CN112696286B - Gel fuel performance test engine - Google Patents
Gel fuel performance test engine Download PDFInfo
- Publication number
- CN112696286B CN112696286B CN202011450702.1A CN202011450702A CN112696286B CN 112696286 B CN112696286 B CN 112696286B CN 202011450702 A CN202011450702 A CN 202011450702A CN 112696286 B CN112696286 B CN 112696286B
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- China
- Prior art keywords
- combustion chamber
- chamber
- medicine
- insulating sleeve
- vent plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 239000000446 fuel Substances 0.000 title claims abstract description 24
- 238000011056 performance test Methods 0.000 title claims abstract description 8
- 238000002485 combustion reaction Methods 0.000 claims abstract description 46
- 239000003814 drug Substances 0.000 claims abstract description 28
- 239000007921 spray Substances 0.000 claims abstract description 15
- 238000007789 sealing Methods 0.000 claims abstract description 11
- 239000011505 plaster Substances 0.000 claims abstract description 10
- 238000012360 testing method Methods 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 230000007721 medicinal effect Effects 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 11
- 238000009413 insulation Methods 0.000 description 8
- 238000005273 aeration Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000000843 powder Substances 0.000 description 3
- 239000004593 Epoxy Substances 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 229920002160 Celluloid Polymers 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000009841 combustion method Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229920001220 nitrocellulos Polymers 0.000 description 1
- 239000002674 ointment Substances 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229940126589 solid medicine Drugs 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
Images
Classifications
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- 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
-
- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- 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
- F02K9/97—Rocket nozzles
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N31/00—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods
- G01N31/12—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods using combustion
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Physics & Mathematics (AREA)
- Molecular Biology (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a gel fuel performance test engine which comprises a combustion chamber, a first insulating sleeve, a medicine chamber, a first vent plate, a rear sealing cover, a second insulating sleeve, a second vent plate, a supporting sleeve, a spray pipe, a base, a thrust adapter and a plaster, wherein the base is connected with one end of the combustion chamber through an internal thread; the spray pipe is arranged on the rear sealing cover, and the plaster is arranged in the medicine chamber. The strength of the invention can reach 120Mpa, which meets the use of the paste fuel with strong medicinal properties.
Description
Technical Field
The invention belongs to a technology for testing the drug property of rocket projectile fuel, and particularly relates to a gel fuel performance testing engine.
Background
Because the gel fuel is a novel high-energy medicine, the current method for testing the physicochemical property of the gel fuel is a combustion method, the physicochemical property is obtained by observing the flame temperature and the combustion speed, but the research method cannot simulate the deflagration condition of the gel fuel under the conditions of high temperature and high pressure. In engineering, gel fuel is usually used for replacing solid medicines to carry out tests on finished engines, but the method has the defects that the fuel property of the gel fuel is unknown, and the situations of engine shell breakage and nozzle explosion are easy to occur.
Disclosure of Invention
The invention aims to provide a gel fuel performance test engine.
The technical scheme for realizing the purpose of the invention is as follows: a gel fuel performance test engine comprises a combustion chamber, a first insulating sleeve, a medicine chamber, a first vent plate, a rear sealing cover, a second insulating sleeve, a second vent plate, a support sleeve, a spray pipe, a base, a thrust adapter and a plaster, wherein the base is connected with one end of the combustion chamber through an internal thread; the spray pipe is arranged on the rear sealing cover, and the plaster is arranged in the medicine chamber.
Preferably, a gap is left between the outer wall of the medicine chamber and the inner wall of the combustion chamber.
Preferably, the medicine chamber is fixed at one end of the combustion chamber through four supporting legs.
Preferably, a pressure measuring hole penetrating through the heat insulation sleeve is formed on the side wall surface of the combustion chamber close to the end surface. The design leaves a gap due to the material, but when the pressure measuring device is used, a small amount of paper sheets need to be added in the circumferential direction and the axial direction for fixing, and meanwhile, the pressure measuring port does not need to be blocked.
Preferably, open in the middle of the base has two symmetrical holes, the thrust adapter side is equipped with two holes.
Preferably, the nozzle is a conical nozzle, the convergence half angle is 22.5 degrees, and the expansion half angle is 7.5 degrees.
Compared with the prior art, the invention has the advantages that: (1) the strength of the invention can reach 120Mpa, and the use of the paste fuel with strong medicinal properties is satisfied; (2) the invention is provided with the pressure measuring hole and the pressure measuring adapter at the same time, and can obtain the pressure and the thrust value at the same time.
The present invention is described in further detail below with reference to the attached drawings.
Drawings
FIG. 1 is a block diagram of the present invention.
Fig. 2 is a schematic view of the nozzle structure.
