CN114060168B - Large initial thrust end-combustion charge solid rocket engine - Google Patents
Large initial thrust end-combustion charge solid rocket engine Download PDFInfo
- Publication number
- CN114060168B CN114060168B CN202111310418.9A CN202111310418A CN114060168B CN 114060168 B CN114060168 B CN 114060168B CN 202111310418 A CN202111310418 A CN 202111310418A CN 114060168 B CN114060168 B CN 114060168B
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- combustion
- solid rocket
- rocket engine
- charge
- propellant
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 61
- 239000007787 solid Substances 0.000 title claims abstract description 41
- 239000003380 propellant Substances 0.000 claims abstract description 37
- 239000007921 spray Substances 0.000 claims abstract description 12
- 238000010304 firing Methods 0.000 claims abstract description 3
- 239000002360 explosive Substances 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 4
- 235000013372 meat Nutrition 0.000 claims description 4
- 229910000737 Duralumin Inorganic materials 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 7
- 101000606504 Drosophila melanogaster Tyrosine-protein kinase-like otk Proteins 0.000 description 4
- 239000003814 drug Substances 0.000 description 2
- 229940079593 drug Drugs 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
Classifications
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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
-
- 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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
-
- 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
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- 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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention belongs to the field of solid rocket engines, and particularly relates to an end-combustion charge solid rocket engine with large initial thrust. The end-combustion charge solid rocket engine comprises a combustion chamber shell (1), an end-combustion charge (2), an ignition system (3) and a spray pipe fixing body (4); the end combustion charging (2) is filled in the combustion chamber shell (1), and a groove body or a blind hole is formed in the end face of the end combustion charging (2) and used for increasing an initial combustion face; the ignition system (3) is arranged on the convergence section of the spray pipe fixing body (4); the ignition system (3) is provided with a propellant small grain (7), the ignition system (3) simultaneously ignites the end-fire charge (2) and the propellant small grain (7), and the propellant small grain (7) is used for increasing initial thrust. The invention can effectively promote the initial thrust of the end-firing grain solid rocket engine.
Description
Technical Field
The invention belongs to the field of solid rocket engines, and particularly relates to an end-combustion charge solid rocket engine with large initial thrust.
Background
For the solid rocket engine for the aircraft, the caliber is smaller, the charging space is very limited, and the end-combustion charging mode has the advantages of maximum charging density (full charging), simple structure, stable thrust of a balancing section and the like on the premise of meeting the technical indexes such as thrust, total flushing, working time and the like, and is more and more popular with designers along with the great improvement of the technical level of the propellant.
However, end-fire charge solid rocket engines also have significant disadvantages, such as small initial combustion area, especially smaller average combustion area in the balance section, of conventional end-fire charge solid rocket engines. When the end-fire charge solid rocket engine is ignited, the ignition rate of the initial combustion surface is generally not more than 80%, which causes that the initial thrust of the traditional end-fire charge solid rocket engine is generally only half of the thrust of the balance section, and the initial thrust is small. The front sliding block is firstly separated from the track, and then the sliding block is separated from the track after the engine is ignited when the guide rail is launched. According to the launching flow, it is easy to judge that after the front sliding block is off-track and before the rear sliding block is not off-track, the aircraft can generate a low head angle to rotate around the rear sliding block, then the tail part of the aircraft can rotate at the same head-up angular speed, the initial thrust of the end-combustion charge solid rocket engine is small, the problems are more obvious, and the tail part of the aircraft can interfere with the launching frame in the launching process. In addition, because the aircraft launching platform usually comprises a helicopter, the typical severe launching condition provided by the helicopter is ultra-low altitude hovering low elevation launching, at the moment, after the aircraft leaves the orbit at the rear sliding block, the aircraft is influenced by the previous low head angular velocity, the launching elevation angle is very low, the aircraft speed is low, aerodynamic force is insufficient to control, the phenomenon of falling high can occur, and when the falling high is larger than the launching height of the helicopter, the aircraft can be caused to touch the ground.
Disclosure of Invention
The invention aims to: when the end-fire charge solid rocket engine is ignited, the ignition rate of an initial combustion surface is generally not more than 80%, which causes that the initial thrust of the traditional end-fire charge solid rocket engine is generally only half of the thrust of a balance section, the initial thrust is small, the tactical missile guide rail is low in off-track speed and large in off-track low-head angular speed, and the tactical missile guide rail is quite unfavorable. The invention provides an end-combustion loading solid rocket engine with large initial thrust, which aims to solve the problem of small initial thrust of the end-combustion loading solid rocket engine.
The technical scheme is as follows: the end-combustion charge solid rocket engine with large initial thrust is provided, and comprises a combustion chamber shell 1, an end-combustion charge 2, an ignition system 3 and a spray pipe fixing body 4;
the end-combustion charge 2 is filled in the combustion chamber shell 1, and a groove body or a blind hole is formed in the end face of the end-combustion charge 2 and used for enlarging an initial combustion face;
the ignition system 3 is arranged on the convergence section of the spray pipe fixing body 4; the ignition system 3 is provided with a propellant charge 7, the ignition system 3 igniting both the end-fire charge 2 and the propellant charge 7, the propellant charge 7 serving to increase the initial thrust.
