CN109882313B - Design method of solid engine spray pipe capable of generating lateral thrust - Google Patents
Design method of solid engine spray pipe capable of generating lateral thrust Download PDFInfo
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- CN109882313B CN109882313B CN201811457179.8A CN201811457179A CN109882313B CN 109882313 B CN109882313 B CN 109882313B CN 201811457179 A CN201811457179 A CN 201811457179A CN 109882313 B CN109882313 B CN 109882313B
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- 239000007921 spray Substances 0.000 title claims abstract description 36
- 239000007787 solid Substances 0.000 title claims abstract description 23
- 238000013461 design Methods 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000002485 combustion reaction Methods 0.000 claims description 10
- 238000002679 ablation Methods 0.000 claims description 4
- 238000003763 carbonization Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 2
- 238000013146 percutaneous coronary intervention Methods 0.000 claims description 2
- 239000002737 fuel gas Substances 0.000 abstract description 4
- 238000009413 insulation Methods 0.000 description 21
- 238000011161 development Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention provides a solid engine spray pipe capable of generating lateral thrust and a design method thereof. The solid engine nozzle capable of generating the lateral thrust has the advantages that the convergent section of the solid engine nozzle is designed into a spherical asymmetric structure form, the axis of the engine and the axis of the nozzle form a certain included angle, the structure ensures that the engine can simultaneously generate the axial thrust and the lateral thrust in the working process, the fuel gas symmetrically flows in the expansion section, the thrust loss of the asymmetric flow is reduced, the structure is simple, the process feasibility is strong, and the reliability is high.
Description
Technical Field
The invention belongs to the technical field of solid rocket engines, and particularly relates to a design method of a solid engine spray pipe capable of generating lateral thrust.
Background
With the development of solid rocket engines, the types of engines are more and more diversified, and the structural design of the engines is more and more important. In recent years, new requirements are put on engines by the general department, and during the operation of the engines, the axial thrust and the lateral thrust need to be generated simultaneously.
Therefore, if a solid rocket engine which has a simple structure and can generate lateral thrust can be designed according to a specific working environment, the increase of the passive mass brought by the generation of the lateral thrust or the loss of the thrust brought by the asymmetry of the gas flow at the outlet of the jet pipe can be reduced, and a positive effect on the design of a missile or a rocket can be achieved.
Disclosure of Invention
In view of the above, the invention provides a method for designing a solid engine nozzle capable of generating a side thrust, which is to design a nozzle convergent section into a spherical asymmetric structure, so that fuel gas at the nozzle outlet flows symmetrically and forms a certain included angle with the axial direction of a combustion chamber, thereby ensuring that an axial thrust and a side thrust are generated simultaneously in the engine working process, and reducing the thrust loss caused by asymmetric flow at the nozzle outlet.
The technical scheme for realizing the invention is as follows:
a solid engine spray pipe capable of generating lateral thrust is characterized in that a convergent section of the spray pipe is of a spherical asymmetric structure, a sphere center is located at the intersection point of an engine axis and a spray pipe axis, the inner and outer surfaces of the convergent section are spherical surfaces and are asymmetric to the spray pipe axis, a half angle of a heat insulation layer interface of the convergent section is symmetric to the spray pipe axis, the solid engine spray pipe mainly comprises the heat insulation layer of the convergent section and a shell coated outside the heat insulation layer, and a certain included angle is formed between the spray pipe axis and the engine axis.
A design method of a solid engine spray pipe capable of generating side thrust comprises the following specific processes:
designing a spherical asymmetric structure consisting of a heat insulating layer of a convergent section and a shell coated outside the heat insulating layer at the convergent section of the spray pipe, wherein the connecting surface between the convergent section and the throat liner assembly is a step surface, and a certain included angle is formed between the axis of the spray pipe and the axis of an engine;
designing the inner diameter of the heat insulating layer of the convergent section
According to the throat diameter Dt of the engine jet pipe and the nozzle combustion chamber interface size
Calculating the inner diameter SR of the heat insulation layer ball of the convergence section;
wherein ε is a convergence ratio,
setting a half angle of a heat insulating layer interface of a convergence section;
thirdly, designing the thickness of the heat insulating layer of the convergent section
According to the section of the longest generatrix of the profile surface in the convergent section (namely the initial position of the heat insulating layer of the convergent section and the axis of the engine
Profile) maximum average ablation rate r1And carbonization ratio r2Calculating the minimum thickness t of the heat insulating layer of the convergence section1；
(t1-(r1+r2)t)/t1F (3) or more, wherein t is the working time of the engine, and f is the safety margin;
fourthly, judging whether the parameters designed in the second step and the third step meet the requirement formula (4), if so, entering the fifth step, otherwise, returning to the second step;
wherein,
ruler for connecting combustion chamberCun, cun;
fifthly, designing the minimum thickness t of the shell at the convergent section of the spray pipe2So that the requirement of allowable stress is met,
wherein, PCIs the combustion chamber pressure, [ sigma ]]Allowable stress;
thus, the design of the engine nozzle is completed.
Further, the invention is described
The value range of (A) is 35-55 degrees.
Furthermore, the step of the step surface at the joint of the heat insulation of the convergent section and the throat insert assembly is not less than 2 levels.
Advantageous effects
The solid engine nozzle capable of generating the lateral thrust has the advantages that the convergent section of the solid engine nozzle is designed into a spherical asymmetric structure form, the axis of the engine and the axis of the nozzle form a certain included angle, the structure ensures that the engine can simultaneously generate the axial thrust and the lateral thrust in the working process, the fuel gas symmetrically flows in the expansion section, the thrust loss of the asymmetric flow is reduced, the structure is simple, the process feasibility is strong, and the reliability is high.
Drawings
FIG. 1 is a schematic illustration of an engine nozzle configuration according to the present invention;
wherein 1-convergent section heat insulation layer, 2-nozzle convergent section shell, 3-nozzle throat insert component and expansion section
Detailed Description
The invention is described in detail below with reference to the figures and the specific examples.
The invention relates to a solid engine spray pipe capable of generating lateral thrust, which is shown in figure 1, wherein a convergent section structure of the spray pipe consists of a convergent section heat insulation layer 1 and a shell 2 coated outside the heat insulation layer, the convergent section heat insulation layer plays roles in scouring resistance and heat insulation, and the spray pipe convergent section shell plays a role in bearing pressure and is connected with a combustion chamber; the connection surface between the convergent section and the throat insert assembly is a step surface, and a certain included angle is formed between the axis of the spray pipe and the axis of the engine.
The solid engine spray pipe capable of generating the lateral thrust has the advantages that the convergent section of the solid engine spray pipe capable of generating the lateral thrust is designed into a spherical asymmetric structure, the spherical center is positioned at the intersection point of the axis of the engine and the axis of the spray pipe, the inner surface and the outer surface of the convergent section are spherical surfaces and are asymmetric to the axis of the spray pipe, the half angle of the interface of the heat insulation layer of the convergent section is symmetric to the axis of the spray pipe, the structure ensures that the engine can generate the axial thrust and the lateral thrust simultaneously in the working process, fuel gas flows symmetrically in the expansion section, the thrust loss of asymmetric flow is reduced, the structure is.
The invention relates to a design method of a solid engine spray pipe capable of generating lateral thrust, which comprises the following specific processes:
(1) the design method is characterized in that the spray pipe convergence section is of a spherical asymmetric structure consisting of a convergence section heat insulation layer and a shell coated outside the heat insulation layer, the connection surface between the convergence section and the throat liner assembly is a step surface, and a certain included angle is formed between the axis of the spray pipe and the axis of the engine.