Detailed Description
As shown in figure 1, the gel fuel performance test engine comprises a combustion chamber 1, a first insulating sleeve 2, a medicine chamber 3, a first vent plate 4, a rear sealing cover 5, a second insulating sleeve 6, a second vent plate 7, a supporting sleeve 8, a spray pipe 9, a base 10, a thrust adapter 11 and a plaster 12, the base 10 is connected with one end of the combustion chamber 1 through an internal thread, the thrust adapter 11 is connected with one end of the combustion chamber 1 through an external thread, the first heat insulation sleeve 2 is arranged on the inner wall of the combustion chamber 1, the explosive chamber 3 is arranged in the combustion chamber 1, the first aeration plate 4 is arranged in the combustion chamber 1, and is positioned at the end of the medicine chamber 3, the second aeration plate 7 is fixed on the first aeration plate 4 through a supporting sleeve 8, the rear sealing cover 5 is arranged at one end of the combustion chamber 1, and the second heat-insulating sleeve 6 is fixed between the combustion chamber 1 and the rear sealing cover 5; the nozzle tube 9 is arranged on the rear cover 5, and the plaster 12 is arranged in the medicine chamber 3.
In a further embodiment, a gap is left between the outer wall of the medicine chamber 3 and the inner wall of the combustion chamber 1.
In a further embodiment, the chamber 3 is fixed at one end of the combustion chamber by four support legs.
In a further embodiment, a pressure measuring hole penetrating through the heat insulating sleeve 2 is formed on the side wall surface of the combustion chamber 1 near the end surface.
In a further embodiment, two symmetrical holes are formed in the middle of the base 10, and two holes are formed in the side face of the thrust adapter 11. If the front end ignites, the wire is led out through two holes in the side surface of the thrust adapter, and is inserted into the front end through two holes in the base 10 to ignite. If the rear end is ignited, the pressure can be measured on two holes on the side surface of the thrust adapter.
In a further embodiment, the nozzle 9 is a conical nozzle with a convergence half angle of 22.5 ° and an expansion half angle of 7.5 °.
In a further embodiment, the throat diameter of the lance 9 is 3.5 to 6 mm.
In some embodiments, the combustion chamber 1, the first aeration plate 4, the rear cover 5, the second aeration plate 7, the support sleeve 8, the nozzle 9, the base 10 and the thrust adapter 11 are all made of 45-grade steel, and are mainly used for bearing high temperature and high pressure and can be reused; the first heat insulation sleeve 2 and the second heat insulation sleeve 6 are thickened epoxy heat insulation sleeves; the medicine chamber 3 adopts combustible nitrocotton; plaster 12 is the gel fuel tested.
According to the invention, according to the performance and interface requirements of an engine igniter, a chemical chamber is formed by hot stamping of celluloid, ignition is performed in a front-mounted manner, and double-path redundancy of a insensitive ignition head is realized. In order to avoid the adverse effect of ignition gas generated by ignition powder on the surface, a front ignition medicine box is adopted, and the rear end is used for ignition. In addition, two layers of rectifying plates are designed at the rear end of the ointment to rectify the ignition gas. The jet pipe is a key part of the engine, and when the engine works, high-temperature and high-pressure fuel gas in the combustion chamber flows through the jet pipe, and then heat energy and pressure potential energy are converted into high-speed kinetic energy, so that thrust is generated. Considering factors such as processing period, experiment cost and the like, the conical spray pipe is adopted, the convergence half angle of the spray pipe is 22.5 degrees, and the expansion half angle of the spray pipe is 7.5 degrees.
Considering that the synthesis amount of certain key components is small, 100 g-order composite medicine cannot be prepared, and the complexity of a pouring process with extremely small medicine loading amount is combined, so that the prepared paste medicine/semi-solidified paste medicine is filled in a heat-insulating medicine chamber, vacuumized, vacuumed, bubble-exhausted, stuck with a stopper sheet on the upper surface, and a quasi-constant combustion surface, the trajectory curve is stable, and the preparation process and the preparation period can be greatly shortened.
The method has the advantages that the small dosage is considered, the engine is verified to be a thick-wall metal shell, the heat absorption capacity is large, the heat insulation protection of the inner cavity of the engine needs to be enhanced, and the measure of thickening the epoxy heat insulation sleeve is adopted to ensure the accurate evaluation of the specific impact of the engine.
Due to the fluidity of the paste charge, if the back-end ignition is directly adopted, the powder gas generated by the ignition powder directly impacts the surface of the paste, so that the difference between the combustion surface and the ideal combustion surface is large, and therefore, a rectifying plate and the like are required to rectify the ignition gas. The semi-solidified paste has little influence of ignition gas on the surface, and can adopt rear-end ignition.
The combustion chamber 1 is enclosed by a casing and serves as a combustion space for fuel; the first insulating sleeve 2 has the function of reducing heat conduction in the shell, so that higher temperature can be obtained in the engine; the medicine chamber 3 is a place for filling fuel; the first vent plate 4 enables the rear gas to ignite the medicine in the combustion chamber through the vent plate and prevents the residue from flowing to block the spray pipe; the rear end cover 5 and the combustion chamber shell are connected by threads to form an engine shell together; the second heat insulation sleeve 6 reduces heat conduction, so that fuel gas can keep high temperature and high pressure in the engine; the second vent plate 7 enables the rear gas to ignite the medicine in the combustion chamber through the vent plate and prevents the residue from flowing to block the spray pipe; the supporting sleeve 8 divides the two vent plates to filter residues twice; the jet pipe 9 accelerates the gas flow to obtain higher thrust; a force receiving member for receiving the thrust of the base 10; the thrust adapter 11 introduces the engine thrust into the adapter of the thrust sensor and is connected with the combustion chamber shell by threads; plaster 12 is a solidified gel.
