CN110714854B - Solid rocket engine charge cluster type pouring tool and method - Google Patents
Solid rocket engine charge cluster type pouring tool and method Download PDFInfo
- Publication number
- CN110714854B CN110714854B CN201910974448.6A CN201910974448A CN110714854B CN 110714854 B CN110714854 B CN 110714854B CN 201910974448 A CN201910974448 A CN 201910974448A CN 110714854 B CN110714854 B CN 110714854B
- Authority
- CN
- China
- Prior art keywords
- material receiving
- chassis
- receiving disc
- solid rocket
- engine
- 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.)
- Active
Links
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
- F02K9/08—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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Casting Devices For Molds (AREA)
Abstract
A solid rocket engine charging cluster type pouring tool and a method belong to the technical field of energetic material preparation and filling, and comprise a chassis, a material receiving disc and a pattern plate assembly, wherein multiple engines are placed on the chassis, the material receiving disc is in matched combination with the multiple engines and the chassis, after the material receiving disc is connected with the chassis, the multiple engines are intensively bound, and the pattern plate assembly and the material receiving disc are in matched installation. Multiple engines are compactly arranged on a chassis one by one, positioned, intensively bound and integrally hoisted; the chassis and the material receiving disc have simple structures and are convenient to use; the size of the pattern plate is large, the opening of the pattern plate is not limited by the size of a single engine, and all corresponding spaces in the material receiving disc are covered; the pouring time of the tool can be greatly shortened, and the medicine slurry is exhausted more thoroughly. The tool is simple in structure, and the overall production efficiency of the powder charging line is improved; the method simplifies the operation flow of the pouring procedure, lightens the workload, reduces the labor intensity and saves the charging cost.
Description
Technical Field
The invention relates to a solid rocket engine charge cluster type pouring tool and a method, and belongs to the technical field of energetic material preparation and filling.
Background
The batch charging production of the small solid rocket engine generally adopts a one-cylinder multi-vacuum pouring process, and a plurality of pouring cylinders operate simultaneously. The production mode is as follows: and (3) assembling the auxiliary tool prepared before production with an engine, then placing the assembled auxiliary tool and engine into a casting cylinder, and assembling the auxiliary tool with a pattern plate assembly, a casting cylinder cover, a medicine pouring pipe, a valve, a hopper and other tools. Adding propellant slurry with specified mass into a hopper, and opening a valve for pouring after the vacuum degree in each pouring cylinder reaches a specified pressure value. And after the pouring is finished, the pouring hopper and the valve are disassembled, cleaned and arranged, and part of the pouring tool is disassembled, cleaned, arranged and put in storage.
In the production mode, engines need respective matched tools, the space of a casting cylinder is limited by the arrangement, assembly and operation of the tools, the engines cannot be effectively utilized, and the number of the engines is small; the holes of the pattern plate are limited by the opening of the engine, the number of the holes is small, and the pouring time is long in order to completely remove the gas in the slurry. A large amount of tool preparation, assembly, disassembly, cleaning, arrangement and warehousing work are required for pouring, and more manpower, auxiliary materials and charging work hours are consumed. The traditional production mode has difficulty in meeting the objective requirement of model mass production.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and the solid rocket engine charge cluster type pouring tool and the solid rocket engine charge cluster type pouring method are provided. Multiple engines are compactly arranged on a chassis one by one, positioned, intensively bound and integrally hoisted; the chassis and the material receiving disc are simple in structure and convenient to use, and can avoid independent processing, preparation, assembly and cleaning of multiple engine tools; the size of the pattern plate is larger, the opening of the pattern plate is not limited by the size of a single engine, the number of holes is more, the pattern plate is uniformly distributed and arranged from the center to the outer circle in an effective space circle by circle, and all corresponding spaces in the receiving plate are covered; during pouring, the fine propellant strips dispersed by the pattern plates partially directly fall into an engine through the material receiving disc feed opening, partially fall on the material receiving plate outside the material receiving disc feed opening, and flow into the engine through the feed opening after being stacked, so that the pouring time can be greatly shortened, and the medicine slurry is more thoroughly exhausted.
