CN108626028B - Rotary driving charging structure for laser chemical combined propeller - Google Patents
Rotary driving charging structure for laser chemical combined propeller Download PDFInfo
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- CN108626028B CN108626028B CN201810436098.3A CN201810436098A CN108626028B CN 108626028 B CN108626028 B CN 108626028B CN 201810436098 A CN201810436098 A CN 201810436098A CN 108626028 B CN108626028 B CN 108626028B
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- steering engine
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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
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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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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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
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Lasers (AREA)
Abstract
The rotary driving charging structure for the laser chemical combined propeller comprises a turntable, a rotary steering engine and at least two combustion chambers; the rotary steering engine is connected with the rotary table and used for driving the rotary table to rotate; the combustion chambers are fixedly connected with the rotary table in a sealing way, and the rotation of the rotary table drives each combustion chamber to rotate; each combustion chamber is filled with a solid propellant; the combustion chambers are arranged in parallel, and the rotary steering engine is arranged in parallel with the combustion chambers. The rotary driving charging structure for the laser chemical combined thruster is small in size and light in weight, and can meet the power requirement of micro-satellite orbit control.
Description
Technical Field
The invention relates to a laser solid micro thruster, in particular to an rotary driving charge structure for a laser chemical combined thruster.
Background
The existing propulsion system of the microsatellite is limited by the size and the weight of the satellite, the loading amount is low, the total thrust of a thruster is too low, the satellite cannot make large orbit deviation and maneuvering, and the orbit changing function of the satellite is severely limited. The loading of the microsatellite propulsion system is increased, so that various performances of the microsatellite are obviously improved, and the microsatellite is easy to ensure formation flight, thereby completing various tasks. The traditional propulsion system is relatively large in size and mass and is not suitable for the use of the microsatellite.
The laser propulsion engine disclosed in patent CN102062019A is a liquid rocket engine with adjustable combustion chamber volume, and the laser propulsion engine comprises a pressurization structure for driving liquid propellant, so that the propulsion engine is complex in structure, heavy in weight and not suitable for microsatellites.
The laser propulsion device disclosed in patent CN101737201A is a target belt type laser plasma engine, the laser is transmitted through a substrate target belt and is irradiated on a propellant through focusing, the laser plasma combined propulsion system disclosed in patent CN105201769A is an engine which generates plasma through laser ablation and is accelerated through a magnetic field, and the thrust provided by the two engines is very small and is in the micro Newton level.
Disclosure of Invention
The invention aims to provide rotary driving charging structures for a laser chemical combined propeller, which have small volume and light weight, have thrust above millinewton magnitude and can meet the power requirement of micro-satellite orbit control.
In order to achieve the purpose, the invention provides rotary driving charging structures for a laser chemical combined propeller, which comprise a turntable, a rotary steering engine and at least two combustion chambers, wherein the rotary steering engine is connected with the turntable and used for driving the turntable to rotate, the combustion chambers are fixedly connected with the turntable in a sealing mode, the rotation of the turntable drives the combustion chambers to rotate, solid propellants are filled in the combustion chambers, the combustion chambers are arranged in parallel, and the rotary steering engine and the combustion chambers are arranged in parallel.
The rotary driving charging structure for the laser chemical combination propeller comprises a combustion chamber shell, an th flange, a second flange, a lens, a heat insulating layer, a solid propellant and a base, wherein the lens is arranged between the th flange and the second flange, the th flange is connected with the second flange, the second flange is connected with the end of the combustion chamber shell, the base is arranged in the combustion chamber shell, the heat insulating layer is arranged in the combustion chamber shell, the end of the heat insulating layer is supported on the base, the end of the heat insulating layer is supported on the second flange, a gap is reserved between the heat insulating layer and the combustion chamber shell, a through hole is formed in the base, the gap and the through hole form a gas flow channel, the solid propellant is arranged in the heat insulating layer, a boss is formed at the joint of the th flange and the second flange, a second boss is arranged on the outer wall of the combustion chamber shell, and the rotary disc is clamped between the boss and the second boss, so that the connection between the rotary disc and the combustion chamber is achieved.
The rotary driving charging structure for the laser chemical combined propeller comprises a combustion chamber shell, wherein an inner cavity of the combustion chamber shell comprises two sections, wherein the section is cylindrical, the section is horn-shaped, the diameter of the horn-shaped section is gradually reduced from inside to outside and is used as a spray pipe, a gas flow channel is communicated with the spray pipe, and a base is arranged at the junction of the two sections.
The rotary driving charging structure for the laser chemical combination thruster is characterized in that the end, close to the second flange, of the heat insulating layer is provided with a petal-shaped edge, and the petal-shaped edge is supported on the second flange.
The rotary driving charge structure for the laser chemical combination thruster is characterized in that the joint of the th flange and the second flange, the joint of the second flange and the combustion chamber shell and the joint of the lens and the second flange are coated with high-temperature sealant.
The rotary drive charge configuration for a laser chemical combination pusher described above, wherein the combustion chamber housing, the thermal insulation layer, the solid propellant, the lens, the base, the th flange and the second flange are coaxial.
The rotary driving charging structure for the laser chemical combined propeller is characterized in that the turntable is provided with a plurality of through holes, wherein through holes are located in the center of the turntable and used for mounting a rotary steering engine, and the rest through holes are uniformly distributed along the circumference and used for assembling a combustion chamber.
The rotary driving charging structure for the laser chemical combined propeller is characterized in that laser emitted by a laser irradiates on the solid propellant through a lens, and the rotary steering engine drives the rotary disc to rotate so as to ignite the solid propellant in different combustion chambers.
Compared with the prior art, the invention has the beneficial technical effects that:
1) according to the rotary driving charging structure for the laser chemical combined propeller, the combustion chambers and the rotary steering engine and the combustion chambers are arranged in parallel, so that the space utilization rate is high, and the charging structure is small in size; the combustion chambers can be charged differently, so that the charging amount is improved, different thrust combinations can be provided through charging matching, and the power requirement of the microsatellite orbit control is met; the solid propellant is adopted, a supercharging device is not needed, the structure of the propeller is greatly simplified, and the weight of the propeller is reduced;
2) the rotary driving charging structure for the laser chemical combined propeller has the advantages that the combustion chamber is simple and compact in structure, small in size and light in weight;
3) the rotary driving charging structure for the laser chemical combined propeller has the advantages that the combustion chamber and the spray pipe are designed integrally, the structure is simple and compact, and the volume and the weight are reduced;
4) according to the rotary driving charging structure for the laser chemical combined propeller, the base is matched with the petal-shaped edges to limit the heat insulation layer in the axial direction and the radial direction, so that a gas flow channel is supported;
5) according to the rotary driving charging structure for the laser chemical combined thruster, a good sealing effect can be achieved only by coating a high-temperature sealant, and the structure of the rotary driving charging structure is simplified;
6) according to the rotary driving charging structure for the laser chemical combined propeller, the rotary disc and the rotary steering engine are adopted to rotate each combustion chamber, lasers are used for igniting the propellant in each combustion chamber, and the propeller is simple in structure and light in weight.
Drawings
The rotary driving charging structure for the laser chemical combination thruster is provided by the following embodiments and the attached drawings.
Figure 1 is a cross-sectional view of a rotary drive charge configuration for a laser chemical combination pusher in accordance with a preferred embodiment of the present invention.
FIG. 2 is a cross-sectional view of a single combustion chamber in a preferred embodiment of the invention.
FIG. 3 is a schematic view of a turntable in a preferred embodiment of the present invention.
Figure 4 is a schematic diagram of the operation of a rotary drive charge configuration for a laser chemical combination pusher in accordance with a preferred embodiment of the present invention.
Detailed Description
The rotary drive charge configuration for a laser chemical combination pusher of the present invention will be described in further detail at step with reference to fig. 1-4.
FIG. 1 is a cross-sectional view of a rotary drive charge configuration for a laser chemical combination pusher in accordance with a preferred embodiment of the present invention; FIG. 2 is a cross-sectional view of a single combustion chamber in accordance with a preferred embodiment of the present invention.
Referring to fig. 1 and 2, the rotary driving charge structure for the laser chemical combined thruster of the present embodiment includes a turntable 4, a rotary steering engine 9 and at least two combustion chambers;
the rotary steering engine 9 is connected with the turntable 4, and the rotary steering engine 9 is used for driving the turntable 4 to rotate;
the combustion chambers are fixedly connected with the rotary table 4 in a sealing manner, and the rotation of the rotary table 4 drives each combustion chamber to rotate; each combustion chamber is filled with a solid propellant;
the combustion chambers are arranged in parallel, and the rotary steering engine 9 is arranged in parallel with the combustion chambers.
The rotary driving explosive loading structure for the laser chemical combined propeller is characterized in that the combustion chambers and the rotary steering engine 9 and the combustion chambers are arranged in parallel, the space utilization rate is high, the explosive loading structure is small in size, the explosive loading of the combustion chambers can be different (namely different propellants can be loaded in different combustion chambers), the explosive loading amount is improved, different thrust combinations can be provided through explosive loading matching, the power requirement of micro satellite orbit control is met, the propeller structure is greatly simplified due to the fact that a solid propellant is adopted, a pressurizing device is not needed, the weight of the propeller is reduced, the combustion chambers are rotated by the rotary disc and the rotary steering engine, lasers can be used for igniting the propellants in the combustion chambers, and the propeller is simple in structure and light in weight.
Preferably, the rotary drive charge configuration of the present embodiment comprises six combustion chambers.
The structure of each combustion chamber is the same, and the combustion chamber comprises a combustion chamber shell 5, an -th flange 1, a second flange 3, a lens 2, an insulating layer 6, a solid propellant 7 and a base 8;
the lens 2 is placed between the th flange 1 and the second flange 3, the th flange 1 and the second flange 3 are connected through bolts, and the lens 2 is clamped between the th flange 1 and the second flange 3;
the second flange 3 is connected with the end of the combustion chamber shell 5, the inner cavity of the other end of the combustion chamber shell 5 is designed into a horn shape and is used as a spray pipe 15, the heat insulating layer 6 and the base 8 are both arranged in the combustion chamber shell 5, the end of the heat insulating layer 6 close to the horn-shaped spray pipe is supported on the base 8, the other end of the heat insulating layer 6 is supported on the second flange 3, a gap 10 is reserved between the heat insulating layer 6 and the combustion chamber shell 5, a through hole 11 is arranged on the base 8, the gap 10 and the through hole 11 are communicated to form a gas flow channel, the gas flow channel is communicated with the horn-shaped spray pipe, and gas generated by the combustion chamber is sprayed out of the horn-shaped spray pipe through the gas flow channel;
the solid propellant 7 is arranged in the heat insulating layer 6;
Referring to fig. 2, preferably, the combustion chamber housing 5 is a circular tube-shaped structure, the end of the inner cavity is a circular opening, the end of the inner cavity is a trumpet-shaped opening, the diameter of the trumpet-shaped opening gradually decreases from inside to outside, that is, the inner cavity of the combustion chamber housing 5 comprises two sections, the section is cylindrical, the section is a trumpet-shaped opening, a third boss is arranged at the junction of the two sections and on the inner wall of the combustion chamber housing 5, and the base 8 is placed on the third boss.
The combustion chamber and the spray pipe are designed integrally, the structure is simple and compact, and the volume and the weight are reduced.
Referring to fig. 1, the insulating layer 6 is preferably a cylindrical structure with two open ends, the end of which is supported on the base 8, and the end of which is provided with a petaloid rim 14, the petaloid rim 14 being supported on the second flange 3, the cooperation of the base 8 and the petaloid rim 14 axially and radially limiting the insulating layer 6 and supporting the gas flow passage.
Referring to fig. 2, preferably, the flange 1 has a circular ring structure, the outer wall of the flange 1 is stepped, the second flange 3 also has a circular ring structure, the outer wall and the inner wall of the flange are both stepped, the stepped outer wall of the flange 1 is matched with the stepped inner wall of the second flange 3, a groove is formed in the second flange 3, the lens 2 is placed in the groove, the second flange 3 is supported on the combustion chamber housing 5 by using the stepped outer wall of the second flange 3, that is, the th section with a small outer diameter is inserted into the second flange 3, and the section with a small outer diameter of the second flange 3 is inserted into the combustion chamber housing 5.
Because the pressure inside the combustion chamber is low, the joint of the th flange 1 and the second flange 3, the joint of the second flange 3 and the combustion chamber shell 5 and the joint of the lens and the second flange do not need sealing ring structures, and the joints can be sealed only by coating high-temperature sealant, so that the structure of the rotary driving charge structure can be simplified.
The combustion chamber housing 5, the thermal insulation layer 6, the solid propellant 7, the lens 2, the base 8, the -th flange 1 and the second flange 3 are coaxial.
FIG. 3 is a schematic view of the turntable in the preferred embodiment of the present invention.
Referring to fig. 3, the turntable 4 is provided with seven through holes, wherein through holes are regular hexagons, the regular hexagons 41 are located in the center of the turntable 4, the other six through holes are circles, six circular through holes 42 are uniformly arranged along the circumference, the regular hexagons 41 are used for mounting the rotary steering engine 9, and the six circular through holes 42 are used for assembling six combustion chambers.
Figure 4 is a schematic diagram of the operation of a rotary drive charge configuration for a laser chemical combination pusher in accordance with a preferred embodiment of the present invention.
Referring to fig. 4, laser 17 emitted by a laser 16 is irradiated on the solid propellant 7 through the lens 2, and the rotary steering gear 9 drives the rotary disc 4 to rotate so as to ignite the solid propellant 7 in different combustion chambers.
Claims (5)
1. A rotary driving charging structure for a laser chemical combined propeller is characterized by comprising a turntable, a rotary steering engine and at least two combustion chambers;
the rotary steering engine is connected with the rotary table and used for driving the rotary table to rotate;
the combustion chambers are fixedly connected with the rotary table in a sealing way, and the rotation of the rotary table drives each combustion chamber to rotate; each combustion chamber is filled with a solid propellant;
the combustion chambers are arranged in parallel, and the rotary steering engine is arranged in parallel with the combustion chambers;
the combustion chamber comprises a combustion chamber shell, an th flange, a second flange, a lens, an insulating layer, a solid propellant and a base;
the lens is arranged between the th flange and the second flange, and the th flange is connected with the second flange;
the heat insulation layer is arranged in the combustion chamber shell, the end of the heat insulation layer is supported on the base, the other end of the heat insulation layer is supported on the second flange, a gap is reserved between the heat insulation layer and the combustion chamber shell, the base is provided with a through hole, and the gap and the through hole are communicated to form a gas flow channel;
the solid propellant is filled in the heat insulation layer;
a boss is formed at the joint of the th flange and the second flange, a second boss is arranged on the outer wall of the combustion chamber shell, and the turntable is clamped between the th boss and the second boss, so that the connection between the turntable and the combustion chamber is realized;
the inner cavity of the combustion chamber shell comprises sections which are cylindrical, and sections which are trumpet-shaped, wherein the diameter of the trumpet-shaped sections is gradually reduced from inside to outside and is used as a spray pipe, and a fuel gas flow channel is communicated with the spray pipe;
the flange is of a circular ring structure, the outer wall of the flange is step-shaped, the second flange is also of a circular ring structure, the outer wall and the inner wall of the second flange are step-shaped, the step-shaped outer wall of the flange is matched with the step-shaped inner wall of the second flange, a groove is formed in the second flange, and the lens is arranged in the groove;
and the joint of the th flange and the second flange, the joint of the second flange and the combustion chamber shell and the joint of the lens and the second flange are coated with high-temperature sealant.
2. The rotary drive charge configuration for a laser chemical combination pusher of claim 1 wherein the insulation layer is provided with a petal-like rim adjacent the end of the second flange, the petal-like rim being supported on the second flange.
3. The rotary drive charge configuration for a laser chemical combination pusher of claim 1, wherein the combustion chamber housing, the thermal insulation layer, the solid propellant, the lens, the base, the th flange, and the second flange are coaxial.
4. The rotary driving charge structure for the laser chemical combination propeller as recited in claim 1, wherein the turntable is provided with a plurality of through holes, wherein through holes are located in the center of the turntable and used for mounting the rotary steering engine, and the rest through holes are uniformly arranged along the circumference and used for assembling the combustion chamber.
5. The rotary driven charge structure for the laser chemical combination propeller as recited in claim 1, wherein laser emitted by the laser irradiates on the solid propellant through the lens, and the rotary steering engine drives the rotary disk to rotate so as to ignite the solid propellant in different combustion chambers.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810436098.3A CN108626028B (en) | 2018-05-09 | 2018-05-09 | Rotary driving charging structure for laser chemical combined propeller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810436098.3A CN108626028B (en) | 2018-05-09 | 2018-05-09 | Rotary driving charging structure for laser chemical combined propeller |
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| CN108626028A CN108626028A (en) | 2018-10-09 |
| CN108626028B true CN108626028B (en) | 2020-01-31 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110145412B (en) * | 2019-05-27 | 2020-11-03 | 北京理工大学 | Gate type solid rocket engine |
| CN110284995B (en) * | 2019-06-14 | 2020-07-24 | 北京理工大学 | Disk transfer type chambered solid rocket engine |
| CN111022215B (en) * | 2019-11-15 | 2021-09-07 | 上海新力动力设备研究所 | Line light spot scanning type laser chemical micro-thruster |
| CN111071491B (en) * | 2019-12-09 | 2023-08-11 | 西安近代化学研究所 | Annular solid propellant charging structure |
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| CN102297042A (en) * | 2010-06-25 | 2011-12-28 | 中国科学院电子学研究所 | Inspiration laser thruster with low igniting threshold |
| CN104330519A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Particle airflow suspension laser ignition experiment device |
| CN106353449A (en) * | 2016-11-03 | 2017-01-25 | 上海理工大学 | Dynamic testing device and dynamic testing method for burning speed of initiative laser type solid rocket propellant |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9255549B1 (en) * | 1997-07-21 | 2016-02-09 | William S. Brown | Laser ignition for liquid propellant rocket engine injectors |
| CN104181160B (en) * | 2014-08-25 | 2019-07-12 | 南京理工大学 | A kind of signal pickup assembly based on the experiment of solid propellant laser ignition |
| CN104963790B (en) * | 2015-06-01 | 2017-05-24 | 上海御虹激光设备有限公司 | Laser ignition device |
| CN105181878B (en) * | 2015-08-03 | 2017-02-01 | 南京理工大学 | Rotating speed adjustable laser ignition rotation experimental device |
| CN105044274B (en) * | 2015-08-03 | 2016-07-06 | 南京理工大学 | The laser ignition experimental provision of many sample continuous ignitions |
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2018
- 2018-05-09 CN CN201810436098.3A patent/CN108626028B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102297042A (en) * | 2010-06-25 | 2011-12-28 | 中国科学院电子学研究所 | Inspiration laser thruster with low igniting threshold |
| CN104330519A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Particle airflow suspension laser ignition experiment device |
| CN106353449A (en) * | 2016-11-03 | 2017-01-25 | 上海理工大学 | Dynamic testing device and dynamic testing method for burning speed of initiative laser type solid rocket propellant |
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