CN115506918A - Combined charging and combustion surface design method for high-thrust-ratio three-stage solid engine - Google Patents
Combined charging and combustion surface design method for high-thrust-ratio three-stage solid engine Download PDFInfo
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- 239000007787 solid Substances 0.000 title claims abstract description 58
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 50
- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000013461 design Methods 0.000 title claims abstract description 32
- 239000003380 propellant Substances 0.000 claims abstract description 43
- 230000001133 acceleration Effects 0.000 claims abstract description 20
- 238000012546 transfer Methods 0.000 claims abstract description 14
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- 239000003814 drug Substances 0.000 claims abstract description 8
- 230000000149 penetrating effect Effects 0.000 claims abstract description 8
- 239000002131 composite material Substances 0.000 claims abstract description 6
- 239000004449 solid propellant Substances 0.000 claims description 17
- 239000002360 explosive Substances 0.000 claims description 13
- 235000013372 meat Nutrition 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 4
- 239000000843 powder Substances 0.000 claims 1
- 238000013507 mapping Methods 0.000 abstract description 3
- 238000009841 combustion method Methods 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 7
- 238000011056 performance test Methods 0.000 description 3
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- 239000003153 chemical reaction reagent Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention relates to a combined charging and combustion surface design method for a three-stage solid engine with a high thrust ratio. Sequentially and axially arranging a first-stage grain, a second-stage grain and a third-stage grain according to the combustion direction; the first-stage grain is a cylinder, and a non-penetrating first cavity is arranged at the axis; and the transfer surface between the first-stage medicine column and the second-stage medicine column is an ellipsoid surface. The take-off grade charging adopts high-burning-rate propellant, the endurance grade charging adopts low-burning-rate propellant, the acceleration grade charging adopts medium-burning-rate propellant, and the charging transition sections are connected in a bonding mode. And realizing the optimal design of the combustion surface of the composite charging transition section based on a mapping method and a parallel layer combustion method. The combined charging method is suitable for combined charging design of the multi-thrust solid rocket engine.
Description
Technical Field
The invention relates to a high-thrust-ratio three-stage solid engine combined charge and combustion surface design method, which is mainly used for multi-thrust solid rocket engine combined charge design and mainly relates to the fields of solid rocket engine combined charge design technology, complex-structure propellant charge combustion surface design technology and the like.
Background
Solid rocket motors are a power source for solid rocket weapons. The geometry of the propellant charge of the solid rocket engine determines the dynamic process of propellant combustion and finally determines the time-thrust curve of the solid rocket weapon. Therefore, the design work of the grain geometry is one of the core tasks of solid rocket engine design.
The operational requirements of solid rocket weapons dictate that the ideal thrust-time curve is often a three-stage thrust curve "launch-endurance-acceleration" wherein the launch section requires relatively more thrust, the endurance stage requires relatively less thrust, and the final acceleration requires relatively more thrust.
In the design process of the engine, the magnitude of the thrust and the dynamic change process cannot be directly designed, and the design of the charging geometric structure and the combustion area is required to be indirectly realized. The larger the combustion surface area at the present time, the larger the thrust. The solid propellant charge burns layer by layer during the engine operation, and each burning of one layer will cause the combustion area to change at the next moment, and the change process of the charge combustion surface in the process is very complicated and is accompanied by the change of the topological structure.
Due to the complexity of the layer-by-layer combustion phenomenon of the solid propellant charge and the limitation on the overall shape and size of the charge, in engineering practice, it is difficult to obtain a charge geometrical structure matched with a launching-endurance-acceleration thrust curve by a common empirical design method, and in the past, the charge combustion surface is changed by adjusting the charge structure to realize thrust change.
The method realizes the emitter-grade high-thrust work by depending on an initial large combustion surface structure, and realizes the endurance-grade low-thrust work by depending on a relatively small combustion surface after the large combustion surface is burnt out. However, the method can only realize two-stage thrust adjustment, has a small thrust adjustment ratio, generally realizes the adjustment of the thrust from large to small, and cannot meet the adjustment requirement of a high-performance weapon system on the multi-stage thrust.
Disclosure of Invention
The invention aims to provide a high-thrust-ratio three-stage solid engine combined charge and combustion surface design method, which meets the requirements of engine launching, endurance and acceleration on the large thrust ratio of charge; the residual explosive between stages can be effectively reduced, and the stable and reliable transfer of the ballistic trajectory in the explosive is realized.
