CN203214193U - Angle box for composite skirt of solid rocket engine - Google Patents
Angle box for composite skirt of solid rocket engine Download PDFInfo
- Publication number
- CN203214193U CN203214193U CN 201320205098 CN201320205098U CN203214193U CN 203214193 U CN203214193 U CN 203214193U CN 201320205098 CN201320205098 CN 201320205098 CN 201320205098 U CN201320205098 U CN 201320205098U CN 203214193 U CN203214193 U CN 203214193U
- Authority
- CN
- China
- Prior art keywords
- plate
- composite material
- side plate
- angle box
- skirt
- 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.)
- Expired - Lifetime
Links
Images
Abstract
The utility model provides an angle box for a composite skirt of a solid rocket engine. The angle box for the composite skirt of the solid rocket engine comprises a bottom plate, wherein the bottom end of the bottom plate is connected with a side plate, the side plate is provided with two rib plates that are perpendicularly connected with the bottom plate, the other end of each of the two rib plates is connected with a web plate, a square cavity is formed by the two rib plates, the web plate and the bottom plate in a surrounding manner, an explosive bolt connecting nut hole is arranged on the bottom plate in the square cavity, cover plate connecting holes are arranged at the upper end of the square cavity, and holes connected with the side surface of the composite skirt are arranged on the side plate. A reinforcing rib is arranged between the outer side of the web plate and the side plate. Lightening holes are arranged on the two rib plates and the web plate. Holes connected with the side surface of the composite skirt on the side plate comprise four unthreaded holes on the two sides, one unthreaded hole at the bottom end and a threaded hole in the middle. The bottom plate is connected with the side plate by an angle of 95-110 degrees, and the connecting surface is in arc transition. An explosive bolt connecting space is provided on the angle box and most of the load born by the composite skirt can be transferred to the angle box, so that the load on the composite skirt is effectively reduced, and the reliability of the composite skirt under the action of various loads is improved.
Description
Technical field
The utility model belongs to Space Dynamic's technical field, is specifically related to a kind of solid propellant rocket composite material skirt angle box.
Background technique
The solid rocket motor case joint skirt is that the integral body of housing is extended, is used for realizing and being connected of body miscellaneous part, and in order to alleviate architecture quality, the mass ratio of raising motor, the composite material skirt has obtained extensive use gradually.But skirt will stand the effect of multiple load such as axial compression, moment of flexure, shearing.In order to improve the reliability of composite material skirt, most of research concentrates on material and process aspect, and otherwise research is less.How just the load transfer of bearing of composite material skirt has reduced the load on the condensation material skirt to the box of angle, improves the reliability of composite material skirt under various load effects and does not still have research.
Summary of the invention
The purpose of this utility model is a kind of solid propellant rocket composite material skirt angle box of design, and the load transfer that the composite material skirt is born reduces the load on the composite material skirt to the box of angle, the reliability of raising composite material skirt under various load effects.
The technical solution of the utility model: a kind of solid propellant rocket composite material skirt of the present utility model comprises base plate with the angle box, the base plate bottom connects side plate, have on the side plate and base plate two floors connected vertically, two floor the other ends are connected with web, two square chambeies that floor, web and base plate surround, on side's chamber inner bottom plate blasting bolt attaching nut hole is arranged, there is the cover plate attachment hole upper end, square chamber, at side plate attachment hole with composite material skirt side is arranged.
Described solid propellant rocket composite material skirt angle box has stiffening rib between web outside and side plate.
At two floors and web lightening hole is arranged.
Described solid propellant rocket composite material skirt angle box has with the attachment hole of composite material skirt side at side plate to comprise unthreaded hole of four unthreaded holes, bottom of both sides and the screw at middle part.
Described base plate becomes 95～110o angle to be connected with side plate, the junction surface arc transition.
Advantage of the present utility model: the utility model is connected with the skirt cylinder by screw, bolt and nut, the composite material skirt end face hole of opening the light, can provide the blasting bolt connection space on the box of angle, the load major part that the composite material skirt bears is transferred on the box of angle, effectively reduce the load on the composite material skirt, improve the reliability of composite material skirt under various load effects, effectively alleviated the passive quality of Stage Separation of Missile.The utility model effectively reduces the load on the skirt, can provide corresponding usage space according to user demand equally, such as for separating of the installation of blasting bolt.
Description of drawings
Fig. 1 perspective view of the present utility model.
Fig. 2 plan structure schematic representation of the present utility model.
Fig. 3 is the A-A sectional view of Fig. 2.
Fig. 4 is the worm's eye view of Fig. 2.
Embodiment
Below in conjunction with accompanying drawing and example the utility model is done explanation in further detail.
As shown in Figure 1 and Figure 2, solid propellant rocket composite material skirt of the present utility model comprises base plate 1 with the angle box, base plate 1 bottom connects side plate 2, have on the side plate 2 and base plate 1 two floor 3a connected vertically, two floor 3a the other ends are connected with web 3b, and the square chamber 3c that two floor 3a, web 3b and base plate 1 surround has blasting bolt attaching nut hole 10 on the square chamber 3c inner bottom plate 1, there is cover plate attachment hole 7 chamber 3c upper end, side, at side plate 2 attachment hole with composite material skirt side is arranged.
Between the web 3b outside and side plate 2, stiffening rib 4 is arranged.
At two floor 3a and web 3b lightening hole 8 is arranged.
As Fig. 3: have with the attachment hole of composite material skirt side at side plate 2 to comprise unthreaded hole 5 of four unthreaded holes, bottom of both sides and the screw 9 at middle part.
The interior profile of its latus inframedium 2 outsides and composite material skirt is undertaken bonding by gluing, by five radially unthreaded hole 5 and screw 9 employing bolt or screw connections, increase connection reliability again.Base plate 1 is fitted with composite material skirt interior edge face.
As Fig. 4: 2 one-tenth 95～110o angles of base plate 1 and side plate are connected the junction surface arc transition.
The upper end has cover plate attachment hole 7 to be used for the installation of cover plate, and the protection motor body is unaffected when blasting bolt is worked; The design that lightening hole 8 on two floor 3a and the web 3b adopts for loss of weight.
Above-mentioned example is just in order to further specify the technical solution of the utility model, and protection domain of the present utility model is not limited to this.
Claims (5)
1. solid propellant rocket composite material skirt angle box, comprise base plate (1), it is characterized in that: base plate (1) bottom connects side plate (2), have on the side plate (2) and base plate (1) two floors connected vertically (3a), two floors (3a) the other end is connected with web (3b), two floors (3a), the square chamber (3c) that web (3b) and base plate (1) surround, on side's chamber (3c) inner bottom plate (1) blasting bolt attaching nut hole (10) is arranged, there is a cover plate attachment hole (7) upper end, side chamber (3c), at side plate (2) attachment hole with composite material skirt side is arranged.
2. solid propellant rocket composite material skirt angle box according to claim 1 is characterized in that: between web (3b) outside and side plate (2) stiffening rib (4) is arranged.
3. solid propellant rocket composite material skirt angle box according to claim 1 and 2 is characterized in that: at two floors (3a) and web (3b) lightening hole (8) is arranged.
4. solid propellant rocket composite material skirt angle box according to claim 1 and 2 is characterized in that: have with the attachment hole of composite material skirt side at side plate (2) to comprise four unthreaded holes of both sides, a unthreaded hole (5) of bottom and the screw (9) at middle part.
5. solid propellant rocket composite material skirt angle box according to claim 1 and 2 is characterized in that: base plate (1) becomes 95～110o angle to be connected the junction surface arc transition with side plate (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320205098 CN203214193U (en) | 2013-04-22 | 2013-04-22 | Angle box for composite skirt of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320205098 CN203214193U (en) | 2013-04-22 | 2013-04-22 | Angle box for composite skirt of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203214193U true CN203214193U (en) | 2013-09-25 |
Family
ID=49203738
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320205098 Expired - Lifetime CN203214193U (en) | 2013-04-22 | 2013-04-22 | Angle box for composite skirt of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203214193U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103909658A (en) * | 2014-03-28 | 2014-07-09 | 湖北三江航天江北机械工程有限公司 | Composite material connecting skirt forming method and mold and inner rubber core mold forming mold |
| CN105628350A (en) * | 2014-10-31 | 2016-06-01 | 北京航天万源科技公司 | Safety box for fixing explosive bolt when explosive blot is tested |
| CN108569422A (en) * | 2018-02-11 | 2018-09-25 | 浙江兆华机械制造有限公司 | A kind of rocket segmental structure |
| CN109186375A (en) * | 2018-07-26 | 2019-01-11 | 西安航天动力技术研究所 | A kind of composite material solid propellant rocket Zhong Qun bindiny mechanism and forming method |
| CN112610574A (en) * | 2020-12-14 | 2021-04-06 | 西安鑫垚陶瓷复合材料有限公司 | Metal reinforcing component for ceramic matrix composite material support and support assembling method |
-
2013
- 2013-04-22 CN CN 201320205098 patent/CN203214193U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103909658A (en) * | 2014-03-28 | 2014-07-09 | 湖北三江航天江北机械工程有限公司 | Composite material connecting skirt forming method and mold and inner rubber core mold forming mold |
| CN105628350A (en) * | 2014-10-31 | 2016-06-01 | 北京航天万源科技公司 | Safety box for fixing explosive bolt when explosive blot is tested |
| CN108569422A (en) * | 2018-02-11 | 2018-09-25 | 浙江兆华机械制造有限公司 | A kind of rocket segmental structure |
| CN108569422B (en) * | 2018-02-11 | 2022-11-01 | 浙江兆华机械制造有限公司 | Rocket sectional structure |
| CN109186375A (en) * | 2018-07-26 | 2019-01-11 | 西安航天动力技术研究所 | A kind of composite material solid propellant rocket Zhong Qun bindiny mechanism and forming method |
| CN109186375B (en) * | 2018-07-26 | 2020-12-11 | 西安航天动力技术研究所 | Composite material solid rocket engine middle skirt connecting mechanism and forming method |
| CN112610574A (en) * | 2020-12-14 | 2021-04-06 | 西安鑫垚陶瓷复合材料有限公司 | Metal reinforcing component for ceramic matrix composite material support and support assembling method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203214193U (en) | Angle box for composite skirt of solid rocket engine | |
| CN102928005B (en) | A kind of structural member of sensor | |
| CN203787887U (en) | Cable tray | |
| CN203854491U (en) | Car storage battery fixing structure | |
| CN202335160U (en) | Vehicle control unit casing | |
| CN203192731U (en) | Vehicle storage battery safety box | |
| CN203103816U (en) | Easily detached box body for box-type substation | |
| CN204415119U (en) | A kind of automobile power assembly suspending | |
| CN203148647U (en) | Balance sleeve | |
| CN104389875B (en) | Detachable fastening assembly for three-direction perpendicular concurrent wooden components | |
| CN208272840U (en) | Fixed bracket | |
| CN202796983U (en) | Solar cell frame | |
| CN203192735U (en) | Storage battery safety box for small car | |
| CN205806183U (en) | A kind of double screw retention moves structure | |
| CN201796973U (en) | Installing and fixing structure of automobile storage battery | |
| CN201774088U (en) | Multifunctional bus connector | |
| CN205715191U (en) | A kind of nested cap nut | |
| CN205010467U (en) | Wing and fuselage connecting device | |
| CN102966208A (en) | Connecting structure for self-tension pull bar | |
| CN208533775U (en) | Assembled double steel plate shear wall | |
| CN203215084U (en) | Wire clamp easy to dismount and mount | |
| CN214833672U (en) | Novel three-dimensional shock insulation sliding plate support | |
| CN206865884U (en) | A kind of isolation mounting for warship electronic module | |
| CN202797834U (en) | Novel bus duct | |
| CN202449701U (en) | Elevator sedan top plate connecting structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170714 Address after: 431400 Hubei province Wuhan Honggang village in Xinzhou District of Yangluo Economic Development Zone, Yangluo Development Zone, five floor, room 504 Patentee after: Aerospace Science and Technology Rocket Technology Co.,Ltd. Address before: 430040 Jinshan Road, Hubei, Wuhan, No. 9 Patentee before: THE GENERAL DESIGNING INSTITUTE OF HUBEI SPACE TECHNOLOGY ACADEMY |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130925 |
|
| CX01 | Expiry of patent term |