The working principle of the invention is as follows: the ignition cartridge bag passes through the spray tube and inserts the combustion chamber, the wire stretches out through the spray tube and connects ignition, the back high temperature high pressure gas of ignition passes through two breather plates and gel fuel contact, ignite gel fuel, the back gas of gel combustion passes through the breather plate and forms high temperature high pressure gas at whole combustion chamber, then spout from the spray tube blowout, pressure measurement hole connection pressure sensor on the combustion chamber measures pressure, open in the middle of the base, also can connect pressure sensor in thrust adapter both sides and obtain pressure, thrust sensor measures thrust from thrust adapter.
Claims (3)
1. The gel fuel performance test engine is characterized by comprising a combustion chamber (1), a first insulating sleeve (2), a medicine chamber (3), a first vent plate (4), a rear sealing cover (5), a second insulating sleeve (6), a second vent plate (7), a support sleeve (8), a spray pipe (9), a base (10), a thrust adapter (11) and a plaster (12), wherein the base (10) is connected with one end of the combustion chamber (1) through an internal thread, the thrust adapter (11) is connected with one end of the combustion chamber (1) through an external thread, the first insulating sleeve (2) is arranged on the inner wall of the combustion chamber (1), the medicine chamber (3) is arranged in the combustion chamber (1), the first vent plate (4) is arranged in the combustion chamber (1) and is positioned at a port of the medicine chamber (3), the second vent plate (7) is fixed on the first vent plate (4) through the support sleeve (8), the rear sealing cover (5) is arranged at one end of the combustion chamber (1), and the second heat-insulating sleeve (6) is fixed between the combustion chamber (1) and the rear sealing cover (5); the spray pipe (9) is arranged on the rear sealing cover (5), and the plaster (12) is arranged in the medicine chamber (3); a gap is reserved between the outer wall of the medicine chamber (3) and the inner wall of the combustion chamber (1); the medicine chamber (3) is fixed at one end of the combustion chamber through four supporting legs; pressure measuring holes penetrating through the first insulating sleeve (2) are formed in the position, close to the end face, of the side wall surface of the combustion chamber (1), gaps are reserved due to material design, but when the combustion chamber is used, paper sheets are added in the circumferential direction and the axial direction for fixing, and meanwhile, a pressure measuring port does not need to be blocked; two symmetrical holes are formed in the middle of the base (10), and two holes are formed in the side face of the thrust adapter (11).
2. The gel fuel performance testing engine of claim 1, characterized in that the nozzle (9) is a conical nozzle with a convergence half angle of 22.5 ° and a divergence half angle of 7.5 °.
3. A gel fuel performance test engine according to claim 1, characterized in that the throat diameter of the lance (9) is 3.5-6 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011450702.1A CN112696286B (en) | 2020-12-12 | 2020-12-12 | Gel fuel performance test engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011450702.1A CN112696286B (en) | 2020-12-12 | 2020-12-12 | Gel fuel performance test engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112696286A CN112696286A (en) | 2021-04-23 |
| CN112696286B true CN112696286B (en) | 2022-05-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011450702.1A Expired - Fee Related CN112696286B (en) | 2020-12-12 | 2020-12-12 | Gel fuel performance test engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112696286B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006226202A (en) * | 2005-02-18 | 2006-08-31 | Asahi Kasei Chemicals Corp | Two-step thrust rocket motor |
| CN103604905A (en) * | 2013-11-20 | 2014-02-26 | 西安近代化学研究所 | Combustion speed testing method for gel propellant |
| CN105003357A (en) * | 2015-07-17 | 2015-10-28 | 南京理工大学 | Pasty propellant fuel gas generator ignition device based on solid rocket engine |
| CN205977460U (en) * | 2016-08-02 | 2017-02-22 | 袁逸凡 | Rocket engine of anti -backfire |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
-
2020
- 2020-12-12 CN CN202011450702.1A patent/CN112696286B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006226202A (en) * | 2005-02-18 | 2006-08-31 | Asahi Kasei Chemicals Corp | Two-step thrust rocket motor |
| CN103604905A (en) * | 2013-11-20 | 2014-02-26 | 西安近代化学研究所 | Combustion speed testing method for gel propellant |
| CN105003357A (en) * | 2015-07-17 | 2015-10-28 | 南京理工大学 | Pasty propellant fuel gas generator ignition device based on solid rocket engine |
| CN205977460U (en) * | 2016-08-02 | 2017-02-22 | 袁逸凡 | Rocket engine of anti -backfire |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
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| Publication number | Publication date |
|---|---|
| CN112696286A (en) | 2021-04-23 |
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Granted publication date: 20220520 |