In order to achieve the purpose, the technical scheme adopted by the invention comprises the following steps:
a combined charge of a three-stage solid engine with high thrust ratio is provided with a primary charge column, a secondary charge column and a three-stage charge column which are sequentially and axially connected in the combustion direction;
the first-stage grain is a cylinder, and a non-penetrating first cavity is arranged at the axis;
and the transfer surface between the first-stage medicine column and the second-stage medicine column is an ellipsoid surface.
Optionally, the first-stage grain penetrates through the first cavity from the end, the bottom of the first cavity is a blind hole, and the rear end of the blind hole is connected with a first transfer surface;
the first cavity is a star-shaped cavity.
Optionally, the length-to-diameter ratio of the ellipsoid is 2.
Optionally, the cross-sectional shape of the first cavity is a 6-8 star shape.
Optionally, the secondary explosive column is a cylinder; the third-level grain is a cylinder, a second cavity penetrating through the axis is arranged at the axis, and the second cavity is a star-shaped cavity.
Optionally, the cross-sectional shape of the second cavity is a 6-8 star.
Optionally, the third-stage grain is a cylinder, the second transition surface is a second transition interface with the second-stage grain, and the second transition surface is an ellipsoid surface, an arc surface or a vertical surface.
A high-thrust-ratio three-stage solid engine combined charge combustion surface design method is disclosed, wherein the high-thrust-ratio three-stage solid engine combined charge is any one of the high-thrust-ratio three-stage solid engine combined charges; the primary explosive column is prepared by adopting a propellant A; the secondary explosive column is prepared by adopting a propellant B; the third-level grain is prepared by adopting a propellant C;
the design method specifically comprises the following steps:
step 1: selecting the diameter D of the solid rocket engine based on the overall performance index requirement of the solid rocket weapon c And the ideal time-thrust curve, F, of the solid engine to be designed 1 、F e And F a Respectively representing the thrust required by launching, endurance and acceleration stages, and the required working time is T 1 、T e And T a ；F e ＜F a ＜F 1 ；
Step 2: selecting an end face combustion solid propellant A suitable for a cruising stage to obtain the throat area A of the engine spray pipe t Such that a face combustion charge produced on the basis of propellant A, when operating in an engine, generates a thrust force F e (ii) a Obtaining an actual thrust coefficient C F ；
And 3, step 3: calculating the pressure of the combustion chamber of the solid engine in three working stages of launching, endurance and acceleration under ideal conditions, and calculating the ideal pressure P in the launching stage 1 ＝F 1 /(C F ·A t ) Ideal pressure P in endurance phase e ＝F e /(C F ·A t ) Ideal pressure P in acceleration phase a ＝F a /(C F ·A t )；
And 4, step 4: considering the diameter D of the solid rocket engine c Throat area A t And the actual thrust coefficient C F Selecting a solid propellant B suitable for the launch phase, designing the star-shaped solid propellant charge such that the designed star-shaped charge based on propellant B has a stable working time T 1 Thrust is as great as F 1 ；
And 5: modifying the geometric structure of the star-shaped charge, and modifying the direction of the star-shaped charge far away from the spray pipe into a blind hole; the front end face of the blind hole and the side face of the star-shaped charge are in transition by using an ellipsoid, and the ratio of the major axis to the minor axis of the ellipsoid is about 2; the thickness of the blind hole is the same as that of the star-shaped charged meat;
step 6: drawing a two-dimensional change track of the combustion surface of the blind-hole star-shaped charge designed in the previous step in the working process based on a drawing method and a parallel layer combustion rule until the top end of the star-shaped charge with the blind hole burns to the outer wall surface of the charge, and recording the characteristic charge combustion surface S on the cross section at the moment 1 ；
And 7: curved surface S obtained in the above step 1 As the transfer surface of the first-stage grain and the second-stage grain; duration T of endurance period in consideration of requirements e Ideal pressure P for endurance section e And the burning rate parameter of the propellant A, and calculating the meat thickness L of the propellant which should be possessed by the end-burning charge in the endurance period e ；
And step 8: selecting a solid propellant C suitable for the acceleration stage, wherein the solid propellant C is in a star-shaped charge structure and meets the thrust requirement F of the acceleration stage as much as possible a And operating time requirement T a The initial combustion surface of the star-shaped charge with the blind hole designed in the step is recorded as S a 。
The invention discloses combined charge of a high-thrust-ratio three-stage solid engine, which is designed by adopting the design method of the combined charge combustion surface of the high-thrust-ratio three-stage solid engine.
The invention has the advantages that:
the combined charge of the high-thrust-ratio three-stage thrust solid rocket engine provided by the invention adopts a propellant combination form with different burning rates of low, medium and high, and meets the requirements of engine launching, endurance and acceleration on the large thrust ratio of charge; the combustion surface design method can effectively reduce the residual explosive between stages and realize the stable and reliable transfer of the trajectory in the explosive charge.