The purpose of the invention is realized by the following technical scheme:
a solid rocket engine charge cluster type pouring tool comprises a pattern plate assembly, a receiving disc and a chassis;
the external multi-engine is fixedly arranged between the receiving tray and the chassis; the pattern plate assembly is arranged on the material receiving disc; the receiving tray is provided with a feed opening corresponding to the position of the external multi-engine; the external propellant falls to the receiving disc through the pattern plate assembly and then flows into the external multi-engine through the feed opening;
the card assembly is provided with a plurality of through holes, the diameter of each through hole is phi 3 mm-phi 5mm, and the through holes form a plurality of concentric circles; on any concentric circle, the distance between the centers of two adjacent through holes is 8-20 mm, and in the two adjacent concentric circles, the distance between the through holes on the concentric circle with the larger radius is smaller than that on the concentric circle with the smaller radius.
Preferably, the distance between the through hole in the faceplate assembly and the feed opening in the receiving tray is 240-300 mm.
Preferably, flanges are arranged on the edge of the bottom plate and the edge of the material receiving plate; the flange of the chassis and the flange of the material receiving disc are jointly used for limiting the external multi-engine, so that the external multi-engine is tightly arranged.
Preferably, a plurality of vertical hoisting connecting rods are arranged on a flange of the chassis, and the chassis is connected with the flange of the material receiving disc through the vertical hoisting connecting rods.
Preferably, the lifting device further comprises a cross rod, wherein the cross rod is located between the base plate and the material receiving disc and used for connecting two adjacent vertical hoisting connecting rods.
Preferably, the material receiving disc is provided with a hoisting connecting block, and the hoisting connecting block is used for being connected with the hoisting connecting vertical rod.
Preferably, a positioning ring is arranged on the feed opening and used for being embedded into an opening of an engine to complete positioning.
Preferably, the material receiving disc is provided with a positioning hole on the end surface close to the flower plate assembly, and the positioning hole is used for connecting the material receiving disc with the flower plate assembly.
Preferably, the material receiving disc is provided with a protrusion at the edge of the end face close to the card assembly, and the protrusion is used for limiting the external propellant.
A solid rocket engine charging cluster type pouring method adopts the tool and comprises the following steps:
s1, closely arranging and placing multiple engines on the chassis; then the material receiving disc is installed, and a feed opening of the material receiving disc corresponds to the position of the multiple engines;
s2, connecting the chassis with the material receiving tray by using a plurality of vertical hoisting connecting rods; connecting two adjacent hoisting connecting vertical rods by using a cross rod;
s3, connecting the multiple engines, the chassis, the material receiving tray, the hoisting connecting vertical rods and the cross rods into a whole, hoisting the whole into a vacuum casting cylinder, and then installing the pattern plate assembly on the material receiving tray;
s4, pouring propellant, wherein the propellant is scattered to the material receiving disc through the through hole of the pattern plate assembly, one part of the propellant directly flows into the engine through the material outlet of the material receiving disc, and the other part of the propellant flows into the engine through the material outlet after being stacked on the material receiving disc.
Compared with the prior art, the invention has the following beneficial effects: 1. simple structure through concentrating the mode of constraint, has broken through traditional technology space and time limitation, has realized single mass pouring production, very big improvement the whole production efficiency of powder charge line. 2. The operation flow of the pouring procedure is simplified, the workload is reduced, and the labor intensity is reduced; 3. the auxiliary material allowance, the energy consumption, the labor cost of repeated operation and the processing cost of the tool matched with the multiple engines independently are avoided, and the charging cost is saved.
Drawings
FIG. 1 is a schematic view of a beam casting tool;
FIG. 2 is a schematic view of the chassis;
FIG. 3 is a schematic view of a take-up pan;
FIG. 4 is a schematic view of a card;
FIG. 5 is a schematic view of a cluster vacuum casting process.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Example 1:
a solid rocket engine charge cluster type pouring tool comprises a pattern plate assembly, a material receiving disc, a chassis and a cross rod.
The external multi-engine is fixedly arranged between the receiving tray and the chassis; the pattern plate assembly is arranged on the material receiving disc; the receiving tray is provided with a feed opening corresponding to the position of the external multi-engine; the external propellant falls to the receiving disc through the pattern plate assembly and then flows into the external multi-engine through the feed opening;
the card assembly is provided with a plurality of through holes, the diameter of each through hole is phi 3 mm-phi 5mm, and the through holes form a plurality of concentric circles; on any concentric circle, the distance between the centers of two adjacent through holes is 8-20 mm, and in the two adjacent concentric circles, the distance between the through holes on the concentric circle with the larger radius is smaller than that on the concentric circle with the smaller radius.
The distance between the through hole on the flower plate assembly and the feed opening on the receiving disc is 240-300 mm.
Flanges are arranged on the edge of the bottom plate and the edge of the material receiving plate; the flange of the chassis and the flange of the material receiving disc are jointly used for limiting the external multi-engine, so that the external multi-engine is tightly arranged. And a plurality of hoisting connecting vertical rods are arranged on the flange of the chassis, and the chassis is connected with the flange of the receiving tray through the hoisting connecting vertical rods. The cross rod is located between the chassis and the material receiving disc and used for connecting two adjacent vertical hoisting connecting rods. The receiving plate is provided with a hoisting connecting block, and the hoisting connecting block is used for being connected with the hoisting connecting vertical rod. And the positioning ring is arranged on the feed opening and is used for being embedded into the opening of the engine to complete positioning. The material receiving disc is provided with a positioning hole on the end face close to the flower plate assembly, and the positioning hole is used for connecting the material receiving disc with the flower plate assembly. The material receiving disc is provided with a bulge at the edge of the end face close to the pattern plate assembly and used for limiting the external propellant.
A solid rocket engine charging cluster type pouring method adopts the tool and comprises the following steps:
s1, closely arranging and placing multiple engines on the chassis; then the material receiving disc is installed, and a feed opening of the material receiving disc corresponds to the position of the multiple engines;
s2, connecting the chassis with the material receiving tray by using a plurality of vertical hoisting connecting rods; connecting two adjacent hoisting connecting vertical rods by using a cross rod;
s3, connecting the multiple engines, the chassis, the material receiving tray, the hoisting connecting vertical rods and the cross rods into a whole, hoisting the whole into a vacuum casting cylinder, and then installing the pattern plate assembly on the material receiving tray;
s4, pouring propellant, wherein the propellant is scattered to the material receiving disc through the through hole of the pattern plate assembly, one part of the propellant directly flows into the engine through the material outlet of the material receiving disc, and the other part of the propellant flows into the engine through the material outlet after being stacked on the material receiving disc.
Example 2:
a small solid rocket engine charge cluster casting tool (namely a solid rocket engine charge cluster casting tool) is provided with a chassis, a material receiving disc and a pattern plate assembly, wherein a multi-engine is placed on the chassis, the material receiving disc is installed in a matched mode with the multi-engine and the chassis, the material receiving disc is connected with the chassis to form a centralized constraint on the multi-engine, and the pattern plate assembly is installed in a matched mode with the material receiving disc, as shown in figure 1.
As shown in figure 2, the chassis is a polygonal structure with convex edges according to the size of an engine, multiple engines share one chassis, the outer circle of a part of the engine is internally tangent to the convex edges of the chassis, the outer circle of the part of the engine is tangent to the outer circle of the part of the engine, the bottom of the engine is limited, hoisting connection vertical rods are uniformly distributed outside the convex edges, threaded holes are formed in connecting rods, the connection vertical rods are connected with each other through cross rods, the cross rods form a fence and are limited as the upper part of the engine, and the multiple engines are compactly arranged and positioned.
As shown in fig. 3, the flange structure is taken to the polygon that the take-up (stock) pan corresponds with the chassis, the position that corresponds the engine is opened there is the feed opening, there is the holding ring in the feed opening, in the holding ring embedding engine upper end opening, take-up (stock) pan periphery is equipped with the chimb, it is spacing to be used for propellant medicine thick liquid circumference, the chimb is equipped with the hoist and mount connecting block outward, be connected montant one-to-one with hoist and mount on the chassis, carry out chassis and take-up (stock) pan through eyebolt and connect, be equipped with the.
As shown in figure 4, the perforated areas of the flower plates do not correspond to the openings of the engines one by one, are not limited by the size of a single engine, are uniformly distributed and arranged from the center to the outer circle one by one in an effective space, and cover all the corresponding spaces in the receiving tray.
The card component is provided with a plurality of through holes, the diameter size range of the through holes is phi 3mm to phi 5mm, the through holes are uniformly distributed and arranged on a central circle, the distance range between the central points of two through holes is 8mm to 20mm, and the central circle is at the same central point, namely all the through holes form a plurality of concentric circles. The central circles are arranged from inside to outside one by one, the distance between the quadrant points on two central circles which are separated from each other is 8-20 mm, the distance between the central points of two through holes of 2 adjacent central circles from inside to outside is decreased by 1mm, the minimum distance between the central points of two through holes of phi 3mm through holes is not less than 8mm, and the minimum distance between the central points of two through holes of phi 5mm through holes is not less than 10 mm. The diameter of the central circle of the inner ring is consistent with the distance between two parallel sides of a hexagon formed by the central points of the engines distributed on the inner ring, and the diameter of the central circle of the outer ring is consistent with the distance between two parallel sides of a hexagon formed by the central points of the engines distributed on the outer ring.
The method for determining the diameter of the through hole comprises the following steps: the initial viscosity of propellant slurry is less than 80Pa s, and the diameter of the corresponding through hole is phi 3 mm; the initial viscosity of propellant slurry is 80Pa s-150 Pa s, and the diameter of the corresponding through hole is phi 4 mm-phi 5 mm; the initial viscosity of propellant slurry is more than 150Pa s, and the diameter of the corresponding through hole is phi 5 mm.
The center circle spacing is determined by completing the casting operation at a casting speed of not more than 15 g/hole/min for a period of time during which the viscosity of the propellant increases to 250Pa "s. The distance between the center circles is selected so that the casting operation is completed at a casting speed of not more than 15 g/hole/min within the time period in which the viscosity of the propellant increases to 250Pa "s. The applicable period of the propellant slurry is short corresponding to the propellant slurry with the higher viscosity, more through holes need to be set, the spacing distance of the central circles can be selected from small to large, the applicable period of the propellant slurry is long corresponding to the propellant slurry with the lower viscosity, and the spacing distance of the central circles can be selected from large to small.
The solid rocket engine charge cluster pouring method is suitable for the condition that the initial viscosity of propellant slurry is not more than 150Pa s.
A small solid rocket engine charge cluster type pouring process method is shown as 5 and comprises the following steps:
A. during assembly, multiple engines share one chassis, are compactly arranged one by one and are positioned on the chassis;
B. during assembly, the positioning ring of the blanking opening of the receiving disc is embedded into the upper opening of the engine, and the receiving disc hoisting connecting block is installed in a way of being matched with the hoisting connecting vertical rod on the chassis;
C. during assembly, a lifting ring screw penetrates through the material receiving disc hoisting connecting block and is screwed into a threaded hole in a hoisting connecting vertical rod on the chassis to form an integral assembly, so that concentrated constraint is formed on the multi-engine;
D. during assembly, after the integral assembly is hoisted into a vacuum casting cylinder, the pattern plate assembly is matched and arranged on a connecting block with a positioning hole on the flange of a material receiving disc;
E. during pouring, the fine propellant powder strips dispersed by the pattern plates partially directly fall into the engine through the receiving disc feed opening, partially fall on the receiving plate outside the receiving disc feed opening, and flow into the engine through the feed opening after being stacked.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A solid rocket engine charge cluster type pouring tool is characterized by comprising a pattern plate assembly, a material receiving disc and a chassis;
the external multi-engine is fixedly arranged between the receiving tray and the chassis; the pattern plate assembly is arranged on the material receiving disc; the receiving tray is provided with a feed opening corresponding to the position of the external multi-engine; the external propellant falls to the receiving disc through the pattern plate assembly and then flows into the external multi-engine through the feed opening;
the card assembly is provided with a plurality of through holes with equal diameters, the diameter of each through hole is phi 3 mm-phi 5mm, and the through holes form a plurality of concentric circles; on any concentric circle, the distance between the centers of two adjacent through holes is 8-20 mm, and in the two adjacent concentric circles, the distance between the through holes on the concentric circle with the larger radius is smaller than that on the concentric circle with the smaller radius.
2. The solid rocket engine charge cluster casting tool of claim 1, wherein the distance between the through hole on the faceplate assembly and the feed opening on the take-up pan is 240 mm-300 mm.
3. The solid rocket engine charge cluster casting tool of claim 1, wherein flanges are arranged on the edge of the base and the edge of the material receiving tray; the flange of the chassis and the flange of the material receiving disc are jointly used for limiting the external multi-engine, so that the external multi-engine is tightly arranged.
4. The solid rocket engine charge cluster casting tool of claim 3, wherein a plurality of vertical hoisting connecting rods are arranged on a flange of the chassis, and the chassis is connected with the flange of the take-up pan through the vertical hoisting connecting rods.
5. The solid rocket engine charge cluster casting tool of claim 4, further comprising a cross bar, wherein the cross bar is located between the chassis and the take-up pan and used for connecting two adjacent vertical hoisting connecting rods.
6. The solid rocket engine charge cluster casting tool of claim 4, wherein the take-up pan is provided with a hoisting connecting block, and the hoisting connecting block is used for being connected with the hoisting connecting vertical rod.
7. The solid rocket engine charge cluster casting tooling of claim 1, wherein a positioning ring is arranged on the feed opening, and the positioning ring is used for being embedded into an opening of an engine to complete positioning.
8. The solid rocket engine charge cluster casting tooling of claim 1, wherein the take-up pan is provided with positioning holes on the end surface close to the faceplate assembly, and the positioning holes are used for connecting the take-up pan with the faceplate assembly.
9. The solid rocket engine charge cluster casting tooling of claim 1, wherein the take-up pan is provided with a protrusion at the edge of the end face close to the face plate assembly for limiting the external propellant.
10. A solid rocket engine charge cluster casting method is characterized in that the tool of any one of claims 1 to 9 is adopted, and the method comprises the following steps:
s1, closely arranging and placing multiple engines on the chassis; then the material receiving disc is installed, and a feed opening of the material receiving disc corresponds to the position of the multiple engines;
s2, connecting the chassis with the material receiving tray by using a plurality of vertical hoisting connecting rods; connecting two adjacent hoisting connecting vertical rods by using a cross rod;
s3, connecting the multiple engines, the chassis, the material receiving tray, the hoisting connecting vertical rods and the cross rods into a whole, hoisting the whole into a vacuum casting cylinder, and then installing the pattern plate assembly on the material receiving tray;
s4, pouring propellant, wherein the propellant is scattered to the material receiving disc through the through hole of the pattern plate assembly, one part of the propellant directly flows into the engine through the material outlet of the material receiving disc, and the other part of the propellant flows into the engine through the material outlet after being stacked on the material receiving disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910974448.6A CN110714854B (en) | 2019-10-14 | 2019-10-14 | Solid rocket engine charge cluster type pouring tool and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910974448.6A CN110714854B (en) | 2019-10-14 | 2019-10-14 | Solid rocket engine charge cluster type pouring tool and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110714854A CN110714854A (en) | 2020-01-21 |
| CN110714854B true CN110714854B (en) | 2020-08-14 |
Family
ID=69211626
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910974448.6A Active CN110714854B (en) | 2019-10-14 | 2019-10-14 | Solid rocket engine charge cluster type pouring tool and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110714854B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112253330B (en) * | 2020-08-28 | 2022-04-12 | 上海航天化工应用研究所 | Forming device for freely filling silver-embedded wire into explosive column and using method thereof |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3413384A (en) * | 1967-04-24 | 1968-11-26 | Thiokol Chemical Corp | Method of obtaining unidirectional orientation of monofilaments in curable elastomeric materials |
| RU2004130731A (en) * | 2003-10-20 | 2006-04-10 | Снекма Мотер (Fr) | TURBOJET ENGINE BLADE, IN PARTICULAR, FAN BLADE, AND METHOD FOR MAKING IT |
| RU2274760C2 (en) * | 2004-06-30 | 2006-04-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Method of loading rocket engine with solid-propellant multigrain charge |