(2) Design of inner diameter of heat insulation layer of convergent section (i.e. inner surface of heat insulation layer of convergent section can be determined)
And designing the inner molded surface of the nozzle throat liner according to the working conditions of the engine to obtain the throat diameter Dt. The deflection angle theta is generally 10-45 degrees, the convergence ratio epsilon is 2-3, and epsilon is increased along with the increase of the deflection angle theta.
In the formula
-a given half angle of the thermal insulation layer interface of the convergent section is selected within the range of 35-55 °;
The SR is selected within the allowable range of the SR obtained by the equations (1) and (2).
(3) Design of the thickness and connection of the thermal insulation layer in the convergence section
The heat insulating layer of the convergent section is most seriously washed at the position of the longest generatrix section (I-quadrant line section) of the profile in the convergent section, and the average ablation rate and the carbonization rate are respectively r1And r2. After working, the non-carbonized thickness of the convergent heat insulation layer is not less than f of the total thickness.
(t1-(r1+r2)t)/t1≥f (3)
Where t is the engine operating time s, f is the safety margin.
Calculating the minimum thickness t of the heat insulating layer of the convergent section according to a formula (3)1。
The step at the joint of the heat insulating layer of the convergent section and the throat insert component is not smaller by 2 grades, and the step height h1、h2And length L1Not less than 4 mm.
(4) Combustion chamber interface size verification
Combustor port size
The following requirements have to be met,
if the formula (4) does not meet the requirement, returning to the step (2) to recalculate SR and t1。
(5) Nozzle shell convergent section thickness design
The convergence section of the spray pipe shell is checked by adopting spherical tensile stress with the tensile stress of
In the formula PC-combustion chamber pressure MPa;
[ sigma ] -allowable stress MPa.
Calculating according to a formula (5) to obtain the minimum thickness t of the convergent section of the nozzle shell2。
From this, the design of the engine nozzle is completed.
The nozzle convergent section structure is assembled in the sequence that the expansion section heat insulation layer is bonded with the nozzle shell, then the throat lining assembly is bonded, then the convergent section heat insulation layer is bonded with the throat lining assembly and the nozzle shell convergent section, and finally the pressure curing is carried out.
Example (c):
the present example is illustrated by taking as an example a design of the convergent section of the engine nozzle, the maximum operating pressure P of the engine of this designc12.7MPa, working time t 3s, and the size of the combustion chamber interface
The nozzle deflection angle θ is 20 °.
1) Designing throat insert profile according to engine working condition to obtain Dt equal to 91mm and convergence ratio epsilon equal to 2, substituting formula (1) and formula (2), taking SR equal to 85.5mm,
2) average ablation rate r of heat insulating layer in convergent section10.65mm/s, carbonization rate r2Substituting the formula (3) with 2.0mm/s and f 0.4, and taking t114 mm; the step at the joint of the heat insulation of the convergent section and the throat lining assembly is 2-level h1、h2、L1Is 4 mm.
3) SR, t1Substituting into a formula (4) to meet the requirement;
4) nozzle shell convergent section material [ sigma ]]Allowable stress is 360MPa, SR, t1、PCSubstituting into formula (5) to obtain t2Not less than 1.8mm, taking t into account of mechanical deviation, heat treatment and other factors2＝2.2mm。
From this, the design is completed.
The above description and the annexed drawings represent preferred embodiments of the invention, and those skilled in the art will be able to make numerous modifications, according to the different needs of the solid rocket engine, without departing from the scope of the invention as defined in the appended claims, and therefore the invention is broad.