Drawings
In order to more clearly illustrate the embodiments of the present invention and the design thereof, the drawings required for the embodiments will be briefly described below. The following drawings are only some embodiments of the invention, and it will be obvious to those skilled in the art that other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a flow diagram of a high thrust ratio tertiary combination charge design;
FIG. 2 is an idealized time-thrust curve for a solid engine to be designed;
FIG. 3 is a preliminary designed star shaped solid rocket engine charge;
FIG. 4 is a solid rocket engine charge with a star-shaped blind hole configuration;
FIG. 5 is a schematic diagram of a combined charge propellant interface bus based on a mapping method and parallel layer combustion laws;
FIG. 6 is a schematic illustration of a unitized solid rocket engine charge as finally contemplated by the present invention;
FIG. 7 is a schematic three-dimensional structure of a first three-stage thrust composite charge of an embodiment;
FIG. 8 is a comparison plot of internal ballistic performance design versus actual measurement in one example;
the reference numbers in the figures denote:
1-first-level grain, 11-first cavity, 12-blind hole, 2-second-level grain, 3-third-level grain and 31-second cavity;
a-a first transfer surface, b-a second transfer surface.
Detailed Description
In order to make the purpose and technical solution of the present invention more apparent, the present invention is further described with reference to the following specific examples. The examples are merely illustrative and do not limit the scope of the invention. The experimental procedures used in the following examples are conventional ones unless otherwise specified, and materials, reagents and the like used therein are commercially available.
The invention provides a high-thrust-ratio three-stage-thrust solid rocket engine combined charge and a combustion surface design method thereof, which can accurately design the geometric structure of the high-thrust-ratio three-stage-thrust solid rocket engine combined charge, solve the problems of lower thrust, fewer stages and the like of the traditional method for realizing two-stage thrust by adjusting the combustion surface, and meet the requirements of a high-performance weapon system on engine launching-endurance-acceleration multi-stage power.
In the invention, the first-stage grain corresponds to a take-off stage, the second-stage grain corresponds to a cruising stage, and the third-stage grain corresponds to a speed-up stage.
With reference to fig. 6 and 7, the combined charge of the high-thrust-ratio three-stage solid engine is provided with a primary charge 1, a secondary charge 2 and a tertiary charge 3 in a shaft connection manner in sequence according to the combustion direction; the primary grain 1 is a cylinder, and the axis of the primary grain is provided with a first non-penetrating cavity 11; and the transfer surface between the first-stage medicine column 1 and the second-stage medicine column 2 is an ellipsoid surface.
In the embodiment of the disclosure, a first cavity 11 is arranged at the end of the primary explosive column 1 in a penetrating manner, a blind hole 12 is arranged at the bottom of the first cavity 11, and a first transfer surface a is arranged at the rear end of the blind hole 12; the first cavity 11 is a star-shaped cavity.
In an embodiment of the present disclosure, the aspect ratio of the ellipsoid is 2.
In the embodiment of the present disclosure, the cross-sectional shape of the first cavity 11 is a 6-8 pointed star.
In the embodiment of the present disclosure, the secondary charge 2 is a cylinder; the third-stage grain 3 is a cylinder, a second cavity 31 penetrating through the axis is arranged at the axis, and the second cavity 31 is a star-shaped cavity.
In the embodiment of the present disclosure, the cross-sectional shape of the second cavity 31 is a 6-8 pointed star.
In the embodiment of the present disclosure, the transition surface between the third-stage grain 3 and the second-stage grain 2 is a second transition surface b, and the second transition surface b is in the shape of an ellipsoid, an arc surface or a vertical surface.
