CN110792528B - A kind of multi-ring groove medicine type structure forming combined core mold and process - Google Patents
A kind of multi-ring groove medicine type structure forming combined core mold and process Download PDFInfo
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- CN110792528B CN110792528B CN201911068901.3A CN201911068901A CN110792528B CN 110792528 B CN110792528 B CN 110792528B CN 201911068901 A CN201911068901 A CN 201911068901A CN 110792528 B CN110792528 B CN 110792528B
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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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Abstract
本发明提供了一种多环槽药型结构成型组合芯模及工艺，组合芯模包括主芯模、伞盘、套管、卡环和作动环，所述的主芯模为柱状结构；所述的卡环为非封闭的环形结构，外侧有凸台；所述的套管安装在主芯模外，限制卡环在主芯模轴向的位置；采用温度敏感的作动环环绕在卡环外，在温度低于阈值时作动环不形变，卡环凸台与伞盘内壁配合，限定伞盘沿主芯模的轴向运动；在温度高于阈值时作动环形变缩小，带动卡环凸台脱离伞盘，主芯模能够相对伞盘轴向运动。本发明无需进行车削等机械加工操作，可一次成型多个预埋可消融装置，可重复使用多次，无需拆装，节省时间、提高效率。
The invention provides a combined core mold and a process for forming a multi-ring groove medicine type structure. The combined core mold includes a main core mold, an umbrella disc, a sleeve, a snap ring and an actuating ring, and the main core mold is a columnar structure; The snap ring is a non-closed annular structure with a boss on the outside; the sleeve is installed outside the main core mold to limit the position of the snap ring in the axial direction of the main core mold; a temperature-sensitive actuating ring is used to surround it. Outside the snap ring, the actuating ring does not deform when the temperature is lower than the threshold value. The snap ring boss cooperates with the inner wall of the umbrella disc to limit the axial movement of the umbrella disc along the main core mold; when the temperature is higher than the threshold value, the actuation ring shrinks and shrinks. The boss of the snap ring is driven to separate from the umbrella plate, and the main core mold can move axially relative to the umbrella plate. The present invention does not need to perform machining operations such as turning, can form multiple pre-embedded ablative devices at one time, can be reused for many times, does not need disassembly and assembly, saves time and improves efficiency.
Description
Technical Field
The invention relates to a charging and forming process of a solid rocket engine.
Background
The working environment of the solid rocket engine is harsh, the requirement on the temperature adaptability of the engine is wide, the performance requirement is high, a high-filling charge structure design is needed, the stress of the high-filling charge structure is generally high, and a high-filling charge stress release structure becomes a key technology of the engine.
The application of the foreign radial annular groove charging structure is earlier, the corresponding technology is mature, the foreign engines adopting stress release groove charge type include American TU-780 engines, AIM-120 engines and RAM missile engines, and the foreign radial annular groove structure mainly adopts three ways: (1) machining, namely turning a formed annular groove in the propellant in a turning mode by adopting a telescopic turning tool device; (2) pre-embedding an ablatable device, pre-embedding an umbrella disc made of ablatable material in a propellant, and forming an integral body after the umbrella disc and the propellant are solidified, wherein the propellant burns together when burning; (3) the pre-buried detachable device through devices such as the detachable umbrella disk structure, after the propellant solidifies, takes out the umbrella disk after dismantling, the shaping annular.
The method is limited by the technical level and propellant materials in China, the single-ring groove is mainly used for forming in China at present, an umbrella disc structure capable of being ablated is adopted, the umbrella disc made of the ablatable material is fixed on a propellant pouring tool and is solidified into a whole when being poured along with the propellant, and the single-ring groove forming is realized by disassembling a propellant pouring core mold. The core mould used in the forming process is a detachable core mould, one end of the detachable core mould is provided with threads, the sleeve is fixed on the core shaft of the core mould through the detachable core mould, and the ablatable umbrella disc is fixed through the sleeve and the core shaft, so that the ablatable umbrella disc is prevented from changing in position when medicine slurry is poured. After the slurry is solidified, the sleeve is drawn out from one end, and the mandrel is drawn out from the other end, so that the molding of the single ring groove is realized.
The advantages of the forming process at home and abroad are as follows: (1) machining and forming, wherein a turning forming mode is adopted, and the structural size, the position and the number of the annular grooves of a forming surface can be adjusted at will; (2) the ablatable device is pre-embedded, the speed of molding the single ring groove is high, and the structure of the molding tool is simple; (3) the detachable device is embedded in advance, and a multi-ring groove structure can be formed. The disadvantages of each forming process are as follows: (1) the mechanical processing molding has the advantages that the structure of a molding cutter is complex, the failure rate is high, and in the propellant turning process, the propellant is easy to generate heat by friction and ignite; (2) the built-in ablatable device has the defects that only a single ring groove can be formed, and a multi-ring groove structure cannot be formed; (3) the embedded ablatable detaching device is complex in structure, the forming tool is installed firstly at each time, the propellant solidifies and then the detaching device is detached, and the working efficiency is low.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a forming technology of a high-loading radial multi-annular-groove charging structure, which can realize the forming of a high-adaptability high-performance engine structure. The invention relates to an application technology of a solid rocket engine.
The technical scheme adopted by the invention for solving the technical problems is as follows: a combined core mould for forming a multi-ring-groove medicine-shaped structure comprises a main core mould, an umbrella disc, a sleeve, a snap ring and an actuating ring.
The main core mold is of a columnar structure; the clamping ring is of a non-closed annular structure, and a boss is arranged on the outer side of the clamping ring; the sleeve is arranged outside the main core mould to limit the position of the snap ring in the axial direction of the main core mould; the temperature-sensitive actuating ring is adopted to surround the outside of the clamping ring, the actuating ring does not deform when the temperature is lower than a threshold value, and the lug boss of the clamping ring is matched with the inner wall of the umbrella disc to limit the axial movement of the umbrella disc along the main core mold; when the temperature is higher than the threshold value, the actuation ring is reduced to drive the clamp ring boss to separate from the umbrella disk, and the main core die can axially move relative to the umbrella disk.
The invention comprises a plurality of umbrella disks, a plurality of sleeves, a plurality of snap rings and a plurality of actuating rings, wherein the umbrella disks and the sleeves which are provided with the snap rings and the actuating rings are alternately arranged on a main core mould.
The present invention further includes a fixing nut threadedly coupled to one end of the main core mold to define an axial position of the sleeve and the snap ring on the main core mold.
The structural form of the snap ring comprises an open ring structure and a segmented structure; in the split ring structure, the snap ring is of a non-integral structure and is opened along the circumferential direction; in the segmented structure, the clamping ring is cut into three or four segments to form a non-closed ring; the cross section of the snap ring is U-shaped or L-shaped.
The section of the actuating ring is square, rectangular or circular.
The actuating ring is made of shape memory alloy, shape memory polymer or bimetallic strip temperature sensitive materials with different linear expansion coefficients.
The invention also provides a process for forming a multi-ring-groove medicine type structure by using the combined core mold, which comprises the following steps: the clamping ring and the actuating ring are sleeved together and are arranged outside the main core mold, and the clamping ring is matched with the umbrella disc; alternately sleeving the umbrella disc and the sleeve on the main core mold, and axially positioning the sleeve and the main core mold to obtain a multi-ring-groove forming core mold; filling the multi-ring groove forming core mold into a combustion chamber shell of a solid rocket engine, pouring a propellant into the combustion chamber shell, heating to 60-70 ℃, preserving heat, and taking the propellant as a moving ring to shrink and deform to drive a snap ring to deform so that the snap ring is separated from an umbrella disc; and after the propellant is solidified, drawing out the main core mold.
The umbrella disc is installed in the environment of 60-70 ℃, after standing to normal temperature, the actuating ring is restored to the original state, the clamping ring is sleeved in the umbrella disc, and downward propellant casting is carried out.
The invention has the beneficial effects that: aiming at the serious shortage of the forming technology of the radial annular groove charging structure, the invention provides the forming technology of the radial multi-annular groove charging structure, the radial annular groove charging structure is formed, and the production efficiency is improved under the implementation condition of the existing process.
Compared with the prior art, the invention has the following remarkable advantages:
1) the embedded part is an ablatable device, does not need to be subjected to machining operations such as turning and the like, and has no danger of igniting propellant;
2) a plurality of pre-embedded ablatable devices can be formed at one time, and a plurality of umbrella discs are formed;
3) after the combined core mold is installed once, the combined core mold can be repeatedly used for many times without disassembly and assembly, so that the time is saved, and the efficiency is improved.