Claims (3)
1. A design method of a solid engine spray pipe capable of generating side thrust is characterized by comprising the following specific processes:
designing a spherical asymmetric structure consisting of a heat insulating layer of a convergent section and a shell coated outside the heat insulating layer at the convergent section of the spray pipe, wherein the center of a sphere is positioned at the intersection point of the axis of an engine and the axis of the spray pipe, the inner and outer surfaces of the convergent section are spherical surfaces and are asymmetric to the axis of the spray pipe, the half angle of the interface of the heat insulating layer of the convergent section is symmetric to the axis of the spray pipe, the connecting surface between the convergent section and a throat insert assembly is a step surface, and a certain included angle is formed between the axis of the spray;
designing the inner diameter of the heat insulating layer of the convergent section
Calculating the inner diameter SR of the heat insulating layer ball of the convergent section according to the throat diameter Dt of the engine spray pipe and the nozzle combustion chamber interface size phi D;
wherein ε is a convergence ratio,
setting a half angle of a heat insulating layer interface of a convergence section;
thirdly, designing the thickness of the heat insulating layer of the convergent section
According to the maximum average ablation rate r of the section of the longest generatrix of the profile in the convergence section1And carbonization ratio r2Calculating the minimum thickness t of the heat insulating layer of the convergence section1；
(t1-(r1+r2)t)/t1F (3) or more, wherein t is the working time of the engine, and f is the safety margin;
fourthly, judging whether the parameters designed in the second step and the third step meet the requirement formula (4), if so, entering the fifth step, otherwise, returning to the second step;
wherein,
is the combustor port size;
fifthly, designing the minimum thickness t of the shell at the convergent section of the spray pipe2So that the requirement of allowable stress is met,
wherein, PCIs the combustion chamber pressure, [ sigma ]]Allowable stress;
thus, the design of the engine nozzle is completed.
2. The method of designing a solid state thrust vectoring nozzle as claimed in claim 1, wherein said thrust side effect nozzle is provided
The value range of (A) is 35-55 degrees.
3. The method of designing a solid state thrust vectoring nozzle as claimed in claim 1 wherein said convergent section is insulated by no less than 2 steps from the step face where the throat insert assembly is joined.
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| CN201811457179.8A CN109882313B (en) | 2018-11-30 | 2018-11-30 | Design method of solid engine spray pipe capable of generating lateral thrust |
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| CN201811457179.8A CN109882313B (en) | 2018-11-30 | 2018-11-30 | Design method of solid engine spray pipe capable of generating lateral thrust |
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| CN109882313B true CN109882313B (en) | 2021-07-06 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573648A (en) * | 1983-01-20 | 1986-03-04 | Ford Aerospace And Communications Corp. | Ram air combustion steering system for a guided missile |
| JPH09177609A (en) * | 1995-12-21 | 1997-07-11 | Mitsubishi Heavy Ind Ltd | Thrust adjusting mechanism for side thruster of flying craft |
| CN106677925A (en) * | 2015-11-06 | 2017-05-17 | 上海新力动力设备研究所 | Design method for diffusing section of narrow-slit spray pipe of lateral-force engine |
| CN107084074A (en) * | 2017-05-23 | 2017-08-22 | 湖北航天技术研究院总体设计所 | A kind of high-performance side jet pipe solid propellant rocket |
| CN108590885A (en) * | 2018-05-10 | 2018-09-28 | 北京理工大学 | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure |
-
2018
- 2018-11-30 CN CN201811457179.8A patent/CN109882313B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573648A (en) * | 1983-01-20 | 1986-03-04 | Ford Aerospace And Communications Corp. | Ram air combustion steering system for a guided missile |
| JPH09177609A (en) * | 1995-12-21 | 1997-07-11 | Mitsubishi Heavy Ind Ltd | Thrust adjusting mechanism for side thruster of flying craft |
| CN106677925A (en) * | 2015-11-06 | 2017-05-17 | 上海新力动力设备研究所 | Design method for diffusing section of narrow-slit spray pipe of lateral-force engine |
| CN107084074A (en) * | 2017-05-23 | 2017-08-22 | 湖北航天技术研究院总体设计所 | A kind of high-performance side jet pipe solid propellant rocket |
| CN108590885A (en) * | 2018-05-10 | 2018-09-28 | 北京理工大学 | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure |
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