The primary explosive column is prepared by adopting a propellant A; the secondary explosive column is prepared by adopting a propellant B; the third-level grains are prepared by adopting a propellant C;
the invention relates to a method for designing a combined fuel charge combustion surface of a high-thrust-ratio three-stage thrust solid rocket engine, which is obtained by calculation according to a zero-dimensional internal ballistic equation set of the conventional solid rocket engine, the specific design flow is shown in the attached figure 1, and the method mainly comprises the following steps:
step 1: selecting the diameter D of the solid rocket engine based on the overall performance index requirement of the solid rocket weapon c And the ideal time-thrust curve of the solid engine to be designed, see figure 2. The magnitudes of the thrust required by the launching stage, the endurance stage and the acceleration stage are respectively F 1 ，F e ，F a Required workRespectively has a time length of T 1 ，T e ，T a (ii) a In general, F e Is significantly less than F 1 And F a ，F a ＜F 1 ；
And 2, step: selecting an end face combustion solid propellant A suitable for a endurance stage to obtain the throat area A of the engine nozzle t Such that a face combustion charge produced on the basis of propellant A, when operating in an engine, generates a thrust force F e (ii) a Obtaining an actual thrust coefficient C F ；
And 3, step 3: calculating the pressure of the combustion chamber of the solid engine in three working stages of launching, endurance and acceleration under ideal conditions, and ideal pressure P in the launching stage 1 ＝F 1 /(C F ·A t ) Ideal pressure P in endurance phase e ＝F e /(C F ·A t ) Ideal pressure P in the acceleration phase a ＝F a /(C F ·A t )；
And 4, step 4: considering the diameter D of the solid rocket engine c Throat area A t And the actual thrust coefficient C F Selecting solid propellant B suitable for the launching stage, designing star-shaped solid propellant charge (see figure 3) by adopting a general star-shaped solid rocket engine grain design method, and enabling the designed star-shaped charge based on the propellant B to approach T in an attempt to stabilize working time (without residual propellant) 1 Thrust magnitude as close as possible to F 1 (ii) a In this step, since F 1 Is generally significantly greater than F e The overall burning rate of propellant B is therefore generally significantly higher than that of propellant a;
and 5: on the basis of the work of the previous step, the geometrical structure of the star-shaped charge is modified, and the front (the direction far away from the spray pipe) of the star-shaped charge is modified into a blind hole structure, which is shown in the attached figure 4; the front end face of the blind hole and the side face of the star-shaped charge are in transition by using an ellipsoid structure, the ratio of the major axis to the minor axis of the ellipsoid is about 2;
and 6: based on a mapping method and a parallel layer combustion rule, a two-dimensional combustion surface change track of the blind hole-containing star-shaped charge designed in the previous step in the working process is drawn until the blind hole-containing star-shaped charge is providedThe star-shaped tip of the charge burning to the outer wall of the charge, recording the time at which the cross-section characterizes the charge burning surface S 1 See fig. 5;
and 7: curved surface S obtained in the above step 1 As the transfer surface of the first-stage grain and the second-stage grain; duration T of endurance period in consideration of requirements e Ideal pressure P for endurance section e And the burning rate parameter of the propellant A, and calculating the meat thickness L of the propellant which should be possessed by the end-burning charge in the endurance period e ；
And 8: selecting a solid propellant C suitable for the acceleration stage, wherein the solid propellant C is in a star-shaped charge structure and meets the thrust requirement F of the acceleration stage as much as possible a And operating time requirement T a The initial combustion surface of the star-shaped charge with the blind hole designed in the step is recorded as S a . The resulting design of the composite charge is shown in figure 6.
The first embodiment is as follows:
based on a certain project, the propellant charge design of take-off, endurance and acceleration is developed, and the propellant charge design is verified through an internal ballistic performance test.
The charge is composed of propellant A, propellant B and propellant C, and the charge structure is shown in figure 7. The propellant A is a high-burning-rate propellant, is used for taking off-grade charging and is in a star-hole shape; the propellant B is a low-burning-rate propellant, is used for endurance charge and is in an end-burning shape; the propellant C is a medium-burning-rate propellant, is used for accelerating-level charging and is in an end-burning shape; the coating layer is made of ethylene propylene diene monomer; the charging transition section is designed by referring to the technical scheme.
An internal ballistic performance test is carried out through the ground test run of the engine, and an internal ballistic performance curve is shown in a figure 8. The inner ballistic performance test curve shows that the design form of the explosive charge can meet the requirement of a large thrust ratio (14).
The preferred embodiments were discussed in detail with preference to the above selection in conjunction with the accompanying drawings and are not intended to limit the invention. The specific technical features described above can be combined in any suitable form without contradiction, and the present invention is not described in detail. Any means that can be easily modified or modified by those skilled in the art, such as arbitrary combination or equivalent substitution, is adopted without departing from the scope of the technical solution, and the essence of the technical solution is not affected and still falls within the protective scope of the technical solution represented by each embodiment of the present invention.
Claims (9)
1. A combined charge of a three-stage solid engine with a high thrust ratio is characterized in that a first-stage grain (1), a second-stage grain (2) and a third-stage grain (3) are sequentially and axially connected in the combustion direction;
the primary grain (1) is a cylinder, and a non-penetrating first cavity (11) is arranged at the axis;
and the transfer surface between the primary medicine column (1) and the secondary medicine column (2) is an ellipsoid surface.
