement is difficult to obtain; too many parameters result in high complexity of an optimization model, unacceptable time cost of optimization design and great difficulty in practical application to engineering.
Disclosure of Invention
Aiming at the problems that the theoretical flow and the actual flow of the valve are obviously different and the maximum theoretical flow of the valve cannot be achieved in the process of realizing the linearization of the valve rod displacement and the valve flow of the solid attitude control engine gas valve in the prior art, the invention provides the actual flow matching design method of the molded surface of the solid attitude control engine gas valve, which can realize the design of the molded surface of the valve with higher efficiency, correct the difference between the theoretical flow and the actual flow of the valve, ensure that the linearity of the valve rod displacement-valve flow meets the design requirement and avoid the problem that the valve rod displacement-theoretical flow curve has high linearity but the valve rod displacement-valve flow curve cannot achieve the same linearity.
In order to achieve the aim, the invention provides a method for matching and designing the actual flow of the molded surface of a gas valve of a solid attitude and orbit control engine, which comprises the following steps:
step 1, acquiring a spray pipe profile curve coordinate point set, and initializing a flow curve as a theoretical target flow curve;
step 2, determining a corresponding equivalent throat area curve based on the flow curve, and obtaining a valve rod profile curve coordinate point set meeting the equivalent throat area curve based on a recursive matching design method;
step 3, performing computational fluid dynamics simulation based on the spray pipe profile curve coordinate point set and the valve rod profile curve coordinate point set to obtain the actual maximum flow of the valve, correcting a theoretical target flow curve according to the actual maximum flow of the valve to obtain an actual target flow curve, and updating the flow curve into the actual target flow curve;
step 4, obtaining an updated valve rod profile curve coordinate point set according to the updated flow curve, and then carrying out computational fluid dynamics simulation according to the spray pipe profile curve coordinate point set and the updated valve rod profile curve coordinate point set to obtain a valve rod displacement-valve flow curve;
step 5, judging whether the current valve rod displacement-valve flow curve meets the convergence condition:
if yes, outputting a current valve rod profile curve coordinate point set;
otherwise, updating the flow curve according to the error between the current valve rod displacement-valve flow curve and the actual target flow curve, and returning to the value step 4 to continue iteration.
Compared with the best technology in the prior art, the invention has the advantages that:
1. compared with the valve profile design based on the existing scheme, the design result accuracy is higher;
2. compared with the valve profile optimization design based on the intelligent optimization algorithm, the valve profile optimization design method based on the intelligent optimization algorithm is simpler in design process, higher in design efficiency and capable of ensuring the linearity of a design result under the condition of low calculation cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a flow chart of a design method in an embodiment of the present invention;
FIG. 2 is a schematic diagram of a coordinate point corresponding to a minimum throat area formed by a tangent point of a nozzle profile and a valve stem profile and a translated tangent line and the nozzle profile when the valve is fully closed according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of Taylor local expansion slope search according to an embodiment of the present invention;
FIG. 4 is a schematic illustration of a solid attitude control engine gas valve profile in accordance with an exemplary embodiment of the present invention;
FIG. 5 is a schematic diagram illustrating a comparison of design results of flow matching without correcting a theoretical target flow in an example according to an embodiment of the present invention;
FIG. 6 is a schematic diagram illustrating a comparison of flow matching design results after theoretical target flow is corrected in an example according to an embodiment of the present invention;
FIG. 7 is a graphical comparison of valve stem profile design results in an example embodiment of the present invention;
FIG. 8 is a schematic diagram comparing flow matching design results for a valve stem relative stroke of 8mm in an example of an embodiment of the invention;
FIG. 9 is a comparative graphical illustration of valve stem profile design results for a valve stem having a relative stem travel of 8mm in an example embodiment of the present invention;
the implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the motion situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The embodiment discloses a method for matching and designing actual flow of a molded surface of a gas valve of a solid attitude orbit control engine, which is based on a theoretical target flow curve, combines a binary search method, taylor local expansion and the like to obtain a valve rod molded surface curve coordinate point set by recursion, corrects the theoretical target flow curve based on the actual maximum flow of a valve and obtains an actual target flow curve, obtains a corresponding valve rod molded surface coordinate point set by adopting the same valve rod molded surface design method, obtains a valve rod displacement-valve flow curve by calculating fluid dynamics simulation, corrects the valve rod molded surface curve coordinate point set according to root mean square error between the valve flow curve and the target flow curve, and circularly calculates the fluid dynamics simulation-valve rod molded surface curve coordinate point set correction process until the error meets the design requirements. Compared with other implementation schemes, the method can obviously improve the effectiveness of the design result and ensure that the linearity of the valve rod displacement and the actual flow of the valve meets the design requirement.
Referring to fig. 1, the actual flow matching design method for the solid attitude control engine gas valve profile in the present embodiment specifically includes the following steps 1-5.
Step 1, acquiring the throat diameter of the spray pipe, the radius of a transition arc at the upstream of the throat, a convergence half angle and working pressure
Figure 604704DEST_PATH_IMAGE001
Characteristic propellant speed->
Figure 397080DEST_PATH_IMAGE002
Theoretical target flow curve->
Figure 597117DEST_PATH_IMAGE003
And a convergence error->
Figure 324902DEST_PATH_IMAGE004
. And determining a nozzle profile curve coordinate point set according to the known nozzle throat diameter, the known upstream transition arc radius and the known convergence half angle, namely obtaining different nozzle profile curve coordinate point sets by changing the nozzle throat diameter and/or the upstream transition arc radius and/or the known convergence half angle of the nozzle throat, so as to meet the design requirements of different solid attitude and orbit control engines. Initializing a flow curve pick-up>
Figure 938286DEST_PATH_IMAGE005
Is a theoretical target flow curve, i.e.>
Figure 144139DEST_PATH_IMAGE006
。
And 2, determining a corresponding equivalent throat area curve based on the flow curve, and obtaining a valve rod profile curve coordinate point set meeting the equivalent throat area curve based on a recursive matching design method.
In the specific implementation process, the flow formula of ideal gas one-dimensional isentropic flow can be used
Figure 401945DEST_PATH_IMAGE007
Is calculated to obtainFlow curve->
Figure 159685DEST_PATH_IMAGE008
Corresponding equivalent throat area curve>
Figure 732137DEST_PATH_IMAGE009
I.e. is->
Figure 741681DEST_PATH_IMAGE010
。
In this embodiment, the specific process of obtaining the valve stem profile curve coordinate point set satisfying the equivalent throat area curve based on the recursive matching design method is as follows:
step 2.1, calculating and obtaining a tangent point of the spray pipe molded surface and the valve rod molded surface when the valve is completely closed based on a dichotomy
Figure 978627DEST_PATH_IMAGE011
The specific implementation mode is as follows:
step 2.1.1, obtaining the valve rod displacement in the equivalent throat area curve as
Figure 782635DEST_PATH_IMAGE012
Equivalent throat area of time
Figure 105032DEST_PATH_IMAGE013
, wherein ,
Figure 918267DEST_PATH_IMAGE014
For the relative stroke of the valve rod>
Figure 885086DEST_PATH_IMAGE015
Calculating the step length;
step 2.1.2, searching a tangent point of the spray pipe and the valve rod when the valve is completely closed on the spray pipe profile curve by adopting a bisection method
Figure 719050DEST_PATH_IMAGE016
So that it satisfies the following equation:
Figure 528743DEST_PATH_IMAGE017
wherein ,
Figure 145669DEST_PATH_IMAGE018
at a point->
Figure 826050DEST_PATH_IMAGE019
Along a line tangent to the nozzle>
Figure 237439DEST_PATH_IMAGE020
Axial negative direction translation pick>
Figure 409795DEST_PATH_IMAGE021
The minimum throat area formed by the rear part and the spray pipe profile is as follows:
Figure 423887DEST_PATH_IMAGE022
wherein ,
Figure 365298DEST_PATH_IMAGE023
is a spray pipe profile curve coordinate point set and is used for collecting and combining>
Figure 806644DEST_PATH_IMAGE024
Respectively is a valve rod profile curve coordinate point set and is used for collecting and combining>
Figure 466295DEST_PATH_IMAGE025
Concentrating the coordinate point of the spray pipe profile curvenThe horizontal coordinate value of the point is greater or less>
Figure 304586DEST_PATH_IMAGE026
Centralizing the curve coordinate points of the valve rod profilepThe abscissa value of the point;
step 2.2, the upper point of the molded surface of the spray pipe is dotted
Figure 366083DEST_PATH_IMAGE027
Is located on the tangent line edge->
Figure 978330DEST_PATH_IMAGE028
Axial negative direction translation pick>
Figure 859699DEST_PATH_IMAGE029
The back straight line is used as a valve rod local molded surface curve, and a coordinate point corresponding to the minimum throat area formed by the molded surface of the spray pipe on the valve rod local molded surface curve is solved and obtained>
Figure 215594DEST_PATH_IMAGE030
Will point out>
Figure 866018DEST_PATH_IMAGE031
And a point->
Figure 914745DEST_PATH_IMAGE032
Sequentially adding a valve rod profile curve coordinate point set and initializing recursion algebra>
Figure 283410DEST_PATH_IMAGE033
That is, as shown in FIG. 2, the transition arc in FIG. 2 is the transition arc of the curve of the profile of the nozzle, and the arc tangent line is the point on the profile of the nozzle which is greater or less than the predetermined value>
Figure 442996DEST_PATH_IMAGE034
The local profile of the valve rod is the point on the profile of the spray pipe>
Figure 947926DEST_PATH_IMAGE035
Is located on the tangent line edge->
Figure 308500DEST_PATH_IMAGE036
Negative direction shaft translation>
Figure 289095DEST_PATH_IMAGE037
The latter straight line;
step 2.3, obtaining the valve rod displacement in the equivalent throat area curve as
Figure 127738DEST_PATH_IMAGE038
Equivalent temporal throat area->
Figure 877388DEST_PATH_IMAGE039
Searching for a lung satisfying equivalent throat area based on dichotomy>
Figure 408863DEST_PATH_IMAGE040
In the valve stem profile partial taylor expansion line slope>
Figure 486541DEST_PATH_IMAGE041
And forming equivalent throat area on the local Taylor expansion straight line of the current valve rod profile and the spray pipe profile
Figure 253509DEST_PATH_IMAGE042
As a new point>
Figure 733031DEST_PATH_IMAGE043
And combining the new point>
Figure 297392DEST_PATH_IMAGE044
Adding a valve rod profile curve coordinate point set, referring to fig. 3, the specific implementation mode is as follows:
step 2.3.1, initialize the slope search interval
Figure 127945DEST_PATH_IMAGE045
And obtaining the valve rod displacement of ^ in the equivalent throat area curve>
Figure 167445DEST_PATH_IMAGE046
Equivalent throat area in time>
Figure 32633DEST_PATH_IMAGE047
, wherein ,
Figure 640332DEST_PATH_IMAGE048
For the maximum value of the slope search, is greater or less than>
Figure 82815DEST_PATH_IMAGE049
The minimum value searched for the slope;
step 2.3.2, order point
Figure 801372DEST_PATH_IMAGE050
For local flare point, search slope ^ and ^ in slope search interval by dichotomy>
Figure 521066DEST_PATH_IMAGE051
And the slope is->
Figure 424300DEST_PATH_IMAGE052
And passes through the partial expansion point->
Figure 963866DEST_PATH_IMAGE053
Is taken as the current partial deployment line, wherein the slope @>
Figure 876327DEST_PATH_IMAGE054
Satisfies the following conditions: the minimum throat area formed by the current local expansion straight line and the molded surface of the spray pipe is equal to the target equivalent throat area (based on the current valve rod displacement)>
Figure 184949DEST_PATH_IMAGE055
；
Step 2.3.3, the minimum throat area formed by the local Taylor expansion straight line of the current valve rod molded surface and the molded surface of the spray pipe is equal to the equivalent throat area
Figure 400030DEST_PATH_IMAGE056
As a new point->
Figure 285946DEST_PATH_IMAGE057
And will pick up the point>
Figure 611885DEST_PATH_IMAGE058
Adding a valve rod profile curve coordinate point set;
step 2.4, convergence judgment: order to
Figure 165226DEST_PATH_IMAGE059
Judgment is made>
Figure 285629DEST_PATH_IMAGE060
Whether or not:
if yes, entering step 2.5;
otherwise, returning to the step 2.3 to continue iteration;
step 2.5, according to the existing valve rod profile coordinate point data concentrated by the valve rod profile curve coordinate point, increasing the circle center as
Figure 924421DEST_PATH_IMAGE061
Radius is->
Figure 54051DEST_PATH_IMAGE062
Wherein, is taken on>
Figure 71685DEST_PATH_IMAGE063
The slope of the local Taylor expansion line of the valve stem profile at the last iteration of step 2.3, is->
Figure 750273DEST_PATH_IMAGE064
、
Figure 751727DEST_PATH_IMAGE065
Is the point in the last iteration of step 2.3 @>
Figure 278523DEST_PATH_IMAGE066
The horizontal and vertical coordinate values of (a);
and 2.6, adding the coordinate point set on the circular arc in the step 2.5 into the valve rod profile curve coordinate point set, and outputting the valve rod profile curve coordinate point set.
In this embodiment, the slope search interval in step 2.3.1 is
Figure 681822DEST_PATH_IMAGE067
。
In the specific implementation process, the specific search process using the bisection method search in step 2.1.2 and step 2.3.2 is a conventional technical means in the field, and therefore details thereof are not repeated in this embodiment.
Step 3, performing computational fluid dynamics simulation based on the spray pipe profile curve coordinate point set and the valve rod profile curve coordinate point set to obtain the actual maximum flow of the valve, correcting a theoretical target flow curve according to the actual maximum flow of the valve to obtain an actual target flow curve, and updating the flow curve into the actual target flow curve, wherein the specific implementation process comprises the following steps:
step 3.1, importing the spray pipe profile curve coordinate point set and the valve rod profile curve coordinate point set into grid division software to complete non-structural grid division and grid file output;
step 3.2, importing the grid file output by the grid division software into computational fluid dynamics simulation software, and obtaining the actual maximum flow of the valve by solving a two-dimensional axisymmetric conservation type Navier-Stokes equation of compressible flow
Figure 675186DEST_PATH_IMAGE068
；
Step 3.3, correcting the theoretical target flow curve according to the actual maximum flow of the valve to obtain an actual target flow curve, which specifically comprises the following steps:
Figure 757412DEST_PATH_IMAGE069
Figure 494424DEST_PATH_IMAGE070
in the formula ,
Figure 486650DEST_PATH_IMAGE071
for the actual target flow curve, is>
Figure 244391DEST_PATH_IMAGE072
In order to be a theoretical target flow rate curve,
Figure 954858DEST_PATH_IMAGE073
is the actual maximum flow of the valve>
Figure 354615DEST_PATH_IMAGE074
Is the theoretical maximum flow of the valve;
and 3.4, updating the flow curve into an actual target flow curve.
Step 4, obtaining an updated valve rod profile curve coordinate point set according to the updated flow curve, and then performing computational fluid dynamics simulation according to the spray pipe profile curve coordinate point set and the updated valve rod profile curve coordinate point set to obtain a valve rod displacement-valve flow curve, wherein the specific implementation process is as follows:
step 4.1, obtaining an updated valve rod profile curve coordinate point set according to the updated flow curve by adopting the same method as the step 2;
step 4.2, importing the spray pipe profile curve coordinate point set and the updated valve rod profile curve coordinate point set into meshing software to complete non-structural meshing and new mesh file output;
step 4.3, importing a new grid file output by the grid division software into computational fluid dynamics simulation software, and obtaining a valve rod displacement-valve flow curve by solving a compressible flowing two-dimensional axisymmetric conservation type Navier-Stokes equation
Figure 466928DEST_PATH_IMAGE075
。
Step 5, judging whether the current valve rod displacement-valve flow curve meets the convergence condition, namely judging
Figure 536515DEST_PATH_IMAGE076
Whether or not, wherein>
Figure 858912DEST_PATH_IMAGE077
For the number of steps of displacement of the valve stem, is>
Figure 672147DEST_PATH_IMAGE078
Is the first in the valve flow curveiThe valve rod is displaced to correspond to the valve flow>
Figure 904545DEST_PATH_IMAGE079
Is a reality ofIn the target flow rate curveiThe flow of the valve corresponding to the displacement of each valve rod is combined>
Figure 4088DEST_PATH_IMAGE080
To converge the error:
if yes, the current valve rod displacement-valve flow curve is obtained
Figure 689148DEST_PATH_IMAGE081
Outputting a corresponding valve rod profile curve coordinate point set as a design result;
if the flow curve is not established, updating the flow curve based on the error between the current valve rod displacement-valve flow curve and the actual target flow curve, returning to the value step 4 to continue iteration, wherein the updating process of the flow curve is that
Figure 430707DEST_PATH_IMAGE082
。/>
The present invention is further described below with reference to specific examples.
Fig. 4 is a geometric configuration of a solid attitude and orbit control engine gas valve, and some design parameters and operating parameters of the solid attitude and orbit control engine gas valve are shown in table 1, then the specific embodiment of the molded surface design of the valve stem of the solid attitude and orbit control engine gas valve is as follows:
(1) A binary search method and Taylor local development recursion are adopted to obtain a valve rod profile coordinate point set;
1.1 Initializing a profile tangent point search interval as a transition arc boundary, calculating a tangent point of the spray pipe profile and the valve rod profile based on a binary search method, and updating a valve rod profile coordinate point set;
1.2 Update a set of existing valve stem profile coordinate points based on the calculated step size;
1.3 Computing a Taylor local expansion slope based on a binary search method, solving the equivalent throat area and then performing recursion to obtain a next local expansion point computing point;
1.4 Convergence determination: if the target curve is calculated, turning to the step 1.5), otherwise, turning to the step 1.2) to continue recursive calculation;
1.5 Increasing the valve stem profile head arc;
1.6 Outputting a valve rod profile curve coordinate point set corresponding to the target flow curve;
(2) Calling gridding division software to output an unstructured gridding file;
(3) Calling computational fluid dynamics simulation software to obtain the actual maximum flow of the valve;
(4) Correcting the theoretical target flow curve according to the actual maximum flow of the valve to obtain an actual target flow curve;
(5) Obtaining a valve rod profile curve and a spray pipe profile curve coordinate point set meeting the flow curve requirement according to the method in the step (1);
(6) Calling gridding division software to output an unstructured gridding file;
(7) Calling computational fluid dynamics simulation software to obtain a valve rod displacement-valve flow curve;
(8) And (3) convergence judgment: and (4) if the root mean square error of the valve flow curve and the target flow curve meets the design requirement, outputting a valve rod profile curve and a spray pipe profile curve coordinate point set meeting the linearity requirement, otherwise, updating the flow curve requirement according to the error of the flow curve and the actual target flow curve, and turning to the step (5) to continue iteration.
TABLE 1 solid attitude and orbit control engine gas valve part design parameters and working parameters
Figure 517612DEST_PATH_IMAGE083
Based on the parameters, the design of the valve rod profile without correcting the theoretical target flow and under the condition of correcting the theoretical target flow is developed aiming at the state that the relative stroke of the valve rod is 4 mm. As shown in fig. 5, due to flow loss, the matching design flow obtained based on the recursive optimization method cannot be completely matched with the theoretical target flow, and the flow loss also causes that the maximum theoretical flow of the valve cannot be achieved, and if the theoretical target flow is not modified, the linearity of the gas valve near the maximum flow is difficult to ensure;
the flow matching design result after the theoretical target flow is corrected is shown in fig. 6, at this moment, the flow matching design result is basically consistent with the target flow, and meanwhile, because the theoretical flow and the actual flow of the valve are different, the molded surface design result based on the recursive optimization method cannot really realize the linear change of the valve flow along with the displacement height of the valve rod;
the valve rod profile design result is shown in fig. 7, and the gas valve profile design result based on numerical simulation and the gas valve profile design result based on recursive optimization are also obviously different;
aiming at the state that the relative stroke of the valve rod is 8mm, the valve rod profile design under the theoretical target flow correction is developed, as shown in fig. 8 and 9, the simulation result shows that the linearity of the flow matching design result after the theoretical target flow correction is better, and the gas valve profile design result based on numerical simulation and the gas valve profile design result based on recursion optimization have obvious difference;
in conclusion, the valve rod profile obtained by the numerical simulation-based actual flow matching design method of the solid attitude and orbit control engine gas valve profile can ensure linear change of valve rod displacement and valve flow height, and the design result meets the design requirement.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims (9)

1. A method for matching and designing actual flow of a molded surface of a gas valve of a solid attitude and orbit control engine is characterized by comprising the following steps:
step 1, acquiring a spray pipe profile curve coordinate point set, and initializing a flow curve as a theoretical target flow curve;
step 2, determining a corresponding equivalent throat area curve based on the flow curve, and obtaining a valve rod profile curve coordinate point set meeting the equivalent throat area curve based on a recursive matching design method;
step 3, performing computational fluid dynamics simulation based on the spray pipe profile curve coordinate point set and the valve rod profile curve coordinate point set to obtain the actual maximum flow of the valve, correcting a theoretical target flow curve according to the actual maximum flow of the valve to obtain an actual target flow curve, and updating the flow curve into the actual target flow curve;
step 4, obtaining an updated valve rod profile curve coordinate point set according to the updated flow curve, and performing computational fluid dynamics simulation according to the spray pipe profile curve coordinate point set and the updated valve rod profile curve coordinate point set to obtain a valve rod displacement-valve flow curve;
step 5, judging whether the current valve rod displacement-valve flow curve meets the convergence condition:
if so, outputting a current valve rod profile curve coordinate point set;
otherwise, updating the flow curve according to the error between the current valve rod displacement-valve flow curve and the actual target flow curve, and returning to the step 4 to continue iteration.
2. The method for designing actual flow matching of a solid attitude and orbit control engine gas valve profile according to claim 1, wherein in step 2, the set of valve stem profile curve coordinate points that satisfy the equivalent throat area curve is obtained based on a recursive matching design method, specifically:
step 2.1, calculating and obtaining a tangent point of the spray pipe molded surface and the valve rod molded surface when the valve is completely closed based on a dichotomy
Figure 668347DEST_PATH_IMAGE002
；
Step 2.2, solving to obtain the upper point of the molded surface of the spray pipe
Figure 319908DEST_PATH_IMAGE003
Is located on the tangent line edge->
Figure 693120DEST_PATH_IMAGE005
Axial negative direction translation pick>
Figure 822750DEST_PATH_IMAGE007
Coordinate point which corresponds to the minimum throat area formed by the rear nozzle profile>
Figure 105964DEST_PATH_IMAGE008
Will point out>
Figure 787481DEST_PATH_IMAGE009
And point
Figure 523356DEST_PATH_IMAGE010
Sequentially adding a valve rod profile curve coordinate point set and initializing recursion algebra>
Figure 315732DEST_PATH_IMAGE011
, wherein ,
Figure 719031DEST_PATH_IMAGE012
Calculating the step length;
step 2.3, obtaining the valve rod displacement in the equivalent throat area curve as
Figure 181236DEST_PATH_IMAGE014
Equivalent temporal throat area->
Figure 794620DEST_PATH_IMAGE015
Search for a satisfaction of equivalent throat area based on dichotomy>
Figure 474DEST_PATH_IMAGE016
In the valve stem profile partial taylor expansion line slope>
Figure 117334DEST_PATH_IMAGE018
And the minimum throat area formed by the local Taylor expansion straight line of the current valve rod profile and the spray pipe profile is equal to the equivalent throat area>
Figure 281599DEST_PATH_IMAGE019
As new coordinate pointsPoint->
Figure 992066DEST_PATH_IMAGE020
And will pick up the point>
Figure 860665DEST_PATH_IMAGE022
Adding a set of valve stem profile curve coordinate points, wherein>
Figure 238557DEST_PATH_IMAGE023
Is the relative stroke of the valve rod;
step 2.4, order
Figure 167199DEST_PATH_IMAGE024
Is judged according to>
Figure 364962DEST_PATH_IMAGE025
Whether or not:
if yes, entering step 2.5;
otherwise, returning to the step 2.3 to continue iteration;
step 2.5, according to the valve rod profile curve coordinate points, concentrating the existing valve rod profile coordinate points, and increasing the circle center as
