CN108626028A - The rotation for combining propeller for laser chemistry drives charge constitution - Google Patents
The rotation for combining propeller for laser chemistry drives charge constitution Download PDFInfo
- Publication number
- CN108626028A CN108626028A CN201810436098.3A CN201810436098A CN108626028A CN 108626028 A CN108626028 A CN 108626028A CN 201810436098 A CN201810436098 A CN 201810436098A CN 108626028 A CN108626028 A CN 108626028A
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- CN
- China
- Prior art keywords
- flange
- rotation
- combustion chamber
- turntable
- charge constitution
- 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.)
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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
- F02K9/08—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
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lasers (AREA)
Abstract
The rotation driving charge constitution for laser chemistry joint propeller of the present invention includes turntable, rotate steering wheel and at least two combustion chambers；The rotate steering wheel is connect with the turntable, and the rotate steering wheel is for driving the turntable to rotate；The combustion chamber is connected with turntable sealing, and the rotation of the turntable drives each combustion chamber rotation；Each combustion chamber is equipped with solid propellant；Each combustion chamber is arranged parallel to, and the rotate steering wheel is arranged in parallel with the combustion chamber.The rotation for laser chemistry joint propeller of the present invention drives charge constitution, small, light-weight, and can meet the power demand of microsatellite orbits controlling.
Description
Technical field
The present invention relates to laser solid micro-thrusters, more particularly, to a kind of rotation for combining propeller for laser chemistry
Drive charge constitution.
Background technology
The propulsion system of existing microsatellite is limited to satellite size and weight, and explosive payload is low, leads to thruster
It always breaks through low, and satellite can not be made to do the deviation of big track and motor-driven, so that it is become rail function and be severely limited.Increase small defend
The explosive payload of star propulsion system will significantly improve the various aspects of performance of microsatellite, and microsatellite is made to be easy to ensure formation flight,
To complete various tasks.And traditional propulsion system volume and quality are all relatively large, are not suitable for the use of microsatellite.
The laser propelled engine that patent CN102062019A is disclosed is a kind of adjustable liquid rocket hair of combustion chamber volume
Motivation.Include pressurized construction to drive liquid propellant, the laser propelled engine, causes propelling motor complicated, again
Amount is big, is not suitable for microsatellite.
The laser propulsion device that patent CN101737201A is disclosed is a kind of laser plasma engine of target belt, is swashed
Light transmission crosses that base target band logical is over-focusing to be radiated on propellant.The laser plasma combination that patent CN105201769A is disclosed
Propulsion system is a kind of laser ablation generation plasma, and passes through the engine that magnetic field accelerates.What both engines provided
Thrust all very littles are micro- ox magnitude.
Invention content
The purpose of the present invention is to provide a kind of rotations for combining propeller for laser chemistry to drive charge constitution, volume
It is small, light-weight, and thrust can meet the power demand of microsatellite orbits controlling more than milli ox magnitude.
To achieve the above object, the present invention provides a kind of rotation driving powder charge for laser chemistry joint propeller
Structure, including turntable, rotate steering wheel and at least two combustion chambers；The rotate steering wheel is connect with the turntable, the rotation rudder
Machine is for driving the turntable to rotate；The combustion chamber is connected with turntable sealing, and the rotation of the turntable drives each burning
Room rotates；Each combustion chamber is equipped with solid propellant；Each combustion chamber is arranged parallel to, the rotate steering wheel and the combustion chamber
Parallel arrangement.
The above-mentioned rotation for laser chemistry joint propeller drives charge constitution, wherein the combustion chamber includes burning
Room housing, first flange, second flange, lens, heat insulation layer, solid propellant and pedestal；The lens are placed in first method
It is blue between the second flange, the first flange is connect with the second flange；The second flange and the combustion chamber
One end of shell connects；The pedestal is placed in the combustion chamber shell body；The thermal insulation is placed in the combustion chamber shell body,
One end supports on the base, and the other end is supported in the second flange；The heat insulation layer and the burning chamber shell it
Between there are gap, the pedestal is equipped with through hole, and gap and through hole perforation constitute gas flow channel；The solid propellant propulsion
Agent is loaded in the heat insulation layer；The junction of the first flange and the second flange forms first boss, the combustion chamber
The outer wall of shell is equipped with second boss, and the turntable is clamped between the first boss and the second boss, realizes
Connection between the turntable and combustion chamber.
It is above-mentioned for laser chemistry joint propeller rotation drive charge constitution, wherein the burning chamber shell it is interior
Chamber includes two sections：One section is cylindric, and another section is horn-like；Horn-like section of diameter is gradually reduced from inside to outside, is used as jet pipe,
Gas flow channel is penetrated through with jet pipe；The intersection at two sections is arranged in the pedestal.
The above-mentioned rotation for laser chemistry joint propeller drives charge constitution, wherein the heat insulation layer is close to second
One end of flange is equipped with petal-shaped edge, which is supported in the second flange.
It is above-mentioned for laser chemistry joint propeller rotation drive charge constitution, wherein the first flange with it is described
Second flange junction, the second flange and the burning chamber shell junction and the lens connect with the second flange
The place of connecing is coated with elevated-temperature seal agent.
The above-mentioned rotation for laser chemistry joint propeller drives charge constitution, wherein the burning chamber shell, described
Heat insulation layer, the solid propellant, the lens, the pedestal, the first flange and the second flange are coaxial.
The above-mentioned rotation for laser chemistry joint propeller drives charge constitution, wherein the turntable is equipped with multiple logical
Hole, one of through-hole is located at the center of turntable, for installing rotate steering wheel；Remaining through-hole is evenly distributed along the periphery, and is used for group
Fill combustion chamber.
The above-mentioned rotation for laser chemistry joint propeller drives charge constitution, wherein the laser that laser is launched
By lens lighting on solid propellant, rotate steering wheel driving disc rotation, to be used for lighting the different indoor solids of burning
Propellant.
Compared with prior art, the method have the benefit that：
1) rotation for laser chemistry joint propeller of the invention drives charge constitution, between each combustion chamber and revolves
It comes about using parallel arrangement between machine and combustion chamber, space availability ratio is high so that charge constitution is small；At least two burnings
Room, and each combustion chamber powder charge can be different, not only increase explosive payload, and can arrange in pairs or groups by powder charge and provide different thrusts combinations,
Meet the power demand of microsatellite orbits controlling；Using solid propellant, it is not necessarily to supercharging device, enormously simplifies propeller knot
Structure alleviates propeller weight；
2) rotation for laser chemistry joint propeller of the invention drives charge constitution, chamber structure simple, tight
It gathers, it is small, light-weight；
3) rotation for laser chemistry joint propeller of the invention drives charge constitution, combustion chamber and jet pipe integration
Design, it is simple and compact for structure, help to reduce volume and weight；
4) the rotation driving charge constitution for laser chemistry joint propeller of the invention, pedestal and petal-shaped edge
Cooperation limits heat insulation layer on axially and radially, supports gas flow channel；
5) rotation for laser chemistry joint propeller of the invention drives charge constitution, only applies elevated-temperature seal agent energy
The sealing effect reached simplifies the structure of rotation driving charge constitution；
6) rotation for laser chemistry joint propeller of the invention drives charge constitution, using turntable and rotate steering wheel
Each combustion chamber is rotated, each indoor propellant of burning can be lighted using a laser so that propeller structure is simply, again
Amount is light.
Description of the drawings
The rotation for laser chemistry joint propeller of the present invention drives charge constitution by embodiment below and attached drawing
It provides.
Fig. 1 is the section view of the rotation driving charge constitution for laser chemistry joint propeller of present pre-ferred embodiments
Figure.
Fig. 2 is the sectional view of separate unit combustion chamber in present pre-ferred embodiments.
Fig. 3 is the schematic diagram of present pre-ferred embodiments turntable.
Fig. 4 is that the rotation driving charge constitution work in present pre-ferred embodiments for laser chemistry joint propeller is former
Reason figure.
Specific implementation mode
Charge constitution is driven to the rotation for combining propeller for laser chemistry of the present invention below with reference to Fig. 1~Fig. 4
It is described in further detail.
Fig. 1 show the rotation driving charge constitution for laser chemistry joint propeller of present pre-ferred embodiments
Sectional view；Fig. 2 show the sectional view of separate unit combustion chamber in present pre-ferred embodiments.
Referring to Fig. 1 and Fig. 2, the rotation driving charge constitution for laser chemistry joint propeller of the present embodiment includes turning
Disk 4, rotate steering wheel 9 and at least two combustion chambers；
The rotate steering wheel 9 is connect with the turntable 4, and the rotate steering wheel 9 is for driving the turntable 4 to rotate；
The combustion chamber is connected with the sealing of the turntable 4, and the rotation of the turntable 4 drives each combustion chamber rotation；Each burning
Room is equipped with solid propellant；
Each combustion chamber is arranged parallel to, and the rotate steering wheel 9 is arranged in parallel with the combustion chamber.
The rotation for laser chemistry joint propeller of the present embodiment drives charge constitution, between each combustion chamber and revolves
It comes about using parallel arrangement between machine 9 and combustion chamber, space availability ratio is high so that charge constitution is small；At least two burnings
Room, and each combustion chamber powder charge can different (i.e. different combustion chambers can fill different propellants), not only increase explosive payload, and
It can be arranged in pairs or groups by powder charge and different thrusts combinations are provided, meet the power demand of microsatellite orbits controlling；Using solid propellant,
Without supercharging device, propeller structure is enormously simplified, alleviates propeller weight；Each combustion is rotated using turntable and rotate steering wheel
Room is burnt, each indoor propellant of burning can be lighted using a laser so that propeller structure is simple, light-weight.
Preferably, the rotation driving charge constitution of the present embodiment includes six combustion chambers.
Each chamber structure is identical.The combustion chamber include burning chamber shell 5, first flange 1, second flange 3,
Lens 2, heat insulation layer 6, solid propellant 7 and pedestal 8；
The lens 2 are placed between the first flange 1 and the second flange 3, the first flange 1 and described second
Flange 3 is bolted, and the lens 2 are clamped between the first flange 1 and the second flange 3；
The second flange 3 is connect with one end of the burning chamber shell 5, the other end of the burning chamber shell 5 it is interior
Chamber be designed as it is horn-like, be used as jet pipe 15；The heat insulation layer 6 and the pedestal 8 are placed in the burning chamber shell 5, described
Heat insulation layer 6 is supported on close to one end of horn-like jet pipe on the pedestal 8, and the other end of the heat insulation layer 6 is supported on described
On two flanges 3；There are gaps 10, the pedestal 8 to be equipped with through hole 11 between the heat insulation layer 6 and the burning chamber shell 5,
Gap 10 and the perforation of through hole 11 constitute gas flow channel, which penetrates through with horn-like jet pipe, combustion chamber production
Raw combustion gas is sprayed through the gas flow channel by horn-like jet pipe；
The solid propellant 7 is loaded in the heat insulation layer 6；
The first flange 1 and the junction of the second flange 3 form first boss 12, the burning chamber shell 5
Outer wall is equipped with second boss 13, and the turntable 4 is clamped between the first boss 12 and the second boss 13, realizes
Being connected between the turntable 4 and combustion chamber.
Referring to Fig. 2, preferably, the burning chamber shell 5 is tube-shaped structure, inner cavity one end is circular open, in
The chamber other end is flare openings, and diameter is gradually reduced the flare openings from inside to outside, i.e. the inner cavity of the burning chamber shell 5
Including two sections：One section is cylindric, and another section is horn-like, and two sections of intersection, the inner wall of burning chamber shell 5 are equipped with third
Boss, the pedestal 8 are placed on the third boss.
Combustion chamber and jet pipe integrated design, simple and compact for structure in the present invention, helps to reduce volume and weight.
Referring to Fig. 1, preferably, the heat insulation layer 6 is the tube structure of both ends open, one end is supported on the pedestal 8
On, the other end is equipped with petal-shaped edge 14, which is supported in the second flange 3.Pedestal 8 and petal-shaped
The cooperation at edge 14 limits heat insulation layer 6 on axially and radially, supports gas flow channel.
Referring to Fig. 2, preferably, the first flange 1 is circular ring structure, outer wall is step-like, and the second flange 3 is also
For circular ring structure, outer wall, inner wall are step-like；1 step-like outer wall of the first flange and the second flange 3 are step-like
Inner wall coordinates, and a groove is formed in the second flange 3, and the lens 2 are placed in the groove；The second flange 3 utilizes
Its step-like outer wall support is on the burning chamber shell 5.One section of small insertion second method of i.e. described 1 outer diameter of first flange
In orchid 3,3 outer diameter of the second flange small one section is inserted into the burning chamber shell 5.
Since combustion chamber pressure is relatively low, the first flange 1 and 3 junction of the second flange, second method
Orchid 3 is not necessarily to ring structure with 5 junction of the burning chamber shell and the lens with the second flange junction, only applies
Elevated-temperature seal agent, that is, salable, so as to the structure of the simplification rotation driving charge constitution.
It is the burning chamber shell 5, the heat insulation layer 6, the solid propellant 7, the lens 2, the pedestal 8, described
First flange 1 and the second flange 3 are coaxial.
Fig. 3 show the schematic diagram of present pre-ferred embodiments turntable.
Referring to Fig. 3, the turntable 4 is equipped with seven through-holes, and one of through-hole is regular hexagon, the regular hexagon through-hole 41
Positioned at the center of turntable 4, remaining six through-hole is circle, and six circular through holes 42 are evenly distributed along the periphery.The regular hexagon
Through-hole 41 is for installing rotate steering wheel 9, and six circular through holes 42 are for assembling six combustion chambers.
Fig. 4 show the rotation driving charge constitution work for laser chemistry joint propeller in present pre-ferred embodiments
Make schematic diagram.
Referring to Fig. 4, the laser 17 that laser 16 is launched is radiated at by lens 2 on solid propellant 7, rotate steering wheel 9
Driving disc 4 rotates, to be used for lighting the different indoor solid propellants 7 that burn.
Claims (9)
1. for laser chemistry joint propeller rotation drive charge constitution, which is characterized in that including turntable, rotate steering wheel and
At least two combustion chambers；
The rotate steering wheel is connect with the turntable, and the rotate steering wheel is for driving the turntable to rotate；
The combustion chamber is connected with turntable sealing, and the rotation of the turntable drives each combustion chamber rotation；Each combustion chamber is equipped with
Solid propellant；
Each combustion chamber is arranged parallel to, and the rotate steering wheel is arranged in parallel with the combustion chamber.
2. the rotation for laser chemistry joint propeller drives charge constitution as described in claim 1, which is characterized in that institute
It includes burning chamber shell, first flange, second flange, lens, heat insulation layer, solid propellant and pedestal to state combustion chamber；
The lens are placed between the first flange and the second flange, and the first flange connects with the second flange
It connects；
The second flange is connect with one end of the burning chamber shell；The pedestal is placed in the combustion chamber shell body；It is described
Thermal insulation is placed in the combustion chamber shell body, and one end supports on the base, and the other end is supported in the second flange；
There are gap between the heat insulation layer and the burning chamber shell, the pedestal is equipped with through hole, gap and through hole perforation
Constitute gas flow channel；
The solid propellant is loaded in the heat insulation layer；
The junction of the first flange and the second flange forms first boss, and the outer wall of the burning chamber shell is equipped with
Second boss, the turntable are clamped between the first boss and the second boss, realize the turntable and combustion chamber
Between connection.
3. the rotation for laser chemistry joint propeller drives charge constitution as claimed in claim 2, which is characterized in that institute
The inner cavity for stating burning chamber shell includes two sections：One section is cylindric, and another section is horn-like；Horn-like section of diameter from inside to outside by
It is decrescence small, it is used as jet pipe, gas flow channel is penetrated through with jet pipe；The intersection at two sections is arranged in the pedestal.
4. the rotation for laser chemistry joint propeller drives charge constitution as claimed in claim 2, which is characterized in that institute
It states heat insulation layer and is equipped with petal-shaped edge close to one end of second flange, which is supported in the second flange.
5. the rotation for laser chemistry joint propeller drives charge constitution as claimed in claim 2, which is characterized in that institute
It is circular ring structure to state first flange, and outer wall is step-like；The second flange is also circular ring structure, and outer wall, inner wall are
It is step-like；The step-like outer wall of first flange coordinates with the step-like inner wall of the second flange, the shape in the second flange
At a groove, the lens are placed in the groove；The second flange is using its step-like outer wall support in the combustion chamber shell
On body.
6. the rotation for laser chemistry joint propeller drives charge constitution as claimed in claim 5, which is characterized in that institute
State first flange and the second flange junction, the second flange and the burning chamber shell junction and the lens
It is coated with elevated-temperature seal agent with the second flange junction.
7. the rotation for laser chemistry joint propeller drives charge constitution as claimed in claim 2, which is characterized in that institute
State burning chamber shell, the heat insulation layer, the solid propellant, the lens, the pedestal, the first flange and described
Two flanges are coaxial.
8. the rotation for laser chemistry joint propeller drives charge constitution as described in claim 1, which is characterized in that institute
It states turntable and is equipped with multiple through-holes, one of through-hole is located at the center of turntable, for installing rotate steering wheel；Remaining through-hole is circumferentially
Uniformly arrangement, for assembling combustion chamber.
9. the rotation for laser chemistry joint propeller drives charge constitution as described in claim 1, which is characterized in that swash
The laser that light device is launched is by lens lighting on solid propellant, and rotate steering wheel driving disc rotates, to be used for lighting not
With the indoor solid propellant that burns.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
|---|---|---|---|
| CN201810436098.3A CN108626028B (en) | 2018-05-09 | 2018-05-09 | Rotary driving charging structure for laser chemical combined propeller |
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| Publication Number | Publication Date |
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| CN108626028A true CN108626028A (en) | 2018-10-09 |
| CN108626028B CN108626028B (en) | 2020-01-31 |
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| CN201810436098.3A Active CN108626028B (en) | 2018-05-09 | 2018-05-09 | Rotary driving charging structure for laser chemical combined propeller |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110145412A (en) * | 2019-05-27 | 2019-08-20 | 北京理工大学 | Gate-type solid propellant rocket |
| CN110284995A (en) * | 2019-06-14 | 2019-09-27 | 北京理工大学 | A kind of disk transfer type locellus solid propellant rocket |
| CN111022215A (en) * | 2019-11-15 | 2020-04-17 | 上海新力动力设备研究所 | Line light spot scanning type laser chemical micro-thruster |
| CN111071491A (en) * | 2019-12-09 | 2020-04-28 | 西安近代化学研究所 | Annular solid propellant charging structure |
Citations (8)
| 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 |
| CN104181160A (en) * | 2014-08-25 | 2014-12-03 | 南京理工大学 | Signal acquisition device based on experiments of laser-induced ignition of solid propellants |
| CN104330519A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Particle airflow suspension laser ignition experiment device |
| CN104963790A (en) * | 2015-06-01 | 2015-10-07 | 上海御虹激光设备有限公司 | Laser ignition device |
| CN105044274A (en) * | 2015-08-03 | 2015-11-11 | 南京理工大学 | Laser igniting experiment apparatus with multi-test piece continuous igniting function |
| CN105181878A (en) * | 2015-08-03 | 2015-12-23 | 南京理工大学 | Rotating speed adjustable laser ignition rotation experimental device |
| US9255549B1 (en) * | 1997-07-21 | 2016-02-09 | William S. Brown | Laser ignition for liquid propellant rocket engine injectors |
| 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 |
-
2018
- 2018-05-09 CN CN201810436098.3A patent/CN108626028B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9255549B1 (en) * | 1997-07-21 | 2016-02-09 | William S. Brown | Laser ignition for liquid propellant rocket engine injectors |
| 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 |
| CN104181160A (en) * | 2014-08-25 | 2014-12-03 | 南京理工大学 | Signal acquisition device based on experiments of laser-induced ignition of solid propellants |
| CN104330519A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Particle airflow suspension laser ignition experiment device |
| CN104963790A (en) * | 2015-06-01 | 2015-10-07 | 上海御虹激光设备有限公司 | Laser ignition device |
| CN105044274A (en) * | 2015-08-03 | 2015-11-11 | 南京理工大学 | Laser igniting experiment apparatus with multi-test piece continuous igniting function |
| CN105181878A (en) * | 2015-08-03 | 2015-12-23 | 南京理工大学 | Rotating speed adjustable laser ignition rotation experimental 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 |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110145412A (en) * | 2019-05-27 | 2019-08-20 | 北京理工大学 | Gate-type solid propellant rocket |
| CN110284995A (en) * | 2019-06-14 | 2019-09-27 | 北京理工大学 | A kind of disk transfer type locellus solid propellant rocket |
| CN111022215A (en) * | 2019-11-15 | 2020-04-17 | 上海新力动力设备研究所 | Line light spot scanning type laser chemical micro-thruster |
| 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 |
| CN111071491A (en) * | 2019-12-09 | 2020-04-28 | 西安近代化学研究所 | Annular solid propellant charging structure |
| 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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| CN108626028B (en) | 2020-01-31 |
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