2. The high-thrust-ratio three-stage solid engine combined charge of claim 1, wherein the first-stage charge (1) is provided with a first cavity (11) through the end part, the bottom of the first cavity (11) is a blind hole (12), and the rear end of the blind hole (12) is provided with a first transfer surface (a);
the first cavity (11) is a star-shaped cavity.
3. A high thrust ratio three stage solid engine composite charge according to claim 1 or claim 2 wherein the ratio of the length to the diameter of said ellipsoid is 2.
4. A high thrust ratio three stage solid engine composite charge according to claim 1 or 2 wherein the cross-sectional shape of said first cavity (11) is a 6 to 8 star.
5. A high thrust ratio tertiary solid engine composite charge according to claim 1 or 2, characterised in that the secondary charge (2) is a cylinder;
the three-stage grain (3) is a cylinder, a second cavity (31) penetrating through the axis is arranged at the axis, and the second cavity (31) is a star-shaped cavity.
6. A high thrust ratio tertiary solid engine shaped charge according to claim 5 characterised in that the cross-sectional shape of the second cavity (31) is 6 to 8 star-shaped.
7. The high-thrust-ratio three-stage solid engine combined charge according to claim 1 or 2, wherein an adapter surface between the three-stage charge column (3) and the two-stage charge column (2) is a second adapter surface (b), and the second adapter surface (b) is in the shape of an ellipsoid, an arc surface or a vertical surface.
8. A design method of a combined charging combustion surface of a high-thrust-ratio three-stage solid engine is characterized in that the combined charging of the high-thrust-ratio three-stage solid engine is the combined charging of the high-thrust-ratio three-stage solid engine according to any one of claims 1 to 7; the primary explosive column is prepared by adopting a propellant A; the secondary explosive column is prepared by adopting a propellant B; the third-level grain is prepared by adopting a propellant C;
the design method specifically comprises the following steps:
step 1: selecting the diameter D of the solid rocket engine based on the overall performance index requirement of the solid rocket weapon c And the ideal time-thrust curve, F, of the solid engine to be designed 1 、F e And F a Respectively representing the thrust required by launching, endurance and acceleration stages, and the required working time is T 1 、T e And T a ；F e ＜F a ＜F 1 ；
Step 2: selecting an end face combustion solid propellant A suitable for a endurance stage to obtain the throat area A of the engine nozzle t Such that a face combustion charge produced on the basis of propellant A, when operating in an engine, generates a thrust force F e (ii) a Obtaining an actual thrust coefficient C F ；
And 3, step 3: calculating the pressure of the combustion chamber of the solid engine in three working stages of launching, endurance and acceleration under ideal conditions, and calculating the ideal pressure P in the launching stage 1 ＝F 1 /(C F ·A t ) Ideal pressure P in endurance phase e ＝F e /(C F ·A t ) Ideal pressure P in acceleration phase a ＝F a /(C F ·A t )；
And 4, step 4: considering the diameter D of the solid rocket engine c Throat area A t And the actual thrust coefficient C F Selecting a solid propellant B suitable for the launch phase, designing the star-shaped solid propellant charge such that the designed star-shaped charge based on propellant B has a stable working time T 1 Thrust is as great as F 1 ；
And 5: modifying the geometric structure of the star-shaped charge, and modifying the star-shaped charge in the direction away from the spray pipe into a blind hole; the front end face of the blind hole and the side face of the star-shaped charge are in transition by using an ellipsoid, and the ratio of the major axis to the minor axis of the ellipsoid is about 2; the thickness of the blind hole is the same as that of the star-shaped charged powder;
step 6: drawing a two-dimensional change track of the combustion surface of the blind-hole star-shaped charge designed in the previous step in the working process based on a drawing method and a parallel layer combustion rule until the top end of the star-shaped charge with the blind hole burns to the outer wall surface of the charge, and recording the characteristic charge combustion surface S on the cross section at the moment 1 ；
And 7: curved surface S obtained in the above step 1 As the transfer surface of the first-stage grain and the second-stage grain; duration T of endurance period in consideration of requirements e Ideal pressure P for endurance section e And the burning rate parameter of the propellant A, and calculating the meat thickness L of the propellant which should be possessed by the end-burning charge in the endurance period e ；
And 8: selecting a solid propellant C suitable for the acceleration stage, wherein the solid propellant C is in a star-shaped charge structure and meets the thrust requirement F of the acceleration stage as much as possible a And operating time requirement T a The initial combustion surface of the star-shaped charge with the blind hole designed in the step is recorded as S a 。
9. A combined charge of a three-stage solid engine with a high thrust ratio is characterized by being designed by the combined charge combustion surface design method of the three-stage solid engine with the high thrust ratio, which is defined in claim 8.
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