Figure 178197DEST_PATH_IMAGE026
Radius is->
Figure 266720DEST_PATH_IMAGE027
Wherein, is taken on>
Figure 772788DEST_PATH_IMAGE028
The slope of the local Taylor expansion line of the valve stem profile at the last iteration of step 2.3, is->
Figure 316902DEST_PATH_IMAGE029
、
Figure 933828DEST_PATH_IMAGE031
As the point of the last iteration of step 2.3
Figure 755153DEST_PATH_IMAGE032
The horizontal and vertical coordinate values of (a);
and 2.6, adding the coordinate point set on the circular arc in the step 2.5 into the valve rod profile curve coordinate point set, and outputting the valve rod profile curve coordinate point set.
3. The method of matching design for actual flow of a profile of a gas valve for a solid attitude control engine of claim 2, wherein in step 2.1, the tangent point between the profile of the nozzle and the profile of the valve stem when the valve is fully closed is obtained based on a dichotomy calculation
Figure 556756DEST_PATH_IMAGE034
The method specifically comprises the following steps:
step 2.1.1, obtaining the valve rod displacement in the equivalent throat area curve as
Figure 463532DEST_PATH_IMAGE035
Equivalent temporal throat area->
Figure 618570DEST_PATH_IMAGE036
；
Step 2.1.2, searching a tangent point of the spray pipe and the valve rod when the valve is completely closed on the spray pipe profile curve by adopting a bisection method
Figure 684615DEST_PATH_IMAGE037
So that it satisfies the following equation:
Figure 532485DEST_PATH_IMAGE038
wherein ,
Figure 51191DEST_PATH_IMAGE039
at a point->
Figure 9920DEST_PATH_IMAGE040
Along a line tangent to the nozzle>
Figure 540259DEST_PATH_IMAGE041
Negative direction shaft translation>
Figure 418085DEST_PATH_IMAGE042
The minimum throat area formed by the rear part and the spray pipe profile is as follows:
Figure 299453DEST_PATH_IMAGE043
wherein ,
Figure 186507DEST_PATH_IMAGE045
is a spray pipe profile curve coordinate point set and is used for collecting and combining>
Figure 836931DEST_PATH_IMAGE046
Respectively are a set of valve rod profile curve coordinate points,
Figure 761024DEST_PATH_IMAGE048
is a spray pipe molded surface curve coordinate point centralizationnThe horizontal coordinate value of the point is greater or less>
Figure 254323DEST_PATH_IMAGE050
Centralizing the curve coordinate points of the valve rod profilepThe abscissa value of the point.
4. The method for matching and designing actual flow of a solid attitude control engine gas valve profile according to claim 2, wherein step 2.3 specifically comprises:
step 2.3.1, initialize the slope search interval
Figure 554854DEST_PATH_IMAGE051
And obtaining an equivalent throat areaThe valve rod in the curve is displaced by->
Figure 452927DEST_PATH_IMAGE052
Equivalent temporal throat area->
Figure 282343DEST_PATH_IMAGE054
, wherein ,
Figure 403883DEST_PATH_IMAGE055
For the maximum value of the slope search, is greater or less than>
Figure 367160DEST_PATH_IMAGE056
The minimum value searched for the slope;
step 2.3.2, order point
Figure 992176DEST_PATH_IMAGE057
Search for slope ^ greater or lesser than in slope search interval by dichotomy for local flare point>
Figure 382706DEST_PATH_IMAGE059
And the slope is->
Figure 460383DEST_PATH_IMAGE061
And passes through the partial expansion point->
Figure 368297DEST_PATH_IMAGE062
Is taken as the current partial deployment line, wherein the slope @>
Figure 972453DEST_PATH_IMAGE063
Satisfies the following conditions: the minimum throat area formed by the current local expansion straight line and the molded surface of the spray pipe is equal to the target equivalent throat area (based on the current valve rod displacement)>
Figure 409251DEST_PATH_IMAGE064
；
Step 2.3.3, will presentThe minimum throat area formed by the valve rod profile and the spray pipe profile on the local Taylor expansion straight line is equal to the equivalent throat area
Figure 364437DEST_PATH_IMAGE065
As a new point->
Figure 544883DEST_PATH_IMAGE066
And will pick up the point>
Figure 144492DEST_PATH_IMAGE068
And adding a valve rod profile curve coordinate point set.
