CN109707534B - Radial interlayer type double-pulse engine - Google Patents
Radial interlayer type double-pulse engine Download PDFInfo
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- CN109707534B CN109707534B CN201811628188.9A CN201811628188A CN109707534B CN 109707534 B CN109707534 B CN 109707534B CN 201811628188 A CN201811628188 A CN 201811628188A CN 109707534 B CN109707534 B CN 109707534B
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Abstract
The invention discloses a radial interlayer type double-pulse engine, which comprises a second combustion chamber shell, a soft interlayer, a first combustion chamber shell, a first pulse grain component, a second pulse grain component, an ignition device and a spray pipe: the two ends of the second combustion chamber shell are respectively provided with a front opening and a rear opening; the soft interlayer divides the inner cavity of the shell of the second combustion chamber into a first combustion chamber and a second combustion chamber; the first combustion chamber shell is fixedly arranged in the first combustion chamber and is provided with a medicine baffle plate and a bottom plate, a first hole is formed in the medicine baffle plate, and a second hole is formed in the bottom plate; the first pulse grain component comprises a first grain, the first grain is provided with an inner hole, the first grain is fixedly arranged in the first combustion chamber shell, and two ends of the inner hole are respectively communicated with the first hole and the second hole; the second pulse grain component comprises a heat insulation layer adhered to the inner wall of the second combustion chamber shell and a second grain filled between the heat insulation layer and the soft interlayer; the ignition device and the spray pipe are respectively arranged at the front opening and the rear opening. The invention has high space utilization rate.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a radial interlayer type double-pulse engine.
Background
According to the use characteristics of some missile weapons, strict space and mass constraints are imposed on the power system of the missile weapons, and the missile weapons also need to have the characteristics of short-time large-thrust launching and long-time small-thrust cruising, so that double thrust with larger span needs to be provided for an engine under the limited space and mass constraints, and the required filling ratio and the mass ratio are high. The conventional scheme adopts a two-stage engine, a single-chamber double-push or axial interlayer/bulkhead double-pulse engine scheme, but the conventional scheme has the defects of low space utilization rate and heavy structural mass and is difficult to meet the use requirement.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a radial interlayer type double-pulse engine with high space utilization rate.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows: a radial stratified double-pulse engine, comprising:
a second combustion chamber housing having a front opening and a rear opening at both ends thereof, respectively;
the tubular soft interlayer is fixedly arranged in the shell of the second combustion chamber, the axial direction of the tubular soft interlayer is the same as that of the shell of the second combustion chamber, and two ends of the tubular soft interlayer are respectively communicated with the front opening and the rear opening; the soft interlayer separates the inner cavity of the shell of the second combustion chamber and forms a first combustion chamber and a second combustion chamber which are distributed inside and outside;
the tubular first combustion chamber shell is axially the same as the soft interlayer and is fixedly arranged in the first combustion chamber, one end of the tubular first combustion chamber shell, which is close to the front opening, is provided with a medicine baffle plate, and one end of the tubular first combustion chamber shell, which is close to the rear opening, is provided with a bottom plate, the medicine baffle plate is provided with a first hole, and the bottom plate is provided with a second hole corresponding to the first hole;
the first pulse grain component comprises a tubular first grain, an inner hole is formed in the first grain along the axial direction of the first grain, the first grain is fixedly arranged in the first combustion chamber shell, and two ends of the inner hole are respectively communicated with the first hole and a second hole corresponding to the first hole;
the second pulse grain component comprises a heat insulation layer adhered to the inner wall of the second combustion chamber shell and a second grain filled between the heat insulation layer and the soft interlayer;
the ignition device is arranged at the front opening;
and the spray pipe is arranged at the rear opening.
Furthermore, the soft interlayer comprises a heat insulation sleeve and a metal connecting sleeve, and two ends of the metal connecting sleeve are respectively connected with the ignition device and the heat insulation sleeve.
Furthermore, a boss is arranged on the wall surface of the metal connecting sleeve connected with the heat insulating sleeve.
Further, a first artificial debonding layer is arranged on the part, connected with the second grain, of the heat insulation sleeve.
Furthermore, a plurality of exhaust grooves are formed in the first combustion chamber shell along the circumferential direction of the first combustion chamber shell, and the extending direction of the exhaust grooves is the same as the axial direction of the first combustion chamber shell.
