CN104696105A - Variable thickness housing of solid rocket engine - Google Patents
Variable thickness housing of solid rocket engine Download PDFInfo
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- CN104696105A CN104696105A CN201310663296.0A CN201310663296A CN104696105A CN 104696105 A CN104696105 A CN 104696105A CN 201310663296 A CN201310663296 A CN 201310663296A CN 104696105 A CN104696105 A CN 104696105A
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- cylindrical shell
- thickness
- varying
- missile wing
- section
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Abstract
The invention discloses a variable thickness housing of a solid rocket engine, which comprises a spinning cylinder body, a front section and a rear section, wherein the spinning cylinder body is in a variable thickness structure; the front section and the rear section are welded at the front end and the rear end of the spinning cylinder body; missile wing support lugs are welded on the spinning cylinder body; and integral reinforcement with 0.5mm wall thickness is arranged on welding surfaces of the missile wing support lugs. The variable thickness housing of the solid rocket engine ensures the structural strength of the engine during working; the reliability of the engine is improved via partial thickening sections; the integral reinforcement is performed on welding parts of the missile wing support lugs via the thickening sections; external bearing requirements of missile wings on the missile wing support lugs are ensured; the passive mass is reduced; a utilization rate of a raw material is increased; and a mass ratio of the engine is increased.
Description
Technical field
The present invention relates to solid propellant rocket field, be specifically related to a kind of solid propellant rocket Varying-thickness housing.
Background technique
Burning chamber shell is one of vitals in engine structure, and it is the storage tank of filling solid propellant agent, is again the place of propellant combustion, meanwhile, is also the constituent element of missile airframe.Under the prerequisite meeting the requirement of reseach of engine charter, in motor combustion chamber case design, various loading demands when flight test should be considered when structural design, and ensure the reliable connection of cabin, front and back section, improve the integrally-built reliability of guided missile.
The spinning cylindrical shell of existing burning chamber shell mainly adopts the structural type of equal thickness.
Mainly passive quality is large for the structural type Problems existing of equal thickness, and utilization rate of raw materials low-mass ratio is low.
Summary of the invention
The object of the invention is to for above-mentioned Problems existing, provide a kind of solid propellant rocket Varying-thickness housing, while the various loading demands when considering flight test, the reliable connection of cabin section before and after ensureing, improves the integrally-built reliability of guided missile.
In order to solve above-mentioned technical problem of the present invention, solution provided by the invention is to provide a kind of solid propellant rocket Varying-thickness housing, comprising: spinning cylindrical shell, leading portion and back segment; Spinning cylindrical shell adopts the structural type of Varying-thickness; Described leading portion and back segment are welded on the rear and front end of spinning cylindrical shell, spinning cylindrical shell are welded with missile wing journal stirrup; The face of weld of missile wing journal stirrup arranges the integral reinforcement of wall thickness 0.5mm.
Further, described spinning cylindrical shell overall length is 1926mm, cylindrical shell wall thickness 1.9mm, spinning cylindrical shell have employed the structural type of four sections of thick sections of opposite position, every section of thick section spacing is respectively 136mm, 158mm, 158mm vertically, and every section of thick section axial length is 80mm, and wall thickness is 2.4mm.
The present invention is owing to have employed the housing of Varying-thickness, and compared with prior art, its advantage and beneficial effect are:
1) ensure that structural strength during engine operation, add engine reliability by partial thickening section simultaneously;
2) by thick section, integral reinforcement has been carried out to missile wing journal stirrup weld, ensure that the outer year requirement of missile wing to missile wing journal stirrup;
3) reduce passive quality, improve utilization rate of raw materials, improve motor mass fraction.
Accompanying drawing explanation
By reading the detailed description done non-limiting example done with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the structural representation of apparatus of the present invention solid propellant rocket Varying-thickness housing.
Embodiment
See the accompanying drawing that the embodiment of the present invention is shown, hereafter in more detail the present invention will be described.But the present invention can realize in many different forms, and should not be construed as by the restriction in the embodiment of this proposition.On the contrary, it is abundant and complete open in order to reach for proposing these embodiments, and makes those skilled in the art understand scope of the present invention completely.In these accompanying drawings, for clarity sake, may be exaggerated size and the relative size in layer and region.
Solid propellant rocket Varying-thickness housing comprises spinning cylindrical shell 1, leading portion 2 and back segment 3, described leading portion 2 and back segment 3 are welded on the structural type of the rear and front end employing Varying-thickness of spinning cylindrical shell 1, requirement is coordinated according to overall mechanical interface, according to the axial distribution position of missile wing journal stirrup, spinning cylinder section 1 have employed the structural type of four sections of thick sections of opposite position.
Described spinning cylindrical shell 1 adopts the structural type of Varying-thickness, cylindrical shell overall length is 1926mm, cylindrical shell wall thickness 1.9mm, consider that missile wing journal stirrup will bear the various external load functions of missile wing, welding simultaneously can weaken the intensity of stack shell body, on the face of weld of each circle missile wing journal stirrup, carry out the integral reinforcement of wall thickness 0.5mm.Coordinate to require the axial distribution position about missile wing journal stirrup according to general machine simultaneously, cylinder section have employed the structural type of four sections of thick sections of opposite position, every section of thick section spacing is respectively 136mm, 158mm, 158mm vertically, every section of thick section axial length is 80mm, and wall thickness is 2.4mm.
According to totally assign mechanical interface coordinate requirement, determine the physical dimension of burning chamber shell, consider the factor such as manufacture technics simultaneously, determine the concrete structure size of described spinning cylindrical shell 1, leading portion 2, back segment 3.According to technical process, first program is in advance set to spinning machine, thus the wall thickness of thick section and axial length are accurately controlled, ensure that wall thickness seamlessly transits, to guarantee to produce the least possible residual stress in process of production simultaneously.Then spinning cylindrical shell 1, leading portion 2 and back segment 3 are welded, after completing soldering, whole housing is heat-treated, subsequently fine finishing is carried out to leading portion 2 and back segment 3 and put in place.If do not adopt the structure of Varying-thickness, in order to meet the outer year requirement of overall missile wing to missile wing journal stirrup, overall wall thickness will be large compared with existing design wall thickness, directly increases the passive quality of motor; According to the structure of Varying-thickness, like this meeting under the prerequisite that overall missile wing carries requirement outward to missile wing journal stirrup, at utmost reduce the passive quality of motor.
For diameter 230mm motor, coordinate to require the axial distribution position about missile wing journal stirrup according to general machine, have employed Varying-thickness shell construction, determine position and the axial length of corresponding four sections of thick sections on spinning cylindrical shell 1, and the axial length of thick section is accurately controlled by spinning machine, thickness and each certain distance, guarantee every section of axial length 80mm, these two critical dimensional requirements of thickness 2.4mm.
As calculated, the Varying-thickness structural design that this housing cylinder carries out, can reduce and adopt the passive quality of equal thickness design to be about 4.54kg.
This structure is applied in this model, and Product Process and productibility are verified, and have passed the body static test under the outer load combined effect of interior pressure, and repeatedly ground and flight test, and structure is reliable, meets general requirement.
To those skilled in the art, obviously the invention is not restricted to the details of above-mentioned one exemplary embodiment, and when not deviating from spirit of the present invention or essential characteristic, the present invention can be realized in other specific forms.
Claims (4)
1. a solid propellant rocket Varying-thickness housing, is characterized in that, comprising: spinning cylindrical shell, leading portion and back segment;
Described spinning cylindrical shell adopts the structural type of Varying-thickness;
Described leading portion and back segment are welded on the rear and front end of spinning cylindrical shell, spinning cylindrical shell are welded with missile wing journal stirrup; The face of weld of described missile wing journal stirrup arranges the integral reinforcement of wall thickness 0.5mm.
2. solid propellant rocket Varying-thickness housing according to claim 1, is characterized in that, described spinning cylindrical shell overall length is 1926mm, cylindrical shell wall thickness 1.9mm.
3. solid propellant rocket Varying-thickness housing according to claim 2, is characterized in that, described spinning cylindrical shell have employed the structural type of four sections of thick sections of opposite position, and every section of thick section spacing is respectively 136mm, 158mm, 158mm vertically.
4. solid propellant rocket Varying-thickness housing according to claim 3, is characterized in that, described every section of thick section axial length is 80mm, and wall thickness is 2.4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310663296.0A CN104696105A (en) | 2013-12-10 | 2013-12-10 | Variable thickness housing of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310663296.0A CN104696105A (en) | 2013-12-10 | 2013-12-10 | Variable thickness housing of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104696105A true CN104696105A (en) | 2015-06-10 |
Family
ID=53343570
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310663296.0A Pending CN104696105A (en) | 2013-12-10 | 2013-12-10 | Variable thickness housing of solid rocket engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN104696105A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736969A (en) * | 2018-12-11 | 2019-05-10 | 上海新力动力设备研究所 | A kind of solid propellant rocket spinning shell of part convex |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2218472C1 (en) * | 2003-02-06 | 2003-12-10 | Открытое акционерное общество Федеральный научно-производственный центр "Станкомаш" | Housing of solid-propellant rocket engine |
| CN201843700U (en) * | 2010-10-25 | 2011-05-25 | 湖北航天技术研究院总体设计所 | Igniter motor shell with integral structure |
| US20110192136A1 (en) * | 2008-07-16 | 2011-08-11 | Diehl Bgt Defence Gmbh & Co. Kg | Solid-propellant motor |
| RU2447310C1 (en) * | 2010-11-08 | 2012-04-10 | Открытое акционерное общество "Федеральный научно-производственный центр "Станкомаш" | Solid-propellant rocket engine body |
| CN202596923U (en) * | 2012-04-18 | 2012-12-12 | 湖北航天技术研究院总体设计所 | Airborne solid rocket engine casing |
-
2013
- 2013-12-10 CN CN201310663296.0A patent/CN104696105A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2218472C1 (en) * | 2003-02-06 | 2003-12-10 | Открытое акционерное общество Федеральный научно-производственный центр "Станкомаш" | Housing of solid-propellant rocket engine |
| US20110192136A1 (en) * | 2008-07-16 | 2011-08-11 | Diehl Bgt Defence Gmbh & Co. Kg | Solid-propellant motor |
| CN201843700U (en) * | 2010-10-25 | 2011-05-25 | 湖北航天技术研究院总体设计所 | Igniter motor shell with integral structure |
| RU2447310C1 (en) * | 2010-11-08 | 2012-04-10 | Открытое акционерное общество "Федеральный научно-производственный центр "Станкомаш" | Solid-propellant rocket engine body |
| CN202596923U (en) * | 2012-04-18 | 2012-12-12 | 湖北航天技术研究院总体设计所 | Airborne solid rocket engine casing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736969A (en) * | 2018-12-11 | 2019-05-10 | 上海新力动力设备研究所 | A kind of solid propellant rocket spinning shell of part convex |
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Application publication date: 20150610 |