5. The actual flow matching design method for a solid attitude and orbit control engine gas valve profile according to any one of claims 1 to 4, characterized in that in step 3, the actual maximum flow of the valve is obtained by performing computational fluid dynamics simulation based on a nozzle profile curve coordinate point set and a valve stem profile curve coordinate point set, specifically:
guiding the spray pipe profile curve coordinate point set and the valve rod profile curve coordinate point set into meshing software to complete non-structural meshing and outputting a meshing file;
introducing the grid file into computational fluid dynamics simulation software, and obtaining the actual maximum flow of the valve by solving a two-dimensional axisymmetric conservation type Navier-Stokes equation of compressible flow
Figure 876824DEST_PATH_IMAGE070
。
6. The method for matching and designing the actual flow of the molded surface of the gas valve of the solid attitude and orbit control engine according to claim 5, wherein in the step 3, the theoretical target flow curve is corrected according to the actual maximum flow of the valve to obtain an actual target flow curve, which is specifically as follows:
Figure 929094DEST_PATH_IMAGE071
Figure 37864DEST_PATH_IMAGE073
in the formula ,
Figure 491979DEST_PATH_IMAGE074
for the actual target flow curve, is>
Figure 536159DEST_PATH_IMAGE076
Is a theoretical target flow curve, is selected>
Figure 200358DEST_PATH_IMAGE078
Is the actual maximum flow of the valve>
Figure 988186DEST_PATH_IMAGE080
Is the theoretical maximum flow of the valve.
7. The method for matching and designing actual flow of a profile of a gas valve of a solid attitude and orbit control engine according to any one of claims 1 to 4, wherein in step 4, a valve stem displacement-valve flow curve is obtained by performing computational fluid dynamics simulation on the nozzle profile curve coordinate point set and the updated valve stem profile curve coordinate point set, and specifically:
importing the spray pipe profile curve coordinate point set and the updated valve rod profile curve coordinate point set into meshing software to complete non-structural meshing and new mesh file output;
introducing a new grid file into computational fluid dynamics simulation software, and obtaining a valve rod displacement-valve flow curve by solving a compressible flowing two-dimensional axisymmetric conservation type Navier-Stokes equation
Figure 441949DEST_PATH_IMAGE081
。
8. A method for matching and designing actual flow of a solid attitude control engine gas valve profile according to any one of claims 1 to 4, wherein in step 5, said convergence condition is:
Figure 391450DEST_PATH_IMAGE082
in the formula ,
Figure 418312DEST_PATH_IMAGE083
for the number of steps of displacement of the valve stem, is>
Figure 868885DEST_PATH_IMAGE084
Is the first in the valve flow curveiThe valve rod is displaced to correspond to the valve flow>
Figure 297592DEST_PATH_IMAGE085
Is the first in the actual target flow curveiThe valve rod is displaced to correspond to the valve flow>
Figure 542629DEST_PATH_IMAGE086
Is the convergence error.
9. The method for matching design of actual flow for a solid attitude control engine gas valve profile according to any one of claims 1 to 4, wherein in step 5, said updating the flow curve based on the error between the current valve stem displacement-valve flow curve and the actual target flow curve, specifically:
Figure 322366DEST_PATH_IMAGE087
in the formula ,
Figure 186417DEST_PATH_IMAGE088
is a flow curve->
Figure 328685DEST_PATH_IMAGE089
For an actual target flow curve>
Figure 151148DEST_PATH_IMAGE090
Is a valve stem displacement-valve flow curve. />
CN202211161938.2A 2022-09-23 2022-09-23 Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine Active CN115859492B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211161938.2A CN115859492B (en) 2022-09-23 2022-09-23 Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211161938.2A CN115859492B (en) 2022-09-23 2022-09-23 Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine

Publications (2)

Publication Number Publication Date
CN115859492A true CN115859492A (en) 2023-03-28
CN115859492B CN115859492B (en) 2023-05-05

Family

ID=85661096

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211161938.2A Active CN115859492B (en) 2022-09-23 2022-09-23 Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine

Country Status (1)

Country Link
CN (1) CN115859492B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117952023A (en) * 2024-03-26 2024-04-30 中国人民解放军国防科技大学 Design method for sectional flow regulation valve rod profile of solid attitude and orbit control engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110645118A (en) * 2019-10-31 2020-01-03 湖北航天技术研究院总体设计所 Equal-flow solid attitude control thrust device and design method
CN114861352A (en) * 2022-05-05 2022-08-05 中国人民解放军国防科技大学 Method and device for designing valve rod profile of solid attitude and orbit control engine gas valve

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110645118A (en) * 2019-10-31 2020-01-03 湖北航天技术研究院总体设计所 Equal-flow solid attitude control thrust device and design method
CN114861352A (en) * 2022-05-05 2022-08-05 中国人民解放军国防科技大学 Method and device for designing valve rod profile of solid attitude and orbit control engine gas valve

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
YONG WANG等: "Flow and thrust characteristics of an expansion-deflection duall-bell nozzle" *
王鹏宇等: "多工况下变推力固体发动机喉栓喷管型面一体化优化设计" *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117952023A (en) * 2024-03-26 2024-04-30 中国人民解放军国防科技大学 Design method for sectional flow regulation valve rod profile of solid attitude and orbit control engine
CN117952023B (en) * 2024-03-26 2024-06-07 中国人民解放军国防科技大学 Design method for sectional flow regulation valve rod profile of solid attitude and orbit control engine

Also Published As

Publication number Publication date
CN115859492B (en) 2023-05-05

Similar Documents

Publication Publication Date Title
CN115859492A (en) Actual flow matching design method for molded surface of gas valve of solid attitude and orbit control engine
CN112346359B (en) Direct force-aerodynamic force composite control numerical simulation method based on CFD and RBD coupling
CN113642122B (en) Single-shot-table-based remote interception emission data acquisition method and system
CN111191359B (en) Method for constructing space killer zone model of air-defense missile and calculating shooting data
CN110617744B (en) Carrier rocket guiding method
CN109379780B (en) Wireless sensor network positioning method based on self-adaptive differential evolution algorithm
CN111079290A (en) Engine model correction method based on improved multivariate cosmic algorithm
CN112231835B (en) Thrust performance and deflection efficiency integrated vectoring nozzle outlet area optimization method
CN112528420B (en) Dynamic boundary condition switching method for jet flow time sequence control simulation
CN114440711B (en) Four-stage solid carrier rocket trajectory optimization method based on particle swarm optimization
CN114861352A (en) Method and device for designing valve rod profile of solid attitude and orbit control engine gas valve
CN113779704B (en) Multi-target optimization method for throat plug type variable thrust solid rocket engine nozzle profile
CN112131670A (en) Aero-engine model iterative algorithm based on hybrid adaptive differential evolution
CN115828412A (en) Single-chamber double-thrust solid rocket engine proportioning parameter design method considering outer ballistic constraint
CN112711816A (en) Flight projectile trajectory correction method based on meteorological grid
CN114611416A (en) LS-SVM modeling method for nonlinear unsteady aerodynamic characteristics of missile
CN115906286A (en) Rocket design method and device with coupled inner and outer trajectories, electronic equipment and storage medium
CN106021835B (en) A kind of flight path design method towards optimal scouting
CN113076610A (en) Design method of binary adjustable air inlet channel
CN113359819A (en) Optimal guidance law with collision angle constraint and acceleration limitation
CN110220414B (en) Coincidence method in terminal guided projectile firing plan
CN114935277B (en) Online planning method for ideal trajectory of gliding Cheng Zhidao shell
CN111737815B (en) Flight system drop point error correction method based on dimensionless form
CN110457647B (en) Method for estimating bullet encounter time of rotating missile
CN108717257A (en) A kind of PID active engine mount control methods based on particle group optimizing

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant