CN107524545A - Detachable umbrella disk - Google Patents
Detachable umbrella disk Download PDFInfo
- Publication number
- CN107524545A CN107524545A CN201710716459.5A CN201710716459A CN107524545A CN 107524545 A CN107524545 A CN 107524545A CN 201710716459 A CN201710716459 A CN 201710716459A CN 107524545 A CN107524545 A CN 107524545A
- Authority
- CN
- China
- Prior art keywords
- umbrella valve
- round platform
- umbrella
- charge
- valve
- 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.)
- Pending
Links
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
Abstract
The invention provides a kind of removable umbrella dish structure, is alternately connected by 3 pieces of umbrella valve A and 3 pieces of umbrella valve B, encloses a round platform, round platform is provided with through hole vertically and through hole coordinates with core；Be shaped as interior arc lengths of the described umbrella valve A in round platform bottom surface is more than outer arc length；Be shaped as interior arc lengths of the described umbrella valve B in round platform bottom surface is less than outer arc length；Described umbrella valve A and umbrella valve B is coaxially bonded in the position that powder column stress concentration is corresponded on powder charge core after enclosing round platform.The present invention can reduce solid propellant rocket motor charge structural stress level, realize strain relief, on the premise of charge constitution filling fraction is ensured, the stress level of charge constitution can meet the low-temperature working structural intergrity of engine, solve the charge constitution integrality problem of engine low temperature work.
Description
Technical field
The present invention relates to a kind of charge constitution stress release device of solid propellant rocket.
Background technology
The structural intergrity of the charge constitution design of the high M numbers of solid propellant rocket turns into design challenges, particularly low temperature
Structural intergrity.The application of the external powder charge strain relief to engine is more early, and corresponding Technical comparing is ripe, typically adopts
Powder column is segmented with oblique ring channel structures, external strain relief mainly by machining, it is pre-buried can ablating device and
It is pre-buried to remove device to realize.But the country is limited by technological level, propellant material, is released currently for powder charge stress
Put shaping structures technology famine.Removable umbrella dish structure is to realize an important skill of high M numbers charge constitution stress release
Art, can effectively be realized using detachable umbrella disk reduces charge constitution stress level.The country yet there are no report using removable
Unload umbrella disk device and realize strain relief, powder charge strain relief can be realized by using removable umbrella dish structure, it is real
The high-performance and strong adaptability of existing engine, technical foundation is established for the design shaping of motor charge.
The content of the invention
For overcome the deficiencies in the prior art, the present invention provides a kind of removable umbrella dish structure, can reduce solid-rocket
Motor charge structural stress is horizontal, realizes strain relief, on the premise of charge constitution filling fraction is ensured, powder charge
The stress level of structure can meet the low-temperature working structural intergrity of engine, solve the powder charge knot of engine low temperature work
Structure integrality problem.
The technical solution adopted for the present invention to solve the technical problems is：A kind of removable umbrella dish structure, by 3 pieces of umbrella valve A
Alternately connected with 3 pieces of umbrella valve B, enclose a round platform, round platform is provided with through hole vertically and through hole coordinates with core；Described umbrella
Be shaped as interior arc lengths of the valve A in round platform bottom surface is more than outer arc length；Described umbrella valve B is shaped as interior arc length round platform bottom surface
Degree is less than outer arc length；Described umbrella valve A and umbrella valve B, which encloses coaxially to be bonded on powder charge core after round platform, corresponds to powder column stress
The position of concentration.
Described umbrella valve A and umbrella valve B is made of polytetrafluoroethylmaterial material.
The beneficial effects of the invention are as follows：Powder column strain relief is molded, realizing is ensuring the premise of filling fraction
The strain relief of lower charge constitution, it is ensured that charge constitution low stress level.Examined by the ground experiment of multiple engine
Core, it was demonstrated that significant effect of the present invention, technical foundation is established for the design shaping of motor charge structure.
The detachable umbrella disk also extends to other solid propellant rockets, as the premise for ensuring charge constitution integrality
A kind of lower means for improving filling fraction.
The advantages of detachable umbrella disk is simple in construction, compact, clear principle, and reliability is high.
Removable umbrella disk technology is the key technology of China's alternate-engine charge constitution shaping, and the invention is following strong suitable
Important technical basis is established in the development of the anti-air defence day guided missile solid propellant rocket of answering property high-performance.
The material that the detachable umbrella disk uses domesticizes, and wide material sources, good manufacturability, the process-cycle is shorter, and product closes
Lattice rate is high, and cost is low, uniformity is good.
Brief description of the drawings
Fig. 1 is removable umbrella dish structure schematic diagram, wherein, (a) is sectional view, and (b) is right view；
Fig. 2 is umbrella valve A structural representations, wherein, (a) is right view, and (b) is sectional view；
Fig. 3 is umbrella valve B structure schematic diagram, wherein, (a) is right view, and (b) is sectional view；
In figure, 1- umbrella valves A；2- umbrella valves B.
Embodiment
The present invention is further described with reference to the accompanying drawings and examples, and the present invention includes but are not limited to following implementations
Example.
The invention provides a kind of removable umbrella dish structure, and powder charge is realized on the premise of charge constitution filling fraction is ensured
The strain relief of structure, it is ensured that powder charge low stress level, so that it is guaranteed that the low temperature structure integrality of engine.
Detachable umbrella disk is the part that structural stress is larger in corresponding charge constitution, on powder charge core relevant position
Pre-install detachable umbrella disk.In powder charge process, detachable umbrella disk is embedded in charge constitution, is designed using demountable structure,
It can smoothly be taken out by the way of drag hook after charge constitution shaping, while ensure that the strain relief at the larger position of stress
Shaping.
As shown in figure 1, in technical scheme, umbrella disk designs for overall circle ring disk, is divided into 3 pairs of umbrella valves, passes through
Umbrella valve A, umbrella valve B structural design, realize the detachability energy of umbrella disk.As shown in Fig. 2 umbrella valve A designs for fritter, use
The short design of interior arc length outer arc, as acute angle design；As shown in figure 3, umbrella valve B designs for bulk, using the short outer arc length of inner arc
Design, as obtuse angle design, it is possible to achieve umbrella valve A first drawn off, after umbrella valve A is drawn off, and umbrella valve B meeting Automatic-fallings, so as to realize
Detachability energy.
Umbrella valve A uses polytetrafluoroethylmaterial material, milling shaping；Umbrella valve B uses polytetrafluoroethylmaterial material, milling shaping.Choosing
With polytetrafluoroethylmaterial material, it is ensured that umbrella disk can disengage with powder charge, and umbrella valve can be dismantled smoothly.
The shaping of umbrella disk be by 3 umbrella valve A and 3 umbrella valve B spot gluings on core relevant position.
By taking certain detachable umbrella disk of model engine as an example：
The overall size of detachable umbrella disk is Φ 100mm × 90mm；
Implementation result：The strain of charge constitution endoporus is reduced to 26.7% by 31.7%, strain level reduces by 16%；Powder charge
Umbrella disk is smoothly dismantled in structure, and charge constitution flaw detection is without exception.
Claims (2)
- A kind of 1. removable umbrella dish structure, it is characterised in that：Alternately connected by 3 pieces of umbrella valve A and 3 pieces of umbrella valve B, enclose a circle Platform, round platform is provided with through hole vertically and through hole coordinates with core；Described umbrella valve A round platform bottom surface to be shaped as interior arc length big In outer arc length；Be shaped as interior arc lengths of the described umbrella valve B in round platform bottom surface is less than outer arc length；Described umbrella valve A and umbrella Valve B is coaxially bonded in the position that powder column stress concentration is corresponded on powder charge core after enclosing round platform.
- 2. removable umbrella dish structure according to claim 1, it is characterised in that：Described umbrella valve A and umbrella valve B is using poly- Tetrafluoroethene material is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710716459.5A CN107524545A (en) | 2017-08-21 | 2017-08-21 | Detachable umbrella disk |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710716459.5A CN107524545A (en) | 2017-08-21 | 2017-08-21 | Detachable umbrella disk |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107524545A true CN107524545A (en) | 2017-12-29 |
Family
ID=60681691
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710716459.5A Pending CN107524545A (en) | 2017-08-21 | 2017-08-21 | Detachable umbrella disk |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107524545A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110792528A (en) * | 2019-11-05 | 2020-02-14 | 西安长峰机电研究所 | Combined core mold for forming multi-ring-groove medicine type structure and process |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3136831A (en) * | 1961-07-14 | 1964-06-09 | United Aircraft Corp | Casting method |
| CN1227913A (en) * | 1997-12-18 | 1999-09-08 | 联合工艺公司 | Method of and apparatus for manufacturing solid rocket motors |
| CN202129355U (en) * | 2011-06-09 | 2012-02-01 | 西北工业大学 | Spinning core die for members with transverse inner ribs |
-
2017
- 2017-08-21 CN CN201710716459.5A patent/CN107524545A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3136831A (en) * | 1961-07-14 | 1964-06-09 | United Aircraft Corp | Casting method |
| CN1227913A (en) * | 1997-12-18 | 1999-09-08 | 联合工艺公司 | Method of and apparatus for manufacturing solid rocket motors |
| CN202129355U (en) * | 2011-06-09 | 2012-02-01 | 西北工业大学 | Spinning core die for members with transverse inner ribs |
Non-Patent Citations (1)
| Title |
|---|
| 李换朝等: "一种无紧固件连接的塑料模具设计研究", 《机械工程师》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110792528A (en) * | 2019-11-05 | 2020-02-14 | 西安长峰机电研究所 | Combined core mold for forming multi-ring-groove medicine type structure and process |
| CN110792528B (en) * | 2019-11-05 | 2021-09-07 | 西安长峰机电研究所 | Combined core mold for forming multi-ring-groove medicine type structure and process |
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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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20171229 |