Further, a gap exists between the first combustion chamber shell and the soft interlayer.
Further, the first combustion chamber housing has a greater wall thickness on a side thereof adjacent the front opening than on a side thereof adjacent the rear opening.
Further, the second bore inner diameter is not less than the inner bore inner diameter.
Furthermore, the first explosive column adopts double base explosive, and the second explosive column adopts tetrahydroxy tetratomic propellant.
Further, a second artificial debonding layer is arranged on the part, close to the front opening and/or the rear opening, of the heat insulation layer.
Compared with the prior art, the invention has the advantages that:
(1) the engine provided by the invention is only equivalent to one of two-stage engines in space, the space utilization rate is higher than that of a two-stage engine and an axial interlayer type double-pulse engine, and the structural size of the engine is reduced.
(2) The engine provided by the invention is structurally characterized in that the soft interlayer serves as a first combustion chamber shell, and the engine is only equivalent to only one set of combustion chamber shell, so that the passive mass is small.
Drawings
FIG. 1 is a schematic diagram of a radial stratified double-pulse engine according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of a first combustion chamber housing according to an embodiment of the present invention;
FIG. 3 is a right side view of FIG. 2;
FIG. 4 is an enlarged view of a portion A of FIG. 1;
FIG. 5 is a radial stratified dual pulse engine pressure profile provided in accordance with an embodiment of the present invention;
FIG. 6 is a thrust curve diagram of a radial stratified double pulse engine provided in accordance with an embodiment of the present invention.
In the figure: 1. a second combustion chamber housing; 2. a soft interlayer; 20. a heat insulating jacket; 21. a metal connecting sleeve; 210. a boss; 3. a first combustion chamber housing; 30. a medicine baffle plate; 300. a first hole; 301. a hold-down bolt; 31. a base plate; 310. a second hole; 311. a third aperture; 32. an exhaust groove; 33. a gap; 4. a first charge; 40. an inner bore; 5. a heat insulating layer; 6. a second grain; 7. an ignition device; 70. a baffle ring; 71. a seal ring; 8. and (4) a spray pipe.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Referring to fig. 1, an embodiment of the present invention provides a radial interlayer type double-pulse engine, which includes a second combustion chamber housing 1, a tubular soft interlayer 2, a tubular first combustion chamber housing 3, a first pulse charge assembly, a second pulse charge assembly, an ignition device 7, and a nozzle 8; the two ends of the second combustion chamber shell 1 are respectively provided with a front opening and a rear opening; the soft interlayer 2 is tubular, the soft interlayer 2 is fixedly arranged in the second combustion chamber shell 1, the soft interlayer 2 and the second combustion chamber shell 1 are coaxially arranged, and two ends of the soft interlayer 2 are respectively communicated with the front opening and the rear opening; the soft interlayer 2 separates the inner cavity of the shell 1 of the second combustion chamber and forms a first combustion chamber and a second combustion chamber which are distributed inside and outside, namely the inner wall of the soft interlayer 2 encloses into the first combustion chamber, and the second combustion chamber is formed between the inner wall of the soft interlayer 2 and the inner wall of the shell 1 of the second combustion chamber.
Referring to fig. 1, the first combustion chamber housing 3 is tubular, and is coaxially disposed with the soft partition 2 and fixedly disposed in the first combustion chamber, and has a medicine blocking plate 30 disposed at an end close to the front opening and a bottom plate 31 disposed at an end close to the rear opening, the medicine blocking plate 30 is provided with a first hole 300, and the bottom plate 31 is provided with a second hole 310 corresponding to the first hole 300; the line connecting the first hole 300 and the corresponding second hole 310 is the same as the axial direction of the first combustion chamber housing 3; the first pulse grain component comprises a tubular first grain 4, the first grain 4 and the first combustion chamber shell 3 are in the same axial direction, an inner hole 40 is formed in the first grain 4 along the axial direction, the first grain 4 is fixedly arranged in the first combustion chamber shell 3 through a grain blocking plate 30, two ends of the inner hole 40 are respectively communicated with a first hole 300 and a second hole 310 corresponding to the first hole 300, a compression bolt 301 is further arranged on the grain blocking plate 30, and the grain blocking plate 30 is fastened through the compression bolt 301;
referring to fig. 1, the second pulse cartridge assembly comprises a heat insulating layer 5 adhered to the inner wall of the second combustion chamber housing 1 and a second cartridge 6 filled between the heat insulating layer 5 and the soft partition 2;
The embodiment of the invention adopts a radial interlayer mode, the soft interlayer is arranged in the second combustion chamber shell, the inner cavity of the second combustion chamber shell is divided into the first combustion chamber and the second combustion chamber which are distributed inside and outside by the soft interlayer, and equivalently, the first combustion chamber is designed in the inner hole space of the second grain, the space in the second combustion chamber shell can be fully utilized, and the structural size of the engine is reduced.
The engine provided by the embodiment of the invention is only equivalent to one of two-stage engines in space, the space utilization rate is higher than that of a two-stage engine and an axial interlayer type double-pulse engine, and structurally, the soft interlayer serves as a first combustion chamber shell, so that the engine is only equivalent to only one set of combustion chamber shell, and the passive mass is small.
Referring to fig. 2, a plurality of exhaust grooves 32 are formed in the first combustion chamber housing 3 along the circumferential direction of the first combustion chamber housing 3, the extending direction of the exhaust grooves 32 is the same as the axial direction of the first combustion chamber housing 3, in this embodiment, 6 exhaust grooves 32 are provided and are uniformly spaced, the width of the exhaust grooves 32 is uniformly increased from the front opening to the rear opening, in this embodiment, the width of the exhaust grooves 32 near the front opening is 10mm, and the width of the exhaust grooves near the rear opening is 15 mm. Referring to fig. 1, a gap 33 exists between the first combustion chamber housing 3 and the soft partition 2, the thickness of the gap 33 along the radial direction of the first combustion chamber housing 3 is 2-5 mm, and the thickness of the gap 33 increases uniformly from the front opening to the rear opening, in this embodiment, the thickness of the gap 33 near the front opening is 2.5mm, and the thickness of the gap near the rear opening is 3.5mm, and the purpose of the gap 33 is to ensure that the first combustion chamber housing 3 does not crack due to unsmooth exhaust.
The wall thickness that first combustion chamber casing 3 is close to preceding opening one side is greater than its wall thickness that is close to back opening one side, ensures that first combustion chamber casing 3 does not lead to first combustion chamber casing 3 to destroy because of the ablation before a pulse work finishes, and first combustion chamber casing 3 needs even ablation after two pulse works, can not have the bold structure to drop and block up spray tube 8, and the wall thickness that first combustion chamber casing 3 is close to preceding opening one side is 3mm in this embodiment, and its wall thickness that is close to back opening one side is 2 mm.
The number of the first explosive columns 4 included in the first pulse explosive column assembly is selected according to actual conditions, and is generally 10-20, and the aperture, the outer diameter and the length of the inner holes 40 of the first explosive columns 4 are designed according to actual inner ballistic performance and space constraint conditions. In the embodiment, 13 first explosive columns 4 are adopted, and the aperture of an inner hole 40 of each first explosive column 4 is phi 4mm, the outer diameter is phi 12mm, and the length is 135 mm; arranged in the first combustion chamber housing 3 in the following manner: setting three layers, including a central layer, a middle layer and an outer layer which are distributed from inside to outside, wherein the central layer is provided with one, the middle layer is provided with 6, the middle layer is uniformly arranged along the periphery of the central layer at intervals, the outer layer is provided with 6, the middle layer is uniformly arranged along the periphery of the middle layer at intervals, as shown in fig. 2 and 3, in order to match 13 first explosive columns 4, 13 first holes 300 on the explosive baffle 30 are provided, 13 second holes 310 on the bottom plate 31 are provided, in order to ensure smooth exhaust and prevent the bottom plate 31 from being burnt through, the inner diameter of each second hole 310 is not less than the inner diameter of the inner hole 40, and in the embodiment, the inner diameter of each second hole 310 is phi 4.5 mm; referring to fig. 3, a plurality of third holes 311 are further disposed on the bottom plate 31, and in this embodiment, the size of the third holes 311 is Φ 3.5 mm.
Referring to fig. 4, the soft partition 2 comprises a heat insulating sleeve 20 and a metal connecting sleeve 21, and both ends of the metal connecting sleeve 21 are respectively connected with the ignition device 7 and the heat insulating sleeve 20.