The forming technology can also be popularized to other solid rocket engines and is used as a means for forming a high-loading radial annular groove charging structure.
Drawings
FIG. 1 is a schematic view of the overall structure of a shaped charge forming combined core mold of the present invention;
FIG. 2 is a partially enlarged view of the shaped charge forming composite core of the present invention;
FIG. 3 is a schematic view of a split ring structure with a U-shaped cross section;
FIG. 4 is a schematic view of a segmented ring structure having a U-shaped cross-section;
FIG. 5 is a schematic structural view of a split ring with an L-shaped cross section;
FIG. 6 is a schematic view of a segmented ring structure having an L-shaped cross-section;
FIG. 7 is a schematic view of a circular cross-section actuator ring structure;
FIG. 8 is a schematic view of a square cross-section actuator ring configuration;
figure 9 is a schematic view of a rectangular cross-section actuator ring structure.
Detailed Description
The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.
The invention realizes high filling fraction of the charge and strong adaptability and high performance of the engine, solves the technical problems of the forming process of the charge structure with high filling radial multi-ring groove and the combined core mould, optimizes the process of the charge structure on the premise of ensuring the filling fraction, adopts the pre-embedded ablatable device to combine the core mould, realizes the forming of the multi-ring groove pre-embedded ablatable device, reduces the repeated installation and disassembly of the tool and improves the working efficiency.
As shown in fig. 1 and 2, the combined core mold for drug mold forming of the present invention comprises a main core mold 1, an umbrella disk 2, a sleeve 3, a fixing nut 4, a snap ring 5 and an actuating ring 6. The snap ring 5 and the actuating ring 6 are sleeved together and are arranged in the clamping groove at the inner side of the umbrella disk 2. The umbrella disk 2 is sleeved on the main core mould 1, the sleeve 3 is sleeved on the main core mould 1 from the other side of the main core mould 1, and the sleeve and the main core mould 1 are reliably fixed by using the fixing nut 6.
The combined core mold comprises a main core mold, a plurality of umbrella disks, a plurality of sleeves, a fixing nut, a plurality of clamping rings and a plurality of actuating rings. The snap ring and the actuating ring are sleeved together. After a plurality of snap rings and actuating rings are sleeved, the umbrella disc and the sleeve are arranged in the umbrella disc, the umbrella disc provided with the snap rings and the actuating rings and the sleeve are alternately arranged on the main core mold, and finally the main core mold is locked by a fixing nut. When the environmental temperature rises to the deformation temperature of the actuating ring, the actuating ring is shrunk and deformed, the clamping ring is pulled out from the umbrella disk, and the main core mold can be pulled out from the combustion chamber shell after the clamping ring is separated from the umbrella disk, so that the integral demolding is realized.
The structural form of the snap ring can adopt: (1) the snap ring is of a non-integral structure and is opened along the circumferential direction; (2) the clamping ring is divided into three sections or four sections; (3) the cross section structure of the snap ring can adopt a U-shaped structure; (4) the cross-sectional structure of the snap ring can adopt an L-shaped structure.
The actuating ring structure form can take: (1) the whole round structure has a square section; (2) the whole round structure has a rectangular section; (3) the whole is circular, and the section is circular.
The actuating ring can use shape memory alloy, shape memory polymer or bimetallic temperature sensitive material with different linear expansion coefficients.
The technical process for realizing the invention comprises the following steps:
and a multi-ring-groove forming core mold is arranged, a snap ring and an actuating ring are sleeved together and are arranged at the position of a ring groove corresponding to the main core mold, and the top end of the snap ring is clamped in a clamping groove at the inner side of the umbrella disk. The umbrella disk is sleeved on the main core mold, the sleeve is sleeved on the main core mold from the other side, and the sleeve and the main core mold are reliably fixed by using the fixing nut.
And (3) loading the multi-ring groove forming core mold into a solid rocket engine combustion chamber shell, pouring a propellant into the combustion chamber shell, and moving the combustion chamber shell into a drying workshop.
And raising the temperature in the drying room to 60-70 ℃, preserving the heat for a long time, and when the temperature of the drug-shaped forming combined core mold is raised to 60-70 ℃, reducing and deforming the actuating ring to drive the clamping ring to deform so that the clamping ring is separated from the clamping groove of the umbrella disk. After the propellant is solidified, the whole core mould can be directly drawn out from the big end of the main core mould.
When the extraction temperature of the multi-ring groove core mold is 60-70 ℃, an umbrella disc is arranged at the same position, after standing to normal temperature, the actuating ring returns to the original state, and the clamping ring is sleeved in the umbrella disc to carry out downward propellant casting.
In this embodiment, the snap ring 6 is a U-shaped open ring structure, the actuating ring 5 is made of shape memory alloy material, the structure is a circular cross-section structure, and the main core mold 1 is sequentially provided with 3 umbrella disks 2 and sleeves 3. And mounting the mounted drug-shaped forming combined core mold in a solid rocket engine combustion chamber shell, and then pouring 50 ℃ drug slurry. After the slurry casting is finished, the two ends of the solid rocket engine combustion chamber shell are sealed and horizontally placed in a curing room with the ambient temperature of 70 ℃. The temperature of the drug-shaped forming combined core mold is slowly increased, when the temperature is increased to 60-70 ℃, the actuating ring is shrunk and deformed, the snap ring 5 is driven to deform, and the snap ring 5 is separated from the clamping groove of the umbrella disc 2. After the propellant is solidified, the whole core mould can be directly drawn out from the big end of the main core mould 1. When the combined core mold is pulled out from the propellant, the umbrella disc 2 is arranged at the same position, after standing to normal temperature, the actuating ring 6 is restored to the original state, the clamping ring 5 is sleeved in the umbrella disc 2, and the propellant can be sent down for casting.
Claims (8)
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911068901.3A CN110792528B (en) | 2019-11-05 | 2019-11-05 | A kind of multi-ring groove medicine type structure forming combined core mold and process |
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| CN201911068901.3A CN110792528B (en) | 2019-11-05 | 2019-11-05 | A kind of multi-ring groove medicine type structure forming combined core mold and process |
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| CN110792528A CN110792528A (en) | 2020-02-14 |
| CN110792528B true CN110792528B (en) | 2021-09-07 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112571822B (en) * | 2020-10-29 | 2023-03-28 | 上海新力动力设备研究所 | Memory non-metal core mold structure suitable for winding with medicine and shell forming method |
| CN112377326B (en) * | 2020-12-06 | 2022-08-23 | 西安长峰机电研究所 | Multi-ring-groove medicine type mechanical forming core mold of solid rocket engine |
| CN115247617B (en) * | 2022-07-01 | 2025-07-15 | 大连理工大学 | A solid rocket engine radial annular groove grain forming core mold and forming method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5035182A (en) * | 1984-03-28 | 1991-07-30 | The United States Of America As Represented By The Secretary Of The Navy | Bending type ordnance venting device |
| JPH08189510A (en) * | 1995-01-06 | 1996-07-23 | Nec Corp | Separation fitting |
| US6321656B1 (en) * | 2000-03-22 | 2001-11-27 | The United States Of America As Represented By The Secretary Of The Navy | Thermally actuated release mechanism |
| CN105840344A (en) * | 2016-04-20 | 2016-08-10 | 哈尔滨工业大学 | Preparation and safe quick demolding process for solid rocket engine inner hole burning grain |
| CN107524545A (en) * | 2017-08-21 | 2017-12-29 | 西安长峰机电研究所 | Detachable umbrella disk |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2391899A (en) * | 2002-08-12 | 2004-02-18 | Qinetiq Ltd | Shape memory alloy connector and an overwound munition casing |
| US7762078B2 (en) * | 2006-09-13 | 2010-07-27 | Aerojet-General Corporation | Nozzle with temperature-responsive throat diameter |
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2019
- 2019-11-05 CN CN201911068901.3A patent/CN110792528B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5035182A (en) * | 1984-03-28 | 1991-07-30 | The United States Of America As Represented By The Secretary Of The Navy | Bending type ordnance venting device |
| JPH08189510A (en) * | 1995-01-06 | 1996-07-23 | Nec Corp | Separation fitting |
| US6321656B1 (en) * | 2000-03-22 | 2001-11-27 | The United States Of America As Represented By The Secretary Of The Navy | Thermally actuated release mechanism |
| CN105840344A (en) * | 2016-04-20 | 2016-08-10 | 哈尔滨工业大学 | Preparation and safe quick demolding process for solid rocket engine inner hole burning grain |
| CN107524545A (en) * | 2017-08-21 | 2017-12-29 | 西安长峰机电研究所 | Detachable umbrella disk |
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