Optionally, the end-fire charge 2 is fully charged to the combustion chamber housing 1.
Optionally, the end face of the end-fire charge 2 is provided with an annular groove 5 of right-angled trapezoidal cross-section.
Optionally, the ignition system 3 further comprises an ignition cartridge 6 and an igniter 9;
the ignition cartridge 6 is of an annular structure with a gas through hole, and a propellant small explosive column 7 is filled in the ignition cartridge 6;
the ignition cartridge 6 is fixed on the inner side of the convergent section of the nozzle fixing body 4, and the igniter 9 is arranged on the outer side of the convergent section of the nozzle fixing body 4; the igniter 9 ignites both the end-fire charge 2 and the propellant grains 7.
Optionally, the ignition cartridge 6 is made of a pressure resistant erodible material.
Alternatively, the ignition cartridge 6 is of a duralumin material.
Alternatively, the propellant grains 7 are grains having a constant surface or a reduced surface combustion effect.
Optionally, the propellant grains 7 are tubular grains; the meat thickness of the small tubular propellant grains is 0.2 to 1.0 times the depth of the annular groove 5.
The invention has the technical effects that: the ignition system combination consists of an igniter and a small explosive cartridge ignition cartridge with built-in propellant, and can effectively promote the initial thrust of the solid rocket engine with the end-fired explosive cartridge.
Drawings
FIG. 1 is a schematic diagram of a solid rocket engine with a large initial thrust end-fire charge;
FIG. 2 is a schematic view of a combustion chamber housing and an end-fire charge;
FIG. 3 is a partial schematic view of an annular groove of right-angled trapezoid cross section of an end-fire charge;
FIG. 4 is a schematic diagram of an ignition system assembly;
fig. 5 is a schematic diagram of initial thrust.
Detailed Description
In the present embodiment of the present invention,
as shown in fig. 1, the embodiment provides a schematic diagram of a solid rocket engine with a large initial thrust end-fire charge. The solid rocket engine with the large initial thrust and the end-combustion charge mainly comprises a combustion chamber shell 1, the end-combustion charge 2, an ignition system 3 and a spray pipe fixing body 4.
The end-combustion charge 2 is filled into the combustion chamber shell 1 in an adherence pouring mode, the ignition system 3 is fixed on a spray pipe convergence section of the spray pipe fixing body combination 4, and the combustion chamber shell 1 and the spray pipe fixing body 4 are combined in a mechanical connection mode, namely the end-combustion charge solid rocket engine is formed.
As shown in fig. 2 and 3, a partial schematic diagram of an end-fire charge 2 of a solid rocket engine with a large initial thrust and an annular groove 5 with a right trapezoid cross section of the present embodiment is provided. The end-combustion charge 2 is cylindrical and coaxial with the solid rocket engine, at least 1 right trapezoid cross section annular groove 5 is arranged at the initial combustion surface position (rear end surface) of the end-combustion charge 2, the bottom edge of the right trapezoid cross section is flush with the initial end surface, the right trapezoid edge close to the axis of the end-combustion charge 2 is a right angle edge, the other edge and the bottom edge form an included angle of 60 degrees, and the number of the right trapezoid cross section annular grooves 5 and the length of the top edge of the right trapezoid are required to be adjusted according to the initial thrust requirement of the solid rocket engine. The annular groove 5 with the right trapezoid cross section is designed, the combustion surface can be increased by controlling the shape and the angle of the groove body, the local stress at the moment of ignition is avoided, and the manufacturability of the groove body molding is improved.
The meat thickness of the tubular propellant grains is 0.2 to 1.0 times of the depth of the annular groove 5, the burning time of the tubular propellant grains 7 is similar to the burning time of the end-fire charge corresponding to the depth of the annular groove 5, wherein when the burning speed of the tubular propellant grains 7 is similar to the burning speed of the end-fire charge, the meat thickness of the tubular propellant grains 7 is 0.8 to 1.0 times of the depth of the annular groove 5; when the end-fire charge 2 selects a high-fire rate formula propellant and the tubular propellant grains 7 select a low-fire rate formula propellant, the thickness of the tubular propellant grains 7 should be 0.2 to 0.8 times the depth of the annular groove 5, and the larger the difference in fire rate, the smaller the ratio of the thickness to the depth.
As shown in fig. 4, a schematic diagram of a solid rocket engine ignition system combination 3 with a large initial thrust end-fire charge according to an embodiment is provided. The ignition system 3 consists of an ignition explosive box 6 and an igniter 9, wherein a small propellant grain 7 is arranged in the ignition explosive box 6, the dosage of the small propellant grain 7 is adjusted according to the initial thrust requirement of a solid rocket engine, the small propellant grain 7 can select a combustion-reducing surface combustion type or a constant combustion surface combustion type, the combustion-reducing surface combustion type is mainly columnar, and the constant combustion surface combustion type is mainly tubular; if the requirements cannot be met by adjusting the drug loading and the drug type, the formula of the small propellant grains 7 can be adjusted, a double-base propellant is generally selected, and when the requirements cannot be met, the small propellant grains are replaced by a modified double-base propellant, a butylol composite propellant and the like. The shell of the ignition cartridge 6 is made of easily-corroded materials, and is glued to the inner side of the convergent section of the nozzle fixing body assembly 4, the igniter 9 is fixed to the outer side of the convergent section of the nozzle fixing body assembly 4 through threaded connection, and the ignition channel 8 of the igniter 9 is inserted into the ignition cartridge 6.
As shown in fig. 5, a schematic diagram of the initial thrust of a conventional end-fire-charge solid rocket engine and a large initial thrust end-fire-charge solid rocket engine according to the present invention are given respectively.
FIG. 5 shows an initial thrust F0 of a conventional end-firing solid rocket engine, wherein F0 reaches about 7000N at a moment of 0.1s, and F0 gradually climbs to a balance section thrust 15000N within a period of 0.5 s; the invention is used on the basis of a traditional end-combustion charge solid rocket engine, initial thrust F1 is obtained, and the thrust F1 reaches 15000N in the equilibrium section within 0.05s, so that the effect of the end-combustion charge solid rocket engine with large initial thrust is obvious, the initial thrust within 0.1s is obviously increased, and the time for reaching the thrust in the equilibrium section is obviously shortened.
Claims (7)
1. The end-combustion charge solid rocket engine with the large initial thrust is characterized by comprising a combustion chamber shell (1), an end-combustion charge (2), an ignition system (3) and a spray pipe fixing body (4);
the end-combustion charging device comprises a combustion chamber shell (1), wherein an end-combustion charging device (2) is filled in the combustion chamber shell (1), a groove body or a blind hole is formed in the end face of the end-combustion charging device (2), and an annular groove (5) with a right trapezoid cross section is formed in the end face of the end-combustion charging device (2) and used for enlarging an initial combustion face;
the ignition system (3) is arranged on the convergence section of the spray pipe fixing body (4); the ignition system (3) is provided with a propellant small grain (7), the ignition system (3) simultaneously ignites the end-fire charge (2) and the propellant small grain (7), and the propellant small grain (7) is used for increasing initial thrust.
2. End-fire charge solid rocket engine according to claim 1, characterized in that the end-fire charge (2) is fully charged in the combustion chamber housing (1).
3. End-fire charge solid rocket engine according to claim 1, characterized in that the ignition system (3) further comprises an ignition cartridge (6) and an igniter (9);
the ignition explosive box (6) is of an annular structure with a gas through hole, and the propellant small explosive column (7) is filled in the ignition explosive box (6);
the ignition cartridge (6) is fixed at the inner side of the convergent section of the spray pipe fixing body (4), and the igniter (9) is arranged at the outer side of the convergent section of the spray pipe fixing body (4); an igniter (9) ignites both the end-firing charge (2) and the propellant grains (7).
4. End-fire charge solid rocket engine according to claim 1, characterized in that the ignition cartridge (6) is made of a pressure-resistant and erodible material.
5. End-fire charge solid rocket engine according to claim 4, characterized in that the ignition cartridge (6) is made of duralumin material.
6. End-fire charge solid rocket engine according to claim 1, characterized in that small propellant grains (7) are chosen with constant or reduced surface combustion effect.
7. End-fire charge solid rocket engine according to claim 6, characterized in that the propellant grains (7) are tubular grains; the meat thickness of the small tubular propellant grains is 0.2 to 1.0 times the depth of the annular groove (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111310418.9A CN114060168B (en) | 2021-11-05 | 2021-11-05 | Large initial thrust end-combustion charge solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111310418.9A CN114060168B (en) | 2021-11-05 | 2021-11-05 | Large initial thrust end-combustion charge solid rocket engine |
Publications (2)
| Publication Number | Publication Date |
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| CN114060168A CN114060168A (en) | 2022-02-18 |
| CN114060168B true CN114060168B (en) | 2024-01-19 |
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| CN202111310418.9A Active CN114060168B (en) | 2021-11-05 | 2021-11-05 | Large initial thrust end-combustion charge solid rocket engine |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876667B (en) * | 2022-04-27 | 2023-09-12 | 西安零壹空间科技有限公司 | Composite solid rocket engine, charging method and filling equipment |
| CN115929508B (en) * | 2022-10-26 | 2025-06-03 | 上海新力动力设备研究所 | Composite material shell structure with combined slider |
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| CN114060168A (en) | 2022-02-18 |
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