Referring to fig. 4, a boss 210 is arranged on the wall surface of the metal connecting sleeve 21 connected with the heat insulating sleeve 20, a groove is arranged on the heat insulating sleeve 20, and the boss 210 is embedded in the groove to ensure reliable bonding with the heat insulating sleeve 20. for better reliable bonding, the metal connecting sleeve 21 extends into the heat insulating sleeve 20 and forms an extension section penetrating into the heat insulating sleeve 20, and the boss 210 is arranged on the extension section.
The end of the insulating sleeve 20 close to the rear opening is overlapped with the insulating layer 5 to ensure reliable and smooth opening of the adhesive without affecting the exhaust area after opening.
The part of the heat insulation sleeve 20 connected with the second grain 6 is provided with a first artificial debonding layer, the first artificial debonding layer ensures that the heat insulation sleeve 20 is separated from the second grain 6, effective burning surface is ensured, and the thickness of the first artificial debonding layer considers the conditions of pulse ablation, manufacturing deviation, pulse working pressure and the like.
The first explosive column 4 adopts double-base explosive, the second explosive column 6 adopts hydroxyl-terminated four-component propellant, the requirements of short-time large thrust during launching and long-time small thrust during cruising can be met simultaneously, and the double-base explosive has the characteristic of low cost and has great application value.
The part of the heat insulation layer 5 close to the front opening and/or the rear opening is provided with a second manual debonding layer, so that the structural integrity of the second explosive column 6 under the work of first pulse high pressure and the ignition impact of second pulse is ensured.
Referring to fig. 1, the top cover body of the ignition device 7 is connected to the second combustion chamber housing 1 by a retainer ring 70, and referring to fig. 4, the metal connecting sleeve 21 ensures the isolation of the combustion gases in the first and second combustion chambers by means of a radial seal of a sealing ring 71.
In one embodiment of the invention, the influence of the working pressure of the engine on the structure and the performance of the engine is comprehensively considered, the strength of the combustion chamber shell is reasonably exerted, and a pulse working pressure of 10-20 MPa is selected, so that the thrust is high in a short time; the working pressure of the two pulses is (3-5) MPa, and the thrust is small when the two pulses are long. In the engine of the embodiment, the diameter is 140mm, the working pressure of one pulse is 15MPa, the working pressure of two pulses is 3.5MPa, and the ballistic performance in the engine is shown in figures 5 and 6.
The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention. Those not described in detail in this specification are within the skill of the art.
Claims (8)
1. A radial stratified double pulse engine, comprising:
a second combustion chamber housing (1) having a front opening and a rear opening at both ends thereof, respectively;
the tubular soft interlayer (2) is fixedly arranged in the second combustion chamber shell (1), the soft interlayer (2) and the second combustion chamber shell (1) have the same axial direction, and the two ends of the soft interlayer are respectively communicated with the front opening and the rear opening; the soft interlayer (2) separates the inner cavity of the shell (1) of the second combustion chamber and forms a first combustion chamber and a second combustion chamber which are distributed inside and outside;
the tubular first combustion chamber shell (3) is axially the same as the soft interlayer (2) and is fixedly arranged in the first combustion chamber, one end of the tubular first combustion chamber shell, which is close to the front opening, is provided with a medicine baffle plate (30), and one end of the tubular first combustion chamber shell, which is close to the rear opening, is provided with a bottom plate (31), the medicine baffle plate (30) is provided with a first hole (300), and the bottom plate (31) is provided with a second hole (310) corresponding to the first hole (300);
the first pulse grain component comprises a tubular first grain (4), an inner hole (40) is formed in the first grain (4) along the axial direction of the first grain, the first grain (4) is fixedly arranged in the first combustion chamber shell (3), and two ends of the inner hole (40) are respectively communicated with the first hole (300) and the second hole (310) corresponding to the first hole (300);
the second pulse grain component comprises a heat insulating layer (5) adhered to the inner wall of the second combustion chamber shell (1) and a second grain (6) filled between the heat insulating layer (5) and the soft interlayer (2);
the ignition device (7) is arranged at the front opening;
the spray pipe (8) is arranged at the rear opening;
a gap (33) is formed between the first combustion chamber shell (3) and the soft interlayer (2), a plurality of exhaust grooves (32) are formed in the first combustion chamber shell (3) along the circumferential direction of the first combustion chamber shell, and the extension direction of the exhaust grooves (32) is the same as the axial direction of the first combustion chamber shell (3);
the soft interlayer (2) is damaged after the second explosive column (6) is ignited, and gas generated by combustion of the second explosive column (6) passes through the first combustion chamber shell (3) and is sprayed out of the spray pipe (8).
2. A radial-stratified twin pulse engine as defined in claim 1, wherein: the soft interlayer (2) comprises a heat insulation sleeve (20) and a metal connecting sleeve (21), and two ends of the metal connecting sleeve (21) are respectively connected with the ignition device (7) and the heat insulation sleeve (20).
3. A radial-stratified twin pulse engine as defined in claim 2, wherein: and a boss (210) is arranged on the wall surface of the metal connecting sleeve (21) connected with the heat insulating sleeve (20).
4. A radial-stratified twin pulse engine as defined in claim 2, wherein: the part of the heat insulation sleeve (20) connected with the second grain (6) is provided with a first artificial debonding layer.
5. A radial-stratified twin pulse engine as defined in claim 1, wherein: the wall thickness of the first combustion chamber shell (3) close to the front opening side is larger than that of the first combustion chamber shell close to the rear opening side.
6. A radial-stratified twin pulse engine as defined in claim 1, wherein: the inner diameter of the second hole (310) is not smaller than the inner diameter of the inner hole (40).
7. A radial-stratified twin pulse engine as defined in claim 1, wherein: the first explosive column (4) adopts double-base explosive, and the second explosive column (6) adopts tetrahydroxy tetratomic propellant.
8. A radial-stratified twin pulse engine as defined in claim 1, wherein: and a second artificial debonding layer is arranged on the part of the heat insulation layer (5) close to the front opening and/or the rear opening.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811628188.9A CN109707534B (en) | 2018-12-28 | 2018-12-28 | Radial interlayer type double-pulse engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811628188.9A CN109707534B (en) | 2018-12-28 | 2018-12-28 | Radial interlayer type double-pulse engine |
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| CN109707534A CN109707534A (en) | 2019-05-03 |
| CN109707534B true CN109707534B (en) | 2020-07-21 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595782A (en) * | 2019-08-18 | 2019-12-20 | 南京理工大学 | Shaft-diameter mixed double-pulse soft interlayer work simulation device |
| CN110630404B (en) * | 2019-08-20 | 2021-11-19 | 西安航天动力技术研究所 | Double-pulse solid engine |
| CN110529286B (en) * | 2019-08-20 | 2021-11-02 | 西安航天动力技术研究所 | Integral interlayer type double-pulse engine |
| CN110594039A (en) * | 2019-08-20 | 2019-12-20 | 西安航天动力技术研究所 | Interlayer structure for reducing interlayer strain of double-pulse solid engine |
| CN113653571B (en) * | 2021-08-16 | 2022-11-08 | 北京机械设备研究所 | Solid propellant combustion flow stabilizer and solid engine combustion generator |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4864817A (en) * | 1983-05-26 | 1989-09-12 | Morton Thiokol, Inc. | Membrane seal for application to pulsed rocket motor |
| CN106762223A (en) * | 2016-12-18 | 2017-05-31 | 内蒙古航天红峡化工有限公司 | A kind of soft interlayer spacing shaped device of solid rocket motor grain |
| CN108582631A (en) * | 2018-05-08 | 2018-09-28 | 江西航天经纬化工有限公司 | The soft interlayer of two pulses of one kind and its manufacture craft |
-
2018
- 2018-12-28 CN CN201811628188.9A patent/CN109707534B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4864817A (en) * | 1983-05-26 | 1989-09-12 | Morton Thiokol, Inc. | Membrane seal for application to pulsed rocket motor |
| CN106762223A (en) * | 2016-12-18 | 2017-05-31 | 内蒙古航天红峡化工有限公司 | A kind of soft interlayer spacing shaped device of solid rocket motor grain |
| CN108582631A (en) * | 2018-05-08 | 2018-09-28 | 江西航天经纬化工有限公司 | The soft interlayer of two pulses of one kind and its manufacture craft |
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