| JP2010216446A (en) * | 2009-03-19 | 2010-09-30 | Nof Corp | Composite solid propellant and method for manufacturing the same |
| CN103557093A (en) * | 2013-10-24 | 2014-02-05 | 西安航天化学动力厂 | Multiple-combustor continuous pouring dosage accurate control device |
| CN204060970U (en) * | 2014-08-15 | 2014-12-31 | 湖北航天化学技术研究所 | A kind of multiple belt carcass cast deformation charge device admittedly pushing away motor for minor diameter |
| CN106194499A (en) * | 2016-10-08 | 2016-12-07 | 北京航空航天大学 | The propellant packing method of micro combustions room and device |
| CN106401794A (en) * | 2016-11-29 | 2017-02-15 | 西安航天化学动力厂 | Multi-shot feed divider for charging of tactic engine |
| CN107965398A (en) * | 2017-10-19 | 2018-04-27 | 内蒙古工业大学 | A kind of solid propellant rocket lock pin pours into a mould the device of anti-propellant gas enclosure |
-
2019
- 2019-10-14 CN CN201910974448.6A patent/CN110714854B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3413384A (en) * | 1967-04-24 | 1968-11-26 | Thiokol Chemical Corp | Method of obtaining unidirectional orientation of monofilaments in curable elastomeric materials |
| RU2004130731A (en) * | 2003-10-20 | 2006-04-10 | Снекма Мотер (Fr) | TURBOJET ENGINE BLADE, IN PARTICULAR, FAN BLADE, AND METHOD FOR MAKING IT |
| RU2274760C2 (en) * | 2004-06-30 | 2006-04-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Method of loading rocket engine with solid-propellant multigrain charge |
| JP2010216446A (en) * | 2009-03-19 | 2010-09-30 | Nof Corp | Composite solid propellant and method for manufacturing the same |
| CN103557093A (en) * | 2013-10-24 | 2014-02-05 | 西安航天化学动力厂 | Multiple-combustor continuous pouring dosage accurate control device |
| CN204060970U (en) * | 2014-08-15 | 2014-12-31 | 湖北航天化学技术研究所 | A kind of multiple belt carcass cast deformation charge device admittedly pushing away motor for minor diameter |
| CN106194499A (en) * | 2016-10-08 | 2016-12-07 | 北京航空航天大学 | The propellant packing method of micro combustions room and device |
| CN106401794A (en) * | 2016-11-29 | 2017-02-15 | 西安航天化学动力厂 | Multi-shot feed divider for charging of tactic engine |
| CN107965398A (en) * | 2017-10-19 | 2018-04-27 | 内蒙古工业大学 | A kind of solid propellant rocket lock pin pours into a mould the device of anti-propellant gas enclosure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110714854A (en) | 2020-01-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110714854B (en) | Solid rocket engine charge cluster type pouring tool and method | |
| CN211082232U (en) | Device is changed to slush pump valve gap | |
| CN201643807U (en) | Circular ring type water inlet distributor of mechanical stirring clarifier | |
| CN210892796U (en) | Heavy oil tank suction port heater | |
| CN218289039U (en) | Oil storage tank of high leakproofness | |
| CN217084346U (en) | Sampling device for corrosion products of primary loop and filter thereof | |
| CN211250595U (en) | A assembling die for preparation of concrete hourglass dropping board | |
| CN215039533U (en) | Large-scale coil epoxy casting mold | |
| CN221089518U (en) | Welding-free concrete mixing plant silo base | |
| CN115502001A (en) | Packaging and coating device for outer surface of annular structural part and using method | |
| CN214319766U (en) | Hollow fiber membrane component with replaceable filter element and filter tank | |
| CN206645020U (en) | Plant protection unmanned plane | |
| CN103272546B (en) | One is beneficial to the well-mixed oxidation trough of material | |
| CN213701488U (en) | Alloy die for adding tool to valve | |
| CN217440370U (en) | Chemical pump convenient to dismouting | |
| CN221052670U (en) | Manhole well template installation device | |
| CN210012162U (en) | Vertical PE storage tank | |
| CN203777744U (en) | Special filter column for ceftezole acid | |
| CN216225249U (en) | Drum-type wooden activated carbon cleaning and screening device | |
| CN210484214U (en) | Split type particle filtering structure for pump | |
| CN213177324U (en) | Filtering sand cylinder base made of plastic | |
| CN218576582U (en) | Energy-concerving and environment-protective type concrete perforated brick stays hole equipment | |
| CN218794365U (en) | A separator for catalyst production | |
| CN215561522U (en) | Automatic feeding device for blasting pulping | |
| CN217030107U (en) | Breather valve device capable of being manufactured on site and used for dust removal |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |